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OP03-001

1. eese 2 24 Figure 2 21 Science Instrument Static Servicing Envelope Side And Rear Views esse 2 25 Figure 2 22 Science Instrument Static Serving Envelope Isometric 3 D View eee 2 26 Figure 2 23 Science Instrument Dynamic Envelope Isometric 3 D View esee 2 27 Figure 2 24 Science Instrument Dynamic Envelope eesseeseeseeseeeenee rennen enne nennen eene 2 28 Figure 2 25 Science Instrument Cart Pathi iien a E E eere en nretnenee nnns 2 30 Figure 2 26 Science Instrument Cart Positioned On Cart Path essere 2 31 SOFIA IHB 0 0 vii Figures Figure 2 27 Example of the Maximum Science Instrument Cart Footprint Width allowed by SOFIA 2 32 Figure 2 28 USRA Provided Science Instrument Cart eeessssssseseeseeeeeenen eere enne 2 33 Figure 2 29 SOFIA Standard Instrument Rack eese nennen rennen eerte nennen 2 36 Figure 2 30 Standard Instrument Rack Dimensions eese rennen enne eene eret nes 2 38 Figure 2 31 A Typical SOFIA Instrument Rack eese nennen rennen EEN s 2 39 Figure 2 32 Equal Maximum Weight Load in 4 Rack Sections essere 2 41 Figure 2 33 Calculation of Rack Torque Moment essere ener enne nne nennens 2 42 Figure 2 34 Location and Depth L of Chassis Center of Gravity
2. eene 4 15 Table A 1 Acronyms and Terminology eese eee enne nennen nennen trennen A 1 SOFIA IHB 0 0 ix Tab es x SOFIA IHB 0 0 Worksheets Instrument Rack Weight Sheet Leine iens ete tv ea ere la pe telo taco eon deo Ie eb one 2 45 SLSubmittal Status Work Sheet ette tte e en ee tree oe ne Gaanevensdudveesececevsedevbiavustetede 3 9 SOFIA IHB 0 0 xi Worksheets xii SOFIA IHB 0 0 SOFIA IHB 0 0 Br Infrared Astronomy CHAPTER 0 Preface 0 1 Revisi n HISLOLy erint oerte ED DD A EXER ER ta Fea REDE Eee sese x Eust aa Eats 0 2 0 2 Documentation Conventions eese eene nu nnn nna a hans a a aaa ua R44 a R44 Ra aad Rua ada a dA 0 2 0 3 Related Documents eesseseeeeeeseee eese nnne nn nmu anh nu a kan R RR RR 4 SR RR RR RAN RR ERAN RR AR RR RSEN RR RR nnna 0 2 0 1 CHAPTER 0 Preface SOFIA IHB 0 0 0 1 Revision History Revision Comments 0 2 Documentation Conventions TBD 0 3 Related Documents Note If viewing PDF and you have the documents in a common folder you can click the link to open the document Book 1 Science Instrument Development Manual Volume 1 Observatory Overview Volume 2 Observatory Interface Control Documents Volume 3 Observatory Airworthiness Manual Volume 4 Post Instrument Selection Process SI Development Planning Volume 5 Miscellaneous tbd
3. 1 36 TT Other Observatory Sub Systems CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Zenith Water Vapor vs Time After Take Off Typical 4 5 Hours After Take Off Figure 1 17 Typical Zenith Water Vapor Plot During Flight 1 5 4 Global Pointing System GPS A TRAK Systems model 8820 2 GPS Station Clock is installed in the forward electronics con sole with an antenna mounted in the overhead sextant port on the flight deck Accurate time UTC position and altitude can be displayed on the unit s front panel and this information is also available as MCS housekeeping data The position and altitude accuracy is quoted as x 30 m rms Other outputs available include an IRIG B time signal with millisecond accuracy and pulses at 1 Hz or at 1 MHz These outputs are routed to the PI patch panel aft of the experimenter s science instrument rack and can be routed from there to the SI 1 5 5 Vacuum Pumping System There are three independent pumping stations on the Observatory for SI Team use for pre flight operations and during flight Two pumping stations are used for pumping on cryogens and one is used for pumping containers such as the SI Mounting Flange Tub down to pressures of a few millitorr The three pumping stations use identical pumps Leybold Trivac D 40 B oil sealed two stage rotary vane type which have a nominal pumping speed of 27 1 cfm 767 Li min at the pump which translates to a pumping sp
4. Acquisition f x Two Point Chop Peak to Peak Peak to Peak Sensor Output Amplitude Amplitude lc Settling Time Chop Phase Figure 2 48 Definitions for External Command of Secondary mirror Motions The illustration shows external command of secondary mirror motions using the two states of the TTL synchronization line As depicted each rise and fall of the applied reference signal is needed to generate the com plete square wave transition of secondary mirror motions A novel feature of the secondary mirror control electronics is to use the same two state nature of the TTL synchronization line to generate a three point chopping pattern Three point control of the secondary mirror motions is illustrated in Figure 2 49 2 64 T Secondary mirror Control CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 External TTL Input Chop Period Data Phase Pos End Point Three Point Chop Sensor Output E B Mid Point gt 4 Settling Time i Chop Phase Figure 2 49 Three Point Chopping Using A Two State Synchronization Line With The Potential For A 180 Phase Reversal As noted in the interface control document TA_SI_04 the figure above shows that the TTL signal has a 180 degree phase ambiguity for the 3 point chop The analog output described previously can be used must to monitor this phase degeneracy Without any analog and TTL inputs it is pos
5. SOFIA IHB 0 0 Index X SOFIA IHB 0 0 Document Comments 1 need a new figure with flat panels 39 2 See 3 2 7 below Where is this 2 3 Link to section 5 3 4 Is this correct 35 4 Dates Names and Addresses need review in this chapter 1
6. CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Figure 1 9 IR and Visible Tertiaries in their Support Tower The 20 oversized uncoated IR dichroic tertiary is on top and the smaller aluminized tertiary for the FPI is underneath inside the tertiary tower The Nasymth tube opening on the forward side of the pressure bulkhead contains no filter wheel but does provide a mounting surface for fixed pressure window The investigator if needed may provide special pressure windows The interface specifications are provided in ICD TA_SI_02 and are discussed further in Chapter 2 SOFIA Science Instrument ICDs on page 2 1 1 3 1 4 Telescope Imagers With the dichroic tertiary mirror in place the observatory s Focal Plane Imager FPI views nearly the same field of view as the science instrument and can be used for set up and pointing With a fully reflective tertiary mirror the FPI can no longer receive visible light from the tele scope In this case pointing setup and position control can be performed using the Fine Field Imager FFI In addition a science instrument can provide updates to the telescope pointing using the standard SOFIA command line interface commands discussed elsewhere in this manual Chapter 2 Section TBD and may provide their own optical or infrared guide camera Table 1 6 provides various parameters of interest for the FPI FFI and the Wide Field Imager WFI The latter is used primarily for field re
7. Door opening dimensions are measured parallel to the aircraft centerline not flush with the surface of the fuselage at the door location Figure 2 27 Example of the Maximum Science Instrument Cart Footprint Width allowed by SOFIA This figure does not show the overlap of the fully opened passenger door with the aircraft door opening only the aircraft door opening is shown 2 32 uA Science Instrument Cart CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 A sample science instrument cart is illustrated below in Figure 2 28 The USRA provided cart contains several features that accommodate a great many science instrument designs The cart is primarily designed to withstand the severe loads associated with the maximal weight limit of sci ence instruments The cart allows one to adapt to any of the SI in need of transportation The table dimensions of 60 inches by 36 inches allows the cart to safely handle the largest instru ments yet are small enough to make maneuvering the other science instruments less cumber some Seat tracks have been incorporated on the top of the cart to allow for many different mounting fasteners to be used in many different mounting locations The cart also allows for the safe distribution of loading across the aircraft floor panels With such a design it is imperative that the center of gravity be located in a predefined zone as discussed in the ICD SIC_AC_01 An efficient and economical design w
8. V Vacuum System Fitting B Blower System Fitting Figure 2 45 A Schematic Of The U4 Disconnect Panel With Fittings For The Three Upper Deck Vacuum Pumps The details of this interface are described in the document titled the Vacuum Pump System to Science Instrument From the rigid aircraft vacuum lines the lines drop in diameter 38 1 mm 1 5 inches ID to run approximately 15 meters 49 21 feet through the CLA to KF flanges mounted on the counter weight panel of the telescope assembly Vacuum lines from the counter weight plate CWP to the science instrument or instrument mounting flange will also be 38 1 mm 1 5 inches ID and will be provided by USRA Flexible pumping lines will be available in a vari ety of lengths and will always end with a KF vacuum flange 2 60 T Science Instrument and TA Flange Pumping System CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 For instrument teams using the SOFIA SI vacuum pump system USRA will provide suitable pressure sensors and electronics Both the pressure sensor ConvecTorr Gauge and electronics Varian Multi Gauge are described in the SI Vacuum System ICD along with the required opera tional cabling The remote pressure sensor electronics is expected to mount in the PI instrument rack for science teams in need of pressure sensing The pumping speed at the SI flange is expected to be about 460 liters per minute at 1 Torr This is based on a 20 meters 66 feet of 72 9 m
9. Both the telescope and aircraft systems are to avoid this area This volume includes space to allow the science instrument teams to work with and around the science instrument During the science instrument installation phase the telescope is expected to remain in a fixed position typically at an elevation of 40 The static instrument volume is based upon the location of the telescope s instrument flange but also includes the SI volume which is permitted to extend forward of the flange interface See Figure 2 21 and Figure 2 22 The static envelope is fixed with respect to the aircraft structure 2 24 uA Science Instrument Envelope CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 m 90 00 8 2286 KL 10 090 STAI390 STAI 480 12794 lt q Forward 98 00 15 00 2489 2 1905 SIDE VIEW VIEW LOOKING FORWARD Figure 2 21 Science Instrument Static Servicing Envelope Side And Rear Views Science Instrument Envelope qua 2 25 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 STA1480 FORWARD Figure 2 22 Science Instrument Static Serving Envelope Isometric 3 D View 2 26 uA Science Instrument Envelope CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 5 3 Dynamic Instrument Volume Isometric View Figure 2 23 Science Instrument Dynamic Envelope Isometric 3 D View This enve
10. SOFIA EXPERIMENTER S HANDBOOK OP03 001 Book 1 Science Instrument Development Manual Volume 1 Observatory Overview STRATOSPHERIC OBSERVATORY FOR INFRARED ASTRONOMY SOFIA Contract NAS2 97001 Document Number SSMOC_SCIN_MAN_0000 03100 Revised October 2008 DRAFT COPY DO NOT DISTRIBUTE October 15 2008 Contents BVO UTES NEN Nc dc cH IUIUS vii Lc P T C ix WY OURS CUS dinni eia eo o EORR ve E t E A a E dn tes xi IUS EB HOSISCOIM elio wA eU CP m 0 2 0 2 Documentation Conventions e eee e eee ee ee ee eee e ette eto tn sn sn sns sensns seen ene senes eese e sese e eese e e tete eee tete tete eerte ee on 0 2 0 3 Related DOCUMENtS wosscscccscsssesscsvssescsssovsesscoves scesess D E T CQ svdseds vovsessseceeds soesessseoes 0 2 1 1 Overview of SOFIA Observatory and SSMOC eerie eee eee eese eese esten setas ense toss esses stesso setas ena 1 2 1 2 General Description of Observatory Working Environment eee eerie eee seen een eene en atento seta sena 1 3 1 2 1 Observatory Floor Plan eee eee eene eene erroe eror ette etna tnn e tp po StPPP e eO e tone sosoo askooo e tpe estne ese aE 1 3 1 2 1 1 ST Team Work Areas 1 4 1 2 1 2 SILACCESS M EIIGht cscssccsscvessecacesnsesnnsessasssesesecsasessuaseosscdiosssvasocseossectecsacdecsbsnsecssvasessaseees 1 5 1 2 2 Observatory Cabin Environment cscccssccscssccscscc
11. a Approval to access the SI or move aft of the netting restraint must first be given by the flight crew and In Flight Director b SI access is restricted to the forward face of SI or any part of the SI accessible from the for ward side of the barrier railing and c No disconnecting or re connecting of high voltage or power lines is allowed in flight 2 If access to parts of the SI inaccessible for a person forward of the barrier is required then a Approval to access the SI must first be given by the flight crew and In Flight Director b The In Flight Director will turn a Key Activation Switch on the console to brake the TA thus enabling the key to be removed from the console c The key is then used by an experienced trained SI team member to open the barrier gate to access the SI beyond the forward face d No interference with the SI seals or Access Port seals is allowed in flight while the TA gate valve is open and e No disconnecting or re connecting of high voltage or power lines is allowed in flight Telescope Flange and Nasmyth Tube Pump Manifold Netting Restraint SI Rail Barrier Main Deck Zone 2 Figure 1 4 SI Safety Barrier 1 2 2 Observatory Cabin Environment Although all effort was taken to maintain as much as possible the same levels of noise in the Observatory as on a normal passenger aircraft the opening in the aft fuselage for the telescope 1 6 A General Description of Observat
12. A View Looking Down On The SI Panel On The PI Patch Panel Aft Of The PI Instrument Rack The SI portion of the PI patch panel provides a signal connectivity pool communications and power connections between the PI instrument rack MCCS and the telescope mounted science pa Instrument Cabling Patch Panels CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 instrument The SI patch panel consists of co axial tri axial twisted pair and fiber optic lines Additional lines are provides for high voltage signals and science instrument power connectors Communication lines at the SI patch panel are composed of twisted shielded pair lines co axial cables and tri axial cables Shielding of the signal and communications twisted pair cables is provides on a per pair basis and pinned through designate contracts in the connector Signal lines of the SI patch panel are composed of ten N type connectors five BNC adapters and five connec tors of twisted pair bundles and thirty fiber optic ST style adapters Four AC power connectors are available to route power to the science instrument The observatory provides a discrete electri cal connection for use by science instrument equipment in shutting down power from any SI pro vided UPS In addition to the above connectors there are four special purpose connectors cables suitable for DC high voltage lines These lines are rated to a maximum of 15K VDC All of these connections are strai
13. Figure 2 16 Pressure Boundary Configurations for Science Instruments This figure illustrates five possible pressure boundary configurations for science instruments mated to the telescope instrument mounting flange The major mechanical components are the Telescope Mounting flange x xim 2 19 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 full flange the pressure coupler and or the gate valve window The pressure coupler connects the open optical port of the pressure window subassembly with science instruments that use only or additionally a small vacuum sealing interface diameter at the gate valve The science instrument developer is expected to provide the required the pressure cou pler The pressure coupler shares the same interface to the telescope assembly as the optical win dow assembly Some of the various pressure couple configurations have additional connection to the vacuum and or the exhaust fittings feed thorough of the tub When applicable the differential pressure between the forward gate valve pressure plate volume and the aft volume causes the interface plane on the pressure plate to move along the U axis The pressure coupler between the science instrument and the gate value should necessarily accommodate these motions The concept of the optical window assembly is depicted schematically below The figure shows a possible mounting of an optical window element A typical assembly would be mounted to the fla
14. J49 J50 J51 Data Sensors IRIG B me ome oeren see omm O 0 JB amp J87 J58 J59 J52 J53 J GPS Antennas DOTOS Doma O O J55a J55b Figure 2 38 A View Looking Down On The MCCS Panel The schematic above depicts the layout of the patch panel connectors for the MCCS interface The power and grounding approach for equipment in the PI racks and equipment connecting to the SI patch panel is depicted below As an example a portion of the FC power use is routed over the CLA drape for distribution at the science instrument patch panel Power can be routed directly to the SI if no additional power is needed in the PI instrument rack Grounding for science instru ment equipment in the PI racks may be made to the rack structure A pre flight check verifies all electrical bonds established by the science instrument installation Ground points are available on the PI patch panel via nut plates 2 52 uA Instrument Cabling Patch Panels CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 NEUTRAL m ENTIRE P PATCH PANEL TION BETWEEN GROUNDS Figure 2 39 An Example Grounding Approach For Providing Instrument Power From the MCCS Patch Panel Aboard SOFIA fast Ethernet and a gigabit Ethernet LAN access is available for science instru ment networking The MCCS LAN is Ethernet based and support the 100BASE FX and 1000BASE SX standards The available LAN connection points are used
15. Science Instruments and associated equipment are loaded through this door The second passenger door on the port side is also available for personnel access but only person nel access In the case of emergencies all four passenger doors in the mission control area of the observatory are equipped with inflatable slides rafts for emergency egress Data Analysis Observer Work Area TA Electroni Work Are ais S CONFIGURATION PI Console Racks EPO Consoles a E elescope Operator s M 1 Door R2 Door EPO and Yisitor Seating o AA Ro Oi ee aen ee 5 00 U E g 0 7 iq Jo A ie Vaa Vea i A 7 A M A iu z F i 1 Er N P er MCCS Electronics C4 Racks re L1 Door L2 Door OPT CONFIGURATIONS SEE VIEW B Vacuum Pump PERIPHERAL TABLE LAYOUT In Flight Director Consoles SB 4 6 5 10141416 10 6014 016 101 4 0 410l a Main Deck Manifold PI Console plus 2 SI Racks OR 3 SI Racks only Figure 1 1 Schematic Layout of the SOFIA Cabin General Description of Observatory Working Environment Si 1 3 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Figure 1 2 Aft Cabin Mission Control Area 1 2 1 1 SI Team Work Areas Figure 1 1 shows four areas in the mission control area belonging to SI team members 1 The prime area is where the SI electronics and computer are located 20 feet aft of the SI m
16. by fixing by a GUI an AOI around each star so the Tracker can use these limited areas of inter est to calculate the location of the centroids of the stars enclosed in them If the centroid of a track star moves slightly in one direction then the tracker will move the Tracking Position in that same direction to maintain the gyro offset between the Tracking Posi tion and the track star If the Tracking Position is tied to a particular TA Reference Frame TARP position e g boresight i e if the tracking boresight yes flag is in place then the Tracker will signal the TASCU to move the telescope to keep the SI boresight fixed with the Tracking Position Thus nothing would have appeared to move in the focal plane but the Tracker and TASCU have steadied the IR source within the SI boresight If the centroids of the two rotation stars move such that the rotation angle of the line joining them has changed then the tracker will send this deviation to the TASCU where an LOS correc tion will be made In addition based on these corrections and if the IR source being observed is declared inertial i e the inertialzyes flag is in place the Tracker will send to the TASCU modifications required to the gyro readouts which can be reset by the TASCU so that the transformation between the sky and gyro frames is kept constant and correct In this way while inertially track ing are re calibrating the sky to gyro tr
17. information contained in the file If the data provider later provides information of the file type it can be parsed and properly ingested into the relational database PSI SSI Instrument data will only be stored as raw data but the archive will digest enough information from the data headers so that summary information of the PSI SSI data can be stored in the archive Any errors that occur dur ing the archival process will be passed back to the data provider with automatic e mail notification to the person s responsible for the data In case of a fatal error i e a file could not be archived the file will also be copied to the DCS Data Store until the SSMOC archive scientist or a soft ware engineer has investigated the reason for the transfer failure The data file will also remain on the data disk where it was originally created If the science data originated from a PSI SSI instrument the data cycle is completed once the raw data have been successfully ingested by the SOFIA archive and the DCS Core has sent an auto matic e mail to the PI and the SSMOC archive scientist that the data have been successfully archived If the Science data originated from a FSI Instrument the DCS Core will automatically start pipelining the data If the pipeline requires user interaction the pipeline reduction will not commence until normal working hours when the SSMOC personal arrives to start their daily tasks Mission Ground Operations Qua 4 17 C
18. other miscellaneous identifiable direct costs and indirect costs List salaries and wages in appropriate organizational categories e g principal investigator other scientific and engineering professionals graduate students Guidelines for Participation in the Instrument Program n sre 5 7 CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 research assistants and technicians and other non professional personnel Estimate all man power data in terms of man months The cost plan for SOFIA instrument development propos als should include the cost of one trip per year to a SOFIA Instrument Proposers Meeting at Moffett Field CA or Waco TX 2 Explanatory notes should accompany the cost proposal to provide identification and estimated cost of major capital equipment items to be acquired purpose and estimated number and lengths of trips planned basis for indirect cost computation including date of most recent negotiation and cognizant agency and clarification of other items in the cost proposal that are not self evident List estimated expenses as yearly requirements by major work phases 3 For all questions concerning allowable costs proposers should contact Robert Senter USRA 10227 Wincopin Circle Suite 212 Columbia MD 21044 Phone 410 730 2656 Fax 410 730 3496 E mail rsenter hq usra edu 5 3 3 4 Current Support For other current projects being conducted by the principal investigator pro
19. pi Gl offices ciae T 2nd floor Panorama of South and West Walls of the SMOCC Bldg N211 and schematic floor plan Furnishings and utilities in the SI labs include several workbenches 110V AC Ethernet and tele phone a sink with potable water and compressed air lines Facility lab equipment and supplies available to use in the SI labs include SSMOC Ground Facilities for SI Teams Qua 1 41 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 e Portable roughing pump Portable turbo pump Helium leak detector e 220V 60 Hz transformers 2 kVA each Hydraulic lifting device Helium gas cylinder Nitrogen gas cylinder Liquid Nitrogen supply dewar Liquid Helium supply dewar Heat Gun Hand dewars e Oscilloscope Digital Multimeters Bench power supplies Current voltage source UPS e Soldering station Fiber optics termination kit Spectrum Analyzer Logic Analyzer e Signal Generator Lock in Amplifier Electronic Filter Microscope Fiber optics inspection lamps 1 6 2 Pre Flight Integration Facility PIF The TAAS is located in the Pre Flight Integration Facility PIF at the south edge of the hangar floor Acceptable installation of a Science Instrument onto the SOFIA telescope requires an air worthy mechanical connection and a fully adjusted and checked optical alignment To evaluate and refine associated procedures equipment handling and configur
20. pointed straight up i e elevation angle 90 the U and W axes lie in the plane of the page and the V axis is normal to the page With the telescope in this orientation U points in the negative X direction V points in the negative Y direction and W points in the positive Z direction The ele vation EL cross elevation XEL and line of sight LOS angles correspond to rotations about the U V and W axes respectively 2 3 SOFIA Telescope Optical Prescription The architectural design of the SOFIA telescope assembly TA is shown in Figure 2 3 The opti cal design of the TA is a classical Cassegrain with a Nasmyth focus A classical Cassegrain sys tem consists of two imaging optical elements a concave parabolic primary mirror and a convex hyperbolic secondary mirror The primary forms a perfect i e totally free of geometric aberra 2 4 uA SOFIA Telescope Optical Prescription uH NP CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 tions on axis image of an infinite point object This image is placed at the virtual image of the secondary mirror The latter then forms an on axis perfect image of the primary mirror image in the TA focal plane The Nasmyth focus is achieved by folding the optical beam via a flat tertiary mirror onto an actuation axis of the TA for more convenient access to the focal plane image Focal Plane Science Instrument R A IR Radiation Primary Secondary Dichroic Mirror Mirro
21. sess 2 44 Figure 2 35 Science Instrument Counterweight Rack essere rennen eere 2 47 Figure 2 36 Science Instrument Counterweight Rack Showing Grounding Location esses 2 48 Figure 2 37 The Location Of The PI Patch Panel For Cabling Access To MCCS Telescope and Science Instrument Ha rdwWwate 45 nene t Gee oe ee tregua 2 50 Figure 2 38 A View Looking Down On The MCCS Panel eese ener enne 2 52 Figure 2 39 An Example Grounding Approach For Providing Instrument Power From the MCCS Patch Panel 2 53 Figure 2 40 A View Looking Down On The SI Panel On The PI Patch Panel Aft Of The PI Instrument Rack 2 54 Figure 2 41 The SOFIA Telescope With An Illustration Of The Cable Load Alleviator CLA Configuration 2 56 Figure 2 42 Cable Routing Aircraft System To Science Instrument With Signal Cables esses 2 57 Figure 2 43 A Schematic Of Telescope Instrument And PI Rack Grounding eene 2 58 Figure 2 44 A View Showing The Science Instrument Vacuum Lines Manifold CLA And The U4 Disconnect Panel 2 59 Figure 2 45 A Schematic Of The U4 Disconnect Panel With Fittings For The Three Upper Deck Vacuum Pumps 2 60 Figure 2 46 Schematic for Monitoring the Pump Line Pressure Attached to a Science Instrument 2 61 Figure 2 47 A Schematic Of Software And Hardware Connections To The Secondary mirror Control
22. z Cabin Environment Annunciator Panel Archived Primary Storage Tertiary TA M Workstations irror Interface Electronics Cavity Door Subsystem Controller Network p ressure Switch Window Cavity ECS Control Controller Laser Power Printer Distribution Unit Secondary Mirror Control Experimenter Connections High speed amp standard ethernet Figure 1 15 MCS Communication Architecture The TA box in Figure 1 15 shows four important control sub systems 1 TAMCP TA Master Computer Processor This sub system is the communications hub and passes transmissions in correct sequence to and from the other three TA control sub systems below and the MCS 2 TASCU TA Servo Control Unit This sub system is at the heart of the telescope s pointing and control All commands to move the TA or change state of the TA are issued from here In particular this is the sub system that runs the gyro servo control loop that inertially stabilizes the TA pointing to the sky 3 Tracker This sub system visually monitors the sky using one or more of the three images FPI FFI and WFI to correct the gyro servo system for slow gyro drifts or other inaccuracies The Tracker do not move the TA it sends information to the TASCU via the TAMCP so the TASCU can make the physical correction see section 1 3 2 5 Imager Star Tracker on page 1 24 for more on the Tracker process Mission Control Sub System x 1 31 CHAPTER 1 SOF
23. 2 24 2 5 3 Dynamic Instrument Volume eee eee eee ee eene eene seen eee tn etna setae seen seen sees sens Sr EKES 2 27 2 6 Science Instrument Cart otoo torsie sisis 2 29 2 7 Instrument Racks PI RACE ssissscasssescessooscssssbsccessssdecsveesesavsesecessesecaesveucaesdcecaedeestassvosdecesescasesesesssseece 2 34 DP ols PL RACK sicsssnssasonssatsesccnetnssachavecccecsesscassacsensandenascaecseasuesesassassssdesecaedadsacsntsuccenseuccnsseceecstecsnayeacecss 2 34 2 7 25 Counterwelght RACK a zscivsasssseseccsiessccssecssoessdpnencsesnseoaavossscessvnssnndsesesessseciestssdseiesventiecestbessneussd sos 2 45 2 8 Instrument Cabling Patch Pamels ccssccsccscssovsesssecsssccsvessocevss soncsvosesocsstesessesssecossvoassosendscesasecnsses sorisosss 2 48 2 8 1 The MCCS Patch Pannel sccscssscssscssscssccsssensssnsscsscsescscsenesssssssesecescscssessnessesssssssssnessneseoes 2 50 iv SOFIA IHB 0 0 2 8 2 The Science Instrument Patch Panel cccsccssccsscsscsscccsccsscescenscscccsccesccnscnnsenccssccsscencenscenccsccess 2 54 2 8 3 The Cable Load Alleviat0r ccssccsscssscssscssscssssescssscssscssssssssssssssseccscscssessssssecsssssssssnessnessoes 2 55 2 8 4 Science Instrument Grounding Recommendations eee eee eee eee eee eee eerte neenon setae 2 57 2 9 Science Instrument and TA Flange Pumping System eeeee ee essere eren ee eene eerte nete seen osten ose ttna
24. Efficiency of Chopping Secondary Mirror sess eere 1 28 SMA Position Waveforms at Selected Frequencies amp Amplitudes sss 1 29 MCS Communication Architecture eese enne nee en R TEO nennen EEan 1 31 Telescope Temperatures with and without Pre Cool esee nennen 1 34 Typical Zenith Water Vapor Plot During Flight eese 1 37 MADA Intercom Station Control Panel sess eene eene enne nennen nnne nnne nnn 1 38 MOCC Floor Plan 2 ie teure OPER leues 1 41 TAAS Schematic de t Hte OE e E ER RU Een PUR Ee eH SE ER nid 1 43 Portable Chopped Light Source nee eet e ttp ri re EE aia 1 44 Figure 1 22 View of Chopped Hot Plate Mounted at End of TAAS ssssssssessseeeee eene 1 45 Figure 2 1 SOFIA Aircraft Coordinate Systemi neien o enie K E KE enne een eere ee retener etse retener 2 3 Figure 2 2 The SOFIA Telescope Coordinate System essent enne ne nennen 2 4 Figure 2 3 Architectural Design Description Of The SOFIA Telescope eene 2 5 Figure 2 4 Optical System Configuration of the SOFIA Telescope Assembly eee 2 6 Figure 2 5 Secondary mirror Assembly Cross Section eessesseseeseseeeee eene nene eere nren ren emnes 2 8 Figure 2 6 Secondary mirror Button Design Flat Black eese eere 2 9 Figure 2 7 Secondary mirror Butt
25. H Hardware Requirements initial 48 HK 48 SOFIA IHB 0 0 Index Housekeeping HK Data 48 l IMF 10 INF 42 Installation Volume 23 Instrument Cabling Patch Panels 48 Instrument Flange pressure boundary 18 instrument mass result of cryogen boil off 17 Instrument Nasmyth Flange INF 42 Instrument Racks PI Rack 34 instrument volume dynamic 27 static 24 instrument mounting flange 21 instrument mounting flange IMF 10 Interfaces between science instruments 16 L lavatories 7 Line of Sight LOS 25 Line of Sight and Azimuth Resets 25 Lobbying certification regarding 16 LOS motions 25 M MADS Mission Audio Distribution System 38 Mapping Options 35 mass 16 MCCS ICDs 70 MCCS Interface 11 MCCS LAN 67 MCCS Patch Panel 50 MCS 67 18 MCS Command and Keyword References 67 Mechanical Interface 8 Minimum Science Capabilities 13 SOFIA IHB 0 0 implementation 15 Mission Audio Distribution System MADS 38 Mission Control Sub System MCS 18 Mission Controls Subsystem MCS 67 Mission Ground Operations 6 Mounting flange 10 N N211 ICDs 71 Nasmyth 1 16 Nasmyth 2 16 NED 47 Nod Beam Switching Mode 24 Nod Chop Mode 31 O Observatory Cabin Accommodations 7 Observatory Cabin Environment 6 Observatory Data Archive 46 Observatory Flight Profile 8 Observatory Optical Performance 26 Observatory Personnel 8 Observatory Software Simulator 46 Observatory Supp
26. LCD Monitor 2 j il if Control Panel MADS 15 7 x 12 6 Bass eom Audio Headset Connectors 115V 60Hz Outlet Strip Mounting Plate Equipment Access Through This Panel Typical Operator Console Layout Figure 1 3 PI Console 1 2 1 2 SI Access in Flight During flight operations there are safety related limitations to access of Science Instrument SI Safety reviews by NASA and the USRA Team have stated that there is a safety concern associated with accessing an SI in flight while the telescope assembly TA is not braked And operator in such a situation could be pinned or crushed between the SI attached to the TA and the aircraft or struck by the SI If the TA is not braked the SI must be accessed such that the operator cannot be injured Injury can be avoided by using an SI safety barrier Figure 1 4 shows a concept of the SI safety barrier constructed of removable modular barriers placed during flight to demarcate the SI dynamic envelop i e the volume that can be swept out by an SI as the telescope moves within its observing limits These in flight procedures must be followed to access the SI in flight General Description of Observatory Working Environment x ce 1 5 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 If the telescope is to remain operating and unbraked while the SI is accessed or if SI team members must move aft of the netting restraint see Figure 1 4 then
27. SI flange The vacuum seal between the BSB and the SI will be made with an o ring The BSB will form a vacuum seal with the TA using either bellows cou plers or a 41 inch diameter plate and o ring seal In the former case access to the SI flange area is required for installation of the bellows coupler In the latter case the 41 inch flange plate will be transported from the simulator to the TA as part of the SI BSB assembly Each BSB will contain a flip mirror and an optical CCD camera When the flip mirror is engaged light is reflected into this optical CCD camera when the flip mirror is removed from the beam line light passes directly through the BSB and enters the SI through its window The BSB will have a means of adjusting the CCD path length to accommodate the allowable range of back focal distances for SI Mission Ground Operations x xm 4 9 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 Alignment This mechanical alignment orients the SI so that its field of view is centered on the secondary mir ror of the telescope For this procedure the chopped hot plate is mounted on the TA simulator see above and the flip mirror in the BSB is removed from the light path The SI detects the signal from the hot plate which is maximized by tilting positioning either the SI or a mechanism which is an external or internal part of the SI This alignment is the sole responsibility of the PI team there will be no adjustm
28. SOFIA SI Proposal and Review Process SOFIA IHB 0 0 data analysis of calibrated data using standard software routines such as IRAF without requiring the assistance of the PI team A simple method of archiving a summary of the observations will be required 5 1 1 3 Special Purpose Principal Investigator class Science Instrument SSI This is a special purpose instrument specifically designed for a particular observation or set of observations not possible or practical with FSI or PSI instruments This instrument may incorpo rate technologies at the edge of the art that would be too risky to include in a general purpose instrument It is expected that this instrument will be operated by the PI team Normally the instrument will reside at the PI s institution where all maintenance and upgrades will be accom plished Descriptive documentation must be extensive enough so that a potential GI can determine the feasibility of his her proposed observation 5 1 2 Facility Support Equipment In addition consideration will be given to proposals for general purpose devices for the facility For example at least four of the successful SOFIA study grants indicated an interest in an instru ment rotator It is not cost effective to build independent instrument rotators for each instrument Therefore USRA would welcome proposals for a facility rotator A similar situation could also occur with common back ends for heterodyne spectrometers Proposals
29. SOFIA data Access to the SOFIA archive will be through the web The archive will recognize and correctly handle proprietary data d Pipeline reduced calibrated data for standard observing modes will be archived in FITS for mat e Mission observer logs flight plans proposal information audio and video data will also be archived The science capabilities that have been deferred until after ORR are 1 Planning and visualization tools a The minimum science capabilities provide simple editors for AOT AOR generation and obser vation planning but without interactive graphics interfaces for visualization 2 Interactive Data Reduction a Instrument teams will provide interactive data reduction capabilities but they may not be well documented and hence not very user friendly b The facility instruments available at ORR write their data in standard FITS It is therefore expected that observers can export their data to common data reduction packages like IDL IRAF or other reduction packages and interactively reduce their data IDL IRAF CLASS and other commonly used reduction packages will be available at the SSMOC 3 Pipeline reduction of PSI data a Raw PSI data including necessary calibration data will be archived PSI data can therefore be pipeline reduced at a later date if there is enough interest and pending allocation of resources 4 Web based integration time estimators for all science instruments 5 Quick Look a
30. TA systems with the help of telescope and computer operators TA technicians aircraft mechanics and an air worthiness engineer A high fidelity simulation of the actual flight set up sequence will be per formed on the ground to test all aspects of the integrated system d About 90 minutes before each flight of the series the mission director will convene a pre flight briefing with all flight personnel to summarize mission sequence and objectives for that flight e In a morning meeting after each flight the mission director will debrief in person or in a mis sion report aircraft mission system and science representatives on how the airborne observatory performed in flight The meeting will be chaired by the aircraft schedule and planning controller Where appropriate possible necessary corrections will be made prior to the next flight f After the last flight of a mission usually on a Friday morning the SI team will supervise the de installation of the SI The lab where the team assembled the SI will be available for end of series calibrations and disassembly of the SI required before shipping 4 4 2 SI Check out in the SSMOC Installation of a science instrument SI on the observatory will start with installation on the TA MCCS simulator in the SSMOC laboratory This procedure is required for all SI s and will occur one to a few days prior to each installation on the aircraft An authorized and certified technician will insp
31. These equipment and facilities include the standard instrument rack electrical power sources and equipment available before during and after each flight Aspects of the aircraft cabin environment that may be relevant to the experiment design or per formance e g temperature vibration and radio frequency interference The inspection and approval process for installation of an experiment into the aircraft includ ing areas of concern and required documentation e Suggested techniques for fabrication and assembly that can contribute to improving the perfor mance and reliability of the experiment throughout a mission series of flights An outline of the SOFIA safety and airworthiness guidelines are presented in Chapter 3 Airwor thiness on page 3 1 The detailed science instrument airworthiness manual is contained as Vol ume III of this series Installation of research equipment can be very demanding and time consuming if adequate pre cautions are not observed To prevent a disappointing last minute delay or cancellation of a flight or mission because of incompatibilities instrument designers should follow the guidelines in this chapter relating to environmental factors physical constraints and airworthiness considerations 2 2 SOFIA Aircraft and Telescope Coordinate Systems With the selection of the USRA proposal NASA purchased the Clipper Lindbergh 747 SP air craft Boeing production number 21441 from United Ai
32. agreement over 100 000 the applicant certifies that a No Federal appropriated funds have been paid or will be paid by or on behalf of the under signed to any person for influencing or attempting to influence an officer or employee of any agency a Member of Congress in connection with making of any Federal grant the entering into of any cooperative and the extension continuation renewal amendment or modification of any Federal grant or Cooperative agreement b If any funds other than Federal appropriated funds have been paid or will be paid to any person for influencing or attempting an officer or employee of any agency Member of Congress or an employee of a Member of Congress in connection with this Federal grant or cooperative agree ment the undersigned shall complete Standard Form LLL Disclosure Form to Report Lobby ing in accordance with its instructions c The undersigned shall require that the language of this certification be included in the award documents for all sub awards at all tiers including sub grants contracts under grants and cooper ative agreements and subcontracts and that all sub recipients shall certify and disclose accord ingly This certification is a material representation of fact upon which reliance was placed whet this transaction was made or entered into Submission of this certification is a prerequisite for making or entering into this transaction imposed by 51352 title 31 U S Cod
33. analog input signals see TA SI 04 Synchronization is through the output analog signals from the SMA sensors Figure 4 6 illustrates the chops described in 1 through 4 When using the two point chop there are two images of the sky in the focal plane There are three images of the sky when using three point chops Figure 4 6 illustrates the view from the FPI or SI for a two point chop Note Since the FFI and WFI are NOT viewing the sky through the Secondary Mirror their view of the sky is unchanged from the no chop view When the SMA has been initialized at the beginning of a flight and a chop mode is to be used the MCS will run through a short Chop Calibration routine so chop parameters sent to the SMCU will drive the chopper as requested After SMA calibration when using chop modes 1 through 4 the MCS automatically knows where the plus zero and minus images of the sky are in the focal plane with respect to the no chop position of the sky in the focal plane BUT when an observer uses the Analog Chop Mode i e is mode 5 the MCS has no idea where these chopped images are unless the SI com puter gives this information How this information is passed to the MCS is still TBD but there are a number of options If a user plans to use the analog mode for chopping that user should contact the SSMOC to ascertain what inputs the MCS needs from the SI in order to point the telescope 39 cc For chop mod
34. at SSMOC will use the AORs and any additional constraints specified in the Observing Plan to create optimized flight plans initially using the manual flight planner A flight with an FSI instru ment will typically contain targets from more than one project and more than one general investi gator Flight Management x xm 4 5 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 PSI SSI instrument teams will do their own flight planning using the same manual flight planner that the SSMOC uses The teams can however optimize the schedule within all the projects allo cated to their particular instrument without having to fill in AORs or detailed observation plans The manual flight planner creates flight plans for United Airlines UAL which UAL can pass over to air traffic control UAL needs a list of waypoints with altitude aircraft headings true wind speeds and the amount of fuel remaining at each waypoint The manual flight planner also creates flight plans for the In flight Flight Series Director as well as for the observer These flight plans show the airplane heading at the beginning of each leg what targets are observed and for what duration They also list observing mode guide stars and the telescope elevation and cross elevation as well as when a field rotation update is needed Due to inaccuracy in long term weather predictions the flight plan will be adjusted the day before a flight and the manual flight p
35. at the beginning of the flight on the first flight Figure 4 3 shows the situation before a boresight is perfected The SI array as depicted in the SI Data XML file is shown in white including the location of the boresight pixel This location is w r t the TA Reference Frame i e TARF as seen in the FPI The real SI array is shown in yel low however so the real SI boresight is in another location w r t TARF Also shown in Figure 4 3 are the images of a track star with an AOT and an IR source In the chop mode figures show ing the sky in Figure 4 3 and Figure 4 4 represent just one chopped image of the sky Figure 4 4 shows first what happens after an observer requests the TA to move to an IR source with the SI boresight as the designated boresight and tracking enabled with the flag bore sightzyes Since the real SI array w r t TARF is in another location the real designated SI bore sight in the SI array will not have the IR source in it The observer then tweaks i e moves the Tracking Position in TARF and with it follows the IR source on the FPI because the tele scope is moving When the Tracking Position coincides with the Real SI Boresight the observer will issue an SCL acknowledgement and the MCS will update the location of the SI boresight and thus array in TARF If desired the exercise can then be continued to perfect the determination of the alignment of the array with respect to TARF by
36. central hole the outer side surface and space radially along the bottom The dashed line labeled Spi der in the lower plot indicates the temperature of the spider vane in the telescope headring 1 5 3 Water Vapor Measurement The principal purpose for SOFIA is the detection and measurement of far infrared radiation from celestial objects Observations throughout most of the infrared are impossible from ground based 1 34 T Other Observatory Sub Systems CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 observatories due to absorption by water vapor in the troposphere Although SOFIA usually flies above the moist troposphere a measurable amount of water vapor is present in the stratosphere at densities of approximately 2 to 10 parts per million This residual water vapor over burden is suf ficient to have a noticeable affect on most far infrared observations e g broadband photometry or spectroscopy of lines blended with strong water vapor absorption lines 1 5 3 1 Variations in Overburden The water vapor burden at altitude for use in the calibration is affected by the season latitude the jet stream and somewhat by local weather conditions at lower altitudes In general the tropo pause is higher in the local summer and higher water vapor burdens may be encountered This is also true in the tropics throughout the year In temperate latitudes the zenith water vapor overbur den at observing altitudes is typically 5
37. chassis weighs 50 Ib or more Instrument Racks PI Rack 2 43 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 L ue Figure 2 34 Location and Depth L of Chassis Center of Gravity 2 44 uA Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 WORKSHEET 2 1 Instrument Rack Weight Sheet SOFIA INSTRUMENT RACK WEIGHT SHEET Date Serial No Max Total Weight 600 lb Max Weight each bay 300 lb Max Moment 12000 in ib WEIGHT ARM LEFT BAY ITEM Ww H MOMENT or top surface pounds inches WH in Ib i 2 3 4 5 6 T 8 9 10 TOTALS WEIGHT ARM RIGHT BAY ITEM Ww H MOMENT or top surface pounds inches WH in Ib 1 2 3 4 5 6 T 8 9 10 TOTALS 2 7 2 Counterweight Rack In addition to the mounting instrument electronics with the SOFIA Principal Investigator PI rack or within the dynamic instrument envelope science instrument teams can also mount instrument Instrument Racks PI Rack 2 45 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 electronics to the forward surface of the telescope assembly counterweight plate USRA has designed the Counterweight Rack CWR to mate to existing telescope hardware The CWR can support between 100 and 150 kg of science instrument equipment USRA will provide the SOFIA instrumen
38. con forms to is the same as the design data in terms of dimensions and materials An FAA MIDO inspector conducts the conformity inspection or the inspection is delegated to a DAR The DAR is appointed and supervised by the Manufacturing Inspection District Office MIDO and is respon Science Instrument Certification Methods and Roles 3 3 CHAPTER 3 Airworthiness SOFIA IHB 0 0 sible for inspections of all parts test set up and other conformity issues Once your design is com plete and before you begin to build drawings and a request for conformity are submitted to the FAA ACO by the DER The ACO will then contact the MIDO and the request for conformity will be issued to the DAR who is then responsible for conducting the conformity inspection A con formity inspection of a part means that all dimensions materials process call outs and tolerances are checked to make sure that they are exactly as have been specified on the drawing 3 3 Compliance vs Conformity The FARs are the rules that must be followed to obtain certification Compliance with the rules is determined by the DERs working in conjunction with the engineers of the FAA ACO Compli ance is determined by reviewing the documentation provided by the SI team by conducting any required tests and by conducting a Compliance inspection on the aircraft Conformity how ever is the determination by the DAR that the parts that are to be installed on the ai
39. drives the URD correspondingly with the aperture to maintain a precise URD position relative to the upper edge of the aperture assembly ensuring no gap devel ops between the two assemblies 1 5 2 Cavity Environmental Control System CECS The CECS is used to pre condition the telescope and telescope cavity for exposure to the strato sphere where the ambient air temperature is about 50 to 60 Celsius A precool procedure is executed starting five hours TBV before scheduled takeoff to lower the temperature of the SOFIA telescope cavity thereby reducing the temperature difference between the optical surfaces and the recovery air at altitude Recovery air is the air from the stratosphere that is swept into the cavity It has been kinetically warmed so the cavity needs only to be cooled to approximately 30 to 40 Celsius instead of 50 to 60 Celsius At least five hours before takeoff the telescope cavity is inspected and sealed and then purged of moist air by continuous blowing of dry nitrogen gas into the cavity The nitrogen gas is obtained from dewars of liquid nitrogen on the ground During the precool these liquid nitrogen ground dewars are connected to the telescope cavity through ports in the aircraft fuselage After the nitro gen purge has lowered the cavity dewpoint the cooling process begins The PCU cools the cavity air using a liquid nitrogen purge An in situ ventilation system recirculates the
40. eee eerte ener tn eee se tna s tnos etna ne 5 2 5 1 1 2 Principal Investigator class Science Instrument PSI eee eee eere e eere rennen 5 2 5 1 1 3 Special Purpose Principal Investigator class Science Instrument SST 5 3 5 1 2 Facility Support Equipment esee e eee sette eene enne eene ense KSSS Vio ao SKE O Suor sete ss tones etos seen seca 5 3 5 2 Evaluation Criteria In Approximate Order of Importance 4 eee e eee e eee eee esee tenete nete n ee tnaae 5 4 5 3 Guidelines for Participation in the Instrument Program cesse ee ee eee eee eene eene etae tease tn ese tn os eenase 5 5 23941 BUEDOSE Genet eree ee T eee Cos PE eU Te pae C Vno ne ea EN EVA Ce ee EE E ET oo dk e ua pei A ee euN VV Te eR ETFs eo Ce vea OTT 5 5 5 3 2 Period Of Performance q 5 5 5 3 3 Proposal Format and Content csccccsssescscescsesscsecsssscssccescccesccssescesssccessscesccsseccssesceessceresseees 5 5 25 23 39 LA Proposal COMLENC ssssssccscesssdsvesssdscecasedcencsenovessessseaseseasoesssasursoonsossecseosbacdsesseatesdsnsseenssesecssseued 5 5 5 3 3 2 Proposal Length lt ssssacecsacssecscsesessasecensesencsontsseovesscavassaceouaseduncsonsdsossscsecsecsdsesbbssensssecedsssecess 5 7 Toe SEE COTIA EA e a 5 7 5 3 3 4 Current SUPPOTlisisicssscccssesvessdsssoosesossesssnvassacssseissoseas
41. eer SVE E TEEVEE 4 18 4 5 1 Observing Command and Housekeeping Interfaces sescscssccrcscsecsssccscccesccsesccesescesssssesess 4 18 4 5 2 Observing on an Airborne PlatfOrm cccscccsccccccsscssscssscsssssscsssscssccsssessssssssssssessssssessnessees 4 18 4 5 3 Set ups and Observing Modes Supported at ORR cscccsssssssscssssssscssscssessssnsssnssesssssessoeees 4 20 4 5 3 1 Selecting and Perfecting SI Boresight ccscccssscscscescccescsecsccessscseseccesccsesccesssesesscsesess 4 20 A532 StaTe MOE CQ 4 23 4 5 3 3 Nod Beam Switching Mode ccccssccssscscssccscccesccsssccessscessccessescscceseseesescessssesesessees 4 24 4 5 34 Chop ModE eroe eontra ee thee EE otro Pre Sue eeu omae Tae E vont eue e bios beer een voee ern 4 26 4 5 3 5 Nod Chop Mode R 4 31 4 5 3 6 SCAN LS RR asor asse sosise 4 33 4 5 3 7 Various Mapping Options eene eee eere e eere ee eene etate ssoi osten Soib Seisoo neiseis osais 4 35 CHAPTER 5 SOFIA SI Proposal and Review Process 5 1 5 1 USRA SOFIA Science Instrument Proposal Process 4 eere ee ee ee eee ee eee eerte eee tne tas toa se tnoseenase 5 2 5 1 1 Classes of Science Instruments Considered for Development eee eere eee eee eene nn 5 2 5 1 1 1 Facility class Science Instrument FSI e eee ee ee ee ee eee ee
42. for facility support equip ment must 1 clearly show the demand for the equipment being proposed and 2 summarize equipment specifications required in order to meet this demand The estimated cost for the equip ment should be compared to the cost that would have been accrued by USRA if similar equipment had been built by each PI team who required it Any approved SOFIA science instrument must also be accompanied by the complete set of docu mentation required for FAA certification as well as documentation showing compliance with the Interface Control Documents that assure compatibility with the Observatory See Appendix E This documentation is NOT required for purposes of this proposal In the case of FSI s commissioning time will be granted The proposer should put in a draft plan for the commissioning and the expected flight hours needed The actual number of commission ing flight hours granted will be negotiated between the P I and USRA during development To compensate for the large effort needed to build a FSI a flight reward of 50 Successful Flight Hours SFH will be given the successful P I Team during the first 2 years This assumes the nominal 600 SFH year is achieved in the first two years of operation Upon review of the instru ment performance additional grant awards of no more than 100K per year for two years will be considered for PIs that have successfully delivered an instrument The P I must supply a cost pro posal f
43. for science equipment in the PI racks or they can be patches over to the SI portion of the PI patch panel Additional net work connectors provide the interface for routed imager data from each of the fine field wide field and focal plane imagers An additional fiber optic network connection is provided for the SOFIA mission audio distribution system Specific USRA provided hardware is required to decode the digital audio stream needs for observatory headsets For video signals the observatory provides a serial digital interface 270 Megabit SDI and separate RGB analog channels Video channel routing lines require a USRA provided router controller head The MCCS patch panel also provides connectors for thermocouple lines vacuum pressure sen sor lines and two GPS antenna connections The GPS cables are signal feeds from the aircraft GPS antennas mounted in the window plus on both sides of the upper deck Timing signals are provided Please see the MCCS SI 02 interface control document for detailed references to both GPS decoders and timing interface definitions Instrument Cabling Patch Panels 2 53 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 8 2 The Science Instrument Patch Panel Opposite the MCCS patch panel is the SI cable drape panel that connects to a similar patch panel mounted on the port side of the telescope s counterweight flange The layout of the SI patch panel is illustrated in Figure 2 40 Co
44. from rotational disturbances The lowest natural frequency of the telescope assembly is about TBD Hz The Fine Drive System controls motions between the inner cradle and the hydrostatic bearing i e between the inner cradle and the telescope metering structure and optics The Coarse Drive System controls motion between the outer cradle and inner cradle During flight the Coarse Drive can move the telescope in elevation from 15 degrees to 70 degrees the Fine Drive can move the telescope in 3 degrees elevation and the azimuth and LOS directions of the telescope by 3 degrees in quadrature Telescope stabilization and fine pointing are described fur ther in the next sub section The telescope Suspension Sub Assembly SUA is the combination of the VIS outer cradle inner cradle hydrostatic bearing and both the Coarse and Fine drive systems The combination of the aircraft bulkhead the telescope SUA and the Nasmyth tube gate valve or an SI mounted on the SI Flange form the pressure barrier between the Mission area cabin and the telescope cavity 1 12 TT Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Figure 1 8 Perspective Rendering of Telescope Assembly In this perspective view part of the aft bulkhead is cut away to expose the telescope Suspension Assembly SUA Some of the Vibration Isolators are visible as small black cylinders like oreo cookies The aft baffle is
45. in optical isolators associated with the secondary mirror TTL control electronics Instrument teams should note the tradeoffs between chopper amplitude throw and chopper off set Whereas chopper amplitude refers to the A C signal of secondary mirror motions the chop per offset is the corresponding D C component The range of chopper amplitudes and offsets are defined in SOF 1011 as follows a Amplitudes of up to 10 arc minutes peak to peak in object space b Offsets up to 5 arc minutes in object space with an amplitude reduced accordingly Diameter of the field of view is 8 arcmin Boundary for the travel range of the FOV in object space white circle due to offset plus chopping is a circle of 18 arcmin diameter outermost circle ma Nominal center of the FOV without chopping and offset The gray area represents the range of all possible positions for the FOV due to offset plus chopping Figure 2 51 Range of Secondary mirror Field of View for Offset Plus Chopping Amplitudes The mirror angle to object space angle conversion factor for the SOFIA F 20 system is approxi mately 3 74 1 2 66 uA Secondary mirror Control CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 11 SOFIA Software Interface The Mission Controls Subsystem MCS is the major portion of the MCCS operation It provides most operator supervisory control and monitoring of the observatory especially of the telescope assembly The MCS w
46. instruments will be considered for development Facility class instruments FSI Principal Investigator class instruments PSI Special Purpose PI class instruments SSI and Facility Support Equipment For the purpose of this Call for Proposals the four classes of instruments are defined as follows 5 1 1 1 Facility class Science Instrument FSI This is a general purpose reliable and robust instrument that provides state of the art science per formance at commissioning through the use of modern but mature technologies The capabilities of a PSI should be focused on a single well defined science and technology theme It is expected that this instrument will routinely be operated by the designated SSMOC SOFIA Science and Mission Operations Center FSI scientist in support of Guest Investigators GI s who will not be required to have extensive knowledge or experience in infrared instrumentation or observing tech niques Routine maintenance will be provided by the SSMOC where the instrument will be housed during extended periods Major maintenance and or upgrades may be provided by either the PI or the SSMOC as proposed Descriptive documentation must be clear thorough and intui tive so that a GI can propose a science investigation without the necessity of extensive discussion with the SSMOC FSI scientist or the PI team The process of data acquisition reduction and cal ibration should be straightforward and transparent to the GI with t
47. mutually agree to be of a privileged nature will be held in confidence to the extent permitted by law 2 Conformance to Guidance USRA does not have mandatory forms or formats for responses to CFPs however it is requested that proposals conform to the guidelines in these instructions USRA may accept proposals without discussion hence proposals should initially be as com plete as possible and be submitted on the proposers most favorable terms 3 Joint Proposals Where multiple organizations are involved the proposal must be submitted by only one of them It should clearly describe the role to be played by the other organizations and indicate the legal and managerial arrangements contemplated 4 Late proposals A proposal or modification received after the due date specified in this CFP will not be considered 5 Withdrawal Proposals may be withdrawn by the proposer at any time Offerors are requested to notify USRA if the proposal is funded by another organization or of other changed circum stances which dictate termination of evaluation 6 Selection for Award When a proposal is not selected for award the proposer will be notified USRA will explain generally why the proposal was not selected Proposers desiring additional information may contact the Chief Scientist who will arrange a debriefing When a proposal is selected for award negotiation and award will be handled by the USRA Contracts Manager 7 Cancellation of CFP USRA reser
48. of appropriate business person nel who may be contacted during evaluation or negotiation e The name s and affiliation of co investigator s Use a second page if necessary f Date of submission and g Signature of a responsible official or authorized representative of the organization or any other person authorized to legally bind the organization 1 Abstract and Proposal Summary The Title Page should be followed by the Abstract and Proposal Summary page The format for this page is given in Section 3 6 2 Description of Proposed Research FSI Proposals The main body of the technical proposal should follow the Abstract and Proposal Summary page FSI proposals should contain concise descriptions of a the key scientific research areas that the instrument will explore b the scientific strength of the community that will be served by the instrument c the instrument concept its potential performance reliability and user friendliness d why the instrument is well suited to the research goals e why SOFIA is required to carry out the research f a discussion of the construction and operating costs of the instrument g a description of the facilities and personnel available for the instrument development h the management plan for the instrument development and operation i the proposed Education and Public Outreach activities FSI proposals may optionally contain a discussion of how the instrument and its development
49. recommendations for mission assurance The SI developer must include a complete analysis to be submitted for DER approach detailing SI electronics airworthiness and calculations displaying that the interface loads are within the constraints specified Grounding Location Figure 2 36 Science Instrument Counterweight Rack Showing Grounding Location Isometric view of the science instrument counterweight rack displays a grounding location and an example of equipment mounting scheme 2 8 Instrument Cabling Patch Panels The observatory provides for installation and operation of up to three PI equipment racks contain ing electronic equipment use to gather process and analyze scientific astronomical data The Instrument Cabling Patch Panels CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 SOFIA instrument racks are interfaced to one another and other instrument subsystems e g the telescope secondary mirror controller telescope gyroscopic readouts or the USRA provided mis sion control software through cable assemblies provide by instrument teams USRA and NASA government furnished equipment Access to much of the aircraft cabling is accessed through one of several patch panels provided throughout the observatory Cabling patch panels are available in several locations aft of the PI instrument rack on the port side of the aircraft near the telescope s pressure bulkhead and on the telescope counter weight as
50. slightly different configurations of the telescope optical path are available Nasmyth 1 Dichroic tertiary reflects infrared radiation down the Nasmyth tube while optical radiation is reflected along a separate yet parallel path to the observatory s Focal Plane Imager FPI Nasmyth 2 A fully aluminized tertiary reflects both infrared and optical radiation down the Nasmyth tube The fully aluminized tertiary mirror has an aluminum coating of about TBD Angstroms with no protective over coat The Nasmyth 2 configuration is used for Science Instruments that desire a lower telescope emis sivity Table 1 3 Optical Parameters of the Tertiary Mirror Optical Parameter Value Mechanical Parameter Value Free Optical Diameter 440 x 310 mm Dimensions 498 x 354 mm Surface Roughness 2 nm TBD Material Herasil fused silica Wavefront Error 80 nm rms TBC Thickness 3 5 arcmin wedge 45 mm TBC Reflective Coating SAGEM Proprietary Weight 11 kg TBC dichroic Reflectance Thermal Time Constant 15 minutes TBD 0 5 um 0 4 TBV Q 100 um 0 99 TBV FIR Emissivity 0 1 TBV Optical Surface center position mm U 2502 4 V 0 W 86 4 SOF SPE KT 1000 0 03 Dichroic tertiary The first tertiary mirror carries a dichroic coating to allow visible light A lt 1 u m to be separated out for the facility Focal Plane Imager FPI Since it is tilted 45 it has an elliptical perimeter The re
51. the boresight or hot spot of the SI is located by tilting the PCLS to illuminate a particular pixel on the detector array This can be done directly in the case of two dimensional imaging arrays i e simply move the source to the desired location or indirectly i e maximize the signal on a particular pixel Once the IR radiation from the PCLS is at the desired location in the focal plane the BSB flip mirror is engaged so that the image falls on the optical CCD camera and the location of the optical image which is coincident with the IR image is recorded This completes the optical alignment procedure on the TA simulator Knowledge of the proper alignment focus and boresight for each SI are the responsibility of the PI team Other Tasks An instrument rotator plate can be used with the simulator to determine whether the boresight wavelength or other parameters of an SI depend on rotation angle If a particular SI does not use 4 10 uA Mission Ground Operations CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 the rotator plate similar effects due to changes in TA elevation could be investigated by physically removing and reinstalling the SI in different orientations If the boresight varies with rotation angle it is the responsibility of the PI team to fully characterize or remove these effects so that the inflight focal plane imaging system can be operated in a simple and straightforward manner The simul
52. the focal plane while others are flat high emissivity black absorbers In some cases buttons may have optical surfaces that are asymmetrical with respect to the secondary mirror axis as the central obscuration of the telescope can be minimized if the buttons optical surface is de centered see SOFIA Technical Note SER ASD 023 Science instrument teams can select a suitable secondary mirror button from several provided by USRA or they can design and build their own The details of the secondary mirror design require ments are found in SOFIA Document TA SSMO 09 Two possible secondary mirror button designs are illustrated in Figure 2 7 The dimensions given in these figures are only approximate Final dimensions depend upon the material selected for the secondary mirror and button Both designs show exposed screw heads on the button surface fac ing the primary mirror these represent x46 of the button surface and if painted black to suppress star light produce a negligible increase in telescope emissivity lt 0 1 96 Clip on secondary mirror buttons designs are also possible provided they meet all in flight loading specifications SOFIA Telescope Optical Prescription CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Secondary Mirror Mechanism SMM Ww pe UN SS Secondary Mirror SM SM Button Figure 2 5 Secondary mirror Assembly Cross Section Cross section of the SOFIA secondary mirror ass
53. the observer to define in a num ber of coordinate systems a start and end point of a scan a scan rate and the precise time for the start point to be crossed by the scan This data taking scan command will scan using a great circle between the two end points of the scan The scan rate is guaranteed from the very start of the scan to the very end since a ramp up and ramp down are automatically added to the ends of the required scan path to ensure the scan rate along the entire scan path This command also gives as broadcast housekeeping the exact time the start and end points are crossed This is in addition to the normal housekeeping data giving the position of the SI boresight on the sky which is updated every 20 milliseconds and time stamped At ORR will only be able to execute great circle constant velocity scans but soon after ORR will have the capability to map out any pattern on the sky within the maximum speed limits of the telescope i e lt 1 degree sec Figure 4 10 illustrates a data taking constant velocity scan while chopping This scan allows an observer to specify which of the chopped images of the IR source the SI boresight should scan The scan also allows an observer to specify how many times the scan should be repeated and if a return path should also be used At ORR there will not be SCL in place to set up an automatic raster scan but an effective raster scan can be produced by making a seque
54. to 15 um but may exceed 20 um if the aircraft is not above the tropopause At 41 000 feet or higher the WV overburden occasionally drops below 5 um The distribution of stratospheric water vapor can be quite variable and the observed zenith burden may change as much as a factor of three on time scales as short as 15 minutes During flight the current observed water vapor value appears in the housekeeping video display updated every 15 seconds These measurements are also available after each flight as plots from the housekeeping data file for the flight 1 5 3 2 Radiometer Design Atmospheric water vapor measurements will be obtained with an infrared radiometry system developed by Dr Thomas Roellig NASA ARC The sensor is a heterodyne mixer configured for the measurement of the 183 GHz rotational line of water The Water Vapor Monitor WVM is mounted at a fixed elevation of 40 in the upper deck of the aircraft The WVM is responsible for measuring the integrated water vapor at 40 degrees while the SOFIA aircraft is at normal opera tional altitudes These data are used to correct the astronomical infrared data obtained by the tele scope and will also be used in the algorithm that determines successful SOFIA observatory flight hours for contractual purposes The WVM reports its measured water vapor overburden to the air craft Mission Controls and Communication System MCCS once every 15 seconds while the SOFIA observatory is in normal ope
55. using a sequence of IR source peak ups in the corner pixels of the SI array 4 20 uA Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 Entities fixed in Telescope Reference Frame Entities fixed in Sky Reference Frame RA amp DEM Los 3 Figure 4 3 Set up for Boresight Measurement Observing on SOFIA 4 21 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 Tracking on source RA amp Dec with Initial SIRF BS E leiiz as Tracking after moving theTracking Position to the Real SIRF BS Figure 4 4 Measurement of SI Boresight Observing on SOFIA 4 22 a SORIA rsscfpaconsena tef nares Astronomy CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 5 3 2 Stare Mode In this mode the chopper i e TCM is centered and static i e there is only one image of the sky in the focal plane and the Observatory uses the designated SI boresight location within the focal plane to point the telescope Since the SI boresight is the designated boresight a command to the telescope to point at a particular RA and Dec on the sky will result in the telescope moving that particular RA and Dec into the SI boresight in the focal plane Once the gyros have been calibrated to the sky at the beginning of each flight and the SI bore sight has been perfected once per mission per SI reference frame configuration the telescope on SOFIA
56. visible as a large dark plate on the aft right side of the telescope metering structure Although no SI is shown the Counterweight Rack CWR for SI electronics is shown as a large blue box on the upper end of the counterweight assembly supported by braces 1 3 1 1 Telescope Primary Mirror Assembly PMA The main telescope optics are a classical Cassegrain configuration with a 2 7 m diameter f 1 28 paraboloidal primary mirror and a hyperboloidal secondary mirror producing an approximately f 20 beam An optically flat tertiary mirror with a dichroic coating reflects IR to the SI focal plane while transmitting visible light A second tertiary mirror reflects the visible light to the facility Focal Plane Imager FPI Information regarding both tertiary mirrors is included below for com pleteness An alternate aluminized first tertiary is available see section 1 3 1 3 Telescope Ter tiary Mirror Assembly TMA on page 1 16 its dimensions are effectively identical to the dichroic tertiary The following sub sections briefly describe each of the main telescope optical Telescope Design and Performance ex pss 1 13 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 elements including basic parameters followed by a description of some properties of the inte grated telescope optics The optical surface is coated with approximately 1500 TBC Angstroms of aluminum with no protective overcoat Table 1 1gives the optical paramet
57. web GIs and PIs can obtain their data from the archive during the proprietary time period using their assigned DCS login and password Other archive users can register with the archive and obtain a valid user name and password for access if they want to retrieve public data from the archive Any user can browse the archive without being a registered user Search and retrieval of science data will be similar to most astronomical data archives Data can be searched based on Project ID observer names Source name name resolver SIMBAD or NED source type Coordinates or coordinate range Instrument filter frequency or wavelength observing mode Date or time range A query may also be a combination of several search parameters Additionally special queries of any keyword or range of values in a keyword stored in an instrument FITS data header may be executed by SSMOC archive analyst using SQL The archive user interface is still being designed and the details of the browser are therefore TBD 1 7 3 2 Summary Archive The SOFIA archive does not contain a special summary archive Summary information is retrieved from stored metadata information and is available to the astronomy community through the archive browser How the browser will format this information to a user is still TBD but any summary listing will contain at least the following information Project id name of observer PI Instrument filter observing mode inte
58. 0 80 0 90 00 70 0 80 Bl 0 60 0 70 m 0 50 0 60 Figure 1 13 Efficiency of Chopping Secondary Mirror A plot of duty cycle versus chop frequency Hz and throw arc minutes This is based on rise times of 4 to 10 ms measured during early bench tests at room temperature in 2002 Efficiency is the percentage of the time that the position transducer waveform was within 10 arc seconds of either end of the motion TBV 1 28 oA Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 f 10Hz A 4 f 10Hz A 8 f 10Hz A 12 AON m ARSE ym E i E N i ERR is f 20Hz A 8 f 20Hz A 12 f 30Hz A 8 f 40Hz A 8 Figure 1 14 SMA Position Waveforms at Selected Frequencies amp Amplitudes Telescope Design and Performance x m 1 29 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 4 Mission Control Sub System The Mission Control and Communications System MCCS is comprised of two major sub systems the Mission Controls Subsystem MCS and the Observatory Support Subsystem OSS OSS basically consists of the Power Distribution System PDS the Mission Audio Distribution System MADS Video Distribution System VDS and Water Vapor Monitor WVM which will be discussed below in section 1 5 Other Observatory Sub Systems on page 1 32 The MCS however is the major portion of the MCCS operation providing the majo
59. 1 46 1 7 1 Observatory Software Simulator 4 cete eee e esee e ee eee ette ee een seen senos etta sette sete ss toss seriosi isos 1 46 1 7 2 Flight Management FM Software crecer eerte ee eee eene nete einen seta setae to setae ttes tees en setas sena 1 46 5723 Observatory Data Archlve sisstscdcsessesaveisescossiecesnssenvecsivnssvodessecsusvsoscsosssctsaissscsesessoseiesesedsessovaceves 1 46 1 7 3 1 Archive ACCESS M 1 47 T 7 3 2 Summary Archive sccassssassssosssessesssascoenesescasessssectsesosesesecsscassocesscnsscseassoccsedassesescsnsseseodeesses 1 47 1 45 Pipeline Products cscesicecsssovcizssacedeassncscosscccsucscoasedecvevedecseuscessbeoisduestoscusesaasvendseercvessncceaseeecs vesseees 1 48 1 7 5 Housekeeping HK Datta secs saissnsssccesecosetconsssocsoosesosesovensdvousesesescusecssensnsssess svescecteassstveess sons H 1 48 1 7 6 Retrieval Of Data 1 48 1 7 7 User Volumes and Initial Hardware Requirements eere e eese eene eee ee eee ee eene enne tnae 1 48 CHAPTER 2 SOFIA Science Instrument CDS eeeeeeeee ee eee eese sees DL 2 1 INtrOdUuctiOn P 2 2 2 2 SOFIA Aircraft and Telescope Coordinate Systems cerei eee ee eee ee eene eren ee eene teneat n esten as enu 2 2 2 2 1 Aircraft Coordinate System 4 cesse ee ee esee eene eene eren set
60. APTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 to control secondary mirror motions over a 9 volt range with a scaling of approximately 125 arc seconds volt Note that the system is design only requires the actual secondary mirror angle to be within the larger of 2 arc seconds or 10 of the angle defined by the above scaling law for a given input voltage The R and S analog waveform output lines represent the actual measured angle about the respec tive secondary mirror axes Users should note that the analog signals are transformed from a suite of 3 sensor signals assigned to the 3 chopper actuators and located in the tilt control mechanism TCM between the secondary mirror and the chopper base in a 120 degree configuration about the LOS axis The signal represents the actual angle measure between the chopper base and the secondary mirror in the local secondary mirror coordinates Note that commanded offsets to the secondary mirror position by either the observatory or the instrument team are not included in the analog waveform output lines To meet the level 1 requirements of the NASA SOFIA pro gram servo controlled motions of tilt control mechanism are generated by the observatory s flex ible body compensation FBC With a supposedly perfectly steady telescope image no chopping the secondary mirror may in fact exhibit motions relative to the telescope structure Such motions are manifest on the raw analog waveforms
61. Amplitude 2 i e sep aration of the zero and minus chop points on the sky in arcsecs Frequency of Chop in Hz Tilt Offset in arcsecs on the sky Tip Offset in arcsecs on the sky and Chop Angle in degrees 4 External Three Point Chop This mode is similar to mode 3 except the TTL signal driving the chop comes from the SI electronics This signal is passed to the SMCU through the SI SMA Junc tion Box see ICD TA SI 04 Chop parameters that can be set via SCL or GUI in this chop mode are Chop Amplitude 1 i e separation of the plus and zero chop points on the sky in arcsecs Chop Amplitude 2 i e separation of the zero and minus chop points on the sky in arcsecs Tilt Offset in arcsecs on the sky Tip Offset in arcsecs on the sky and Chop Angle in degrees Frequency is set by the SI TTL signal 5 External Analog Chop This mode is completely driven by the SI electronics within the chop amplitude limits and intrinsic time constant limits of the chopper i e 10 arcmins TBV on the sky and 10 milliseconds TBV respectively This mode requires the SI electronics to send and receive analog signals through 4 26 uA Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 the SI SMA Junction Box R and S input and output connectors so that the SMCU will drive rotations about the R and S axes in proportion to the voltages in the
62. B 0 0 Figure 1 21 Portable Chopped Light Source The PCLS provides a focused beam of IR and visible light with f ratio 18 The actual distance to the focused image can be adjusted by moving the secondary mirror of the PCLS The PCLS optics are mounted in a motorized gimbal so that the location of the image produced by the PCLS can be translated in the SI focal plane When the chopped PCLS image has been positioned and focused for maximum IR signal from the SI perhaps from a selected pixel of an array then a diverter mirror can be inserted in front of the SI and the location and back focus of the visible component of the PCLS image can be observed and measured using the TAAS boresight camera The PCLS can use an external TTL synch signal from the SI via a BNC connector on the PCLS control chassis 1 44 yz SSMOC Ground Facilities for SI Teams A CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Figure 1 22 View of Chopped Hot Plate Mounted at End of TAAS The chopped hot plate mounts in the same location at the far end of the TAAS It provides a chopped IR bright disk which can be used to verify that an SI pupil is aligned or that an SI spa tial response pattern a k a antenna pattern or central response lobe is centered on the direction to the center of the telescope secondary mirror The chopped hot plate is mounted on an x y stage so it can also be used to map an SI spatial response pattern This device also a
63. Book 2 Observing Program Guidelines Volume 1 Applying for Observation Time Volume 2 etc Volume n etc 0 2 uA Revision History SOFIA IHB 0 0 Infrared Astronomy CHAPTER 1 SOFIA Design and Operation 1 1 1 3 1 4 1 5 1 6 1 7 Overview of SOFIA Observatory and SSMOC eene nnne nnns 1 2 Telescope Design and Performancce eeeeeeeeeeeeeenee eene nnne nnn nint 1 10 Mission Control Sub System ecerneee triente rettet netter tne tt DR ERR ERU RR n ERR RR uuES 1 30 Other Observatory Sub Systems eese nnne nennen nennen nennen nnns 1 32 SSMOC Ground Facilities for SI Teams eeeeeeeenennenennn nnne nnns 1 39 Software and Data Management seeessseeeeeeeeee nnne nnne nnne nnn nnne nnns 1 46 1 1 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 1 Overview of SOFIA Observatory and SSMOC SOFIA Stratospheric Observatory For Infrared Astronomy carries a gyro stabilized telescope into the dry stratosphere to permit observations of radiation of celestial objects at wavelengths from the visual and into the far infrared and sub millimeter Development of SOFIA was directly inspired by the success of the Gerard P Kuiper Airborne Observatory a NASA Ames aircraft that carried a gyro stabilized 0 9 meter telescope The development of SOFIA was an international effort involving a consortium of Europea
64. Conformity CHAPTER 3 Airworthiness SOFIA IHB 0 0 3 5 1 Conceptual Design Review CODR Conceptual design review is to give information on the overall system design and begin to identify critical safety issues This is the first opportunity to show the DERs the mechanical and electrical specifications and to discuss instrument hazards The outcome of this review should be a list of action items that need further details or analysis on both the SI package and the airworthiness pro cess particulars These may include discussion of particular instrument hazards such as cryogen use calibration gases and failure modes General instrument design parameters will be discussed 3 5 2 SI Airworthiness Submittals and Control Process 1 SI Team assigns an internal team airworthiness liaison to L3 USRA The SI team liaison will communicate with L3 and USRA regarding all airworthiness submittals questions and discussions and will be responsible to develop an understanding of the SI guidelines and practices as much as possible The liaison is to maintain communication with the DER L3 USRA as necessary to enable clarity in status and process for airworthiness For example HIPO Ted Dunham FORCAST George Gull 2 SI Team submits data to Bill Johns 3 Bill Johns forwards data on to appropriate DER Schwartz for structural submittal data Todd Seach for Mechanical systems and safety submittal data SSA FHA FMEA FTA and test pl
65. FC power use is routed over the CLA drape for distribution at the science instrument patch panel CODR Conceptual Design Review CWR Counterweight Rack DAR Designated Airworthiness Representative DCR Document Change Request DCS Data Cycle System SOFIA data acquisition and handling software DER Designated Engineering Representative DIN Deutsche Industrie Norm German Industrial Standard EL Elevation FA Flange Assembly FBC Flexible Body Compensation FCM Focus Centering Mechanism FCMU Focus Controller Mechanism Unit FFI Fine Field Imager A 1 APPENDIX A Acronyms and Terminology SOFIA IHB 0 0 Table A 1 Acronyms and Terminology Acronym Term Description FITS file Frames of any image from the WFI FFI or FPI can be logged in a FITS file FM Flight Management FMI Flight Management Infrastructure FPI Focal Plane Imager FSI Facility Class Instrument fwd Forward GFY Government Fiscal Year Gl Guest Investigators GPS Global Pointing System GVPP Gate Valve Pressure Plate HK Housekeeping HW Hardware VF Interface ICD Interface Control Document IFD In flight Director IMF Instrument Mounting Flange INF Instrument Flange INF Instrument Nasmyth Flange IR Infra Red KNAV LFD Lower Flexible Door LOS Line of Sight LOS Line of Sight MADA Mission Audio Distribution System MCCS PDS MCS Missi
66. FIA Science Instrument ICDs SOFIA IHB 0 0 SI Electronics Rack Active Fine Balancer Gate Valve Shroud BSA Main Plate Manually Removable Counterweighs NT Interface Access Port Exhaust Tube and Vacuum Lines I F Figure 2 11 Schematic Sketch of the SOFIA Flange Assembly Schematic shows flange assembly without the cable load alleviator illustrating volume between the IMF and gate valve pressure window subassembly Available space can be used for purposes including a bore sight box calibration source or mounting of small science instruments 2 14 uA Telescope Mounting flange CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2285 89 96 T Hard Point Cabin Side Insulation in CZ TES Je ere e e e Soe ASO IID SAID ESS SHES IK Dowel Pin DORR RRR KAA etel j ORONS p e t e t SK OY Y AKAM tete XKX i e e oe Uu SD ae U 0 0 Optical Window USRA 7 x PWS Gate Valve FM1 Window to FPI __ Figure 2 12 A Cross Section Of The Instrument Flange And Pressure Window Assembly Without The Counterweight Subassembly Details of the instrument flange for mounting SOFIA science instruments is shown with physical dimensions in millimeters The details of this interface are contained with TA_SI_02 2 4 1 Science Instrument Flange Hard Points In addition to the pressure couple optical window assembly interface there are four tub hard
67. HAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 5 Observing on SOFIA 4 5 1 Observing Command and Housekeeping Interfaces Chapter 1 of this handbook gave an overview of the Observatory sub systems including the Mis sion Control Sub System MCS and the Telescope Assembly TA The SI computer electronics physically connects to the MCS through the PI Patch panel near where the SI Racks are mounted in the Mission Control Area of the Aircraft Cabin There are two mechanisms for communication and data exchange between MCS and the SI sys tem the SOFIA Command Language SCL and data definition XML files SCL allows scientists and other Observatory personnel to control Observatory observations and to access other MCS software functions controls and services from onboard SI computers and Observatory worksta tions i e consoles Commands are entered by activating previously composed scripts XML files and through command line interfaces and GUI selections These SCL commands are passed to MCS where validation and translation into the appropriate direct commands to the telescope or other subsystem occurs As mentioned in Chapter 1 there are two exceptions to the rule that all SI Observatory control and monitoring is through the MCS one exception is the direct interface to the three imagers 1 e FPI FFI and WFD digital outputs the other exception is the direct link to the secondary Mirror Control Unit SMCU see Chapte
68. I Proposal and Review Process SOFIA IHB 0 0 man prepares a final report of the review and delivers the report to the observatory directory within two week of the instrument review The observatory director following receipt from the board chairman distributes the final report to all meeting attendees The basis for the preliminary design review is the development of a project implementation plan PIP The PIP is expected to evolve over the life of the project and serves to describe the instru ment s form and function to the observatory staff The PIP is divided into five sections 1 speci fication and verification of the instrument requirements and design 2 required interface control documents 3 FAA certification plans 4 project management plans schedule and budget and 5 instrument risk identification mitigation and descope Prior to the preliminary design review the SOFIA science support IPT is expected to contribute to the formulation of the PIP and pro vide concurrence on the following issues Preliminary instrument requirements are stated Design concepts are feasible and the proposed approach is viable e Suitable trade study rationale Listed problem areas and risks in the proposed approach e Stated adequacy of schedules resources and planning The primary purpose of the PDR is to verify that the technological implementation satisfies the operational requirements proposed by the instrument teams The review board v
69. IA Design and Operation SOFIA IHB 0 0 4 SMCU Secondary Mirror Control Unit This sub system controls the Focus Centering Mech anism FCM and Tip tilt Chopping Mechanism TCM of the Secondary Mirror Assembly SMA The observer can communicate to it through the MCS which talks to it through the TAMCP The observer can also communicate directly to the SMCU in limited ways through the direct SI to SMA link as described in the ICD TA_SI_04 1 5 Other Observatory Sub Systems The SOFIA observatory requires a host of additional hardware for successful operations both in the air and on the ground A number of these subsystems are described below 1 5 1 Cavity Door System CDS The Cavity Door System was developed to maintain the telescope cavity aero acoustic environ ment within limits to minimize the impact of an open telescope cavity upon aircraft performance and to track position commands from the MCS so as to maintain TA and Cavity Door Aperture alignment The major components consist of Upper Rigid Door URD Aperture Assembly and Lower Flexible Door LFD Fairings e Cavity Door Drive System CDDS RD Seal System 1 5 1 1 Aperture Door Assembly The URD LFD and Aperture Assembly AA are capable of smooth operation within their full ranges of motion on the ground and under operational load conditions specified at altitudes of 35 000 feet and above The normal operating envelope of the observatory with the door o
70. Instrument N 74 Grounding and Power Connections VU above showing SI isolated from TA l 51097 OIL c AYER USER GND meum amp POWER LINES FADILITY gem GROUND LINES FACILITY POWER LINES Figure 2 43 A Schematic Of Telescope Instrument And PI Rack Grounding The science instrument is electrically isolated from the telescope structure 2 9 Science Instrument and TA Flange Pumping System Among the lines within the SOFIA telescope cable load alleviator are three vacuum pump lines The actual vacuum pumps are located in the aft portion of the aircraft s upper deck Vacuum pump lines 76 2 mm 3 inches outer diameter run along the ceiling and drop near the CLA U4 disconnect panel The lines from the pumps to the disconnect manifold is approximately 20 meters 66 feet in length 2 58 A Science Instrument and TA Flange Pumping System CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Vacuum Pumps located on upper deck 3 OD vacuum lines Manifold Disconnect Panel U4 Figure 2 44 A View Showing The Science Instrument Vacuum Lines Manifold CLA And The U4 Disconnect Panel Science Instrument and TA Flange Pumping System SF sae 2 59 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 a KF40 Flange per ISO 2881 1 and DIN 28403 TYP r Centering Ring MDC 710002 I TYP r 98144423 001 Fitting x4 STA 1692 5 STA 1688 0 STA 1683 5
71. SSMOC Ground Facilities for SI Teams CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Access into the SSMOC through all exterior doors of N211 will be controlled through the use of locked or monitored doors Access to the ramp area and SSMOC hangar floor will not be permit ted to unauthorized personnel Examples of controlled areas within the SSMOC which will require special access clearance are aircraft parts equipment storage rooms UAL tool rooms possible PI GI labs and SIL SOFIA flight operations at NASA Ames will not be conducted on Saturday and Sunday However some limited SSMOC facility support will be available on weekends as needed including access to SI labs electrical power network connectivity and access into the aircraft if necessary Also flight operations will not be conducted on 10 Federal holidays New Year s Day January 1 Martin Luther King Day January 20 President s Day third Monday in February Memorial Day last Monday in May ndependence Day July 4 Labor Day first Monday in September Columbus Day October 12 e Veteran s Day November 11 e Thanksgiving last Thursday in November Christmas December 25 Note Aircraft access may be precluded at any time by some maintenance tasks or other aircraft related pre flight activities 1 6 1 2 SSMOC SI Support Physical Facilities The SSMOC floor plan is illustrated in Figure 1 19 Locations that SI teams and Genera
72. The potential benefits of new technology developments that will be incor porated in the instrument together with their associated risks and cost impacts Technology devel opment specific to the instrument should be clearly described 6 Education and Public Outreach It is advantageous for proposals submitted in response to this CFP to include a plan for interfacing with and complementing the SOFIA Education and Public Outreach Activities E PO Two examples of the items to incorporate are 1 a channel to make selected and prepared data publicly available for purposes of education and public information including formats appropriate for the press and 2 a time commitment by instrument team mem bers to interact locally with teachers and students in a specified manner that furthers the goals of E PO Further examples will be posted on the website The points listed above should be addressed in a direct organized and concise manner For Facility Support equipment only 3 4 and 5 above are appropriate Functional overlap of a science instrument proposed in response to this CFP with a proposed SOFIA German instrument will NOT be an issue and will NOT be considered in the evaluation for this CFP A current list of possible German instruments can be obtained by request to USRA 5 3 Guidelines for Participation in the Instrument Program 5 3 1 Purpose These guidelines provide procedural and format information for submission of prop
73. UIT BEWEIS RR 4 3 4 2 2 Flight Planning S Of Wate s cicssescrseossossenssosasocacsocesosensecessvsesesossaossesseesbosavbessstosesesesossssvessooseaobesoese 4 5 4 3 Pre Shipment Pt EIE 4 6 4 4 Mission Ground Operations sscssscssscsssccesssossscsssesssssssesccesssessecssssssssssosssosssesssecsonscsosssosssesssesssnassess 4 6 4 4 1 Overview of SI Team Integration into SSMOC Operations 4 eese eee eite ee seen neenon natns ennae 4 6 4 4 2 SI Check out in the SSMOXC eere eee e e etes eese seen stantes tenens tastes tes sons tn stas eta ESTen 4 7 4 4 2 1 TA MCCS Simulator Procedures 4 eee eee eee eee esee eee etes en tna tn seta sts tt sn setae siso psss 4 8 4 4 3 SI Installation on the Aircraft eee eee eee eese ee eese esee seen tentata sta s ei oss seta stessa ssoi saisie 4 11 4 4 4 SI Data and the SSMOC Data Cycle System DCS eee eee eere eerte eee e teet eene ene seen ot enu 4 13 4 4 5 Minimum Science Capabilities eres eee eee seen eee ee eee ete etta setae enne eaaet te sete stas ease ta sees neta 4 13 4 4 6 Implementation of Minimum Science Capabilities e eese eee eere eese e enne tn eene nano 4 15 SOFIA IHB 0 0 v Contents 4 4 7 Interfaces between Science Instruments MCS and the DCS eee eee ecce eee ee eee ee teet ee 4 16 A S ODserving orn SORTA
74. Unit SMCU 2 62 Figure 2 48 Definitions for External Command of Secondary mirror Motions esee 2 64 Figure 2 49 Three Point Chopping Using A Two State Synchronization Line With The Potential For A 180 Phase Re Mog 2 65 Figure 2 50 Possible Line Delays Schematic esses enne nnne nnns 2 66 Figure 2 51 Range of Secondary mirror Field of View for Offset Plus Chopping Amplitudes 2 66 Figure 4 1 Typical Flight Plan from Moffett Field essen eene enne nnne entente nnns 4 4 Figure 4 2 DCS Components and Interfaces essent nnne een eere en ree trennen 4 16 Figure 4 3 Set up for Boresieht Meas rement s irtee eriein pae rennen rennen teen eas 4 21 Figure 4 4 Measurement of SI Boresight esses netten trennen aE tren rre E as nnns 4 22 Figure 4 5 Nod Beam Sequence of TWO elite erento ree els Baan ERE eet ire cele 4 25 Figure 4 6 Two and Three Point Chopping on the Sky sssseeseeeeeneneneeneen eee menn emen 4 28 Figure 4 7 View from Focal Plane When Two Point Chopping eseeeeeeseeeeeeeeeeeeeeneee eere 4 29 Figure 4 8 Two Point Chopping when Track Star in FFI oo eee ec eeeesecseceseeseeeseceeceseseeesecseesaeeseeesesseeeaeeseeeas 4 30 Figure 4 9 Two Beam Nod Chop Set up sse eene nenne nne eteennretee teen nne nne netten 4 32 Figure 4 10 Scanning while Chopping reete ri
75. Volumes and Initial Hardware Requirements Initially the number of SOFIA archive users is expected to be rather small The user base will grow rapidly once science data become public and with accumulation of new data and increased observing efficiency for each observing cycle The archive is therefore designed to be expandable both in terms of storage capacity and server capacity i e how many simultaneous users the archive can support Since storage media serv ers and data links become cheaper every year there is no reason to over design the archive Dur ing the first year of operations we expect to have at most 10 simultaneous archive users which can be handled by three high performance workstations running the archive software including the Informix server one web server and one FTP server The media for data storage will initially be hard disks with backup on two additional sets of hard disks 1 48 uA Software and Data Management SOFIA IHB 0 0 Infrared Astronomy CHAPTER 2 SOFIA Science Instrument ICDs Z1 Introducti fo oocccreicecceceeesseeceteess teceeeeessccet cess seeetenegstccedesdesiecerecesseceecessdsearetesedizeerivesieaevegsesteeters 2 2 2 2 SOFIA Aircraft and Telescope Coordinate Systems seen 2 2 2 3 SOFIA Telescope Optical Prescription lleeeeeeeeeseeseseeeeee essen ener nennt 2 4 2 4 Telescope Mounting flange neeseeeeeeeeeeeeeeen
76. able of contents should be provided Facility Class Science Instrument proposals shall be limited to 60 pages Principal Investigator Class Science Instrument and Special Purpose Principal Inves tigator Class Science Instrument proposals shall be limited to 30 pages Facility Support Equip ment shall be limited to 15 pages The page limit for all proposals includes the abstract text figures tables references and any appendices but does not include the title page the table of con tents page the budget and its explanation vitae and certification attachments Reprints and pre prints should not be included with the proposal Prior results that are relevant to the proposal should be referenced and or concisely summarized in the text Note All proposals that do not meet these page requirements will be returned to the proposer 5 3 3 3 Cost Plan If USRA funding support is required a cost plan prepared as shown in Appendix D should be sub mitted The total cost of the proposed development should also be reported on the Abstract and Summary Page Instructions for preparing cost plans are as follows 1 Proposals should contain cost and technical parts in one volume do not use separate confiden tial salary pages As applicable include separate cost estimates for salaries and wages fringe benefits equipment expendable materials and supplies services domestic and foreign travel publication or page charges consultants subcontracts
77. additions 4 4 5 Minimum Science Capabilities In order to ensure that the DCS development resources were properly staged the DCS team pre pared a list of minimum requirements in May 2001 These minimum requirements were pre sented to and endorsed by the SOFIA Science Council and the SOFIA Science Steering Committee in summer 2001 and the NASA OSS Origins Subcommittee in May 2002 The minimum Science Capabilities at the time of ORR will be 1 Electronic Proposal preparation tool both for FSI and PSI instruments a Observing time estimators web based tools for FSI instruments tables and graphs for PSI instruments b AOT AOR editors and Observation Planner for FSI instruments visibility estimation will ini tially be done by tables and graphs c Proposal handling software 2 Hlight Planning and Scheduling a Manual at first long term goal is a fully automated planner 3 In flight Quick Look of science data 4 Data Pipelining of FSI data Mission Ground Operations CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 a Algorithms provided by instrument teams b Automation of pipelines implemented by DCS 5 Data Archive a Raw science data including calibration data to be archived for all science instruments All raw data will be available in FITS Ancillary data may be stored in the archive as Binary Large Objects BLOBS b Archiving of all HK data c Ability to search browse and retrieve all
78. aded to the Mission Control Sub Telescope Design and Performance x T 1 21 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 system MCS through XML files The observing modes supported by the SOFIA Mission Con trol System are detailed in Chapter 4 of this book Several sub systems and procedures are involved in providing the stability and precise pointing ability of the telescope These may be described as five stages of increasing precision and stabil ity The five stages are The Aircraft Autopilot See 1 3 2 1 The Aircraft Autopilot on page 1 22 Vibration Isolation See 1 3 2 2 Vibration Isolation on page 1 22 Spherical Hydrostatic bearing See 1 3 2 3 Spherical Hydrostatic bearing on page 1 23 Gyros and torque motors See 1 3 2 4 Gyros and Torque Motors for Three Axes on page 1 23 5 Imager Star Tracker See 1 3 2 5 Imager Star Tracker on page 1 24 BR WN The fine pointing stability is set by the gyro torque motor control system and the fine pointing accuracy precision is set by gyro updates from the imager star tracker system 1 3 2 1 The Aircraft Autopilot The first stage provides the attitude and heading stability of the 747SP aircraft To prepare for observing an object which has initial azimuth A the Pilot turns the aircraft onto a true heading of A 90 placing the object within the 3 azimuth range of the telescope mounting During the observing
79. age support mechanism that provides spatial chopping and control of focus centering and static tip tilt of secondary mirror The Tilt Chopping Mechanism TCM is supported by the Focus Centering Mechanism FCM the latter is effectively a hexapod The Secondary Mirror Assembly is supported above the primary mirror by three CFRP spider vanes The secondary mirror parameters that can be changed in flight are focus centering static tip tilt chopping fre quency amplitude and position angle Details concerning the operations and performance of this system are given in Chapter 2 Various buttons are available to mount onto the center of the secondary mirror These are used to absorb or reflect any thermal emission or reflections from structures nearly on axis such as the tertiary support and the aft end of the hydrostatic bearing tunnel The two buttons that are avail Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 able from the SSMOC have 90 mm diameters one is a reflecting cone the other a flat Ball IR Black button It is the responsibility of the Principal Investigator for each SI to specify a preferred choice of Secondary Mirror and secondary button to the SSMOC Point of Contact for that PI s flight series It is expected that only one configuration of SM and SM button will be used for a particu lar flight series 1 3 1 3 Telescope Tertiary Mirror Assembly TMA Two
80. air and removes any ambient water vapor thus preventing condensation on the SOFIA telescope optics The ground dewars are disconnected about 30 minutes before takeoff At this time the telescope pri mary mirror is usually at about 30 Celsius Nitrogen flow into the telescope cavity is main tained through takeoff with on board liquid nitrogen dewars until the aircraft is above 25 000 After observing is concluded and the door is closed a desiccant dryer connected to the air condi tioning system of the aircraft purges the cavity with warm dry air and maintains an overpressure during descent landing and cavity warm up on the ground to prevent water condensation on the telescope optics The warm up period for the cavity usually is 2 to 3 hours in duration some of which is occurring during descent When the primary mirror temperature has risen above outside ambient dew point access to the cavity is permitted Without using the heaters the cavity may be opened about eight hours after landing Other Observatory Sub Systems x xim 1 33 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Full Pre Cool 93 67 10 20 30 40 50 Time After Take Off hours No Pre Cool 93 46 Primary Mirror 6 sensors ee Spider w ee OS d 20 30 40 50 Time After Take Off hours Figure 1 16 Telescope Temperatures with and without Pre Cool The six primary mirror temperature sensors are located on the uncoated surfaces of the
81. and four stories high Three of the walls contain offices meeting rooms labs and other work areas on three floors The east wall consists almost entirely of motorized hangar doors that open to allow moving the SOFIA aircraft into and out of the han gar Facilities for SI support before and after flight are on the ground floor These include two SI labs and the Pre Flight Integration Facility PIF Other areas offering support for SI teams include Science Support staff computer and data archiving facilities and the Mission Operations and Support MOS staff The Science Support staff is led by the Project Scientist the MOS staff by the MOS Associate Director and both are directly under the Observatory Director 1 6 1 1 Facility Access Due to the nature of the facilities equipment and operations conducted within the SSMOC access to the building interior and certain other areas within N211 is controlled at all times All SOFIA employees and visitors receive appropriate training related to their work assignment or access needs and the SOFIA badge issued to them identifies their level of training and access clearance Personnel without proper clearance or training may have access to all or most facility areas or the Observatory if accompanied by an escort in at all times NASA Ames photo identification badges by themselves are not sufficient permit the wearer to gain access to the SSMOC without first obtaining a SOFIA badge in the lobby
82. and operation plans would change if the proposers wish to have it considered as a PSI if it is not selected as a PSI 3 PSI and SSI Proposals PSI and SSI proposals should contain concise descriptions of a the key scientific research areas that the instrument will explore 5 6 A Guidelines for Participation in the Instrument Program wr HP CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 b the instrument concept its potential performance and reliability c the technology readiness and technology development plan d why the instrument is well suited to the research goals e why SOFIA is required to carry out the research f a discussion of the construction and operating costs of the instrument and the uncertainties in these costs g a description of the facilities and personnel available for the instrument development h the proposed Education and Public Outreach activities The difficult choices that must be made between instrument study proposals will require an evalu ation of estimated system performance including sensitivity field of view spectra range and resolution Each proposal should provide an estimate of these quantities that is understandable to the peer review panel 5 3 3 2 Proposal Length The proposal body should be double spaced using a 12 point font and have inch margins on all sides Pages that fold out are not acceptable Each page should be numbered consecutively and a t
83. aneously and one de installation at its conclusion The science instru ment defines the mission The science instrument could be a facility class instrument FSI a prin cipal investigator class instrument PSI or a special class instrument SSI The FSI will be managed and supported by SSMOC personnel the PSI and SSI by Principal Investigators PI s from the science community Both the FSI s and PST s could have a number of different investiga tors called Guest Investigators GI s using them within a single mission and all science instru ments could have a number of missions within one year The final SOFIA science flight schedule will optimally group the observations the investigators and the science instruments into missions which are scheduled so the highest priority astronomical objects of interest can be observed for the length of time required The need for a deployment or deployments will be assessed and if necessary will be scheduled COMMENT See 3 2 7 below Where is this The scheduling task for all the SSMOC activities resides in the Operations Control Center of the SSMOC see 3 2 7 with inputs from the SSMOC management team and all the SSMOC func tional groups Once the annual schedule has been determined it will be reviewed by the SSMOC management team and NASA and once approved placed on the SOFIA website This then is the master schedule a 12 month plan with all the science flights science instruments in
84. ange is a rotation about the U axis also called EL The other orthogonal axes are the V cross elevation axis also called XEL and the W line of sight axis also called LOS To avoid static friction the telescope motors are not mechanically coupled to the telescope Torques are applied by varying the magnetic fields of stator coils attached to the telescope assem Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 bly s inner cradle The stator fields react against the fixed fields of permanent magnets mounted on a rotor ring attached to the hydrostatic bearing Nasmyth tube The stator currents are modu lated by error signals from their corresponding gyros which are mounted on the telescope near the bearing To permit slewing the telescope manual control of the torque motors is available at the Telescope Control Console The maximum slew rate is 1 degree per second Large elevation changes require rotation of the inner cradle with respect to the outer cradle of the telescope Assembly by the Coarse Drive system which is a direct mechanical drive 1 3 2 5 Imager Star Tracker The fifth stage is represented by the imager tracking system consisting of three imagers their associated optics and digital processing electronics The system uses the digitized video image of a star to obtain relative pointing information at a few Hz with arc second angular resolution Error signals genera
85. ans Bill Johns reviews electrical submittal data Appropriate DER reviews and responds to submittal through Bill Johns Comments directed to team from Bill Johns back to PI Airworthiness liaison for team Iterate package as necessary Keep track of the submittal data and responses using the USRA provided spread sheet The spread sheet will be presented as part of the SITR meeting update NYA tA R For submittal status and to solicit comments call Bill Johns directly If you have a specific ques tion for any of the DERs then they can be contacted directly for assistance and clarification Spe cific engineering and safety concerns questions can be addressed to Ted Brown USRA chief engineer and Richard Bacher SRM amp QA manager Bill Johns 254 867 4148 Bill Johns gIlSL 3Com com Peter Schwartz 830 438 7486 peter schwartz g jetaviation com Todd Seach 903 457 5749 todd_seach hotmail com gt Science Instrument Certification General Process Overview i dm 3 5 CHAPTER 3 Airworthiness SOFIA IHB 0 0 Ted Brown 650 604 6020 tbrown mail arc nasa gov Richard Bacher 650 604 3912 rbacher mail arc nasa gov 3 6 Construction Inspection and Testing This phase of the program will include part manufacturing part conformity inspection and test ing During the part manufacturing phase some or all parts will require part conformity by an FAA DAR Additionally conformity will be required at sub assembly and final assembly phase
86. ansformation automatically and preserving the ability to blind point the telescope NOTE If the IR source being observed is not inertial 1 e non sidereal e g a Solar System body then must set the inertial no flag and no gyro to sky update will take place Observing on SOFIA x xm 4 19 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 The above general description was for centroid type tracking However there is another form of tracking called limb tracking This also can be accommodated by the Tracker with the addi tion of another AOI i e in addition to those around a track star and two rotation stars placed on the limb of the extended object being observed e g the moon 4 5 3 Set ups and Observing Modes Supported at ORR 4 5 3 1 Selecting and Perfecting SI Boresight The SCL User Manual shows how an SI user can designate the SI boresight as described in the SI Data XML file supplied to the MCS by the SI user as the boresight to be used by the MCS to point the telescope instead of the TA boresight or one of the imager boresights for example This manual also shows how an SI observer can perfect the designated SI boresight and SI array rotation w r t the imagers where applicable in either the stare mode or chop mode since some SIs must chop to detect a signal It is assumed that a particular SI boresight need only be perfected once within a flight series and probably
87. arrier between the cabin and cavity The maximum weight permitted for a science instrument and its electronics mounted to the SI Mounting Flange or Counterweight Assembly depends upon the location of the SI s and its equip ment s center of mass with respect to the hydrostatic bearing fulcrum see Chapter 2 SOFIA Science Instrument ICDs on page 2 1 for details After installation of the SI the telescope is balanced by a proper distribution of counter weights on the BSA The telescope assembly must be well balanced about all three axes of motion provided by the spherical hydrostatic bearing The balancing procedure is performed by SOFIA staff and may require several hours for a new SI Small changes in balance e g cryogenic depletion are automatically compensated for by motor driven counterweights during observing Permanent cabling to the science instrument and the secondary mirror controllers are accessible through patch panels located forward of the telescope Additional lines run to a second patch panel mounted on the forward portside of the aircraft s pressure bulkhead A single cable drape connects the two patch panels and eliminates the need for the free hanging cables All science instrument interfaces to the observatory are discussed in Chapter 2 of this document 1 20 T Telescope Design and Performance A dAl a CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Figure 1 10 SI Mounting Flange of Telescope A
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89. at the SSMOC the SSMOC science coordinator will show the PI GI the facilities especially the PI labs PI GI offices telescope MCCS simulator data center and final flight plan 4 6 uA Pre Shipment Logistics CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 ning facilities The PI GI will be introduced to the in flight director for the mission who will help coordinate the PI GI science team with SSMOC operations education and public outreach and mission operations and support aircraft operations and support and the continuous improvement programs during the mission The in flight director will make sure the Observatory especially the telescope is configured correctly for the PSI as per the PI s written instructions on file which have been re confirmed by the PI for that particular mission b After the PSI has been assembled and readied for the mission in a PI lab usually a weeklong process the PI team will be assisted by flight mission crew in integrating the science instrument into the airborne observatory via the telescope MCCS simulators This will occur a few days before their first flight In this way the SSMOC mission crew will be familiarized with the science instrument interfaces to the telescope and MCCS before the first flight c On the first flight day of the series normally a Monday the science instrument will be attached to the telescope on the aircraft and integrated with the aircraft MCCS and
90. ation data taking This allows a modified version of the freeze mode where a smaller LOS deviation is set as the limit and LOS rewinds are performed more frequently The telescope will lose stability if it moves more than 3 from center in azimuth This may occur while slewing in turbulence or if the aircraft develops a large heading error The SOFIA flight planning software calculates the required aircraft heading for a particular flight leg based on a centered telescope in azimuth and the location on the sky at a given UT date time of the object being observed on that flight leg The flight planning software then translates this to a ground track required information for Air Traffic Control If winds aloft are different from those pre dicted then the ground track will differ for a given aircraft heading This is called a ground head Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 ing error and usually has to be corrected either by instigating a slight aircraft heading deviation making the TA not centered in Azimuth or a short dead leg to get back on track No observa tions are carried out on dead legs The Telescope Operator may also find it necessary on occasion to center up the telescope This action mechanically settles the telescope into the centers of the range of the torque motors Cen tering takes about ten TBV seconds after which the telescope may be un cage
91. ations involved a high fidelity replica of the Instrument Nasmyth Flange INF was used as the basis for the TAAS A duplicate of the INF was provided by the TA contractor at the time of construction and the dimensions are within x TBD ofthe actual INF on the telescope A schematic drawing of the TAAS appears in Figure 1 20 1 42 uA SSMOC Ground Facilities for SI Teams wu EF Fa CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 6 foot long Nasmyth type tube to hold INF Vessel and alignment sources Alignment source mounting flange ASMF Exact replica of the TA INF Vessel including insulation and instrument mounting flange System CG aft of to ASMF is 117 inches 4396 front legs with 600 kg of distance to SMA SI installed Distance from nominal focus Figure 1 20 TAAS Schematic A photo of the replica of the INF is shown in Figure 1 20 A 2 meter long tube connects this to a mounting area for alignment sources Both the INF replica and the attached tube are elevated on supports at a height similar to the nominal height of the actual telescope INF above the aircraft cabin floor Three alignment measuring devices are available with the TAAS These include a modified Porta ble Chopped Light Source PCLS adapted from the KAO unit a diffuse emitting chopped hot plate and an optical boresight camera SSMOC Ground Facilities for SI Teams x 1 43 CHAPTER 1 SOFIA Design and Operation SOFIA IH
92. ator will allow polarizing grids to be inserted in the optical path between the simulator sources and the SI The acquisition installation and use of appropriate grids will be the sole responsibility of the individual PI teams The simulator will have a bent optical path 90 degrees with a single reflective tertiary Neither the dual tertiary nor the focal plane imager on the TA will be duplicated on the simulator other than mechanical interferences In conjunction with the facility rotator plate the simulator could be used to measure the polarization of a beam splitter or mirror as a function of angle 4 2 1 c MCCS Interface The simulator will possess an interface patch panel and cable drape identical to that used in flight All electrical connections between the SI and the MCCS will be physically present and the com munication protocols between these two systems can be verified The simulation of MCCS responses to SI commands will be as faithful as possible For example the MCCS indicator of TA stability and the transfers of housekeeping data will be fully operational although the buffer con tents for the latter will either be playbacks of old flight data or dummy data of some sort On the other hand the nod command for the TA will produce a status change in the MCCS but will not be coupled to the alignment sources so there will be no physical change in their output Weight and Balance Only the weight of the SI is measured on th
93. atory Sub Systems e eere ette eee esoe eos Eno atenta setas ets sts stas SESS tasses sens 1 32 1 5 1 Cavity Door System CDS eres e eee eese esee ee eese tenants stes osisssa sesse sesso ta se tns esses tense tns ena 1 32 1 5 1 1 Aperture Door Assembly eese eene eerte enenatis east en sten tosta setas s tesa ease tone tas essen soo 1 32 1 5 1 2 Cavity Door Control e eese eee eene eee ettet enata senses staat en atentos toss tasses sto se tosta seins ease 1 32 IREEZO DANTUR 1 33 1 5 2 Cavity Environmental Control System CECS eee e eee eee eese eese eene entes tea sten sense tane tuae 1 33 1 5 3 Water Vapor Me s remierni 7 ceo esee eere oa cecnssisevotissocesasensesescececsosscasesdavcch soasdceestedseseseseosts EET 1 34 SOFIA IHB 0 0 iii Contents 1 5 3 1 Variations in Overburden cccssscsscssssessscssscsssssssssssessssssssessnessnsscssscscsssessnssnssssnscoese 1 35 1 5 3 2 Radiometer Design 4 eee ee eee ee eese eee eese eee eene setas tna seen sesto sese enses ease tes tenes etos seen ss oS 1 35 1 5 3 3 Principles of Operations eee eee eere eee eene eene eren nette seta senos sten sse ta sets tones eene seen as ena 1 35 1 5 3 4 Calibration sS 1 36 1 5 3 5 Typical Post flight Results cscccsscesssssscssessscesscesccsescessscessecses
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95. bserved The Flight Executor is in flight software that executes a flight plan constructed by the flight planner The cycle scheduler is a software tool needed for gross scheduling of a whole observing cycle The automatic flight planner is an artificial intelligence project being developed by NASA Ames Research Center s Code IC The FMI will be hosted in the SSMOC for planning and simulation purposes and on the SOFIA aircraft workstations for execution and re planning Before every observing cycl e the SSMOC management team will decide how many engineering flights are needed and how much observing time can be supported They will decide what instru ments are available and find out when and how much observing time each PSI SSI team can max imally support After the Time Allocation Committee TAC has ranked the proposals and made their recommendation for time allocation the SSMOC scheduler will use the cycle scheduler to do a preliminary block schedule This schedule will show when each instrument will be on the telescope and for how long but without any detailed flight planning SSMOC personnel will do all the flight planning for FSI instruments using the manual flight plan ner General investigators which have been allocated time by the TAC are required to file a detailed observing plan and a complete set of Astronomical Observation Requests AOR The DCS provides tools for filing the observation plan and associated AORs The flight planner
96. can be set via SCL or GUI in this chop mode are Chop Amplitude i e separation of the plus and minus end points on the sky in arcsecs Frequency of Chop in Hz Tilt Offset in arcsecs on the sky Tip Offset in arcsecs on the sky and Chop Angle in degrees 2 External Two Point Chop This mode is similar to mode 1 except the TTL signal driving the chop comes from the SI electronics This signal is passed to the SMCU through the SI SMA Junction Box see ICD TA SI 04 Chop parameters that can be set via SCL or GUI in this chop mode are Chop Amplitude i e separation of the plus and minus endpoints on the sky in arcsecs Tilt Offset in arcsecs on the sky Tip Offset in arcsecs on the sky and Chop Angle in degrees Frequency is set by the SI TTL signal 3 Internal Three Point Chop This mode is driven by a TTL signal internal to the Secondary Mir ror Control Unit A three point chop consists of three colinear settling points plus zero and minus in a chop cycle The SI data computer synchronizes to the chop by receiving through the SI 5MA Junction Box the same TTL signal that is driving the three point chop see the ICD TA SI 04 ICD TA SI 04 shows how a two state TTL signal drives a three state chop Chop parameters that can be set via SCL or GUI in this chop mode are Chop Amplitude 1 i e sep aration of the plus and zero chop points on the sky in arcsecs Chop
97. ccepts an external TTL synch signal from the SI The IR emitting area is 15 cm diameter TBD and is located 3 meters TBD from the equivalent of nominal focus location 30 cm outside the INF SI mounting surface After either one of these sources are mounted on the TAAS an airtight enclosure may be installed and the light path to the SI may be purged with dry nitrogen gas if desired Note Nitrogen purging should be coordinated in advance with the Mission Operations and Support MOS manager on duty The TAAS is located in the center of the PIF and sufficient floor space is available for one or more SI racks and any other equipment needed 1 6 3 Computational Facilities Other computational support facilities in the N 211 hangar include additional workstations and terminals linked by an Ethernet network which in turn is linked to the Internet While the SOFIA 747SP is parked in or near the hangar the aircraft network may be connected to the hangar net SSMOC Ground Facilities for SI Teams QA 1 45 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 work and so to the Internet by a 200 foot co axial cable The Internet address for the system administrator of the Bldg N 211 network is sysadmin sofia arc nasa gov 1 7 Software and Data Management 1 7 1 Observatory Software Simulator The basic architecture of the computer network and software on the aircraft has been reproduced in a self contained SOFIA Si
98. ce instrument communication and signal cables are contained within the left hand side of the CLA 2 56 T Instrument Cabling Patch Panels CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Patch Panel Power Cables Patch Panel SI Cables and Lines Cables to Balancing Subassembly Cables from Balancing Subassembly to Patch Panel Signal Lines Junction Box Cables from Patch Panel to Science Instruments e g routed by Scientists Cables to Balancing Subassembly Cables to Aircraft Systems Cables from CLA Cable Cable via CLA Cable T Tray to CLA Tray to CLA Figure 2 42 Cable Routing Aircraft System To Science Instrument With Signal Cables 2 8 4 Science Instrument Grounding Recommendations A separate interface document outlines the recommended grounding practices for science instru ments and electronics mounted in the counter weight rack and forward PI instrument rack Instrument Cabling Patch Panels ex 3 2 57 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 BALANCING SUBASSEMBLY 2 RIGHT SI Patch Panel pnver qnd LIEU TELESCOPE OPTICS INSTRUMENT INF INTING FLANGE INF tub SCIENCE INSTRUMENT Gyro Subassembly GYSU NASMYTH TUBE N ms SOFIA Science
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100. ch an itemized list explaining the need for each item and the basis for the estimate E Subtotal Estimated Cost Enter the sum of items 1 2 a through 2 f 3 and 4 F Less Proposed Cost Sharing if any Enter the amount proposed if any If cost sharing is based on specific cost items identify each item and amount in attachment For Total Estimated Cost enter the total after subtracting item 6 from item 5 5 3 8 Additional Proposal Forms and Certifications 5 3 8 1 Certification Regarding Debarment Suspension and Other Responsibility Matters Primary Covered Transactions This certification is required by the regulations implementing Executive Order 12549 Debarment and Suspension 34 CPR Part 85 Section 85 510 Participants responsibilities The regulations were published as Part VII of the May 28 1988 Federal Register pages 19160 19211 Copies of the regulations may be obtained by contacting the U S Department of Education Grants and Con tracts Service 400 Maryland Avenue S W Room 3633 GSA Regional Office Building No 3 Washington D C 20202 4725 telephone 202 732 2505 A The applicant certifies that it and its principals a Are not presently debarred suspended proposed for debarment declared ineligible or volun tarily excluded from covered transactions by any Federal department or agency b Have not within a three year period preceding this application been convicted or had a civil judgment rendere
101. close to the IR 4 18 uA Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 source being observed the closer the better Based on the image of a track star the MCS with Tracker inputs will correct pointing and update the gyro to sky transformation While observing a particular IR source an Area of Interest AOI around a track star is required by the Tracker to stabilize the pointing accuracy of the TA This stabilization is carried out at low frequencies greater than a few Hz High frequency pointing stability is handled through the gyro servo control loop in the TASCU see section 1 4 Mission Control Sub System on page 1 30 but slow gyro drift can cause the gradual loss of pointing accuracy if not corrected with visual reference points on the sky by the Tracker these visual reference points can be provided by stars either in the FPI FFI or the WFI best accuracy is achieved when using the FPI Normally the Tracker works in two ways to stabilize pointing accuracy 1 Positional stability by keeping a known gyro offset from a track star and the Tracking Posi tion usually tied to the SI boresight held constant 2 ROF stability by viewing two rotation stars simultaneously in one imager usually in the WFI to hold the angle of the line between them constant in rotation Both 1 and 2 need good positional information about the track and rotation stars This is done
102. cognition by the Mission Control Sub system MCS 1 18 eA Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 The three imagers use the same model Proscan High Speed Slow Scan camera containing the Thomson 7888A frame transfer CCD The basic nominal properties of this CCD include the fol lowing Table 1 5 Nominal Properties of the Thomson 7888 A Frame Transfer CCD Parameter Value or Range Notes Array Dimensions 1024 x 1024 image area frame transfer readout Pixel Size 14 microns Binning Options 1x1 2x2 4x4 4x4 done off chip Integration Time 10 10 000 ms Data Format 14 bit or 8 bit 2 MHz or 5 MHz rate Maximum Frame Rate 8 frames s 2x2 binning 5 MHz Peak Q E 18 at 4 550 nm Electronic shutter fill factor Read Noise 60 e 5DN Dark current 25 C 12500 e s No FPI cooling CCD at cabin temperature in flight Dark current 20 C 200 e s Likely for WFI FFI Table 1 6 FPI FFI and WFI Parameters Parameter FPI FFI WFI Notes Optics Description Cass TA 8x Schmidt Cass F 2 Petzval lens FPI has 60 cm focus range reticle reduction field expander reimaging optics Aperture Diameter 2500 mm 254 mm 68 mm EFL 6176 mm 733 mm 136 5 mm TRP KT 5100 0 04 Annex B FOV 8x 8 67 x 67 6 0 x 6 0 TRP KT 5100 0 04 Annex B Image Scale 0 47 pxl 4 1 pxl 21 pxl FPI scale varies 1096 over f
103. components also satisfy the relevant safe loading criteria Bending cutting drill ing etc may not modify an instrument rack without prior written approval of the SOFIA Airwor thiness Assurance Office Television monitors are available for mounting in or on top of the Investigator s instrument rack These may be used to display any of the camera fields or the housekeeping video display The choices include a large monitor 13 inch diagonal screen two video inputs for mounting on top of the rack or a chassis containing three small monitors for mounting in the rack Each monitor in the latter unit has a 5 inch diagonal screen and a separate single video input Other SOFIA facil 2 34 uA Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 ity supplied equipment available from USRA includes 110V power distribution panels an 8 channel strip chart recorder and a storage cabinet Relevant physical dimensions of these items are given in Table 2 2 Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Top Web Standard Chassis 19 Lift Handle Typ 2 Places Corner Post Typ 4 Places Corner Tie Down Bracket Fitting Typ 4 Places Center Tee Post Typ 2 Places Reinforcing Strap aft side only Bottom Web ___ Center Tee Chord Typ 2 Places ____ Angle Chord Typ 4 Place
104. components planned for future releases As the key below describes the status of each component is presented in the reference tables with the information for that component 2 12 SOFIA Science Instrument Commissioning All of the SOFIA science instrument interfaces are verified prior to the pre flight review A sub set of the interface control documents ICDs is verified prior to the pre ship review The fol lowing sub sections list how and when each of the science instrument related ICDs are verified by design Final proof of ICD compliance by successful operation is the subject of the section following this one 2 12 1 Global ICDs Layout of personal accommodations Each instrument needs to specify the overall layout of the instrument in the observatory This should include the science instrument racks required both the PI rack and TA rack the number of consoles required and the expected locations of science instrument team members during take off landing and during standard mission operations This layout needs approval prior to the pre ship review SOFIA coordinate system Each instrument needs to specify the location of the SI image plane with respect to the science instrument flange This information is needed for adequate control of the telescope in the SI coordinate system An update of this information is provided via measure ments from the TAAS and after the first few flights Science instrument envelope Each instrument need
105. d Operations erret rnte rrr r ernannt EE Rn taa Ea nun RRRERRE RES SEa EX Ru nnmnnn 4 6 45 Observing on SOFIA nerit ihe e e Rao de re Ran EE Ee A unt ben RA te be RR R iab 4 18 4 1 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 1 Yearly Scheduling of the SSMOC The SSMOC will be scheduled on a Government Fiscal Year GFY cycle i e October 1 to Sep tember 30 of the following calendar year The schedule for a year will be finalized by August Ist of the GFY prior to the GFY being planned The schedule s determination will be based on the science flights awarded the aircraft and observatory maintenance required for that given year and the constraints of the operating budget for that year A scheduling program will be used which will take as inputs Maintenance down times Deployment constraints or preferences Any other SSMOC time constraints Prioritized list of investigator teams with SI s to be used Each investigator team s set of preliminary objects The scheduling program will assist the Operations Controller and the Project Scientist in schedul ing the science flights for a year The year will be divided into flight series or missions with each normally some multiple of a week in duration for ease of installation and removal of science instruments Each mission will have one installation of a science instrument or a suite of science instruments mounted simult
106. d against them for commission of fraud or a criminal offense in collection with obtaining attempting to obtain or performing a public Federal State or Local transaction or contract under a public transaction violation of Federal or State antitrust statutes or commission of embezzlement theft forgery bribery falsification or destruction of records making false state ments Or receiving stolen property c Are not presently indicted for or otherwise criminally or civilly charged by a government entity Federal State or Local with commission of any of the offenses enumerated in paragraph A b of this certification d Have not within a three year period preceding this application proposal had one or more pub lic transactions Federal State or Local terminated for cause or default and B Where the applicant is unable to certify to any of the statements in this certification he or she shall attach an explanation to this application Guidelines for Participation in the Instrument Program CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 C Certification Regarding Debarment Suspension Ineligibility and Voluntary Exclusion Lowered Tier Covered Transactions Sub grants or Subcontracts a The prospective lower tier participant certifies by submission of this proposal that neither it nor its principles is presently debarred suspended proposed for debarment declared ineligible or voluntarily excluded
107. d pumps that are on the actual TA and aircraft so that the investigator can pump on the SI cryogens as needed There will be space reserved for a closed cycle cooler compressor and closed cycle cooler lines to be included in the simulator and TA cable drape The relative placement of the compressor and its lines will be the same as on the aircraft 4 8 uA Mission Ground Operations CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 2 1 b Optical Alignment Focus and Boresighting The TA simulator will be a single structure with a duplicate of the telescope mounting flange at one end and a tertiary mirror and alignment source fixture at the other end The beam line from the alignment source fixture to the tertiary will form a 90 degree angle with the beam line from the tertiary to the SI flange and will reproduce the orientation of the telescope at 40 degrees elevation However the physical separations of the SI flange tertiary and alignment source fixture will be 1 3 to 1 2 the nominal TA separations so that the simulator will have an overall length of only two to three meters Three sources will be available for use in alignment on the simulator a small laser or telescope a broadcasting source hot plate and a focused source portable collimated light source PCLS The first will be used primarily at the SI flange to verify the alignment of the simulator itself this may be the same device that is used for TA alignme
108. d to fully operate the SI in flight on the SOFIA airborne observatory Hence the physical layout of the SI flange assembly the vacuum manifold the MCCS patch panel and the cable drape and con nector flanges will be identical to that on the aircraft The TA simulator mounting flange area will be an exact duplicate of the SI mounting flange area on the TA An instrument rotator identical to that used on the TA will be available for use with the TA simulator Although the simulator will duplicate the TA and MCCS interfaces as accurately as possible it will not duplicate the physical constraints associated with the ceiling or TA counterweight assem bly as these lie well outside the confines of the currently defined SI envelope The simulator will have a floor clearance similar to that of the TA caged at 40 degrees elevation The simulation of the floor clearance for other telescope orientations and SI rotations will be accomplished using several large plywood shims which can be inserted to approximate the location and orientation of the aircraft floor for extreme positions This method is required because the simulator is station ary i e it has no equivalent of the hydraulic bearing on the TA and cannot reproduce the TA azi muth elevation and line of sight motions Hence final verification of all floor clearances will be done on the aircraft before the TA with the SI attached is uncaged The TA simulator will duplicate the vacuum manifold an
109. d to resume observing 1 3 3 Observatory Optical Performance Based on the optical data in Table 1 3 through Table 1 6 the assembled SOFIA Cassegrain tele scope should be capable of producing a 1 0 TBV arc second 80 encircled energy diameter image of a visual point source 1 3 3 1 Focal Plane Image Quality In January 2005 Dunham et al obtained a series of CCD images of stars with very short exposure times under a variety of flight conditions Report SOF XXXX These star images had long exposure FWHM sizes of about 3 arc seconds TB V The large size of the airborne image is pres ently believed to be due to contributions from the shear layer air temperature variations in the cavity and image jitter caused by vibration and dynamic flexure of the telescope structure The shear layer seeing becomes unimportant for wavelengths longer than 5 microns FLITECAM star images at 5 microns are on the order of 1 5 arcsecs FWHM TBV Preliminary analysis implies the telescope provides diffraction limited imaging at infrared wavelengths longer than about 15 TBV microns As a rule of thumb where SOFIA is diffraction limited O 1 arc second 4 10 microns 1 3 3 1 1 Range of focus The secondary mirror positional adjustment provides focus over the range U 600 mm where the U axis is illustrated in Figure 1 11 The secondary mirror is made of silicon carbide with a diameter of 352 mm which is larger than the chopping mechanism housi
110. de available to all Investigators and must be used instead of conventional laboratory instrument racks The completed rack of equipment is bolted to a fixed frame on the aircraft floor on existing seat rails as shown in Figure 2 31 If additional racks are necessary they may be fastened to seat tracks in the cabin floor The recommended procedure in assembling an instrument rack is to first prepare a preliminary scale layout of the equipment in the rack taking into account the loading and moments data pro vided starting with Figure 2 30 and going to Figure 2 36 and Table 2 2 and Table 2 3 A list of components must also be prepared including weights and locations Use Worksheet 2 1 Instru ment Rack Weight Sheet on page 2 45 to assist preparation Based on the scale layout and the worksheet the cognizant USRA SOFIA engineer will check the loading and moments to deter mine if they are properly distributed within the rack Specially designed support trays are avail able for heavier components The SOFIA staff will provide assistance in properly loading the instrument racks and will perform the installation of loaded racks onto the aircraft Instruments may be installed facing forward or aft but note that the forward side of the rack faces the Investigator seating and the aft side faces the telescope and PI cabling patch panel Some instruments may also be attached to the top of the rack using appropriate straps rails or plates provided these
111. deo etc and are labeled with a connector reference designator Each connector on the patch panel has a spacing of at least one inch from any other connector Connectors are identified by a reference designator and SI connectivity reference number for name or function connector part number and mating connector part number as part of the physical interface control document The MCCS interface position of the patch panel provides access to the MCCS and PI supplied rack power and ground lines local area network LAN connections audio video environment 2 50 A Instrument Cabling Patch Panels CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 sensors and a global position system antenna Electrical specifications for the various signal types are described and connector pin out table provided in the actual interface control document Instrument power is provided by an on board frequency converter and an uninterruptible power supply UPS Circuit breakers installed in the MCCS power distribution subsystem observatory power panel provide wire protection for the power feeds FC power is shared between the PI equipment racks and the science instrument as budgeted by the SI team FC power is subject to all outages experienced on the observatory The UPS power is supplied from the MCCS PDS UPS located in the forward cargo compartment UPS power will continue to supply steady state AC over to sensitive loads in the event of a power fail
112. distribution system accurate to at least 1 ms will be provided The LAN will provide internet access via ground umbilical cable connections to the N211 Hangar and support facilities at NASA ARC when the Observatory is in the N211 hangar or near the han gar on the ramp area Figure 1 14 gives an overview look at the MCS communications architecture The SI computer system communicate for the most part through the MCS network switch via the PI Patch Panel see MCCS SI 02 with two exceptions 1 The Secondary Mirror Controller SMC has a direct interface to the SI and this physical and functional link is described in the ICD TA SI 04 Chapter 2 SOFIA Science Instrument ICDs on page 2 1 2 The SI can down load directly the WFI FFI and FPI digital images and store for SI house keeping The Observatory at ORR will only store such images in digital video format Partic ular frames of any image from the WFI FFI or FPI can be requested to be logged in a FITS 1 30 uA Mission Control Sub System CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 file but storing a continuous stream of such data is the responsibility of the SI team through this direct link See MCCS SI 02 i e Chapter 2 in regards to the PI Patch Panel Autopilot thru AIU Video Distribution Subsystem Power Distribution Water Vapor Monitor FMS amp Avionics Control Rack Cooling and Smoke Detection Data Acquisition up to 7
113. e 1 Scientific merit and technical feasibility a For FSI s Scientific merit across a broad range of science that will serve the general astronomy community plus specific merit of the science proposed by the PI team The case for significant demand of the instrument by the community should be made Technical feasibility win include reliability ease of operation robustness of design and fabrication and maturity of the technology b For PSI s Scientific merit of the PI team s proposed investigation capability of the instrument to support science investigations other than the PI team s science Technical feasibility will include reliability robustness of design maximum scientific performance c For SSI s Scientific merit of the PI team s proposed investigation Technical feasibility will include reliability and design for maximum scientific performance 2 Need for SOFIA to carry out the proposed research program 3 The estimated development and two year operational cost of the instrument For PSI instru ments this should include estimated costs for the SSMOC and SSMOC personnel as well as the PI team 4 The capabilities and experience of the investigators and the suitability of available facilities and support staff for the proposed instrument development 5 4 uA Evaluation Criteria In Approximate Order of Importance wr HP CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 5 For PST s and SST s
114. e Any person who fails to file the required certification shall be subject to a civil penalty of not less than 10 000 and not more th311 100 000 for each such failure NA 5 16 uA Guidelines for Participation in the Instrument Program ra CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 Organization Name CFP or AO Number and Title Printed Name and Title of Authorized Representative Signature Date Printed Principal Investigator Name Proposal Title 5 4 USRA Review Process During SI Development SOFIA instrument review policy is intended to facilitate the development of world class instru ments The facility instrument program is a key aspect of USRA s plan for a broad based engage ment of the astronomical community within the operational phase of SOFIA To deliver the instrument performance promised to both NASA and the astronomical community at large the observatory requires a series of reviews for the facility instrument program These are 1 a pre liminary design review 2 a critical design review and 3 an instrument acceptance review These reviews are scheduled for mid 1998 mid 1999 and mid 2001 respectively Within the USRA development program the facility instrument review program is worked in concert with our inter nal science support team The review policies are guided by the past experience of other ground based and space based facilities For science instruments the observatory direct
115. e 2 58 2 10 Secondary mirror Control 4 eee e eee eee ee sees sees soens sseni stessa s tasses stes e ES Eae oE 2 62 2 11 SOFIA S ftw re Interface 2 67 2 11 1 MCS Command and Keyword References scsscssscssscssscsssessssssscssscssssscsenessnssessseseseeees 2 67 2 12 SOFIA Science Instrument Commissioning sessesssesssessesssecsoossoossossoossoossseessesseossocssossoossoossosssssesee 2 68 212 1 GlODAL ICDS ciessscsnsesacansassascsncoetessseenssssoncsdssasecssoseossonsnesnessendanssuacdasde odeesbaseaessdsesiesescseaeousanssaes 2 68 2 12 2 Telescope IC DEEE EEE EEEE E E EES 2 69 PA PALEIS CRDI 2 70 2 12 4 Aircraft p 2 70 PA PASEAR NOI bre 2 71 2 12 6 Operational ICD Verification eee eee esee eene eene eren eren neta stone sensa seen ESSES sets tones etos seen ss ena 2 71 CHAPTER 3 Airworthiness eee ecce eee eee seen eeesessoeeesessseeeesssssseeesssssseeesss D 3 1 Science Instrument Certification 4 eee eee eere eee eee eee ee ee eaae teta sesenta aes tasse NEE ESSER 3 2 SX 1e Orien TE EDO ERE DET em 3 2 3 2 Science Instrument Certification Methods and Roles ecce ee eee ee ee eee eee eene eee eb sese enses eene see 3 2 3 2 1 Designated Engineering Representative DER eese esset seen eintreten atenta setas ens etna eua sno 3 3 3 2 2 Designated Airworthiness Represe
116. e ground No determination of the SI c g is carried out in the TA simulator lab The SI c g is determined in an automated fashion after SI installa tion on the TA 4 4 3 SI Installation on the Aircraft After the SI has been checked out on the TA simulator it will be installed on the aircraft usually on the morning of the first flight day of the mission i e usually Monday morning The de installation of the previous SI will typically occur on the morning after its last flight i e the morning of the previous Friday The mechanical mounting of the SI on the TA will require the assistance of two TA technicians with the aid of an SI cart but will be primarily the responsibil ity of the PI team Concurrently two aircraft mechanics will load the science racks onboard the aircraft secure them in the desired locations and install the associated seating Mission Ground Operations Qua 4 11 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 After mechanical installation is complete the SI will be connected to all of its cables hoses and electronics cryogens will be filled as needed and vacuum pumps will be turned on as appropri ate That is the experiment will be placed in operational flight ready status Although the TA technicians will assist with this activity most of the interconnects e g cable connections to the SI and the SI racks and other details of this installation procedure will be carried out b
117. e iei o sce are tt ae I R RR E aa 4 34 Figure 5 1 Proposal Form Proposal Title Page sesessesesesseseeseeeeeeeeee nennen enne eere teenne nnns 5 10 Figure 5 2 Proposal Form Budget Summary sesseeseeeeeseeeeeee nennen eterne enne nnenneennens 5 11 viii SOFIA IHB 0 0 Tables Table 1 1 Optical Parameters of the Primary Mirror essere 1 14 Table 1 2 Optical Parameters of the Secondary Mirror eeseeseseeeeeeeee rennen 1 15 Table 1 3 Optical Parameters of the Tertiary Mirror nenne rennen 1 16 Table 1 4 Imager Specific tions ierit rte teet ett ebrei etta test Ree e dete epe egere ae eid 1 17 Table 1 5 Nominal Properties of the Thomson 7888 A Frame Transfer CCD sees 1 19 Table 1 6 FPI FFI and WFI Parameters eseeeeeeeeeeeennnn m EE R E nnne nes esr ense se serene 1 19 Table 1 7 Examples of Focal Plane Positions eeeeseeeeeeeeeeeeeeee nennen nennen nennen eren 1 26 Table 1 8 SMMOC Locations 1 11 aute e p tec e Rue Peu debite Hag aeaieie 1 40 Table 2 1 Telescope Assembly Optical First Order 0 0 eee cesceseeeeeeseeeseceseceeeeeeeecaecaaecaeeseeeeeeeaaeeneee 2 6 Table 2 2 Facility Supplied Rack Equipment esee rene enne nee 2 40 Table 2 3 Maximum Chassis Weights eese neret enr en nennen nnne enne nee 2 43 Table 4 1 Implementation of Minimum Science Capabilities
118. e nod beams coincide with the chop beams Figure 4 9 illustrates this combination for a two point chop The nod sequence is defined so the nod beams coincide with the positions on the sky where the SI boresight is positioned to look at the different chopped images of the IR source of interest The observer can also map with pre defined offsets such that these offsets will be simultaneously made in all chopped images and defined nod beams Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 SI Boresight in Beam A using the FPI A n ASAS Ar SIRF BS B minus SI Boresight in Beam A using the FFI SIRF BS minus SRF SS plus 4 SIRF BS Figure 4 9 Two Beam Nod Chop Set up 4 32 i SSTA rsccfpaconsenn tef rearea Astronomy Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 5 3 6 Scan Modes In these modes the chopper i e the TCM can either be under a control loop tip tilt oscillation or not There are two scan modes 1 Scanning to explore 2 Scanning to take data When an observer wishes to do a quick scan set up to explore an IR source or explore possible scan set up parameters he she can use an SCL command that can scan the sky using a number of different coordinate systems scan rates and scan paths However when an observer wants to record data while scanning there is a better command allowing
119. ect the completed simulator installation and describe any changes that will be required to obtain airworthiness approval for the subsequent installation aboard the aircraft Transportation of the SI from the PI lab to the TA simulator lab and subsequently onto the air craft will be facilitated by a SSMOC provided cart designed especially for the purpose of trans porting and mounting the SI on the TA and the TA simulator It is assumed that no more than one or two SSMOC technicians will be required for this effort This cart will be designed to correctly Mission Ground Operations x xm 4 7 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 distribute loads to the aircraft floor for the heaviest allowable SI 600 kg and will enable passage through the aircraft passenger door with the largest allowable SI If the fully assembled SI is larger than the passenger door then the reassembly of the SI inside the aircraft must not add more than 30 minutes to the nominal SI installation time 4 4 2 1 TA MCCS Simulator Procedures The TA MCCS Simulator will aid in determining or verifying a the mechanical and vacuum interfaces between the TA and SI b the optical alignment focus and boresight of the SI with the telescope c the mechanical electrical communication and protocol interfaces with the MCCS 4 2 1 a Mechanical Interface The TA simulator will duplicate all mechanical vacuum and electrical connections require
120. ectronics are nonessential equipment for aircraft operation and so certification involves sim ple safety concerns This section of the manual provides guidelines for design documentation failure analysis and testing of electronics components Section 500 Functional Hazard Analysis Functional Hazard analysis is required for each science instrument and the necessary FAA hazard reporting forms and examples are included in this section Section 600 Operational Procedures and Maintenance Continued Airworthiness This section addresses the maintenance and operation of the science instrument Maintenance operations and continued airworthiness are very much connected under FAR Part 121 and therefore sections 600 and 700 have been combined This section provides some guidance and references for writing and maintaining a logbook and maintenance manual for the science instruments 3 9 Schedule of Submittals Each team shall prepare a standard Gantt chart outlining the instrument certification schedule The dates of submittals and expected approvals will be specified by each science instrument team and Schedule of Submittals CHAPTER 3 Airworthiness SOFIA IHB 0 0 included in the Airworthiness Documentation Logbook by the science team In general the SI team will submit several separate packages The logical sequence for submittals is Structural data including drawings stress analysis drawing tree load path and safety mar
121. ed at the center of its back side to a central flexure The distance of this flexure pivot from the vertex of the secondary mirror optical surface is included below Focus Centering Mechanism FCM the TCM is mounted on a modified hexa pod known as a Stewart platform The six linear actuators can be used to provide focus and cen tering adjustment and static tip tilt of the secondary mirror and the TCM supporting it Additional details on the function and performance of the TCM and FCM are given in Chapter 2 Table 1 2 Optical Parameters of the Secondary Mirror Optical Parameter Value Mechanical Parameter Value Free Optical Diameter 340 352 mm Outside Diameter 352 mm Radius of Curvature 954 13 mm Inside diameter central hole 40 mm Focal Length 3200 mm f 1 28 Inside Diameter central hole 420 mm Conic Constant 1 2980 Central thickness 45 mm Surface Roughness 16 nm TBD Material Silicon Carbide Wavefront Error 16 nm rms Weight 2 1 kg Reflective Coating 100 nm Bare Al Thermal time constant 5 min TBD Reflectance Nominal optimum Optical surface ver U 2500 A 0 5 um 0 95 TBV tex position mm V 0 4 100 um 0 99 TBV W 1848 FIR Emissivity 0 05 TBV Distance of vertex from chop pivot 18 mm TBC point CoG SOF SPE KT 1000 0 03 astrium SSM RP 0168 1000 T ASTR 11 7 2001 Basic mirror parameters are provided in this table for reference A Secondary Mirror is mounted on a two st
122. ed just aft of the PI instrument rack The MCCS SI 03 patch panel contains all of the cable connectors running through the telescope cable load alleviator This includes power cables twisted pair co axial cables tri axial cables fiber optic cables and high voltage cables Only those cables needed for science instrument operations should be listed All cables should include their mating connector specification Power lines should also include the grounding approach and a list of the expected power requirements for each power cable This information is required prior to the pre ship review MCCS SI 04 Verification of the software functional observatory interface is needed at two lev els For the pre ship review the instrument team should demonstrate a successful exchange of rudimentary commands with the observatory Prior to the pre flight review the instrument team should demonstrate the use of all anticipated commands for successful science instrument control of the observatory The list of tests to be performed prior to the pre flight review and the MCS commands to be executed should be completed prior to the pre ship review of the instrument Expected operating modes of the telescope chopping nodding scanning et cetera for successful science instrument operations should also be reviewed prior to the pre ship review 2 12 4 Aircraft ICDs SI AS OI Ifthe instrument team is using an instrument rack other than one provided by the observato
123. ee eese ee esee teen eoor euve netta seen onon eE Esos EKSSi E e 1 21 1 32 T The Aircraft AUtopilotc cscvsscscssescsscsesessesesesissoscssosocsosesesecnedesssosvesosowsesocsesnscdensonsbeoseseseosess 1 22 1 3 2 2 Vibration Isolation PR 1 22 1 3 2 3 Spherical Hydrostatic bearing scccccsccsscscescccscscescccescccsescesssceessscsscccssccesescesscsersoesee 1 23 1 3 2 4 Gyros and Torque Motors for Three AX S cscsscssscsssssssssssssssensscssscscsssssnessssssssscsers 1 23 13 2 5 Imager Star Tracker eese eee vonsccschevcescsedscsevecoesevesessoutdsesesoscnsssiacvesd docs cocssavceskececsvens sers 1 24 1 3 2 60 ROtALON ATISIE sccndesscsscsnssscoonsssecessasccnsdscosesdoosebsdvedeessevessdesseccbossnacsesasssceseseniessdooossssesascoses 1 24 1 3 2 7 Line of Sight and Azimuth Resets cccsscsssssscsssccccccesccsssscesssceesecsecccsssccsssscessccerssesee 1 25 1 3 3 Observatory Optical Performance scsscsssscccsscccccccscccsssccsssccrssscssscscesescesccesscesssscersssereseses 1 26 1 3 3 1 Focal Plane Image Quality eee eee ee se sossar eene ener ee eee Eos n ee en aestas esse toss etna setae 1 26 1 3 3 2 Chopping Secondary Mirror Performance ecce eese eese eene eee ee eren sete seen seen ose etnae 1 27 1 4 Mission Control Sub System Leere eene eese eee e seen neta seen sene se toss etna essen seta se roo ESTES p ESZES sena 1 30 1 5 Other Observ
124. ee nennen nennt nan n nennen ana n aaa n nana nans 3 6 Schedule of Submittals noii eene e eect else E PARERE ead 3 7 3 1 CHAPTER 3 Airworthiness SOFIA IHB 0 0 3 1 Science Instrument Certification 3 1 1 Introduction The primary purpose of FAA science instrument certification aboard SOFIA is SAFETY The guidelines in this manual follow those of the Federal Aviation Administration FAA documents FAR Part 25 The FAA is concerned with the safety of personnel associated with flight and all aspects of the aircraft will be certified under FAA guidelines Certification is not difficult but it does require following specific steps from conceptual designs through instrument construction installation operations and maintenance for the purpose of maintaining a safe environment aboard the Observatory The purpose of this airworthiness and certification procedures manual is to lead a SOFIA science instrument builder through the certification process with information and examples on all aspects of an instrument design that are required to comply with FAR Part 25 guidelines for certification These requirements include mechanical and electrical design and analysis instrument construc tion testing hazard identification and analysis operations and instrument maintenance This manual has been compiled through the efforts of the SOFIA FAA SI Airworthiness IPT which includes scientists engineers FAA Designated Engin
125. eed of 460 Li min at the SI Mounting Flange on the tele scope Only one pumping station is available for first light observations in January 2005 Vacuum lines are permanently installed between the pumps and their respective manifolds and gauges with flexible vacuum tubing providing the interface to the SI on the SI Mounting Flange Other Observatory Sub Systems x m 1 37 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 USRA also supplies a 0 800 Hg mm pressure gauge a 0 50 Hg mm gauge and a millitorr thermo couple gauge for each pumping station The location of the vacuum pump manifold where the 1 800 torr and 1 50 torr gauges are mounted with the pump valves that regulate the pump down speeds is shown in Figure 1 1 and Figure 1 4 Figure 1 4 shows that this pump manifold is for ward of SI Safety Barrier so can be accessed while the telescope is operating The power switches for the pumps are located at the PI Console next to the Telescope Operator s Console See Figure 1 1 1 5 6 Mission Audio Distribution System The SOFIA intercom system provides TBD stations for communication between investigators the mission director and all support systems operations Each station has a volume control and a call button to signal the mission director The IFD can place any combination of stations on one or the other of two channels TBC To facilitate this option all passengers are encouraged to be aware of their station
126. eering Representatives DERs and science instrument builders Some processes and details have not been fully defined at this time but will be inserted as they are produced Instructions will evolve and become more detailed as the first instruments proceed through the certification process This Introduction will define the roles and responsibilities of those involved in the certifi cation process Section 100 1 has a short general list of required steps from conceptual design review to conformity and compliance inspections Section 100 2 describes the sec tions of this manual and Section 100 3 discusses scheduling 3 2 Science Instrument Certification Methods and Roles Science instrument certification will involve communication between the science instrument SI team and the science instrument airworthiness Integrated Product Team SIA IPT as mentioned above the FAA Designated Engineering Representatives DER and the Designated Airworthi ness Representatives DAR The Airworthiness IPT is responsible for the production of the mate rial in this manual and also can be viewed as a resource for the SI builder on questions specific to instrument certification The Federal Aviation Administration is responsible for safety aboard all commercial and privately owned aircraft The FAA appoints individuals to review designs to make inspections to review operations and maintenance and to act on behalf of the FAA to review new designs and requ
127. embly with the baseline concept of the secondary mirror button installed 2 8 uA 7 SOFIA Telescope Optical Prescription CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Concept of a Flat Black SM Button Cross section of Flat Black SM Button Figure 2 6 Secondary mirror Button Design Flat Black SOFIA Telescope Optical Prescription 2 9 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Concept of Conical Reflecting SM Button 1mm N ons CNN Cross section of Conical Reflecting SM Button Figure 2 7 Secondary mirror Button Design Conical Reflecting The above two examples shown are a flat black unit and a conical reflecting surface design Instrument teams may design their own with approval from USRA 2 4 Telescope Mounting flange Science instruments mount at the instrument mounting flange IMF The IMF is part of the Nasymth tube and is located at the forward end of the telescope The part of the science instru 2 10 uA Telescope Mounting flange CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 ment that mounts to the IMF is called the science instrument flange SI flange Figure 2 8 shows a detailed three dimensional representation of the forward end of the Nasymth tube including the IMF Figure 2 9 shows a cross section of the TA structure and its surroundings The structural requirements for the IMF assume a single shear pin and 20 bolts with nuts sup
128. ent made to the nominal TA alignment to accomplish this task Once the SI alignment is optimized this tilt position will be locked down and will remain unchanged for the duration of the mission Note Some investigators may develop SI with no provision for such an orientation adjustment Such SI will still use the simulator to verify that their fixed orienta tion relative to the secondary is adequate for their experiment Focus This adjustment ensures that the optical focus for the TA will coincide with the infrared focus for the SI For this procedure the PCLS is mounted on the TA simulator and the flip mirror in the BSB is initially removed from the light path The focus on the collimator will be adjusted until a small few arcsecs point like source is minimized in spatial extent or gives maximum signal on a single pixel Without changing the PCLS so the image in the SI remains focused the flip mirror in the BSB is engaged and its optical CCD camera is adjusted until its image is focused This focus setting on the optical CCD camera is then locked and remains unaltered for the remainder of the mission Boresighting The boresight procedure maps the IR focal plane onto the optical focal plane for use in pointing and guiding via visible or near IR stars For this procedure the PCLS is mounted on the TA sim ulator and the flip mirror in the BSB is initially removed from the light path Once the SI is aligned and focused in that order
129. erifies that design and fabrication can proceed within allocated costs schedule manpower and facilities The PDR is scheduled prior to the start of major detailed design activities The review board is chartered to look for the following items during PDR e Statement of operational requirements Verification plans for compliance of requirements dentification of inherited designs and standard commercial components Major system design parameters e g performance volume layout power heat rejection interfaces etc Results of major design tradeoffs with justification of the chosen implementation Discussion of key design details including preliminary drawing sketches block diagrams schematics critical components software outline and planning etc Outlines of planned development tests Major support equipment requirements Preliminary operations planning Schedules budget and status of task Major concerns risks and descope options Open items and resolutions plans 5 18 uA USRA Review Process During SI Development wr HP CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 The primary purpose of the CDR is to verify that the detailed design is complete and ready for manufacturing and that fabrication and testing can proceed within allocated cost schedule man power and facilities The review should be scheduled after completion of the design and prior to the fabrication and purchas
130. ers for the Primary Mirror The primary mirror is a solid but light weighted Zerodur f 1 18 paraboloid of 106 5 inches 2705 mm diameter weighing 800 kg It is supported in a CFRP cell by six wiffle tree struc tures each with 3 attachments to the primary mirror giving axial support In addition there are three lateral support structures separated by 120 degrees placed between the outer diameter of the primary mirror and the inner diameter of the support cell The total weight of the Primary Mirror Assembly which has a diameter of about 4 meters and a depth of 1 meter is 2000 kg 4409 25 lbs Table 1 1 Optical Parameters of the Primary Mirror Optical Parameter Value Mechanical Parameter Value Free Optical Diameter 2690 mm Outside Diameter 2705 mm Focal Length 3200 mm f 1 28 Inside Diameter central hole 420 mm Conic Constant 1 Material Zerodur Surface roughness 10 nm TBD Weight 800 kg Wavefront Error 300 nm rms TBD Thermal Time Constant 71 hour TBD Reflective Coating 100 nm Bare Al Optical Surface Vertex Position mm U 2500 V 0 W 906 Reflectance 0 5 um 0 95 TBV 100 u m 0 99 TBV FIR Emissivity 0 05 TBV SOF SPE KT 1000 0 03 The Zerodur blank was provided by Schott Mainz and lightweighted and polished by REOSC Basic parameters of the Primary Mirror optical element are given in this table The Primary Mirror support structure includes an 18 p
131. es 1 through 4 the MCS creates plus minus zero where applicable and no chop versions of the SI boresight and assigns to the chopped images of the IR source and its track star similar titles The fictitious boresights are used when the track star is in the FFI or WFI The fictitious locations on the sky of the images of the IR source and its track star are used when the track star is in the FPI Figure 4 7 and Figure 4 8 illustrate this MCS scheme The fictitious boresights are used in both the FPI and FFI cases to determine the positions of the refer ence beams of a chop as well as the position of the actual SI boresight In the second figure of Figure 4 8 for example the SIRF BS minus lies on the un chopped sky position of the refer ence beam when the actual SI boresight is on the plus image of the IR source in the focal plane of the telescope All chop beam locations on the sky are recorded in MCS Housekeeping The process to set up the chop mode is simple no matter if the track star is in the FPI or the FFI Note if the track star is in the FPI corrections for chop throw instabilities can be made which can t be made if the track star is in the FFI Once the mode is set up the observer can select which image of the sky to observe and map with tracking enabled if desired Observing on SOFIA x xim 4 27 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 2 point Ch
132. esents the dynamic science instrument volume required by in flight operation of the telescope The rack itself is electrically isolated from the telescope assembly A ground termination stud is available and shall be made to at least one of the following ground sources a The ground terminal strip on the SI power panel b The ground stud on the SI patch panel c The science instrument d The telescope assembly Wiring for grounding of the CWR will be provided by the SSMOC facility engineering staff for connections to either the SI parch panel of the SI power panel SI developers are responsible for other desired grounding connections Since the USRA provided CWR is an open truss structure installed instrument components will require enclosures and shielding for electrical and airworthi Instrument Racks PI Rack x xim 2 A7 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 ness requirements As expected all CWR equipment must satisfy the same FAA EMI require ments as any other SI components All the design requirements of the science instrument counterweight rack are contained in the interface control document TA SI 05 Interface details of the counterweight rack as design by USRA are contained in the Science Instrument Equipment to Counterweight Rack ICD The CWR to SI ICD includes the physical dimensions of the payload envelope center of gravity lim its maximum interface loads attachment point locations and
133. esssscccssccesescsssoceesoeses 1 36 1 5 4 Global Pointing System GPS sscscsscsscscsscsecssceccccseccesesccsssceessscsescsseseccesceessccssessersesesescses 1 37 1 5 5 Vacuum Pumping System ccsccsccscsccecesceescscecsscssccscecccsesccesscesssscsesessesescescessscesssscesseseesseses 1 37 1 5 6 Mission Audio Distribution System cree eee ee eerte eere eee osos eoeou seen sets sense etos seen ose isso 1 38 1 5 7 Video Distribution System eee eeee scere eerie e eene eerte eerta setae tona een seen sees sets e sense SSSR ost oS OSE 1 39 1 6 SSMOC Ground Facilities for SI Teams 1 e c eee eee eere cente eee ee ee eene nest en aee ta se tne s toss senos seen sena 1 39 1 6 1 Visiting SI Team Labs and Offices eee eese eere ee eee ee ee eee eene en netta as etn sets sense sosire otrs oss oos 1 39 126 Vel Ba ilitycA CESS PR D 1 39 1 6 1 2 SSMOC SI Support Physical Facilities scsscscscssssssssssessssssscssscsssssssssssesssssesssessoeees 1 40 1 6 2 Pre Flight Integration Facility PIF 4 crecer esset eese teen eere eene enne ta sene se tonat tn sse tnee 1 42 1 6 3 Computational Facilities eese voee eec ro a eoa vents iode no Go e vrac ient pra va o Sa o vana Re Une Re Ten eese UR sods 1 45 1 7 Software and Data Management eere cette eese eene ense n sete ette atenta setas esee tosta seta setae eese eset ee sensn
134. eval of Data 48 ROF 24 Rotation Angle 24 Rotation of the Field ROF 24 S Scan Modes explore and take data 33 Schedule of Submittals 7 Scheduling of the SSMOC 2 Science Instrument and TA Flange Pumping System 58 Science Instrument Cart 29 payload 29 Science Instrument Certification 2 methods and roles 2 process 4 science instrument commissioning 68 Science Instrument Envelope 22 Science Instrument Flange Hard Points 15 Science Instrument Grounding Recommendations 57 Science Instrument Interface 20 Science Instrument Patch Panel 54 Science Instruments classes considered for development 2 mass and center of gravity 16 SCL 18 seating team members 7 secondary Mirror optical parameters 15 Secondary Mirror Control Unit SMCU 32 Secondary Mirror Performance 27 Secondary Mirror Buttons 7 Secondary mirror Control 62 Selecting and Perfecting SI Boresight 20 SI Access in Flight 5 SOFIA IHB 0 0 VII Index SI Airworthiness Submittals and Control Process 5 SI Check out in the SSMOC 7 SI Data and SSMOC Data Cycle System DCS 13 SI Installation 11 SI Submittal Status Work Sheet 9 SI Team Integration into SSMOC Operations 6 SI Team Work Areas 4 SIMBAD 47 Sky Calibrator Mirror 36 SMA 14 SMCU 32 SOFIA Command Language SCL 18 SOFIA Rotation Angle parallactic angle 24 SOFIA Science Instrument Commissioning 68 SOFIA Software Interface 67 Software and Data Management 46
135. eview CODR 5 Construction Inspection and Testing 6 Coordinate Systems 2 aircraft 3 telescope 4 Counterweight Rack 45 cryogen boil off 17 cryogens pumping stations 37 CWR 46 D DAR 3 Data Cycle System DCS 46 data retrieval 48 DCS 46 13 DER 3 Designated Airworthiness Representative DAR 3 Designated Engineering Representative DER 3 Dichroic tertiary 16 Drug Free Workplace Requirements certification 14 Dynamic Instrument Volume 27 E electromagnetic field electromagnetic field 21 Environment science instrument flange 21 environment observatory cabin 6 SOFIA IHB 0 0 F Facility Access 39 Facility class Science Instrument FSI FSI 2 FCMU 62 Final Certification 6 Five Stages telescope precision and stability 22 flight length 7 Flight Management 3 Flight Management FM Software 46 flight management infrastructure FMI 5 Flight Plan from Moffett Field 4 Flight Planning Process 3 Flight Planning Software 5 Flight Standards District Office 4 FM 46 FMI 5 Focal Plane Image Quality 26 Focus 10 range of 26 Focus Controller Mechanism Unit FCMU 62 Foreign Proposers guidelines 8 FPI aluminized tertiary 17 G Global ICDs 68 Global Pointing System GPS 37 GPS 37 Ground Facilities for SI Teams 39 Grounding Recommendations 57 Guidelines for participation in the Instrument Program 5 Guidelines for Participation in the Instrument Program 5 Gyros and Torque Motors 23
136. ew Process SOFIA IHB 0 0 The following items apply only to this Announcement CFP Identifier USRA ID CFP97 001 Letters of Intent to participate in the CFP are due May 1 1997 Letters of Intent must specify the PI s name and institution the class of instrument to be proposed e g facility class science instru ment principal investigator class science instrument etc a brief description of the science instrument and the science expected from the instrument The Letter of Intent should also list the names of co investigators and other collaborative members of the proposing team Letters of Intent are to be sent to SOFIA Peer Review Lunar and Planetary Institute 3600 Bay Area Blvd Houston TX 77058 1113 Letters of Intent may be mailed e mailed or faxed to the recipient FAX 281 486 2160 E Mail cloud pi jsc nasa gov Submit Proposals to SOFIA Peer Review Attn Mary Cloud Lunar and Planetary Institute 3600 Bay Area Blvd Houston TX 77058 1113 Copies Required Original plus twenty 20 copies to the address above plus one courtesy copy as discussed below Obtain Further Information From Technical Dr Jacqueline Davidson Universities Space Research Association Project Scientist for SOFIA c o NASA Ames Research Center M S 245 6 Moffett Field CA 94035 1000 Tele phone 415 604 5531 E mail Davidson cma arc nasa gov Administrative Mary Cloud Lunar and Planetary Institute 3600 Bay Area Blvd Hous
137. ew for the instrument 2 12 5 N211 ICDs SSMO SI 0I Instrument teams need to provide a list of needed equipment prior to the pre ship review Although very little equipment is expected to be available immediately after ORR the list includes laboratory space a few tables and cabinets network connections and a PC configured for e mail web browsing printing and standard office applications Any specialized equipment should accompany the science instrument This list is required prior to the pre ship review SSMO SI 02 The instrument teams should list any observatory test equipment expected for sim ulation of point sources or instrumental beam mapping Very little equipment is currently avail able although special request can be considered This list is also required prior to the pre ship review SSMO SI 03 The instrument team s requirements for cryogenic support during their stay at the SSMOC is require prior to the pre ship review This includes the quantities of cryogenic gases LN2 Lhe any transfer tubes or storage vessels or funnels any room temperature gases N2 He any gas regulators or hoses and any after hours staffing requirement or access needs All these needs should be stated and clarified prior to the pre ship review 2 12 6 Operational ICD Verification Each phase of the science instrument operations and their relationship to final ICD verification must be detailed This is to include laboratory operations aircra
138. exceeding 5 000 Describe the basis for the estimated cost General purpose non technical equipment is not allow able as a direct cost to USRA grants unless specifically approved by the contracting officer Supplies Provide general categories of needed supplies the method of acquisition estimated cost add the basis for the estimate Travel List proposed trips individually describe their purpose in relation to the grant provide dates destination and number of travelers where known and explain how the cost for each was derived Publications Detail publication costs if any listing page changes etc B Other Enter the total of any other direct costs not covered by 2 a through 2 f Attach an itemized list explaining the need for each item and the basis for the estimate C Indirect Costs Identify indirect cost rate s and base s as approved by the cognizant Federal agency including the effective period of the rate Provide the name address and telephone number of the Federal agency and official having cognizance over such matters for the institution If unapproved rates are used explain why and include the computational basis for the indirect expense pool and corre sponding allocation base for each rate 5 12 uA Guidelines for Participation in the Instrument Program wr HP CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 D Other Applicable Costs Enter the total of any other applicable costs Atta
139. ficient personnel controlling the cart so that no one person must exert unsafe levels of force b Caution must be used when ascending and descending aircraft access ramps to maintain control of the cart c Science instrument shall be mounted in a stable position so as to minimize the risk of tipping d When at all possible the cart should be pushed from the short side so as to minimize the risk of tripping Great care should be exercised when pushing the long side of the cart 2 30 uA Science Instrument Cart CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Light Cove c lg Maximum SI Mission Equipment E bun Handrail Assembly Figure 2 26 Science Instrument Cart Positioned On Cart Path Developers should note that the maximum science instrument cart footprint is constrained by the dimensions of the 1L aircraft door As specified in Global 09 the flat portion of the aircraft door is approximately 31 inches in length The maximum cart footprint width should therefore be approximately 30 inches as shown in Figure 2 28 Science Instrument Cart eua 2 31 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Max Cart Deck Vertical Clearance Height 6 am mum sunm Aa REND CUR Um Rmo Max Cart Footprint Width 30 Door Sill Level 51
140. flecting surface is oversized by 20 to deflect the extended wings of the spatial response of far infrared focal plane instruments upward toward the sky rather than continuing horizontally to the aft bulkhead A 2mm diameter alignment mark denotes the proper 1 16 T Telescope Design and Performance A dAl a CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 chief ray position on the optical surface this is displaced 3 45 mm from the mirror center Basic parameters are provided in Table 1 3 for reference FPI aluminized tertiary This mirror is located directly under the IR dichroic tertiary The size of the tertiary support structure and the size of the passage through the bearing constrain the sec ond tertiary to being somewhat undersized with some vignetting 5 of the visible light beam Table 1 4 Imager Specifications Major axis of ellipse is truncated at upper end by 46 6 mm Mechanical Optical Parameter Value Parameter Value Free Opt Diameter 368 x 290 mm Dimensions 373 x 300 mm Surface Roughness 2 nm TBD Material Zerodur Wavefront Error 80 nm rms TBD Weight 7 5 kg Reflective Coating Protected Ag TBC Thermal time constant 15 minutes TBD Reflectance Optical surface center U 2514 2 2 0 5 um 0 1 TBV position mm V 0 A 100 u m 0 99 TBV W 191 0 FIR Emissivity 0 1 TBV SOF SPE KT 1000 0 03 SOF SPE KT 1300 0 02 Telescope Design and Performance
141. from participation in this transaction by any federal department of agency b Where the prospective lower tier participant is unable to certify to any of the statements in this certification such prospective participant shall attach an explanation to this proposal Organization Name CFP or AD Number and Title Printed Name and Title of Authorized Representative Signature Date Printed Principal Investigator Name Proposal Title 5 3 8 2 Certification Regarding Drug Free Workplace Requirements This certification is required by the regulations implementing the Drug Free Workplace Act of 1988 34 CFR Part 85 Subpart F The regulations published in the January 31 1989 Federal Reg ister require certification by grantees prior to award that they will maintain a drug free work place The certification set out below is a material representation of fact upon which reliance will be placed when the agency determines to award the grant False certification or violation of the certification shall be grounds for suspension of payments suspension or termination of grants or government wide suspension or debarment see 34 CFR Part 85 Sections 85 615 and 85 620 I GRANTEES OTHER THAN INDIVIDUALS A The grantee certifies that it will provide a drug free workplace by a Publishing a statement notifying employees that the unlawful manufacture distribution dis pensing possession or use of a controlled substance is prohibited in the g
142. ft installation aircraft ground SOFIA Science Instrument Commissioning Qua 2 71 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 operations aircraft in flight operations and also post flight instrument operations Verification of each instrument ICD is to be listed in a table with a check column for a designated official to ini tial A sample ICD verification document is provided in the appendix to this manual 2 72 uA SOFIA Science Instrument Commissioning wr EH SOFIA IHB 0 0 Infrared Astronomy CHAPTER 3 Airworthiness 3 1 3 2 3 3 3 4 3 5 3 6 3 7 3 8 3 9 Science Instrument Certification c ccccceceeeeeeeeeeeeeeeeeeeeeeeseseesaeaeaea nn nnn nnn nh nahen nanus na nans nn 3 2 Science Instrument Certification Methods and Roles sees 3 2 Compliance vs Conformity e tte rentrer ttai nte fae tonta Font Eine EE RRR YER 3 4 Operations Flight Standards District Office eeeeeeeeeeeneeennn nnn 3 4 Science Instrument Certification General Process Overview 3 4 Construction Inspection and Testing eceeceeeeeeeeeeeeeeeeaseeeeeeeeeeeeeseeeeeeeessnaneeeeeeeeeeees 3 6 Obtaining Final Certification eeeeeeeeeeeeeeeeeeeneenen enne ennt nnn nnne nennen nnn nnne nnns 3 6 Certification Procedures Manual csceseeeeeeeeeee
143. gator has to learn the syntax of the instrument command language which is different for every instrument in order to do an observation For FSI instruments the observation control is done through the DCS DCS provides an Astro nomical Observation Template AOT editor which allows a GI to fully specify an observation i e all the commands for the telescope trackers and secondary mirror assembly as well as all the instrument setup parameters and write it out as an instrument neutral Astronomical Observa tion Request AOR The manual flight planner uses these AORs together with any constraints from the associated Observing Plan to create a flight plan For an observer a flight plan is simply an ordered list of AORs In flight these AORs are passed to a queuer sequencer which translates the AOR into MCS and Instrument commands and parses the commands to MCS and the Instru ment through the instrument control In practice both the AOT editor and the Queuer are likely to be run from the instrument console The Queuer allows the observer to re order the queue add or 4 16 uA Mission Ground Operations CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 delete AORs in the queue and pause halt abort or extend the AOR currently being executed The AOT editor can be used to modify an AOR or even create a completely new AOR which can be inserted into the queuer for execution At the end of a flight all the Science Instr
144. ght through pin to pin connector to connector from the SI patch panel to the CLA disconnect panel to the telescope patch panel using the same science instrument connectivity reference numbers 2 8 3 The Cable Load Alleviator The specific engineering details of cables used within the SOFIA cable load alleviator CLA are described in the interface control document TA_SI_01 This document describes the complete cables and lines arrangement of the cable load alleviator CLA and also the interface between the SI cables and SI lines and the TA cable load alleviator device Furthermore this document also defines the interface to CLA cabling to the SOFIA aircraft The document defined the cable posi tions on the CLA running to the outer cable clamp on the cable tray right side and the aircraft intercostals left side The cable routing from this location to the disconnect panels are described in a separate physical interface control document Details of the water cooling hoses and instru ment vacuum lines are also contained in TA SI OI Instrument Cabling Patch Panels x xum 2 55 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Cable Load Alleviator Ww Cable Tray CLA Coarse Drive CLA Coarse Drive Left Hand Side Right Hand Side Cable Bundle Cable Bundle Inner Cable Bundle Outer Cable Bundle Figure 2 41 The SOFIA Telescope With An Illustration Of The Cable Load Alleviator CLA Configuration All scien
145. gin analysis Drawings include materials fasteners welding specifications etc Electronics data including box to box cabling power loading analysis cable specifications and materials See the SI Airworthiness Manual for a sample Gantt chart that includes typical submittal packages System Safety Assessment Includes functional hazard assessment failure modes and effects fault tree analysis Operations procedures and continued airworthiness plans Preparation for integration onto the aircraft flow chart standard safety procedures operations procedures that pertain to safety relief devices etc storage plans log book requirements etc 3 8 uA Schedule of Submittals CHAPTER 3 Airworthiness SOFIA IHB 0 0 WORKSHEET 3 1 SI Submittal Status Work Sheet SI name acronym Topic Drawing Tree Drawing List Detailed drawings Rev level USRA FAA NASA UAL Received Approved L 3 DER Received Approved Received Approved Received Approved Received Approved Critical Structures Definition Cryogenic Reservoir s Pressure Relief system Cryostat Welding procedures Electrical wiring CWR components PI Rack components Installation of assemblies Kits Detachable components interconnect cabling Action Items RFAs Engineering Change Orders Nonconformance Reports Analyses Structural analysis Electrica
146. gration time water vapor overburden date flight and flight leg source name coordinates in J2000 The amount of the summary information will be configurable by archive users Software and Data Management x xim 1 47 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 7 4 Pipeline Products Pipeline reduced data are available only to accredited users during the proprietary period and to the whole user community after the end of the proprietary period 1 7 5 Housekeeping HK Data Access to HK data will be through a special engineering interface hosted by the DCS This query interface will enable SSMOC staff and DCS accounts to access any data based on keyword key word value time date or time interval or any combination of these MCCS is providing on line tools for monitoring displaying and analyzing HK data The same tools will be available as stand alone versions for analysis of HK archive data 1 7 6 Retrieval of Data All data retrieval from the SOFIA archive will be through an ftp server GIs retrieving their own data will have the highest priority if data retrieval needs to be staged SSMOC staff will be next in priority and registered data miners will have the lowest priority A single user can retrieve at most 10 GB of data at one time Requests for abnormally large i e gt 10 GB data sets will have to be sent to the SOFIA Observer Support and will be handled on a case by case basis 1 7 7 User
147. he assistance of the SSMOC PSI scientist The GI should be able to perform data analysis of calibrated data using standard software routines without requiring the assistance of the SSMOC FSI scientist A simple method of archiving a summary of the observations and the science data will be required A preliminary design review a critical design review and an acceptance review will be held by USRA for FSIs The instrument will be delivered to the SSMOC 5 1 1 2 Principal Investigator class Science Instrument PSI This is a general purpose instrument that is developed and maintained at the state of the art throughout its useful operating life It is expected that this instrument will be operated by the PI team both for its own research as well as for that of successful GI s The interaction of the PI and GI teams is to be determined by mutual consensus for each GI proposal Normally the instrument will reside at the PI s institution where all maintenance and upgrades will be accomplished Descriptive documentation must be clear thorough and intuitive so that a GI can propose a sci ence investigation without the necessity of extensive discussion with the PI team The process of data acquisition reduction and calibration should be straightforward and transparent to the GI requiring only a minimal level of assistance from the PI team The GI should be able to perform 5 2 uA USRA SOFIA Science Instrument Proposal Process wr HP CHAPTER 5
148. he hydrostatic bearing and its matching spherical socket also part of the telescope assembly and called the inner cradle are embedded in the forward cavity pressure bulkhead 2285 SS W S S S a T A EMI ao L1 eee Jf TNI a LEA Ear Ti mi ap be ges LL AI Ct Figure 1 7 Diagram of the Telescope Assembly In this schematic cross section the SOFIA telescope and some features of the cavity opening have been rotated beyond the normal telescope elevation range into the vertical plane The cavity door and its D shaped aperture are slaved to the telescope elevation angle The passive flow control Telescope Design and Performance Qua 1 11 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 fairing runs along the aft edge of the cavity opening and extends over the top of the aircraft The science instrument mounts forward of the telescope in the pressurized cabin Approximate scale 1 TBD Dwg ref TBD The telescope bearing inner cradle system is supported by a telescope outer cradle attached to a ring of axial and tangential pneumatic vibration isolators called the Vibration Isolation System VIS These isolators lie in a plane containing the center of mass of the telescope assembly The VIS provides a degree of isolation from translational vibrations transmitted to the telescope through the bulkhead The hydrostatic bearing support effectively isolates the telescope assembly
149. horn mixes the 183 3 GHz radiation down to a bandwidth of 1 GHz with the radiometer oper ating in double sideband mode The sub harmonic mixer is fed by a phase locked 91 65 GHz local oscillator The intermediate frequency signal out of the mixer is amplified by an RF amplifier with a bandwidth of 100kHz 500MHz before it is sent on to the IF Converter Box 1 5 3 4 Calibration Since the WVM operates as a radiometer accurate gain stability is important In order to achieve this stability the two reference blackbodies are used to periodically insert a stable signal into the radiometer Small motors rotate mirrors that direct images of the black body targets into the feed horn field of view once every 5 seconds One mirror the Sky Calibrator Mirror directs the view of the radiometer between the sky and the black body calibrators The second mirror the Hot Ambient Mirror selects between the hot and ambient temperature black bodies Therefore over a 15 second period the radiometer views the sky for 4 seconds an ambient temperature black body target for 4 seconds and a heated black body target for 4 seconds One second is allowed to move the mirrors at each viewing position The temperatures of the two black body targets are measured with temperature sensors 1 5 3 5 Typical Post flight Results A typical zenith water vapor plot for a flight is shown in Figure 1 17 below The plot is usually provided with temperature and altitude data as well
150. ic ii Foreign f Publication g Other 3 Indirect Costs 4 Other Applicable Costs 5 Subtotal Estimated Costs 6 Less Proposed Cost Sharng ifany 7 Total Estimated Costs APPROVED BUDGET XXXXXXXXX Figure 5 2 Proposal Form Budget Summary Guidelines for Participation in the Instrument Program x 5 11 CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 5 3 7 1 Instructions for Budget Summary Form 1 Provide a separate budget summary sheet for each year of the proposed development program 2 Estimated costs should be entered in Column A Columns B and C are for USRA use only 5 3 7 1 1 Explanation of Proposed Costs Provide in attachments to the budget summary the detailed computations of estimates in each cost category along with any narrative explanation required to fully explain proposed costs A Direct Costs Direct Labor salaries wages and fringe benefits Attachments should list number and titles of personnel amount of time to be devoted to the grant rates of pay and an estimate of labor hours for each position Subcontracts Attachments should describe the work to be subcontracted estimated amount recipient if known and the reason for subcontracting this effort Consultants Identify consultants to be used why they are necessary time to be spent on the project and rates of pay Equipment List separately and explain the need for items of equipment
151. ience instruments the mass and center of gravity between instruments is expected to vary The telescope requires that the instrument mass is less than 600 kg 1322 8 Ibs and that the center of mass lies within the dimensions of the spec 2 16 eA Telescope Mounting flange CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 ified envelope Two envelopes are specified based upon the assumed weight of the science instru ment counter weight rack of 150 kg 330 7 Ibs nominal or 100 kg 220 5 Ibs The operations center of gravity envelope is specified as along the V and W axes A cone shaped by these figures defines the operational c g envelope for all science instruments see Figure 2 14 and Figure 2 15 5000 5000 4000 4000 3000 3000 2000 1000 1000 0 0 50p0 0 15000 20 1000 A 1000 2000 2000 3000 3000 Moment Caused by V distance Nm 4000 4000 Moment Caused by V distance Nm 5000 5000 Moment Caused by U distance Nm Moment Caused by U distance Nm Mass of SI Rack 150 kg Mass of SI Rack 150 kg Figure 2 14 The Maximum Moments Caused by Cg Variations In the V Direction 4000 3000 2000 3000 2000 1000 1000 1000 15900 m 20 2000 1000 2000 3000 Moment Caused by W distance Nm Mo
152. ill allow the science instrument to be wheeled directly from the SSMOC to the telescope and not require extensive vertical adjustments The center of the telescope science instrument flange is specified as 841 5 mm 33 13 inches and should be within x 0 3 of vertical Figure 2 28 USRA Provided Science Instrument Cart This isometric figure shows a sample cart design suitable for use aboard SOFIA Science Instrument Cart Qu 2 33 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 7 Instrument Racks PI Rack The USRA program will provide science instrument teams with a number of electronic racks cer tified for aircraft use and designed for installation aboard SOFIA A principal investigator PI rack is for electronics and computers needed within the immediate seating location of instrument teams A second rack mounted forward to the telescope s counter weight assembly is for instru ment electronics located a short distance from the science instrument itself Schematics of both racks are available to instrument teams who desire to construct their own flight hardware The SOFIA Facility librarian has detailed drawings for these racks and copies will be sent upon request 2 7 1 Pl Rack An instrument rack specifically designed for use on the SOFIA is shown in Figure 2 29 It accepts standard 19 inch wide front panels with packaged electronics attached Pertinent dimensions are shown in Figure 2 30 These racks are ma
153. ill provide the majority of the intersystem communications and facility con trol and monitoring via a local area network LAN The MCS will also provide other ancillary functions including storage and retrieval of data printing and plotting functions computations and intersystem data file transfers The MCS equipment includes servers mission support com puters and operator consoles The MCS consists of a suite of UNIX computers workstations and possibly VxWorks embedded systems Each console accesses a UNIX workstations Through the UNIX operating system users access network peripherals such as disk and tape drives printers and modems The operat ing system allows a system administrator to assign privileges to those resources The servers and workstations will execute software applications and provide access to high capacity disk and tape storage drives Any observatory workstation will be able to print to any of the printers located in easily accessible areas of the cabin This approach allows for reconfigurable workstations and provides reliability through redundancy The MCS housekeeping will archive and make available by name all data received from all sub systems Housekeeping functions accessible via the MCS SOFIA Command Language SCL will return the most current information for all facility data requests without data loss All data will be accurately time tagged upon receipt by the MCS Where possible data will be time tagged whe
154. ing Some long lead items may need to be purchased before this review The review board should look for the following items during CDR Operational requirements and verification of compliance e Summary of major derived design specifications and constraints Response to PDR review board recommendations concerns Major changes since the PDR nterface details and status of agreements Selected design details Critical component status Selected manufacturing details and plans Configuration control plans hardware and software Maintenance plans hardware and software Documentation status drawings documents procedure e Breadboard and prototype test status and results Test plans for the deliverable units Operational features and constraints Spare provisions Support equipment requirements provisions and plans Schedule budget and flow plan status Major concerns open items and plans for resolution The primary purpose of the acceptance review is to give the final stamp of approval for the instru ment as delivered to the SSMOC The following items should be addressed during the acceptance review Delivery of agreed upon systems hardware software supporting components Verification of expected instrument performance e Straight forward data acquisition reduction and calibration Acceptable data archival tools and summary data 5 5 Project Implementation Plan To assist the instrumen
155. ing software is called the Data Cycle System DCS The DCS software is being developed as a distributed software effort Rochester Institute of Technol ogy RIT is developing the DCS Core system architecture and user interaction while UCLA with assistance from IPAC is designing the SOFIA archive Additional DCS efforts are devel oped by the USRA Information System Development ISD and NASA Ames Code SSA The whole DCS will be deployed at the SSMOC where it will be further developed and maintained Note Although the SOFIA contract Statement of Work only required a simple summary science data archive it was decided rather early in the development of SOFIA to provide a modern search able complete archive The SOFIA archive will store all raw data and any pipeline reduced data from SOFIA science instruments All FSI instruments will have data reduction pipelines and pipelines will be added in the future for PSI and SSI instruments as resources allow Additionally the archive will accept reduced data contributed by the FSI PSI or SSI instrument teams and other qualified personnel i e data taken in modes for which SOFIA hosted pipelines do not exist The Statement of Work also did not require automated operation of the instruments but SOFIA has decided that selected modes of FSIs will be operated automatically via commands generated from astronomical observing requests AORs This document describes the details of these operation and archive
156. ion Volume The installation volume refers to the volume of the science instrument or subsystem during instal lation on the aircraft This volume is also to include the science instrument installation cart See Figure 2 19 The installation envelope is defined by the volume suitable for moving through the aircraft doorway i e the distance to the stairs when entering door 1L see Figure 2 25 The height of the envelope was established to allow clear viewing over the SI during travel through the facilities and the aircraft The installation volume height allows the science instrument to roll along the installation cart path without interfering with overhead structures within the aircraft Other aspects of the installation envelope are specified in Global 09 TOP VIEW 15 35 1389 9 qy _ INSTALLATION DIRECTION REAR VIEW 19 00 2006 6 i i 789 9 R6 00 Lu 5 00 5 00 152 4 12T 0 41 00 121 1041 4 SIDE VIEW Figure 2 19 Science Instrument Installation Volume 3 D Solid Modeling Drawing Science Instrument Envelope qua 2 23 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Forward Installation Direction Up Right Isometric View Figure 2 20 Science Instrument Static Serving Envelope Isometric View 2 5 2 Static Instrument Volume The static instrument volume is also known as the stay out envelope
157. ire 3 2 T Science Instrument Certification CHAPTER 3 Airworthiness SOFIA IHB 0 0 ments for aircraft safety The Aircraft Certification Office ACO supervises dERs while the Manufacturing Inspections District Office MIDO supervises DARs The Certification Mainte nance Office CMO will monitor SOFIA Operations The following sections discuss the roles and responsibilities that are held by each of these groups General information and the steps involved in FAA certification from initiation of a certification project through testing conformity inspection and award of a Supplemental Type Certificate STC are listed in Appendix III 3 2 1 Designated Engineering Representative DER The DER is a representative of the Federal Aviation Administration FAA and is quite knowl edgeable in aircraft certification and all aspects concerning safety of flight The DER is appointed and supervised by the cognizant FAA Aircraft Certification Office ACO that handles all engi neering issues with respect to certification The DERs have specific areas of expertise regarding safety such as structural electrical mechanical hazardous materials etc and are responsible for presenting the science instrument designs documents analysis testing etc to the FAA in order to acquire the Supplemental Type Certificate STC required for flight aboard the observatory The DER will aid the science instrument builder in developing the proper docu
158. ists of the Captain First Officer and Second Officer Flight crews are provided from the staff of the USRA SOFIA program In the main cabin two or three members of the SOFIA SSMOC staff operate the telescope and support systems Two crewmem bers are always present in flight they are the In flight Director IFD and the Telescope Operator A Computer Systems Specialist may also be present especially on at least the first flight of a new flight series These crewmembers are seated at their respective consoles The IFD coordinates interaction of the SOFIA staff the investigator team and the flight crew to assure optimum sup port of the research activity and safety The telescope operator activates and controls telescope stabilization the oscillating secondary system and the telescope cavity environments Finding charts and observing plans are prepared by science team members working closely with USRA staff in the SSMOC before the flight These science planning support activities are described fur ther below sections TBD and TBS 1 2 5 Observatory Flight Profile Two commonly used research flight profiles are shown in Figure 1 5 The initial ascent to observ ing altitude requires about 35 minutes The descent and approach for landing requires at least 25 minutes Therefore the maximum time available at observing altitudes is approximately an hour less than the total flight duration including heading and altitude changes Typically a flight i
159. itigation descope Appendix 1 The 1997 Call For Instrument Proposals This Universities Space Research Association USRA Call For Proposals CFP solicits research proposals for the design development and illitial operation of scientific instruments for the Stratospheric Observatory For Infrared Astronomy SOFIA The Observatory is being developed under the auspices of the National Aeronautics and Space Administration NASA under Prime Contract No NAS2 97001 and the Deutsche Agentur fur Raumfahrtangelegenheiten DARA the German Space Agency Instruments are being developed separately under the auspices of NASA and DARA 5 20 uA Project Implementation Plan CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 Participation in this program is open to all categories of organizations both domestic and foreign industry educational institutions other nonprofit organizations NASA centers and other U S government agencies Proposals must be received by 5PM CDT on July 15 1997 Late proposals will be handled as correspondence and returned to the sender The proposals will be evaluated by a USRA selected peer review panel early in September 1997 and notification of results will be made approximately one month later Details relevant to this program are included in the appendices to this announcement and on the SOFIA USRA website http sofia usra arc nasa gov Paper copies of the CFP are available from J Kolon
160. ko Science Administrator Department of Physics and Astronomy UCLA 405 Hilgard Ave Los Angeles CA 90095 Phone 310 206 4548 FAX 310 206 1091 E mail kolonko physics ucla edu Appendix A describes the classes of instruments being solicited and evaluation criteria Appendix B contains the general guidelines for participation in the SOFIA Science Instrument Program Appendix C is the proposal abstract and summary sheet Appendix D provides a Budget Summary format with instructions for its completion Appendix E provides technical information on SOFIA to aid in planning instrument proposals The certification forms in the Attachments should be filled out and attached to the original copy of the proposal to reduce grant processing time Schedule of Events 1 Release of Call for Proposal April 7 1007 2 Letters of Intent Due May 1 1997 3 FAA Workshop May 7 1997 4 Proposal Deadline July 15 1997 5 Peer review Sept 3 5 1997 6 Target Date for Announcement of Proposals Selected Oct 1 1997 Future SOFIA CFP s are anticipated An additional call for major instruments will occur in about 3 years A technology development program specific to SOFIA most likely including detector development will be initiated after the first round of instruments have been selected Detector development proposals will not be considered in response to this solicitation Project Implementation Plan Qua 5 21 CHAPTER 5 SOFIA SI Proposal and Revi
161. l Investi gators are likely to be using or should be aware of include those listed in Table 1 8 The SI labs on the ground floor are intended for preparation of SIs for flight and any post flight work such as calibration diagnosis or preparation for storage or shipping Preparation for flight in the SI lab may include unpacking electronics testing assembly inspections vacuum pumping and initial cryogen transfers This is also the location where electronics chassis can be installed into the SI rack s and the Counterweight Rack CWR Table 1 8 SMMOC Locations Name or Description Rm Size Location SI Lab and enclosed office 129 29 x19 ISW corner SI Lab and enclosed office 130 29 x19 ISW corner Facility SI Lab 135 37x19 Adjacent to west door Pre Flight Integration Facility 121 50 x25 South edge hangar floor Elevator 4 wide door 9 x6 SW corner 1 40 uA SSMOC Ground Facilities for SI Teams CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Table 1 8 SMMOC Locations Name or Description Rm Size Location Guest Investigator office spaces 224 6 17 x10 2nd floor South side Science Support staff offices 245 251 2nd floor West side SI GI Workstations terminals 229 25 x15 2ndfloor South side DCS MCCS support 218 221 2nd floor South side Support Flight Line Figure 1 19 MOCC Floor Plan INI EERING ADMIN OFFICES 3rd floor
162. l power anal System Safety Assessment Report Functional Hazard Analysis Failure Modes Effects Analysis Fault Tree Analysis Zonal Safety Analysis Proof amp Burst Pressure Tests Plan Scheduling for test Final report Quality Assurance CQl designated QA plan FAA Form 8130 9 b EMC EMI compliance Test plan Results NASA Safety Analysis Preliminary Hazard Analysis PA10T NAME Operational Hazard Analysis Maintenance Manual Cryogen filling Operating instructions Ice plug abatement process Installation removal process SI Installation removal process CWR Installation removal process PI Rack Electrical checkout amp grounding Total Wt amp CG install CWR TA balance etc Cart detailed design Weight and size Operation and ICD compliance IR Not part of approval process Schedule of Submittals CHAPTER 3 Airworthiness SOFIA IHB 0 0 3 10 uA Schedule of Submittals SOFIA IHB 0 0 Infrared Astronomy CHAPTER 4 SSMOC Operations and SOFIA Observing Modes 4 1 Yearly Scheduling of the SSMOTC esseseseeeeeeee eene nennen nennen nennen nennen 4 2 42 Flight Management mete PR PE rere 4 3 4 3 Pre Shipment EOogisStiCs ener rtr tirer ENARA ARRAROA NAARAAT A NARRA ER RER ERRARE NARAR 4 6 4 4 Mission Groun
163. lanner is designed so that flight plans can be changed during flight 4 3 Pre Shipment Logistics Location of future shipping and receiving information and other pre arrival logistics arrange ments with the SSMOC and points of contact 4 4 Mission Ground Operations 4 4 1 Overview of SI Team Integration into SSMOC Operations A mission or missions is normally a multiple of a week in length and is defined by the science instrument or the suite of science instruments mounted simultaneously to be used The science instrument could be a FSI PSI or SSI see above In the case of the FSI SSMOC scientists and technicians will ready the science instrument for flight In the case of the PSI and SSI principal investigators PI s from the science community must arrive at the SSMOC between one and two weeks before the first flight to ready their instrument for the mission General investigators GI s who will use the science instruments whether a FSI or PSI will arrive at the SSMOC probably a few days before their first flight to use the data center familiarize themselves with the airborne observatory and finalize their observing strategies The near to final flight plans for the series would have been sent to the SSMOC or generated by SSMOC scientists see 4 3 1 30 days prior to the first flight of the series Below is the sequence of events an investigator will follow within a mission assuming a PSI mis sion a Upon arrival
164. leg the Mission Control Sub system MCS software uses Universal Time the object s coordinates and the aircraft s actual position and attitude to repeatedly calculate the object s present local azimuth and command the corresponding heading via the autopilot For safety rea sons the aircraft heading is not automatically adjusted if the telescope is moved away from the position of the object scheduled for the current leg By fine tuning the autopilot for the current aircraft altitude airspeed and weight excursions in roll are limited to 0 5 TBV degrees The autopilot can limit roll in light turbulence to 2 TBV degrees In normal conditions aircraft pitch and yaw fluctuations are limited to less than one degree The telescope is isolated from these attitude variations by stages three and four described below 1 3 2 2 Vibration Isolation The second stage consists of a series of pneumatic vibration isolators These are mounted within the forward pressure bulkhead of the telescope cavity in a horizontal plane containing the center of mass of the telescope assembly When activated they isolate the telescope system from some of the aircraft translational vibrations assuming light to moderate turbulence passed to the tele scope through the bulkhead In such conditions the telescope assembly may exhibit motions of up to an inch with respect to the cabin primarily in the vertical direction However the inertia of 1 22 TT Te
165. les Each profile example contains nominal 0 5 hour initial climb and 0 5 hour final descent Observing alti tudes shown are at 37K S9K 41K 43K and 45K feet pressure altitude Usually observing may continue uninterrupted during cruise climb from one observing altitude to another Flight at altitudes above 41K require reduced fuel load and are limited to the final hours of the flight Investigators may request in advance the option of observing at an altitude of 45 000 feet This is possible after about 7 hours flight time on a planned 8 5 hour flight General Description of Observatory Working Environment 7 ce 1 9 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 3 Telescope Design and Performance The exposed telescope is shown in Figure 1 6 The opening or door aperture is defined by a con toured aft lip the shear layer control and attached rectangular frame with an overlying upper rigid door and lower flexible door The upper rigid door is moved vertically to cover or uncover the telescope and the lower flexible door covers any unused area below the aperture at elevation angles above the minimum The telescope can be moved in flight through an unvignetted eleva tion range of 20 to 60 above the horizontal During observing the doors are slaved to the tele scope and the opening is just large enough to avoid vignetting the telescope for pointing changes of up to 3 in azimuth LOS relative to the aircraft Theref
166. lescope Design and Performance A dAl a CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 the telescope assembly is significant and this exhibited motion is really the aircraft moving with respect to the telescope assembly 1 3 2 3 Spherical Hydrostatic bearing The third stage is the hydrostatic bearing which floats on a thin film of compressed oil that is fil tered and re circulated The gap between the spherical bearing and its housing is 50 microns 2 mils The spherical shape of the bearing active surfaces provides rotational isolation of the tele scope from the aircraft and permits pointing stabilization or controlled motions with respect to three orthogonal axes Actual telescope pointing control is provided by stages four and five 1 3 2 4 Gyros and Torque Motors for Three Axes Stage four consists of three rate integrating fiber optic gyroscopes and three DC segmented torque motors Each gyro torquer control loop operates on one of the three orthogonal axes cross elevation XEL elevation EL and line of sight LOS Note that this is not a true alt azi muth arrangement the XEL axis actually tilts back from the zenith by an angle equal to the tele scope elevation angle 20 60 as shown in Figure 1 11 W LOS V XEL Figure 1 11 Telescope Control Axes The telescope hydrostatic bearing and Nasmyth Tube are shown schematically at a typical eleva tion angle Movement over the 40 elevation r
167. lines but are subtracted from the analog lines noted as without FBC The later lines should represent the motions of the secondary mirror in addition to those motions required by FBC image stabilization of the SOFIA telescope The FBC signals are not applied at the R and S analog command lines available to science instru ment teams FBC control is added somewhere else within the TCMU electronics Sensing of the secondary mirror position as a result of SI controlled motions on the R and S analog control lines should be determined through sensing of the R and S axis analog waveform outputs with out FBC Most instrument teams are likely to have only a passing interest in the FBC signal assuming a properly functioning system In addition to the analog control and sense lines of the secondary mirror control electronics are two TTL lines one for synchronization of two and three point chopper and another designed as a TTL reference line The configured for external control and operation the TTL input line the external TTL square wave chopper synchronization signal Chop Sync In is responsible for in phase motions of the secondary mirror Note that each transition of the TTL line is expected to initiate a transition of the secondary mirror motions as depicted in Figure 2 48 Secondary mirror Control x xm 2 63 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 External TTL Input Data m It Phase Data Positive Beam
168. lope is fixed relative to the telescope and science instru ment coordinate system Science Instrument Envelope CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 ag Forward Telescope Flange 2500 6 T5 171 5 SIDE VIEW AN IR Beam Location Nasmyth Tube Centerline 120 00 DA 5048 141 41 AFT VIEW LOOKING FORWARD AN Figure 2 24 Science Instrument Dynamic Envelope Side And Rear Views With Telescope At The Nominal Installation Elevation 2 28 uA Science Instrument Envelope CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 6 Science Instrument Cart A cart is used to transport a maximum payload of 600 kg 1320 Ibs science instruments and other equipment through the ground facility up to the aircraft through the passenger door into the main deck passenger compartment and up to the telescope science instrument flange Two interface control documents ICD SIC_SI_01 96162511 and SIC_AC_01 96162512 describe the engineering requirement for instruments planning to use the USRA provided instru ment cart SIC SI 01 or the requirements for instruments planning to deploy their own carts SIC AC 01 Developers should consult the original documentation for specific engineering requirements In general science instrument carts must meet the following requirements a The loaded cart shall be able to maneuver through c
169. lope is the stay in volume for the science instruments such that motions of the telescope assembly e g changes in telescope elevations do not cause the science instrument to interfere with stationary objects within the aircraft The expected range of telescope motions is dictated by normal telescope operations while the observatory is airborne see Figure 2 24 The dynamic envelope is derived from the complete range of possible telescope motions during normal flight operations These are based on the ranges of motion the telescope can go through when uncaged as stated in the Global 09 document For generation of the envelope it was required that no sci ence instrument component could come within 4 inches of any aircraft structure 1 e floor ceil ing etc The dynamic envelope was developed assuming the telescope in its worst case condition of being tilted toward the aircraft floor In this position the telescope was run through its full range of operational motions about the U axis Material was added or subtracted from the SI volume to maintain the 4 inch margin with respect to the aircraft A 45 cutout in the aft sec tion of the volume accounts for struts that support the science instrument counter weight rack see TA SI 05 A protrusion centered on the infrared optical axis of the telescope and forward of the science instrument flange is to accommodate a science instrument rotator often used in polari metric instruments The dynamic enve
170. ly a year will contain about 20 missions with a total of about 50 investigator teams This means on average each mission will last two weeks and will support 2 to 3 investigator teams 4 2 Flight Management 4 2 1 Flight Planning Process Flight planning and scheduling represents a unique problem for SOFIA The visibility of an object depends on where and in what direction the Observatory is flying Contrary to satellite mis sions the Observatory is also affected by weather conditions wind cloud cover precipitable water vapor and by airspace restrictions Flight Management x xm 4 3 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 The zero fuel weight of the Airborne Observatory will be about 366 000 Ib If this is achieved then in order to maximize successful flight hours within each flight science research flight pro files will be either one of the following Flat Flight Profile 0 5 hrs climb 7 0 hrs at 41 000 ft 0 75 hrs descent Step Flight Profile 0 5 hrs climb 2 55 hrs at 41 000 ft 0 1 hrs climb 2 6 hrs at 43 000ft 0 1 hrs climb 1 65 BETA OKI LEG 5 501 s kHHHYV lt FLIGHTi PLH FLIGHT PLAN FOR FEB 4 lze z4 FT HOH a FE5B 13235 FLIGHT A amp Sl SCALE 116 30E 06 Figure 4 1 Typical Flight Plan from Moffett Field Figure 4 1 shows a typical flight plan for a flight from Moffett Field It shows seven observing legs each about an hour long Observing legs can vary i
171. m 2 87 inches ID pipe from the upper deck pumping station to the disconnect manifold and 15 meters 49 21 feet of 38 1 mm 1 5 inches ID hose from the disconnect panel to the science instrument flange on the telescope subassembly This calculation does not include several plumbing unknowns such as bends angles orifices or other restrictions Science instrument teams should expect that one vacuum pump would be used to evacuate the INF tub and that two others will be for pumping on science instrument cryostats However instrument teams should expect only one pump operational immediately following SOFIA s oper ational readiness review This one pump will have to serve both of the purposes listed above Convector Gauge Tube Centering KF Flange Ring Counterweight 14 Piate To SI or INF Tube Clamp Adapter Figure 2 46 Schematic for Monitoring the Pump Line Pressure Attached to a Science Instrument Science Instrument and TA Flange Pumping System x 2 61 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 10 Secondary mirror Control The articulated secondary mirror control for the SOFIA telescope has both software and a hard ware interface The software interface as described below allows the science instrument team to set the amplitude frequency the phase delay of a trigger reference signal internal to the tilt con troller mechanism unit TCMU Changes in the telescope focu
172. ment Caused by W distance Nm 3000 Moment Caused by U distance Nm Moment Caused by U distance Nm 4000 Mass of SI Rack 150 kg Mass of SI Rack 150 kg Figure 2 15 The Maximum Moments Caused by Cg Variations In the W Direction Science instruments that use cryogenic liquids to cool their instruments are expected to produce changes in instrument mass during the flight as a result of cryogen boil off The telescope s active balance subsystem is designed to accommodate nominal changes in instrument mass and a result Telescope Mounting flange x m 2 17 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 ant change in instrument moment around the cross elevation line of sight and elevation axes The limits in changes of instrument moments are specified in the TA_SI_02 document 4 3 Science Instrument Flange Pressure Boundary The pressure boundary between the aircraft cabin and the telescope cavity is established through the mechanical interface between the science instrument and the telescope nasymth tube and gate valve There are a number of possible pressure boundary configurations as illustrated in Figure 2 16 2 18 uA Telescope Mounting flange CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 LC 1 Full Flange w no Coupler 2 No Flange w Coupler 3 No Flange w Window 4 Full Flange w Coupler 5 No Flange Window amp Coupler i E Full Flange Coupler Window
173. mentation package that will then be presented to the FAA The documentation package will include design specifics mechanical designs stress analysis electronic designs hazard analysis maintenance plans oper ations scenarios and any other item required to show compliance of the SI design to the FARs The science instrument documentation package or data package will also include test plans that are required in order to certify a particular aspect of the system or subsystem The DER will begin the process of identifying aspects of your instrument during the conceptual design review For SOFIA the compliance checklist is kept by the administrative DER for the entire project and individual teams do not need to be concerned with this list As designs become more detailed based on design reviews the identification of critical items checklist may involve several itera tions with continual discussion between the science instrument builder the Airworthiness IPT and the DERs Although the FAA has the right to witness any tests that are done they can choose to designate a DER to witness a particular test DERs will assist the SI team in identifying the components of a system that will require testing 3 2 2 Designated Airworthiness Representative DAR Another very important aspect in the certification process is the finding of Conformity Confor mity is an inspection process in which it is determined whether or not the physical instrument
174. mulator located on the second floor of building N 211 The Sim ulator contains a Sun Sparc workstation and other devices necessary to represent an experi menter s workstation the PI patch panel the SCL the two Ethernet networks and associated I O devices The instrument teams may bring their own rack of equipment alongside make connec tions to the Simulator analogous to those to be used on board and perform dry runs of data taking through an authentic interface environment This may be useful before an experiment is installed into the aircraft or on weekends and or deployments where power or access to the aircraft may not be available Shortly after the SOFIA Operational Readiness Review in 2005 the capabilities of the SOFIA simulator hardware will be limited Over time however USRA will fund the devel opment of the simulator to off load the task of system integration and maintenance to the N 211 facility 1 7 2 Flight Management FM Software FM is responsible for developing executing and re planning SOFIA flights based on observing plans developed by users of the Observatory Most FM functions are carried out pre flight in the SSMOC to optimize the route and altitude profile required for observations Portions of FM are also active on board providing flight monitoring to the IFD and rudimentary input to the aircraft s autopilot for maintenance of desired headings FM produces two forms of the flight plane one to be filed wi
175. n extent from about 10 minutes to 4 hours each Hence the number of astronomical objects observed in one flight can range from about 2 to 16 but with an average of about seven Normally at least one object in a flight is a cal ibrator This is a well characterized object so its measurement will calibrate the data for the whole flight 4 4 uA Flight Management CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 2 2 Flight Planning Software The flight management infrastructure FMI is under development by ISD and NASA Ames Code I The purpose of the FMI is to develop arrange optimize and execute aircraft flight legs in order to enable successful execution of a prioritized list of observations The FMI contains four components A manual flight planner A flight executor Acycle scheduler e An automatic flight planner currently an R amp D project The manual flight planner is functionally similar to KNAV which was used on the KAO but com pletely re designed The flight planner plans a flight for a given date taking a set of targets and observing times exposure time plus overheads a model for wind and water vapor observing alti tude and fuel consumption as well as any flight restrictions like restricted airspace or established airspace routes The goal is to construct a flight plan which observes each target for the requested time and minimizes dead legs times when no astronomical target can be o
176. n firms contracted by the German space agency DLR to develop the 2 7 meter SOFIA telescope The SOFIA aircraft is a Boeing 747 SP originally config ured as a commercial passenger aircraft for Pan American Airlines The aircraft was completely overhauled and modified to accommodate the Observatory sub systems that include the SOFIA telescope an on board mission control area a telescope cavity with cavity door and a cavity envi ronment system The aircraft overhaul and modification were done by a team of US companies under a NASA contract to the Universities Space Research Association USRA Research opera tions will begin on SOFIA in 2005 TBC USRA under the same contracted by NASA will operate the SOFIA Observatory for NASA and DLR Operations of SOFIA will be out of NASA Ames Research Center where the Observatory i e the aircraft with the telescope and other mission sub systems will be housed in hangar N211 USRA will run the SOFIA Science amp Mission Operations Center the SSMOC in the same hanger This center will run all mission operations including flight preparation mission planning observatory and aircraft maintenance science planning and the acquisition and retrieval of sci ence data The SSMOC will also maintain a Data Archive of all SOFIA data The Science Instruments used on SOFIA are all built by the science community USRA will release a Call for Instrument Proposals for the development of USA SOFIA science instrumen
177. n it is generated Time synchronization will be provide through the observatory with an IRIG B timing distribution system accurate to at least 1 ms MCS workstations will be synchro nized to less than a millisecond via custom software using the MCS LAN The MCCS LAN used for MCS communications is a redundant fault tolerant network The MCCS LAN minimizes the network latency to ensure adequate transfer of dynamic time critical data The LAN transports this data among aircraft telescope and science instrument systems to facility data processing functions In addition a dedicated Ethernet network 100 Base T or Giga bit will be available to the science instruments At least 32 IP addresses available via numerous physical ports at the MCCS consoles will be made available to the science users The LAN will also provide Internet access via ground umbilical cable connections to the N211 hangar and sup port facilities at the USRA SSMOC 2 11 1 MCS Command and Keyword References The documents referenced below constitute a complete library of all the SCL commands and key words All of this information is maintained within the SOFIA development environment that is in the XML files used to control SOFIA behavior and so it should accurately represent the cur rent system s configuration SOFIA Software Interface Qua 2 67 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 The documents include implemented components as well as
178. n of the coordinate system is located 7366 mm 290 inches forward of the aircraft nose at the intersection of waterline 0 and buttline The waterline plane WL in Figure 2 1 is defined as positive bottom to top and the buttline plane BL is defined as positive pointing to port In this coordinate system the center of the telescope s spherical bearing is located at X 43 942 mm 1730 inches Y 0 mm and Z 5 867 4 mm 231 inches SOFIA Aircraft and Telescope Coordinate Systems qua 2 3 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 2 2 Telescope Coordinate System Flight Direction W Telescope Line of Sight LOS Axis U Telescope Elevation Axis V Telescope Cross Elevation Axis out of page Location of Telescope coordinate system origin Figure 2 2 The SOFIA Telescope Coordinate System U V W coordinate system moves relative to the aircraft with the origin at the center of the spher ical bearing A second coordinate system the U V W coordinate system is defined for the telescope which moves relative to the aircraft The origin of this telescope coordinate system is at the center of the spherical bearing As shown in Figure 2 2 the U axis points along the Nasmyth tube into the cabin the W axis is normal to the Nasmyth tube and parallel to the primary mirror optical axis and the V axis follows the right hand rule or U cross V equals W Hence when the telescope is
179. n the aircraft floor and attachment points requires a reasonable dis tribution of the load over the floor area and a low center of gravity Second the localized effect of components of various weights in the rack will determine the mounting hardware required to han dle aircraft deceleration loading on the rack structure The total equipment load allowable on the standard two bay rack is 270 kg 600 Ibs If the total weight approaches this limit the equipment should be arranged m the rack so that the weight is distributed fairly evenly among the four rack sections as shown in Figure 2 32 However this distribution can vary provided that the total weight for any two sections does not exceed 7620 kg 300 Ibs 2 40 uA Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Figure 2 32 Equal Maximum Weight Load in 4 Rack Sections If possible the heaviest item should be located near the bottom of the rack to keep the total over turning moment of the rack as low as possible The sum of the torque moments produced by the installed equipment as defined in Figure 2 33 must not exceed 1000 ft lb Instrument Racks PI Rack x xim 2 41 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Typ chassis units I wh Tt wh etc for all chassis shelves ET T T w h w h x 1000 ft lb 4 4 pallet f Figure 2 33 Calcula
180. nalysis tools 4 14 uA Mission Ground Operations CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 a For ORR and the first generation instruments the instrument teams provide Quick Look anal ysis tools A long range goal is that DCS would take over Quick Look analysis tools at least for FSI instruments to provide a more uniform look and feel for in flight evaluation of data 4 4 6 Implementation of Minimum Science Capabilities Table 4 1 gives a brief summary of how the minimum science requirements are being imple mented identifies who is contracted to do the work and when the products are being delivered This assumes that all the interfaces between the core DCS the DCS archive science instruments MCS and other software packages are fully defined and adhered to by all parties DCS has devel oped a generic interface document ref 8 and is developing ICDs with the MCS and each FSI to ensure that this will happen PSI Instruments have fewer requirements they only need to adhere to the required keyword list Section 5 and provide a data manifest that defines the science and ancillary data to be archived The DCS and its interactions with the science instruments MCCS and scientific users are shown schematically in Figure 4 2 Table 4 1 Implementation of Minimum Science Capabilities Minimum Science Capability Software Products and Developer Ready By 1 Proposal preparation and APT m
181. nce Instrument ICDs SOFIA IHB 0 0 Table 2 2 Facility Supplied Rack Equipment Item Weight Height Depth 110V power distribution panel 3 17 kg 7 Ibs 127 mm 5 0 in 76 2 mm 3 0 in Utility drawer keyboard try 9 98 kg 22 Ibs 88 9 mm 3 5 in 469 9 mm 18 5 in Heavy chassis support tray 2 72 kg 6 Ibs 25 4 mm 1 0 in 614 68 mm 24 2 in Intercom multiplier box 2 72 kg 6 Ibs 44 45 mm 1 75 in 196 85 mm 7 75 in 19 inch B amp W TV monitor 19 05 kg 42 Ibs 279 4 mm 11 0 in 431 8 mm 17 0 in 9 inch B amp W TV monitor 8 4 98 kg 11 Ibs 226 6 mm 9 0 in 279 4 mm 11 0 in Set of 3 small TV monitors 16 32 kg 36 Ibs 304 8 mm 12 0 in 177 8 mm 7 0 in 8 channel strip chart 8 36 29 kg 80 Ibs 406 4 mm 16 0 in 254 mm 10 0 in Storage cabinet 3 18 kg 7 Ibs 266 7 mm 10 5 in 304 8 mm 12 0 in Usually mounted on top of the rack The depth values listed above do not include clearance needed by chassis for cabling The utility drawer and the support trays use mounting holes at both the front and back of the bay The 110V power distribution panel is described elsewhere The SOFIA Facility Manager should be con tacted for help with any unusual problems encountered in mounting equipment in the rack or if any components are not compatible Two effects must be considered in planning the installation of equipment into the deck First the overall effect of the rack load o
182. nce of data taking scans each offset from the previous scan and each keying off the broadcast housekeeping announcing the end of the previous scan Observing on SOFIA ex xim 4 33 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 Scanning the plus image of the IR Source End Position Pos2 Plus chopper images M t Minus 1 chopper Start Position images Pos1 Scanning the minus image of the IR Source End Position Plus chopper images chopper images Start Position Pos1 Figure 4 10 Scanning while Chopping 4 34 a Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 5 3 7 Various Mapping Options MCS through SCL and or GUIs will support both absolute and relative i e offset mapping using the telescope At ORR mapping using the Secondary Mirror will only be possible using analog signals from the SI see section 5 3 4 But in this latter case the MCS has no knowledge of the position on the sky of the SI boresight This must be followed by the SI COMMENT Link to section 5 3 4 Is this correct Absolute and offset mapping can be done while chopping and or nodding The observer can spec ify which chopped image and or nod position the SI boresight is in when mapping Both absolute map positions and map offsets may be pre defined Thus mapping sequences can be set up in advance Mapping can be carried out usi
183. ne nee nn inner nin in nnn irren 2 10 2 5 Science Instrument Envelope cccecceceeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeaneaneeseeseeeeeeseeeseeeseeneeseeeeeneees 2 22 2 6 Science instrument Cairt erret tenter rnt r RR ER ERR eS 2 29 2 7 Instrument Racks PI Rack rmi Hte nr Re ERR n SIRE ERR RR RR ERRARE ARARAS NEANS 2 34 2 8 Instrument Cabling Patch Panels eeeesseeeeeeeenee nennen nnne nnne niente 2 48 2 9 Science Instrument and TA Flange Pumping System eene 2 58 2 10 Secondary mirror Control inerte Eee rne bein eR En oen xn i ante oar pr Exe E enRDes 2 62 2 11 SOFIA Software Interface enne repetunt et eoa ta iners ap AKARANA ASERRANARAAAARA 2 67 2 12 SOFIA Science Instrument Commissioning eeeeeeeeeeeeeneen nnne nnne 2 68 2 1 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 1 Introduction This section of the SOFIA Handbook concerns the selection design fabrication or modification of experiment apparatus used on board the SOFIA 747SP on the ground or in flight The informa tion in this section addresses the following general categories Size and weight specifications for equipment mounted on the telescope and for apparatus mounted in instrument racks Equipment and facilities either required for use or that are available for use as part of the experiment installation or operation
184. ng but slightly under sized with respect to the f 1 2 light cone of the primary mirror Table 1 7 Examples of Focal Plane Positions Focal plane Focus Setting Position Image Scale f ratio Notes 2760 um 300 mm aft 4 6 mm 1 18 aft limit 1320 um 0 mm aft 4 4 mm 18 8 at SI flange 0 um 300 mm fwd 4 2 imm 19 5 nominal 1220 um 600 mm fwd 4 0 mm 20 5 1 26 A Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Table 1 7 Examples of Focal Plane Positions Focal plane Focus Setting Position Image Scale f ratio Notes 2340 um 900 mm fwd 3 9 mm f 21 fwd limit Reference position is at the Nasmyth SI mounting flange Some examples of focal plane positions and associated values are given in Table 1 7 More detailed tables of back focus location f ratio scale etc for both secondary mirrors are given in Appendix D 1 3 3 1 2 Variations in telescope focus A small shift of focus is known to occur between ground based warm telescope conditions and in flight cold telescope conditions This is normally corrected by adjusting the focus early in the flight while observing a star image in the focal plane video monitor The amount of adjustment has been typically a decrease of about TBD mm TB V in the focus As the telescope cools to the ambient temperature at 41 000 changes in the telescope s focus are expected Such variations d
185. ng a number of different coordinate systems notably the following Equatorial Reference Frame i e RA and Dec Ecliptic Reference Frame i e Lambda Beta Galactic Reference Frame i e 1 b Telescope Reference Frame w r t Aircraft Reference Frame i e EL XEL and LOS WFI Reference Frame FFI Reference Frame FPI Reference Frame SI Reference Frame Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 36 uA Observing on SOFIA SOFIA IHB 0 0 Infrared Astronomy CHAPTER 5 SOFIA SI Proposal and Review Process 5 1 5 2 5 3 5 4 5 5 USRA SOFIA Science Instrument Proposal Process eene 5 2 Evaluation Criteria In Approximate Order of Importance eesssssss 5 4 Guidelines for Participation in the Instrument Program eeeeeennnn 5 5 USRA Review Process During SI Development eene 5 17 Project Implementation Plan ceeeeeeeeeeeeeeeeeenen nennen nnne nnne nnn nennen nnn nennen 5 19 COMMENT Dates Names and Addresses need review in this chapter 5 1 CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 5 1 USRA SOFIA Science Instrument Proposal Process 5 1 1 Classes of Science Instruments Considered for Development In a Call For Proposals CFP for SOFIA four classes of science
186. nge assembly gate valve pressure plate using the same interface as the pressure coupler The refractive chromatical etc characteristics of the window material are likely to affect the focus and image quality of telescope system The optical window assembly needs to withstand any loads caused by motions of the gate valve pressure plate under changing pressures SOFIA will provide the optical window assembly 2 20 A Telescope Mounting flange CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Cavity Side O Ring to TA Mount IR Window Fixation Ring Figure 2 17 Example of an Optical Window Mounting Assembly The fixation ring should not press directly on the window An additional rubber gasket is required for a proper mounting Instrument developers should refer to the TA_SI_02 interface document for further discussion of vacuum fittings and access ports with the instrument mounting flange assembly All landing crash thermal convection radiative loads are also specified in this original design document 2 4 3 Environment about the Science Instrument Flange The electromagnetic field at the center of the instrument mounting flange will be measured during system assembly integration and test verification The recommended grounding practices for instruments are discussed in section 2 7 2 Counterweight Rack on page 2 45 The estimated power spectral density curves for in flight telescope vibrations are given belo
187. nt The second will have an IR black surface which operates at approximately 100 Celcius The third will use a small Cassegrain telescope and a quartz lamp to deliver both visible and IR radiation to the focal plane Its focal range will accommodate all back focal distances allowed for the SI 30 cm to 490 cm from the SI flange Both the latter two sources will use circular chopper wheels and subtend a solid angle equivalent to that of the oscillating secondary mirror of the TA They will be able to accept phase and fre quency from the SI electronics standard TTL or synchronize with an internal clock and provide a reference output The operational frequency range of the hot plate and PCLS choppers will be 5 10 and 5 30 Hz respectively Since access to the TA cavity during installation is highly restricted all SI alignments will be done on the simulator In order to transfer alignments from the simulator to the TA several boresight boxes BSB will be provided for use by the investigators A BSB will be mounted on the SI in front of the SI window before installation on the TA simulator This BSB will remain attached to the SI throughout its mission Hence at least two boresight boxes will be required at any time one will be on the TA with the current flight experiment while the other is being used on the sim ulator by the next SI The BSB will be mounted internal to aft of the SI flange and the SI will be mounted external to forward of the
188. ntative DAR eese ee eee seen tenet en atenta setas enses ena aoo 3 3 3 3 Compliance vs Conformity 4 eee eee eee esee eee ee eee ee eene stones etn setas etes tone se eo sesto setas Oe SEP aKos SESS 3 4 3 4 Operations Flight Standards District Office eee ee eee eee eee eee ee eese en tensa sensa tns essen stesso se tna 3 4 3 5 Science Instrument Certification General Process Overview eee ecce ee eee eee ee ee ene eese ea see tease ue 3 4 3 5 1 Conceptual Design Review CODR 4 eee e eere eren ee eren eerte se tna seen ose tn aseo ta seta etos s toss s tasa 3 5 3 5 2 SI Airworthiness Submittals and Control Process eee e ee ee ee ee eee ee eene ee ee ene sese ea aset eaae ue 3 5 3 6 Construction Inspection and Testing 1 eese ee esee eee scene eee ee eren nette sets tons setas setas etes s tones ense sten sera 3 6 3 7 Obtaining Final Certification Lecce esee e esee eee ee eee eene ense tns ieron ecse sesta sees sete sass setas seen aseo n 3 6 3 5 s Certification Procedures Mantial cscssisessiessnessencVesseucsssseccescsencbecdesdcvedececsesedeconensscencsceconessesenssaeacecssencens 3 6 EP Ee olini Ped 3 7 4 1 Yearly Scheduling of the SSMOC sisccesvcsecsctecessveedcccesecssatsescsnsdsscessdescncsodscecevosescectesveessecsevasececenstendsoss 4 2 4 2 Flight EET 1 RR 4 3 4 2 1
189. numbers In addi tion the IFD has additional channels available for separate communications with the flight crew or ground contact via the aircraft radios ids Other Observatory Sub Systems 1 38 Z iA CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 5 7 Video Distribution System Additional situational awareness and support for mission video archival is provided by the Video Distribution System VDS The VDS routes signals from a number of source display and recording devices Sources include the WFI FFI and FPI imagers cameras mounted in the TA cavity and crew compartments workstation console displays video tape players and connections available at the SI patch panel Users may choose to route the video information from multiple sources and to multiple destinations simultaneously Video may be displayed at any of the con soles recorded to tape or recorded via user hardware connected at the SI patch panel 1 6 SSMOC Ground Facilities for SI Teams The N 211 Hanger which houses the SOFIA Science and Mission Operations Center as well as the Airborne Observatory includes a number of laboratory and office space for use by PI and General investigators 1 6 1 Visiting SI Team Labs and Offices The NASA Ames aircraft hangar Bldg N211 has been refurbished to serve as the SOFIA ground facility housing the SOFIA aircraft and support facilities and staff The building is approximately 300 feet by 300 feet
190. o the aircraft patch panel and from the corresponding telescope patch panel The list should include the cable designation function control sensor power et cetera and con nector specification All power lines should be called out TA SI 02 Verification of the science instrument flange requires the instrument team to provide a drawing package for comparison with that of the observatory This should include the dowel pins and bolt patterns of the as built instrument flange and the anticipated science instrument mass and center of gravity Sign off of a science instrument flange drawing for conformance with the telescope flange by the USRA engineering staff is needed for successful completion of the pre ship review All areas of the telescope interface are completely verified only during science instrument installation on the telescope All instrument weights and c g s are verified following installation on the telescope All applicable documents should be updated for as built consistency for a com pletion of the science instrument post flight review TA SI 04 Each instrument needs to provide a diagrammatic schematic of connections to the telescope tilt mirror controller TMC The schematic should also include a list of the cables and connector specifications to be provided by the SI team in controlling the TMC Note that the TMC interface requires power for SI provided pull up resistors for the optically isolated open collector TTL outputs pro
191. ocus range arc sec pixel Star Image Size 7 13 75 FPI seeing limited 80 CED FFI WFI optics limited Sensitivity 15 13 11 TN EWD 007 TN EWD 008 S N 10 in 1 s Centroid Precision 0 05 1 8 TN EWD 007 TN EWD 008 S N 10 Filters Available 3 ND s 3 ND s 3 ND s red Schott RG1000 red day red day red day A gt 900 nm clear clear clear blankoff blankoff blankoff The table reflects some of the basic optical and performance parameters for each of the three imagers Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 3 1 5 Science Instrument Interface Figure 1 10 shows where the Science Instrument SI will be mounted to the telescope on the cabin side of the pressure bulkhead This is called the SI Mounting Flange and it has a diameter of 1041 4 mm 41 inches The IR beam lies along the axis of this flange Surrounding the SI Mounting Flange is the Counterweight Plate Assembly or Balance Sub Assembly BSA Some SI equipment can be mounted to this Sub Assembly using a Counter weight Rack CWR Part of an empty CWR is visible in Figure 1 10 at the very top of the BSA SOFIA allows various instrument mounting configurations Every instrument configuration must have a demonstrated pressure boundary seal since when the Nasmyth tube gate valve is open required to observe the SI configuration is part of the pressure b
192. odification NASA Ames Code SSA Early 04 proposal handling Observing time estimators for FSIs ARC SS Early 03 Handling amp processing DCS Core amp Archive Early 04 2 Flight planning and scheduling Flight management software USRA ISD and NASA ORR Code IC 3 In flight quick look QLA tools instrument teams Instrument commission ing 4 Data pipelining Pipeline algorithms FSI teams Instrument delivery Pipeline automation Core DCS 5 Data archiving Data archive amp browsers DCS archive Observatory testing An implementation scheduled for deferred items will be developed at a later stage Available staff ing and budgets are not defined well enough at this time to develop realistic schedules Mission Ground Operations CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 In flight Data Ingestion Community Acquisition and Processing Access aovjrju SINSIC XPULIOyUy Archive Front End Web Interface SOFIA and IPAC IRSA interfaces Figure 4 2 DCS Components and Interfaces 4 4 7 Interfaces between Science Instruments MCS and the DCS All instruments connect directly to MCS using TCP IP communication protocol through the MCS patch panel It is therefore always possible to set up and execute an observation directly from the instrument console PSI SSI instruments usually operate in this mode which means that an observer General Investi
193. oint whiffletree lateral supports and interfaces to the rest of the TA metering structure The highly lightweighted 85 Primary Mir ror was figured to compensate for distortion at observing elevation angles An outer annulus 10 cm wide has slightly degraded optical figure the undersized secondary see below excludes this annulus from contributing to focal plane images 1 3 1 2 Telescope Secondary Mirror Assembly SMA Two hyperboloid secondary mirrors are available for use providing a back focus range of 120 cm The DLR secondary mirror is diamond turned Silicon carbide with TBD Angstroms of aluminum with no protective overcoat USRA provides a second aluminum secondary mirror with TBD 1 14 TT Telescope Design and Performance A dAl a CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Angstroms of aluminum with no protective overcoat Table 1 2 gives the optical parameters for both the Secondary Mirrors The secondary mirror is lightweighted Silicon Carbide The secondary mirror is undersized to insure that chopping does not cause the entrance pupil to be displaced beyond the edge of the pri mary mirror In addition a central button 80 mm diameter can be installed over the vertex of the secondary to insure that the focal plane sees only cold sky reflected in the central part of the secondary Chapter 2 SOFIA Science Instrument ICDs on page 2 1 Tilt Chopping Mecha nism TCM the secondary mirror is attach
194. on Controls Subsystem NPT National Pipe Taper American Standard Pipe Thread NT Nasmyth Tube ORR Operational Readiness Review OSS Observatory Support Subsystem PCLS Portable Chopped Light Source PDS Power Distribution System PI Principal Investigator PI Rack Principle Investigator Instrument Rack PIF Pre Flight Integration Facility PMA Telescope Primary Mirror Assembly PSI Principal Investigator class Science Instrument PWS Pressure Window Subassembly RD Reference Document RD Seal System Rigid Door Seal System RIS Rotation Isolation System ROF Rotation of the Field SCL SOFIA Command Language SFH Successful Flight Hours SI Science Instrument APPENDIX A Acronyms and Terminology SOFIA IHB 0 0 Table A 1 Acronyms and Terminology Acronym Term Description SMA Telescope Secondary Mirror Assembly SMCU Secondary Mirror Control Unit SOFIA Stratospheric Observatory For Infrared Astronomy SSI Special Purpose Principal Investigator class Science Instrument SUA Suspension Sub Assembly TA Telescope Assembly TAAS TAC Time Allocation Committee TAMCP TA Master Computer Processor TASCU TA Servo Control Unit TBC To Be Confirmed TBD To Be Determined TBV To Be Verified TCM Tip tilt Chopping Mechanism TCMU Tilt Controller Mechanism Unit TMA Telescope Tertiary Mirror Assembly U V W Coordinates of the TA Coordinate System UAL United Airlines UPS Unin
195. on Design Conical Reflecting seen 2 10 Figure 2 8 3 D View of the Science Instrument Flange eese nennen 2 11 Figure 2 9 Mechanical Telescope Assembly System Configuration With A Mounted Science Instrument 2 12 Figure 2 10 The Orientation Marker Inscribed On The Circumference Of Instrument Mounting Flange 2 13 Figure 2 11 Schematic Sketch of the SOFIA Flange Assembly eese 2 14 Figure 2 12 A Cross Section Of The Instrument Flange And Pressure Window Assembly Without The Counterweight Subassembly dh a ea RD He REESE URP RI P ER o a Pg aite MAE Had 2 15 Figure 2 13 Front View of the Instrument mounting Flange eese eene ene 2 16 Figure 2 14 The Maximum Moments Caused by Cg Variations In the V Direction eese 2 17 Figure 2 15 The Maximum Moments Caused by Cg Variations In the W Direction eee 2 17 Figure 2 16 Pressure Boundary Configurations for Science Instruments sese 2 19 Figure 2 17 Example of an Optical Window Mounting Assembly sesssesseseeeeeeeneneenen eene 2 21 Figure 2 18 Science Instrument Accelerations in the U V and W Directions eene 2 22 Figure 2 19 Science Instrument Installation Volume 3 D Solid Modeling Drawing sss 2 23 Figure 2 20 Science Instrument Static Serving Envelope Isometric View
196. onstructed passageways such as the 1L pas senger door and along the SI cart path As mentioned previously the science instrument cart needs to fit within the installation envelope specified by Global 09 Depending upon the cart length the successful design may require swiveling casters at all wheel locations b The loaded cart shall be able to negotiate 1 20 ramps with all wheels maintaining contact with the floor Maintaining contact with the floor at all times may require a suspension system Any system employed however must be designed to distribute the cart weight so that the load per wheel does not exceed the maximum allowable load per wheel c The loaded cart shall not damage the aircraft floor structure by its usage Aircraft floor panels limit the loads that can be safely transported aboard the SOFIA aircraft Panels along the science instrument installation path have been upgraded to withstand science instrument installation traf fic Details of the maximum wheel load and the dimensions of the allowable center of gravity zones for various science instrument installation weights are contained within SIC AC 01 d The loaded cart shall not apply any loads on the reveal lip surrounding door IL The USRA team is expected to provide access ramps that protect the reveal lip of the aircraft when correctly installed Science Instrument Cart Qua 2 29 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Door 1L SI Ca
197. opping Chop higher set point Chop angie gt p Rotation about R Chop lower set point Rotation about S v 3 point Chopping gt Rotation about R Chop lower set point Chop middie set point Rotation about S v SMA Anglez3 74 Sky Angle Figure 4 6 Two and Three Point Chopping on the Sky 4 28 7 Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 Before Two Point Chop Initiated due SIRF BS After Two Point Chop Initiated munus SIRF BS Figure 4 7 View from Focal Plane When Two Point Chopping Observing on SOFIA iis 4 29 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 After Two Point Chop Initiated SIRF BS minus SIRF BS plus 2n SIRF BS After moving SI Boresight to plus image of IR Source SIRF BS minus re SIRF BSNS A SIRF BS Figure 4 8 Two Point Chopping when Track Star in FFI 4 30 Pen Observing on SOFIA SEFIA rsccfparconsenn tef rearea Astronomy CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 5 3 5 Nod Chop Mode In this mode the chopper 1 e the TCM is under a control loop tip tilt oscillation and the observer wishes to move the SI boresight from one image of an IR source to the next in a pre scribed sequence taking data while the SI boresight is on each image This is a combination of the nod mode and chop mode where th
198. or these awards through a future CFP For PSI s and SST s 30 hours of engineering time on SOFIA will be provided to bring the 7 USRA SOFIA Science Instrument Proposal Process x ee 5 3 CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 instrument on line This time will also be considered as a reward for building the instrument Additional science time can be requested once the instrument is operational through future CFP s Proposals for the development of FSI s may also include an option for a PSI in the event that the instrument is not selected as an FSI In the proposal review process all proposals will be consid ered and discussed at once At that point a decision will be made to select one to three FST s Unsuccessful FSI proposals that have included the PSI option will then be considered for selec tion with the remaining PSI proposals Such proposals must include a clear statement of how the PSI would differ from the PSI and must also include a detailed budget for the PSI option Finally because funds are very limited for this CFP USRA would like to strongly encourage cost and science effectiveness in the proposed instruments Examples would be 1 Real cost sharing with the proposers institution 2 Building extensively on past space and ground based experience and equipment 3 Building extensively on past KAO experience and equipment 5 2 Evaluation Criteria In Approximate Order of Importanc
199. ore the usual small aircraft heading errors do not cause vignetting or loss of pointing stability The telescope can be operated as low as 15 and as high as 70 in elevation angle however vignetting will occur at these angles since the cavity door can only cover the elevation range of 20 to 60 Rigid External Door Shear Layer Control Flex Skirt Figure 1 6 Exposed Telescope The external appearance of the exposed SOFIA telescope showing the upper rigid door the lower flexible door and the passive flow control fairing The telescope and upper rigid door are at an elevation of 20 The apertures of the Wide Field Imager and the Fine Field Imager not shown are in the upper left and lower left forward corner of the telescope head ring 1 10 eA Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 3 1 Telescope Design A diagram of the telescope assembly at 90 in elevation is shown in Figure 1 7 The carbon fiber reinforced plastic telescope frame is designed to be light weight with minimum flexure and low thermal expansion Two guide cameras for acquisition and tracking are installed in the telescope s forward portion of the head ring The cavity side telescope frame or metering structure is attached to the aft side of a steel hydrostatic bearing 48 inches in diameter This hydrostatic bear ing is the single suspension point for the entire telescope instrument assembly T
200. ort Subsystem OSS OSS 30 Observing Command and Housekeeping Interfaces 18 Observing Modes Supported at ORR 20 Observing on an Airborne Platform 18 Observing on SOFIA 18 Operational 71 Operational ICD Verification 71 Operations Flight Standards District Office 4 Optical Alignment Focus and Boresighting 9 Optical Parameters Primary Mirror 14 Secondary Mirror 15 Tertiary Mirror 16 optical window assembly 20 optical window element 20 ORR observing modes 20 SOFIA IHB 0 0 Index Other Observatory Sub Systems 32 P parallactic angle 24 Participation in the Instrument Program Guidelines 5 patch panels Instrument Cabling 48 MCCS 50 Science instrument 54 payload Science Instrument cart 29 PI Rack 34 PIF 42 Pipeline Products 48 PMA 13 Policies And Procedures additional 9 Portal Icons 1 Pre Flight Integration Facility PIF 42 Pre Shipment Logistics 6 pressure boundary instrument flange 18 Primary Mirror optical parameters 14 Principal Investigator class Science Instrument PSI 2 Process 2 Project Implementation Plan 19 Proposal Form Budget Summary 11 Proposal Title Page 10 Proposal Forms 10 Proposal Forms and Certifications additional 13 Proposals format and content 5 PSI 2 pumping stations cryogens 37 Q Queuer 16 VI SOFIA IHB 0 0 R Radiometer calibration 36 principles of operations 35 Radiometer Design 35 Range of Focus 26 Retri
201. ory Working Environment CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 adds noticeably to the cabin noise level which has been measured to be in excess of TBD deci bels This noise level in the cabin may interfere with conversations and may have adverse effects on experiment apparatus Headsets for the mission audio distribution system MADS provided to all flight personnel substantially reduce the apparent noise level and provide adequate ear pro tection However SOFIA science instrument designers should consider the effect of the high acoustic noise level on beam splitters detectors or other sensitive hardware Cabin temperature is maintained at about 20 C TBV during flight Cabin temperatures on the ground may be at least 5 C above the outside ambient especially if on board equipment is being operated and ground air conditioning is not provided Relative humidity in the cabin at observing altitudes is generally less than 10 Focal plane instruments are mounted onto the forward end of the telescope assembly that extends into the pressurized cabin In this arrangement the instrument also serves as the barrier between the pressurized cabin and the un pressurized telescope cavity The pressure differential between the cabin and the telescope cavity is automatically maintained at 8 2 psi TBV or less 1 2 3 Observatory Cabin Accommodations Seating for three members of the P I team is located about 20 feet TBV for
202. ory and chief scientist convene reviews The obser vatory science support integrated product team supports the review efforts The observatory direc tor formulates a review board and appoints a chairman to lead the review The board is instructed to provide constructive comments and avoid extensive problem solving discussions Recommen dations of the board members are captured using request for action forms RFAs provided by the observatory The review board is responsible for making judgments and recommendations concerning the review content The board chairman is responsible for supervising the review mediating discus sions meeting the review objectives and maximizing the value added contribution of the review board Following the review the board meets to discuss findings review and assign RFAs and prepare a draft report The chairman prepares a final report of concerns and recommendations The board rejects or adopts either in part or in full all submitted RFAs from the review The principal investigator for the facility science instrument is responsible for a detailed meeting agenda presenting the material tending to review logistics and assembling a hard copy package of the material to be presented at the review Major concerns of the board following the review are made available to both the PI and the chief scientist observatory director The review board chair USRA Review Process During SI Development CHAPTER 5 SOFIA S
203. osals to the SOFIA Science Instrument Program 5 3 2 Period of Performance All proposals will be considered for a period of performance necessary to design and develop the proposed instrument and to operate the instrument for the first two years of SOFIA science oper ations See Appendix E for schedule 5 3 3 Proposal Format and Content 5 3 3 1 Proposal Content The proposal should contain at least the following material assembled in the order given 1 Cover Letter One copy of the proposal shall be designated as the official copy and should be prefaced by a cover letter signed by an official of the investigator s organization who is authorized Guidelines for Participation in the Instrument Program 5 5 CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 to commit the organization to the proposal and its content The cover letter should refer to the pro posal for SOFIA Science Instrument Development and reference USRA ID CFP97 001 2 Title page The title page must contain a Identification of the CFP by number and title to which title proposer is responding b A brief scientifically valid project title intelligible to a scientifically literate reader and suitable for use in the public press c The legal name and address of the organization and specific division or campus identification if part of a larger organization d Names and telephone numbers of the principal investigator and
204. ot ready at 30 days prior to the mission and is considered not likely to be ready for the mission the back up plan for the mission may be activated This may mean moving a facility class science instrument s mission forward The coordination of the flight planning for a given mission 1 e the flight plans given to the Oper ations Control Center for scheduling purposes will be the responsibility of the PI of the science instrument for the mission flying PSI s and SST s but will be the responsibility of the SSMOC sci ence coordinator for a FSI mission The first two years of operations will consist of a total of 1 200 SFH Successful Flight Hours at or above 41 000 ft in altitude In a normal year after the second year of SOFIA operations there will be a minimum of 960 SFH per year required which translates to 137 successful science flights per year with each flight consisting of about 7 hours at altitude If a total Science Effec tiveness of 0 78 is used see the Overview for this section then to achieve 137 successful science flights about 4 flights per week must be planned and assigned to a science team over a 44 week period the period remaining in a year after taking into account maintenance weekends and other down times for the observatory Hence the peer review committee will assign a total of 176 flights to the science community each year which will assure with 80 confidence 137 success ful science flights per year Typical
205. ounted to the telescope in an area allowing for three SI equipment racks or two such racks and a PI Console 2 A PI console next to the Telescope Operator s console 3 Two workstations facing outboard on the starboard side of the cabin 4 A general working area with a table and four chairs The four areas seat a total of 10 people Note The four seats at the table cannot be used for take off and landing However there is seating available up front in the EPO visitor area for take off and landings Each PI console is as shown in Figure 1 3 and contains two workstation screens Such consoles can display any of the Mission Control GUIs as well as run any SI Team programs GUIs SI team members have control the Observatory through these PI Consoles or directly through their own SI computers in work area 1 This control will be limited to observing type controls 1 4 uA General Description of Observatory Working Environment CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 The science work area 3 is for quick look analysis of data This area will not be present at ORR Operational Readiness Review Annunciator Panel TA Tracker Console Only or NAV Computer CDU MD Console Only Flexible Arm Spotlight Master Power Control SHE ae T Wa 1 TX Space Reserved for MD Console Only e 0 NI M dii S RC Ventilation Control i ND Console Only Video Distribution Control Panel i 1 Audio Distribution 20 1
206. ove on the sky with a right hand rota tion about the U axis of the telescope see Figure 1 11 Rotation Angle R Figure 1 12 The Sense of the Rotation Angle Expected values of the Rotation Angle are listed on the final flight plan Depending on aircraft heading and object elevation angle the rotation angle may not change at all or may change at rates as high as 70 per hour In flight the local vertical of the telescope body may not pass through the zenith due to LOS motions and aircraft attitude fluctuations The current Rotation Angle corrected for LOS angle aircraft pitch and heading error is provided in MCS house keep ing 1 3 2 7 Line of Sight and Azimuth Resets The telescope Line of Sight LOS position may be controlled in several ways The default is the freeze mode in which the telescope is inertially stabilized about the LOS axis resulting in a constant rotation angle for a limited time interval When the telescope approaches a limit of LOS motion 3 from center it must be slewed back to the other limit before the freeze mode can be resumed This LOS rewind takes about ten seconds and the time interval between rewinds may be anywhere from about 10 minutes to over an hour depending upon heading and elevation The science team can specify how far from the LOS limit they should receive a warning of approach ing need for a reset In this way the rewinds can be coordinated with natural pauses in observ
207. pen will be between 35 000 and 45 000 ft and at or below the maximum operating airspeed of Mach no 0 87 TB V The structure will be substantiated to allow continued safe flight with restricted operational limitations in the event the door does not close after use above 35 000 ft such that the airplane can be landed safely 1 5 1 2 Cavity Door Control This Cavity Door Drive System CDDS controls the operation of the URD and aperture LFD assemblies and the URD seal When the URD is in the closed position the CDCS inflates the seal Prior to opening the URD the CDCS sends commands to deflate the seal The URD drive oper ates independently of the aperture assembly drive The MCS provides command inputs to the CDCS to indicate desired position for the aperture assembly to track the telescope In the event the 1 32 TT Other Observatory Sub Systems A dAl a CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 upper rigid door assembly or aperture assembly binds or the AA LFD exceeds velocity limits the control system will remove power from the cavity door system drive motors and apply the brakes 1 5 1 3 Cavity Door Data The MCS determines the desired position for the Aperture Assembly needed to prevent eclipsing the telescope field of view The MCS transmits the desired aperture position setpoint to the CDDS The CDDS compares the new setpoint with the actual aperture position and moves the aperture accordingly The CDDS
208. points on the gate valve pressure plate located on a diameter centered on the IR beam optical axis It is expected that the hard points will be covered by pieces of thermal insulation during normal operations The hard points provide locations for supporting instrumentation within the Nasymth tube and forward of the telescope gate value This might include an extended pressure coupler or a partial science instrument flange Telescope Mounting flange x m 2 15 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Mx THROUGH HOLE 813 5 e BOLTS ASSICCD Pb DICA WEF MAS VE BOLTS AND MUT PLATES ASSIGNED 4 HARDPOINTS AT EACH THREADES MOTI ire aye wor Der ar IMULATION 13 u3cO INSULATION DIAMETER ai IN Tu T INNER and on O RING INNER MAETR c di GAD IK RAA LINIEK wena MAM 7 MAIMIENTI L R FOR JACK SCREVS EQUALLY SPACED 8 x NASMYTH TURE CENTER vama qus LOwCL Fina dS 02 LUUALLY SPACED AT WW CIU REFER TO C C Figure 2 13 Front View of the Instrument mounting Flange A front view of the instrument mounting flange showing the location of the dowel pins the IMF bolt circle the four tub hard points and the pressure coupler window bolt circle This figure illustrates the telescope at an elevation of 90 where the nominal installation elevation is 40 2 4 2 Mass and Center of Gravity of Science Instruments Because of the numerous possible configurations of sc
209. port the science instrument The bolts located on a 41 inch bolt circle centered on the infrared beam are equally spaced in angle The bolt holes in both the IMF and SI flange must be through holes The nuts are optionally secured with the appropriate nut plates There are two 20 bolt hole pat terns offset from each other one has nut plates while the other does not USRA will provide and install all the bolts nuts and nut plates required to mount science instruments to the IMF Differential Pressure Sensor Bypass Valve PWS Gate Valve Temperature Sensor Hardpoint I F Exhaust Tube amp Vacuum Lines I F BS Mounting I F SI Mounting I F IMF Figure 2 8 3 D View of the Science Instrument Flange A 3 D View of the instrument mounting flange with noted points of interest Science instrument bolt directly on the flange using 20 USRA provided fasteners Two dowel pins provide accurate and repeat able alignment of science instruments with respect to the optical axes of the SOFIA telescope The maximum allowable instrument weight is 600 kg 1320 Ibs The maximum allowable moment about the air bearing for an instrument is TBD ft lb Therefore the center of gravity of a maximum weight package must be no more than TBD inches forward of the hydrostatic bearing or TBD inches forward of the IMF mating surface Longer moment arms are acceptable if the weight of the package is proportionately less Instrument teams should note that a fence re
210. priate personnel action against such an employee up to and including termination or 2 Requiring such employee to participate satisfactorily in a drug abuse assistance or rehabilitation program approved for such purposes by a federal State or Local health Law enforcement or other appropriate agency g Making a good faith effort to continue to maintain a drug free workplace through implementa tion of paragraphs a b c d e and f B The grantee shall insert in the space provided below the site s for the performance or work done in connection with tile specific grant Place of Performance Street address city county state zip code Check if there are workplaces on file that are not identified here Il GRANTEES WHO ARE INDIVIDUALS The grantee certifies that as a condition of the grant he or she will not engage in the unlawful manufacture distribution dispensing possession or use of a controlled substance in conducting any activity with the grant Guidelines for Participation in the Instrument Program n 5 15 CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 Organization Name CFP or AD Number and Title Printed Name and Title of Authorized Representative Signature Date Printed Principal Investigator Name Proposal Title 5 3 8 3 Certification Regarding Lobbying As required by S 1352 Title 31 of the U S Code for persons entering into a grant or cooperative
211. quence often called beam switching Figure 4 5 shows a two nod beam A and B sequence The top figure shows the telescope pointed at nod beam A then the telescope moves to nod beam B in the bottom figure This sequence can be repeated any num ber of times and can be extended to more beam positions When the telescope moves to the next nod beam in a sequence the telescope will automatically start tracking as pre prescribed for that nod position It is possible to also map while in nod mode SCL commands allow an observer to map using pre defined offsets in just one nod beam or simultaneously in any number of specified nod beams 4 24 uA Observing on SOFIA CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 SIRF BS T SIRF BS Figure 4 5 Nod Beam Sequence of Two Observing on SOFIA 4 25 iObsenatenyf rrara Astronomy CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 5 3 4 Chop Mode In this mode the chopper 1 e the TCM is under a control loop tip tilt oscillation There are 5 basic modes for the chopper 1 Internal Two Point Chop This mode is driven by a TTL signal internal to the Secondary Mir ror Control Unit SMCU A two point chop has plus and minus endpoints The SI data com puter synchronizes to the chop by receiving through the SI AMA Junction Box the same TTL signal that is driving the chop see the ICD TA SI 04 Chop parameters that
212. r 2 SOFIA Science Instrument ICDs on page 2 1 about the TA SI 04 ICD The MCS is also the collector and broadcaster of all Observatory housekeeping data An SI com puter can subscribe using SCL to receive a selection of this available housekeeping data to place in the headers of SI data files All housekeeping as SI data is time stamped using the IRIGB connection to the MCS Details of SOFIA observing modes and how to use SCL and an SI Data XML File to implement these modes can be found in the SCL User Manual Details on SCL protocols and XML file for mats can be found in MCCS SI 04 mentioned in Chapter 2 of this handbook In this section we only outline the observing set ups and modes that will be supported through SCL at ORR 4 5 2 Observing on an Airborne Platform The MCS at the beginning of a flight uses many aircraft and telescope attitude and position data inputs to estimate the relationship transformation between the gyro read outs and sky coordi nates This transformation is perfected after the first pointing of the telescope in flight on a known source This perfected estimation of the gyro to sky transformation allows for blind pointing to an accuracy of approximately 2 arcmins on the sky the exact level depending on the time since the last sky update and the degree of the slew from the last sky update Pointing accuracy is improved to about the 0 5 arcsecs level with the use of a track star of known sky position
213. r ey T Visible Radiation R Reflection T Transmission Visible Mirror Tertiary Focal Plane Imager Figure 2 3 Architectural Design Description Of The SOFIA Telescope Classical Cassegrain optical design with a Nasmyth focus featuring a concave primary mirror and a convex secondary mirror The Nasmyth focus results from folding the optical beam via a flat tertiary mirror onto an actuation axis of the TA SOFIA Telescope Optical Prescription 2 5 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 The optical design of the SOFIA telescope is described in SOF SPE KT 1000 0 03 The main mechanical distances are shown in Figure 2 4 Nasmyth Tube Entrance BI Flange Figure 2 4 Optical System Configuration of the SOFIA Telescope Assembly Nominal mechanical distances in millimeters between optical components of the SOFIA tele scope assembly The first order optical data for the TA is given in Table 2 1 Since the telescope is refocused with its axial actuated secondary mirror all first order data like the effective telescope focal length and the entrance pupil size are functions of the back focal distance which depends on the science instrument design Axial movement of the secondary mirror for refocusing introduces optical aberrations Only at nominal focus does the telescope provide a perfect Cassegrain image free of axial geometric aberrations As the telescope is refocused at different back focal distances
214. rack need to note when they desire this rack for installation of their equipment A suitable rack will be shipped to the instrument team s home institution when it is needed A schematic and table is required that lists the equipment equipment dimensions the equipment weight and the equipment locations within the rack when assembled for installation aboard the aircraft Note that mount ing diagrams should include the location of the audio distribution patch panel that is provided for science instrument team use by the observatory Any needed power patch panels supplied by the observatory should also be included This material is needed for review prior to the pre ship review All rack weights are verified prior to the pre install instrument review MCCS SI 02 Instrument teams need to provide a table of the cables and connectors used for this interface that includes power networking audio video and GPS signals The table should include function and connector specification A separate table should show the division of power between the frequency converters and the uninterruptible power supply UPS sources The instrument team should indicate how grounding is accomplished using the ground point provided A review of this material is required prior to the pre ship review Any changes are noted prior to the post flight review MCCS SI 03 Instrument teams need to provide a table of the cables and connectors used to connect to this patch panel locat
215. rantee s workplace and specifying the actions that will be taken against employees for violation of such prohibition b Establishing a drug free awareness program to inform employees about 1 The dangers of drug abuse in the workplace 2 The grantees policy of maintaining a drug free workplace 3 Any available drug counseling rehabilitation and employee assistance programs and 4 The penalties that may be imposed upon employees for drug abuse violations occurring in the workplace c Making it a requirement that each employee to be engaged in the performance of the grant be 5 14 uA Guidelines for Participation in the Instrument Program ra CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 given a copy of the statement required by paragraph a d Notifying the employee in the statement required by paragraph a that as a condition of employment under the grant the employee will 1 Abide by the terms of the statement and 2 Notify the employer of any criminal drug statute conviction for a violation occurring in the workplace no later than five days after such conviction e Notifying the agency within ten days after receiving notice under subparagraph d 2 from an employee or otherwise receiving actual notice of such conviction f Taking one of the following actions within 30 days of receiving notice under subparagraph d 2 with respect to any employee who is so convicted 1 Taking appro
216. ration at altitude 1 5 3 3 Principles of Operations The basic technique compares radiometric measurements of the center and wings of the 183 3 GHz rotational line of water vapor to atmospheric models to infer the WV overburden Measure the total water vapor burden along a line of sight between the WVM and the top of the earth s atmosphere Since in practice the aircraft will not be flying perfectly level all the time the WVM measure ments must be corrected for the true aircraft roll and pitch angles during the measurements The Other Observatory Sub Systems x xim 1 35 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 aircraft roll and pitch angles is provided to the WVM by the aircraft flight system autopilot which can measure these parameters to better than 0 1 The Radiometer Head contains an antenna that views the sky two calibrated reference targets one heated and one ambient temperature microwave blackbody an RF switch a mixer a local oscillator an IF amplifier and an inclinometer All of these components are mounted together on a baseplate and are attached to the inner surface of the aircraft fuselage so that the antenna can observe the sky through a microwave transparent window The antenna itself employs a quasi optical design with a microwave lens that feeds a feed horn The beam pattern is Gaussian with a full width half maximum diameter of 0 87 A sub harmonic mixer mounted directly behind the feed
217. rcraft are the same in every particular as the design that is defined by the engineering data 3 4 Operations Flight Standards District Office Once your instrument has received its STC and during SOFIA operations the FAA office that will be responsible for the training of personnel continued Airworthiness etc is the Flight Standards District Office FSDO This office is charged with oversight of the maintenance of the aircraft and subsystems including SIs on board the aircraft More information will be forthcoming on the topic of operations and continued Airworthiness 3 5 Science Instrument Certification General Process Overview Certification of a science instrument will involve a conceptual design review and submission of instrument design data The submittal data will include instrument engineering build to draw ings structural analysis that verifies the instrument design meets all aircraft load conditions elec trical load analysis safety procedures and system safety assessment for the complete instrument Drawing standards and examples are available as are samples of approved data The Science Instrument Airworthiness Manual contains detailed information about the required submittals The following list is intended as a very brief overview of the airworthiness requirements process data deliverables and responsibilities Further details can be found in the complete SOFIA SI Air worthiness Manual 3 4 uA Compliance vs
218. rity of opera tor supervisory control and monitoring of the observatory especially the TA The MCS will pro vide the majority of intersystem communications and facility control and monitoring via a LAN The MCS will also provide other ancillary functions including storage and retrieval of data print ing and plotting functions computations and intersystem data file transfers The MCS equipment includes servers mission support computers and operator consoles The MCS will provide a suite of computer workstations and servers The design concept will use a UNIX workstation at each MCS console with each connected to three UNIX servers by the LAN The standard features of the UNIX operating system allow peripherals such as disk and tape drives printers and modems to be accessible from any workstation on the LAN and allow a system administrator to assign privileges to those resources The servers and workstations will execute software applications and provide access to high capacity disk and tape storage drives Any observatory workstation will be able to print to any of the printers located in easily accessible areas of the cabin This approach allows for reconfigurable workstations and provides reliability through redundancy Housekeeping functions will prevent data loss and ensure timely return of the most current infor mation for all requests for facility data Time tagging and synchronization is required on the observatory and an IRIG B timing
219. rlines in January 1997 The aircraft was later flown to the L 3 facility in Waco Texas for modifications required SOFIA development pro gram Overall aircraft modifications included major revisions to the aricraft s aft structure modi fications of the aircraft interior for scientists and educators creating a cavity in the aircraft fuselage to house the German telescope and installing all the required observatory support sys tems As indicated previously the final layout of personnel accommodations includes worksta tions for a mission director telescope operator and computer specialist as well as work areas designated for scientists and educators The 747 SP aircraft structure provides the initial funda mental coordinate system for SOFIA development program 22 uA Introduction CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 2 1 Aircraft Coordinate System Z Y WL Plane BL Plane Figure 2 1 SOFIA Aircraft Coordinate System The aircraft coordinate system follows the Boeing convention with positive X pointing towards the rear of the aircraft positive Y pointing out the right hand side waterline plane and positive Z pointing up buttline plane as defined by the right hand rule or X cross Y equals Z The yaw pitch and roll angles correspond to rotations about the X Y and Z axes respectively The water line WL and buttline planes BS are illustrated in the figure above The origi
220. rt Path Figure 2 25 Science Instrument Cart Path The hatched areas correspond to reinforced floor panels required to support the maximum allowed weight of SOFIA science instruments A large section forward to the telescope flange is reinforced to allowing staging of multiple science instruments Instrument teams are cautioned that exceeding the instrument cart wheel design load capacity or operating the cart outside of the intended cart path will result in floor panel damage and cause cart instability leading to personnel injury or damage to science instruments All science instrument carts must be loaded in a manner that will ensure that no wheel carries more than the weight spec ified by the existing interface control documents In addition science instrument carts shall have wheels with the following safety features a Wheels shall have the ability to be locked in a manner that prevents any unwanted translation Casters shall be locked and restrained with retainers when the cart is not being moved b Swiveling casters shall have the ability to lock into fixed angular positions a beneficial feature when moving through narrow passageways Due to the heavy nature of some science instruments instrument teams should take great care when maneuvering a loaded science instrument cart The following precautions should be fol lowed at all times when transporting instruments throughout the SSMOC and SOFIA aircrafts a There shall be suf
221. ry then they are required to provide the appropriate design drawing for conformance 2 70 uA SOFIA Science Instrument Commissioning fa CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 with the observatory ICD This interface should closely resemble that of the approved modified KAO PI rack MCCS SI 01 ICD conformance is required for the pre ship review SIC SI 01 Jf the instrument team intends to use the observatory provide science instrument cart documentation is required to demonstrate how the instrument will mount on the cart provided The instrument teams should also indicate when this cart is required prior to the pre install instrument review The needs of the instrument team should be stated prior to the pre ship review SIC AS 0I Instrument teams employing their own carts for installation aboard SOFIA need to demonstrate adherence to the floor loading requirements of the observatory and compliance with the observatory s installation envelope restrictions ICD conformance is required before the pre ship review SIC SSMO OI Successful compliance with SIC AS 01 and the Global 09 should satisfy this ICD Vacuum Pumps Instrument teams should diagram their required pumping configurations for pre flight flight and post flight operations Monitoring of pressure sensors are the responsibil ity of the instrument teams and not those of the observatory housekeeping system This is required prior to the pre install revi
222. s Corner Chord Typ 4 Places Side Web Typ 3 Places E 4 40 111 76 Support Pallet Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 An optional utility drawer keyboard tray is installed in the left bay and a heavy chassis support tray is installed in the right bay Cable chafing guards are installed in some of the lightening holes e g bottom center Equipment may be also mounted on the top surface provided the weight and moment constraints are satisfied Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 4 0 101 60 40 62 1031 75 35 8 909 32 10 32 nutplates 35 0 889 0 7 equal spaces e 42 5 1079 50 Lifting Handle 444 50 17 5 normal 17 6 available 447 04 42 5 1079 50 Hole Pattern Spacing 35 0 889 00 18 25 463 55 from bottom 0 68 17 27 Moment Reference measure up from upper edge of support pallet Figure 2 30 Standard Instrument Rack Dimensions Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Figure 2 31 A Typical SOFIA Instrument Rack COMMENT need a new figure with flat panels Moveable items such as the keyboards mouse and utility drawer seen here are stowed for takeoff and landing Instrument Racks PI Rack x 2 39 CHAPTER 2 SOFIA Scie
223. s The scheduling of conformities must be closely coordinated with the Airworthiness IPT and the FAA DAR Part or assembly testing such as proof amp burst will require 100 FAA conformity of the unit FAA approval of the test plan and 100 FAA conformity of the test setup prior to commencing testing It also requires that the FAA or delegated DER witness the test 3 7 Obtaining Final Certification Successful part or assembly testing are complete per FAA DER approval of the documented results The science teams now must submit the final airworthiness deliverables see section 150 6 for DER review and approval This includes the Electromagnetic Interference EMI and Functional tests The EMI and Functional are ground and flight based tests to ensure there is no interference with the aircraft electrical system and the science instrument operates properly as per design Similar to the part or assembly test these tests will require 100 FAA conformity of the entire science instrument assembly installation FAA approval of the test plan It also requires that the FAA or delegated DER witness the test Successful EMI and Functional tests are complete by FAA DER approval of the documented results With the approved results submitted to the FAA this concludes the certification process with the issuance of the Supplemental Type Certificate STC 3 8 Certification Procedures Manual This SI Airworthiness Certification Procedures Manual i
224. s divided into 2 10 flight legs each leg associated with an object observed on the sky Observing is interrupted for turns usually taking about 2 minutes each when going from one flight leg to another Observing may continue during a cruise climb to higher altitude because of the continual monitoring of overhead water vapor i e atmospheric transmission Climb capability during the observing period is dependent on fuel load and outside air temperature Total flight time is approximately 8 5 hours An SI developer must assume that his her SI must be able to hold cryo gens for at least 12 hours the probable duration between serving of an SI before and after a flight USRA expects to fly the SOFIA aircraft approximately 3 to 4 times a week for approximately 44 weeks of the year NASA requires USRA to obtain approximately 960 successful flight hours per year after the initial Observatory commissioning period following ORR 1 8 A General Description of Observatory Working Environment CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 Flight Profile 6 9h 43k max Flight Profile 7 4h 41k max Altitude 1000 Altitude 1000 6 ETE h ETE h Flight Profile 6 9h 43k max Flight Profile 10h 41k max Altitude 1000 S e e o o E z lt 4 5 ETE h Flight Profile 12 2h 43k max Altitude 1000 Altitude 1000 Figure 1 5 Some Typical SOFIA Research Flight Profi
225. s EEI arias 5 19 APPENDIX A Acronyms and Terminology eee ee eene eee ee eren ee ecce A 1 vi SOFIA IHB 0 0 Figures Figure 1 1 Figure 1 2 Figure 1 3 Figure 1 4 Figure 1 5 Figure 1 6 Figure 1 7 Figure 1 8 Figure 1 9 Figure 1 10 Figure 1 11 Figure 1 12 Figure 1 13 Figure 1 14 Figure 1 15 Figure 1 16 Figure 1 17 Figure 1 18 Figure 1 19 Figure 1 20 Figure 1 21 Schematic Layout of the SOFIA Cabin 6 ete SERE rte he better Der ede ees 1 3 Aft Cabin Mission Control Ar a ope bed te eee e e IRE aa eee 1 4 PECOonSsole7 t i t tt te p e eee penne eee ces 1 5 Sl Safety Barrens iu uote edet eet out de a tenet reete ies piece AES ed 1 6 Some Typical SOFIA Research Flight Profiles eese nne eene 1 9 Exposed Telescope net mee din ar tea a ett e e Rite e e EET 1 10 Diagram of the Telescope Assembly eese eene nennen enne nene enhn en ense nnne treten enne 1 11 Perspective Rendering of Telescope Assembly ssesssssssesseeeseeeeeeennen eene ren emere 1 13 IR and Visible Tertiaries in their Support Tower eese rennen eee 1 18 SI Mounting Flange of Telescope Assembly no SI installed eee 1 21 Telescope Control AXes iore sett ah EPEES UR EORR LER NER cased E tees eee HERE Ue eevee 1 23 The Sense of the Rotation Angle erre m rete ett eit dede te ie ret eset een ba 1 25
226. s are also accomplished via soft ware control of the focus controller mechanism unit FCMU The telescope s TCMU also has a hardware interface as diagrammed below for direct control of oscillatory and programmed sec ondary mirror motions MCCS Ethernet TAMCP Ethernet Analogue Interface BEN BEN FCMU Figure 2 47 A Schematic Of Software And Hardware Connections To The Secondary mirror Control Unit SMCU The motions of the SOFIA secondary mirror are controlled along two axes that lie in a plane per pendicular to the optical axis of the SOFIA telescope The two axes of secondary mirror rotation are called the R and S axes Many of the details regarding the secondary mirror interface and all of the listed reference documents are located in TA SI 04 As depicted the science instrument connects to a junction box that is mounted on the front surface of the counter weight plate of the telescope The junction box houses a number of tri axial low noise connectors for control of the TCMU The lines are divided into several functionalities analog inputs analog output TTL inputs and TTL outputs The analog outputs consist of signals with and without superposition of flexible body compensation The highest priority functionality of the secondary mirror control is the direct analog control of secondary mirror motions The R and S axis analog command lines allow the instrument team 2 62 uA Secondary mirror Control CH
227. s separated into sections to address all possible aspects of the science instrument as follows If viewing PDF you can click this link to open the manual Volume 3 Observatory Airworthiness Manual 3 6 77 Construction Inspection and Testing CHAPTER 3 Airworthiness SOFIA IHB 0 0 Section 100 Introduction This section is an introduction to certification methods and role of the participants A short list of steps as well as an overview of the review process is also included Section 150 Data Submittals This section addresses the content of the data submittals to the FAA Section 200 Documentation The first important aspect of certification is the documentation Section 200 has examples of title blocks and information on a possible numbering scheme for instrument designers It is not required that the procedures be strictly followed but similarity between instruments is key to streamlining this certification process Section 300 Mechanical This section is dedicated to outlining the mechanical drawings and analysis that will be required for each component of the instrument Section 350 Manufacturing This section addresses some of the more specific tasks that will be required during SI manufactur ing It includes process specifications discrepancy reports and a sample test plan flow chart Section 400 Electrical The electronics subsystems within the SIs are largely low power signal processing electronics All SI el
228. s to supply three drawings that show how the instrument can fit within the science instrument installation envelope the science instrument ser vice envelope and science instrument dynamic envelope Each of these drawings can represent the science instrument with approximate dimensions so long as the approximate science instru ment volume falls within the maximum instrument volume required of SOFIA Clearly installa tion tests aboard SOFIA serve as the final verification of compliance with the SOFIA science instrument envelopes The science instrument mass and center of gravity are needed prior to the pre ship review Science instrument grounding scheme Each instrument needs to supply an appropriate ground ing schematic for the instrument This need only show how science instrument grounding is managed and how the instrument s grounding approach is consistent with the observatory s sci ence instrument grounding requirements Major grounds for the instrument are outlined with their connection to the aircraft grounding points Isolation of major science instrument compo nents from the aircraft structure also needs to be specified This needs approval prior to the pre 2 68 uA SOFIA Science Instrument Commissioning wr EP CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 ship review 2 12 2 Telescope ICDs TA SI 0l Each instrument needs to provide a list of the science instrument cables and their connector interface t
229. scope balance is complete an observing sequence will be run to exercise all inter faces and subsystems to test for electrical interferences and to look for any other potential prob lems As many systems as possible will be activated including the secondary mirror assembly the telescope gyros the telescope torque motors as well as the RIS The TA VIS Vibration Isolation System need not be activated Small forces will be applied to the telescope by hand to test EMI interference from the torque motors A simulated tracking routine will be used to check that all the correct MCCS signals are being sent to the PI electronics and that the MCCS and TA i e the secondary mirror are receiving all signals from the PI electronics In general this test period should take no longer than 1 hour but could be much longer if problems are uncovered If such problems are in the SI then the Observatory Director will make a decision whether to substitute a contingency mission using a facility SI This stage of the SI checkout would often be run in par allel with the cavity cooldown sequence see below After installation is complete and all ancillary equipment is stowed an airworthiness inspec tion of the set up will be conducted by an aircraft mechanic 4 12 uA Mission Ground Operations CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 4 4 SI Data and the SSMOC Data Cycle System DCS The SOFIA data acquisition and handl
230. seassocdesesvesedssssenassseaasasencssesesnsioosecs easeee 5 8 Tee REDA L c 5 8 5 3 4 Certifications 5 8 5 3 5 Additional Guidelines for Foreign Proposers And Proposals With Foreign Participation 5 8 5 3 6 Additional Policies And Procedures ssscssscsssccssssssssscsscssscesensssesscscssscsssssnessssscsscscssesees 5 9 5 97 5 Proposal FOLIIS ee eost E ioo oe eio hos lov Ue eerte eno e ev or eae EVI Te ovo eere soto evo e tie eee tl rone LV UY RE eee EUR aS 5 10 5 3 7 1 Instructions for Budget Summary Form 4 eere eee eee eerte e eee seen attese tn sse tn oe etase 5 12 5 3 8 Additional Proposal Forms and Certifications eere eee eee esee eene eene tentat tasa sense tn ae tna 5 13 5 3 8 1 Certification Regarding Debarment Suspension and Other Responsibility Matters Primary Covered Transactions 5 13 5 3 8 2 Certification Regarding Drug Free Workplace Requirements s sscssscsssssssessseesecsees 5 14 5 3 8 3 Certification Regarding Lobbying eee eee Lect eese eee esee e eene eren seas tons oK oos isin 5 16 5 4 USRA Review Process During SI Development eere ee eee esaet testen stas tasas tasse inst es sten sens 5 17 5 5 Project Implementation Plan 4 eee ee ee ente ee ee eee eee seen etta neta seen sesto sesto ESTEE DEO E E
231. sembly The details of the patch panels are described in several documents a MCCS SI 02 to describe the cabling interface between the USRA provided PI rack and the mission control and communications system MCCS b MCCS SI 03 to describe the cabling interface between the USRA provided PI rack and the telescope mounted science instrument c TA SI 01 to describe the actual cabling within the SOFIA cable load alleviator device d The global electrical schematic detailing the grounding scheme between the telescope science instrument counter weight rack and the PI instrument rack Instrument Cabling Patch Panels x xus 2 49 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 IFS 1196 39 SI Panel FS 1178 393 PI Rack Ref Optional Rack Location LBL 5 16 F LBL 41 501 MCCS Panel PI Patch Panel PI Rack Ref Figure 2 37 The Location Of The PI Patch Panel For Cabling Access To MCCS Telescope and Science Instrument Hardware The PI patch panel as illustrated is divided into two sections an MCCS panel MCCS_SI_02 and an SI panel MCCS_SI_03 The panel is located aft of the PI instrument racks The layout of the MCCS panel is illustrated in Figure 2 40 2 8 1 The MCCS Patch Panel Throughout the PI patch panel the connectors are arranged to provide easy access to connect and disconnect cable assemblies The connectors are group by type e g power data signal vi
232. should blind point to an accuracy of 2 arcmins TBV depending on the sky distance and time duration from the last verified pointing In order to obtain a translational pointing accuracy of about 0 5 arcsecs on the sky an observer must assign a track star with known sky coordinates with each position to be observed The closer the track star to the object being observed the more accurate the pointing since ROF errors have less affect on translational pointing errors when the distance between the track star and IR source is small The track star is called into use by defining an AOI around it and instigating tracking either through SCL commands or a GUI once the observer or Telescope Operator has commanded the telescope to the position to be observed The Tracker will maintain the known gyro offset between the track star and the object of interest throughout the stare mode observa tion The pointing stability of the SOFIA telescope is still to be verified but is expected to be close to 1 arcsecs RMS at ORR improving to about 0 5 arcsecs RMS or better within three years of opera tions Thus at ORR may have a higher pointing accuracy than stability which means the centroid of the object being observed is within about 0 5 arcsecs but that there is a pointing blur with an RMS value of 1 arcsecs Those of you with large diffraction limited beams will hardly notice Rotation stability i e the stability of ROF as well as transla
233. sible to operate the secondary mirror controller and verify a stated level of functionality In additions to the analog outputs mentioned previous a sin gle TTL output is available as a TTL trigger This reference is subject to a software commanded phase delay controlled by a designated keyword to the TCMU hardware When zeroed the TTL output should track any internal or externally applied reference signal Adjustments to the chop per phase reference can serve as a means of phase locking instrument electronics to triggered secondary mirror motions The phase delay is typically required for account for electrical and mechanical delays is system level secondary mirror motions Using only internal software con trol the observatory can verify secondary mirror motions by monitoring the analog and TTL out puts under a range of chopper amplitudes and frequencies An external TTL generator can serve to verify the phase stability of the system When monitored by the observatory such diagnostics can provide a continuous baseline for successful secondary mirror chopping operations Secondary mirror Control x xm 2 65 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 TTL sync IN t1 Opto coupler lt 250 usec delay 50usec sampling jitter Digital IO TTL Ref output t2 Opto coupler 2 ae delay 50usec operation 2 8usec Figure 2 50 Possible Line Delays Schematic Possible line delays associated with the built
234. software interface 67 Special Purpose Principal Investigator class Science Instrument SSI 3 Spherical Hydrostatic bearing 23 SSI 3 SSMOC SI Support Physical Facilities 40 Star Tracker 24 Stare Mode 23 Static Instrument Volume 24 stay out envelope see also static instrument volume 24 T TA Flange Pumping System 58 TA Master Computer Processor TAMCP 31 TA Servo Control Unit TASCU 31 TA MCCS Simulator Procedures 8 TCMU 62 Telescope Coordinate System 4 Telescope Design 11 Telescope ICDs 69 Telescope Imagers 18 Telescope Mounting flange 10 Vill SOFIA IHB 0 0 telescope optical path Nasmyth 1 16 Nasmyth 2 16 Telescope Optical Prescription 4 Telescope Pointing and Control 21 Telescope Primary Mirror Assembly PMA 13 Telescope Secondary Mirror Assembly SMA 14 Telescope Tertiary Mirror Assembly TMA 16 Terminology 1 tertiary Mirror optical parameters 16 The Aircraft Autopilot 22 Tilt Controller Mechanism Unit TCMU 62 TMA 16 U U V W coordinate system 4 second coordinate system 4 Upper Rigid Door URD 32 URD 32 User Volumes 48 USRA Review Process during SI development 17 V Vacuum Pumping System 37 Variations in Overburden 35 VDS 39 Vibration Isolation 22 Video Distribution System VDS 39 Visiting SI Team Labs 39 Vitae proposals 8 Ww water vapor WV overburden 35 water vapor burden 35 Water Vapor Measurement 34 WV 35 Z zenith water vapor plot 36
235. spher ical aberration is introduced Details on the changes in image quality with telescope focus are pro vided in the SOFIA technical document SOF SPE KT 1000 0 03 Table 2 1 Telescope Assembly Optical First Order First Order Parameter Value Entrance pupil diameter lt 2500 mm 8 2 feet Nominal focal length 49141 mm 161 2 feet Unvignetted field of view 4 arcminutes for chop amplitudes up to 5 arcminutes off axis Aperture stop location Secondary mirror Aperture stop diameter 352 mm 13 9 inches FPI eyepiece focal length 785 mm 30 9 inches Nominal FPI exit pupil diameter 40 mm 1 6 inches 2 6 uA SOFIA Telescope Optical Prescription ja CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Table 2 1 Telescope Assembly Optical First Order First Order Parameter Value FPI angular magnification 62 6 FoV at FPI exit pupil 4 2 arcmin 2 3 1 Secondary Mirror Buttons The secondary mirror button defines the central aperture stop for the telescope and prevents sci ence instruments from imaging themselves Specifically the button ensures that the primary mir ror hole and the edges of the tertiary mirror are not visible in the science instrument focal plane The details of the button design depend on wavelength and other science instrument specific con siderations For example some buttons are reflectors scatter cones deflecting cold sky emis sion into
236. ssembly no SI installed 1 3 2 Telescope Pointing and Control During taxi takeoff and ascent the telescope is caged i e fixed with respect to the bulkhead and braked with respect to the inner cradle About five to ten minutes before observing is to begin the observatory staff begins activating the telescope stabilization system and uncages the telescope The telescope must remain braked i e locked into position with respect to the inner cradle until the aircraft is on heading to observe and this is also the case every time the aircraft turns to go onto a new heading for a new observing leg The telescope aperture door is normally kept closed until the aircraft is at 35 000 feet or higher After the flight crew has leveled off the aircraft at the initial assigned altitude the door is raised to expose the telescope Opening the door takes about two minutes TB V After the In flight Direc tor IFD receives verification from the flight deck that the aircraft will remain level and is on the correct heading the Telescope Operator may un brake the telescope and begin actively slewing or pointing the telescope The Telescope Operator or the Investigator will then have control of the telescope for fine pointing However the IFD may override telescope control at any time The SI team can control the telescope through Mission Control GUIs or through command lines issued from an SI computer or PI Console or commands downlo
237. stricts access to science instruments during flight Special permission is required from the in flight Telescope Mounting flange x x 2 11 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 director to access the instrument within the designated perimeter while the TA is activated during normal flight operations W Spider Balancing Subassembly Secondary Mirror Asmblyy Nominal Focal Plane 2285 mm 89 96 in Science Instrument l l l 4 I Headring I N l l 2 ys 7c UA SS ce cm sA penen CCC m EEE ere de SP YZ z Visible Mirror LLL Se E SAA SSSES E M3 2 lt 7 J LLL ge LISS ZZ E Aircraft Wheel Well Flange Assembly with Instrument Flange Primary Mirror U V W 0 0 0 R FPI Tertiary Mirror Assembly Pedestal Bearing Nasmyth Tube Starframe Primary Mirror Cell Figure 2 9 Mechanical Telescope Assembly System Configuration With A Mounted Science Instrument The pressure boundary for a science instrument can be made a At the instrument mounting flange b To the telescope gate valve c With a separate window attached to the gate valve Some possible configurations are shown in Figure 2 16 The IMF includes 4 precision machined dowel pins equally spaced on a TBD inch bolt circle and separated by 90 One of the dowel pins has to take the shear forces in the event of a crash landing and during extreme telescope maneuvers i e slamming into
238. t development teams the science support integrated product team has for mulated a standard template for all SOFIA facility instruments to use in the development of a Project Implementation Plan PIP The outline addresses all of the review board concerns listed above and provides a standard format for the each team to following in presenting PDR materials The table of contents for the PIP is as follows Project Implementation Plan CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 1 Specification and Verification of Instrument Design 1 1 Final design to specifications level 1 1 1 1 System design guidelines 1 1 2 System performance parameters 1 1 3 System performance model 1 1 4 Operational constraints 1 2 Design implementation work break down structure 1 3 Derived design dependent requirements level 2 and verification plans 1 3 1 Instrument hardware 1 3 2 Instrument software 1 3 3 Instrument operational concepts 1 4 Facility instrument verification and acceptance plans 2 Required Interface Control Documents 2 1 External Interface Control Documents and Verification Plans 2 2 Internal Interface Control Documents and Verification Plans 3 FAA Certification Plans 3 1 Cryostat 3 2 Instrument mount 3 3 Instrument electronics 3 4 Instrument installation 4 Project management 4 1 Integrated product teams 4 2 Program schedule 4 3 Program budget 4 4 Program deliverables 5 Risk identification m
239. t program with two counterweight racks and made available at the SOFIA Science and Missions Operations Center SSMOC Science instrument teams in need of their own rack can order needed hardware through USRA The counterweight rack will be mounted as required by SI teams If the CWR is not required telescope assembly counterweights will be installed utiliz ing the same mounting points and locations as the CWR Instrument teams should note that use of the USRA CWR might result in degradations in telescope pointing performance beyond nominal limits All cabling for electronics with the CWR must meet the interface requirements stated in TA SI Ol Science instrument teams shall provide any vibration isolation as needed by their equipment An installed CWR is shown in Figure 2 36 The CWR is typically mounted before the science instruments using a cart and lifting device provided by USRA The CWR will be equipped with lifting fixtures for mounting and ground handling The CWR is attached to the telescope coun terweight plate through bolts and fixed nut plates on the rack structure 2 46 uA Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 CWR shown in its location on the forward side of the CWP Details on attachment points are shown in subsequent figures 4 Figure 2 35 Science Instrument Counterweight Rack The telescope points toward the zenith The yellow shaded volume repr
240. ted by the tracking computer are fed into the gyro torquer control loops Typ ical tracking accuracy using the FPI is about 0 5 arc second for stars brighter than about visual magnitude 15 TBV Slightly fainter stars may be used with longer FPI integration times but with slightly degraded pointing accuracy The FFI provides a field of view of 70 arc minutes with a visibility limit of V 2 13 with a one second exposure Offset tracking is possible for any star in the field brighter than V 13 with a similar exposure time Further details on the tracking system are given later in this section 1 3 2 6 Rotation Angle As in all alt azimuth systems rotation of the sky image occurs in the focal planes of the telescope and the attached cameras The orientation of the sky around an object being observed as mea sured in the telescope focal plane is defined by a Rotation Angle or Rotation of the Field ROF The SOFIA Rotation Angle is similar to the Parallactic Angle which is formed by great circle arcs from the object to the zenith and to the north celestial pole However on SOFIA the Rotation Angle i e ROF is measured clockwise from the up direction in the focal plane to the north celestial pole as shown in Figure 1 12 Up is the same for all imagers on SOFIA and is the 1 24 T Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 direction the line of sight of the telescope W axis would m
241. telescope hard stops Since the fas teners for the IMF use only through holes accurate positioning of a science instrument requires two of these pins one for position and the other for angle Four jackscrews are provided to assist in the removal of science instruments after a mission is completed Four additional hard points inside the Nasymth tube tub are available for mounting other science instrument hardware 2 12 uA Telescope Mounting flange CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 The two dowel pins not in use by a particular science instrument can be removed temporarily if desired or required There is free volume inside the flange assembly between the IMF and the gate valve pressure window subassembly This volume can be used for different purposes including a bore sight box calibration source or the mounting of small science instruments The complete engineering details for the IMF are contained within the interface control docu ment TA SI 02 Detail Markers Side View TA IMF Front View I INF NM Tube SI Flange _ Figure 2 10 The Orientation Marker Inscribed On The Circumference Of Instrument Mounting Flange An orientation marker is provided to register the instrument mounting flange and the science instrument flange The schematic shows the orientation of this marker with the UVW coordinate system of the telescope Telescope Mounting flange x xm 2 13 CHAPTER 2 SO
242. terruptible Power Supply URD Upper Rigid Door USRA Universities Space Research Association VDS Video Distribution System VIS Vibration Isolation System WFI Wide Field Imager Wt Weight WV Water Vapor WVM Water Vapor Monitor XEL Cross Elevation A 3 APPENDIX A Acronyms and Terminology SOFIA IHB 0 0 Index A Acronyms 1 Additional Guidelines for Foreign Proposers 8 Aircraft and Telescope Coordinate Systems 2 Aircraft Coordinate System 3 Aircraft ICDs 70 Alignment 10 AOR 16 AOT 16 Aperture Assembly AA 32 Aperture Door Assembly 32 Archive Access 47 Astronomical Observation Request AOR 16 Astronomical Observation Template AOT 16 Audio Distribution System 38 Azimuth Resets 25 B Balance Sub Assembly BSA 20 Beam Switching Mode 24 Boeing convention coordinates 3 Boresight selecting and perfecting 20 Boresighting 10 BSA 20 C Cable Load Alleviator 55 cabling patch panels instruments 48 Cavity Door Control 32 Cavity Door Data 33 Cavity Door Drive System CDDS 32 Cavity Door System CDS 32 Cavity Environmental Control System CECS 33 CDDS 32 CDS 32 CECS 33 center of gravity 16 central aperture stop SOFIA IHB 0 0 Index secondary mirror buttons 7 Certification Procedures Manual 6 changes in instrument mass cryogenic liquids 17 Chop Mode 26 CODR 5 commissioning science instruments 68 Computational Facilities 45 Conceptual Design R
243. th the FAA for subsequent use by air traffic control and one to be used by the IFD in monitoring and controlling adherence with the flight plan The IFD uses FM s Flight Executor sub function to monitor performance against planned ground track in the presence of disturbances due primarily to unplanned wind velocity direction or revisions to planned observations If deviations exceed expected ATC tol erances the IFD uses FM to re plan remaining flight legs for subsequent re filing with the FAA 1 7 3 Observatory Data Archive The SSMOC has a Data Cycle System DCS which is an integrated environment with computa tional modules planning tool and databases Some of the modules are commercial off the shelf 1 46 uA Software and Data Management CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 COTS software Others are custom programs written by specialists The system design is modu lar and has an architecture that can accommodate interfaces with many external components and has the flexibility to change over the lifetime of the SOFIA mission The DCS architecture is designed as a distributed system with user access via the Web The user interface is personalized by the application of XML and XSL DSSSL yielding web pages HTML unique for each user s need The archive software system employs a Java front end con nected to an Informix RDBMS backend 1 7 3 1 Archive Access Access to the SOFIA archive is through the
244. ti tution of the country from which the non U S participant is proposing Such endorsement should be in the form of a letter attached to each copy of the proposal and should indicate 5 8 uA Guidelines for Participation in the Instrument Program wr EP CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 1 The proposal merits careful consideration by USRA and 2 If the proposal is selected sufficient funds will be made available to undertake the activity as proposed Proposals must be forwarded to USRA in sufficient time to arrive before deadline established for this Call For Proposals All proposals must be in English All U S proposals which include non U S participation must follow all other guidelines and requirements described in this CFP 5 3 6 Additional Policies And Procedures 1 Restriction on Use and Disclosure of Proposal Information In order to protect trade secrets or other proprietary information that is confidential or privileged such information should be clearly identified and marked in the proposal In any event all efforts will be made to protect information contained in proposals but USRA assumes no liability for use and disclosure of information not clearly marked as proprietary A solicited proposal that results in a USRA award becomes part of the record of that transaction and may be available to the public on spe cific request however information or material that USRA and the awardee
245. tion of Rack Torque Moment USRA and the FAA require safety factors in panel loading to handle 6 0 g vertical loading and 9 g forward deceleration A heavy chassis may require a supporting tray Table 2 3 provides examples of maximum chassis weight as a function of front panel height As shown in the table the weight limits are somewhat different for the two sides of the rack Table 2 3 shows the larger weight lim its that use of supporting trays provide 2 42 A Instrument Racks PI Rack CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Table 2 3 Maximum Chassis Weights Max Allowed Weight W Ibs Front Panel Standard Max Allowed FWD side of rack AFT side of rack Height Moment no with no inches M ft lb tray tray tray with tray 3 5 7 23 Ib 35 Ib 35 Ib 45 5 Ib 5 25 9 3 26 45 52 63 7 14 35 54 67 80 5 8 75 18 7 43 62 87 98 10 5 23 4 52 71 105 115 5 12 25 28 61 80 122 133 14 32 8 70 89 140 151 Notes e The actual moment at point B is M W L where point B and distance L are defined in Figure 2 33 The allowable moment M at point B includes a 6 0 g down factor The maximum allowable weight W at the c g includes a 9 0 g forward load factor Weight limits with tray assume no equipment mounted directly in line on opposite side of rack e fa tray is used the moment limit M can be disregarded e For ease of handling a tray is recommended when the
246. tional stability can also be moni tored by the Tracker when two rotation stars are chosen within the FOV of the WFI or FFI and AOIs have been drawn around them However rotation stability is monitored by the Tracker only when the tracking keyword attribute inertial is set to yes Note rotation stability is expected to be on the order of millidegrees RMS TBV with gyro pointing alone Stare mode also includes tracking on non sidereal objects such as Solar System bodies Non sidereal positions on the sky can be specified using an ephemeris file containing orbital parame ters for a particular Solar System object Note while tracking on such sources will not be updating the gyro to sky transformation the tracking inertial no flag will be set Observing on SOFIA x xim 4 23 CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 4 5 3 3 Nod Beam Switching Mode In this mode the chopper i e TCM is centered and static i e there is only one image of the sky in the focal plane and the Observatory uses the designated SI boresight location within the focal plane to point the telescope SOFIA SCL and GUIs enable the observer or Telescope Operator to easily set up a series of positions on the sky nod positions or nod beams with tracking information including AOIs at each position in a particular observing sequence i e a nod sequence The most common sequence is a two nod beam se
247. ton TX 77058 1113 Telephone 281 486 2143 Fax 281 486 2160 E Mail cloud Ipi jsc nasa gov In order to facilitate the review process proposers are strongly urged to send one courtesy copy of their proposal to Dr Eric Becklin SOFIA Chief Scientist UCLA Department of Physics and Astronomy 405 N Hilgard Ave Los Angeles CA 90095 1562 Your interest and cooperation in participating in the SOFIA program are appreciated 5 22 uA Project Implementation Plan CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 Dr Paul Coleman President Universities Space Research Association Project Implementation Plan 5 23 CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 5 24 uA Project Implementation Plan SOFIA IHB 0 0 Infrared Astronomy APPENDIX A Acronyms and Terminology A 1 Acronyms and Terminology eese nennen nnn nnne nnne n nter nn nennen ener nennen A 1 Table A 1 Acronyms and Terminology Acronym Term Description AA Aperture Assembly AO Area of Interest AOR Astronomical Observation Request AOT Astronomical Observation Template BSA Balancing Subassembly BSB Boresight Boxes c g Center of Gravity CCD CDDS Cavity Door Drive System CDDS Cavity Door Drive System CDS Cavity Door System CECS Cavity Environmental Control System cfm Cubic feet per minute CLA drape
248. ts every three years once SOFIA is in full operation Funds will be awarded based on a peer review process More details on this process are in Chapter 5 The German science community also develops science instruments for SOFIA their funding is under a different process This overview chapter of the Experimenter s Handbook Chapter 1 is to familiarize a new or potential SOFIA SI developer with the SOFIA Observatory and SSMOC Other chapters in this handbook will address the observatory interface requirements that must be met by SI developers of SOFIA instruments and SI Teams using the observatory and general SOFIA operations infor mation pertaining to readying a SI at the SSMOC for flight and data acquisition i e observing and data archiving 1 2 uA Overview of SOFIA Observatory and SSMOC CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 2 General Description of Observatory Working Environment 1 2 1 Observatory Floor Plan A schematic layout of the Observatory onboard Mission Control area is shown in Figure 1 1 and includes the location of the telescope at the aft end of the cabin the arrangement in the cabin of consoles seating connector panels and other support equipment An interior view of the main cabin is shown in Figure 1 2 On the ground personnel and equipment access is through the first passenger side door on the port left side 1 e L1 door reached from the N211 hangar via a per manent platform
249. ument data and MCCS HK data will be archived In order to identify which files need to be archived each data provider will create a data manifest A data manifest is an XML document with a list of data entries which identifies who created the file and when the type of the file the size or checksum of the file and where it is located The data manifest can also contain any number of error report elements The error report elements are only created by the archiving software and are not generated by the data providers Addition of an error report element to the data manifest provides a mechanism for recording processing errors while the archiving process is going on Both MCS and Science instruments are likely to automatically update the data manifest each time a new file is created When the Observatory is physically connected to SSMOC via a high speed LAN the DCS core will automatically collect these data manifests presumably via a CRON like process and trans fer them to the SOFIA archive which will immediately start archiving the data from all the differ ent data providers MCS archive science instrument data disks etc The SOFIA archive will have data drivers for all common file types and these drivers will parse the information into the rela tional database If a file type is not recognized it will still be stored in the archive as a large binary object This means that it can be retrieved from the archive but that one cannot search on any
250. ure UPS is used for battery backup to the PI patch panel UPS power is proved and shared between all PI and SI requirement racks as budgeted by the SI team Both the UPS and non UPS power have circuit breaker protection with a 20 ampere limiting breaker All aircraft breakers provide observatory power wire protection and are not intended as circuit protection for science instrument equipment A 28VDC line is provided for the Mission Audio Distribution Subsystem The return path for the 28VDC line is ground at a ground stud beneath the panel in the floor This connector also provides the pins for an emer gency power shutdown discrete This discrete is provide by the observatory for use by science instrument equipment in shutting down power output from any instrument provide UPS and its use is mandatory if any science instrument UPS is present Instrument Cabling Patch Panels x xm 2 51 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Power SES J1 J2 J3 Fiber Data iga IDA DOA DO DOA DOZIRT Naz amas DOWD DOSAN D o o Q o n0 go o o D J4 J5 J J7 J J9 J10 J114 J12 J13 Unos nac Wann Des DOA Om Nair NAAB DONADI DOER fa si Jig Sir Ja Jig D Bi JB Ja DGS DD AG Dogs a DAAA Dood n o O o nO J24 J25 J26 J27 J28 429 Coax Video TRO e THO D TED C D TED Ro J31 amp J33 J34 R J36 J37 THO TED THO TED TH TED THD TED TED Yo fo 6 O O bo O 6 J39 J40 J41 J423 J43 J44 J45 4 amp 8 J47 TAD TED TBU Tan oO O O gc J48
251. uring a flight are reduced since the telescope cavity is pre cooled to stratospheric temperatures before a flight 1 3 3 2 Chopping Secondary Mirror Performance The oscillating secondary system provides stationary or chopped images at frequencies of 0 5 to 20 Hz An external drive input permits phase control by the SI The chopping amplitude may be set as high as 10 arc minutes on the sky however the tilt of the secondary mirror produces coma as large as about an arc minute at the maximum 10 arc minute amplitude An offset control can be used to tilt the chopping motion away from symmetry about the optical axis However if the tilt controller mechanism TCM is used to create an offset the maximum chop amplitude avail able is reduced by twice the offset Maximum chop amplitude 10 arc minutes 2 x offset TBV The chop direction with respect to azimuth may be changed in flight through a range of 180 If chopping needs to be set at a particular position angle P with respect to North on the sky for rota tion angle R the chopping angle O with respect to azimuth would be set to O P 90 degrees R If O 0 add 180 degrees TBV The efficiency of the oscillating secondary motion is shown in Figure 1 13 The waveforms were recorded from the position transducers used by the chopping control feedback loop Telescope Design and Performance CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 E 0 90 1 00 0
252. ves the right to make no awards under this CFP and to cancel this CFP USRA assumes no liability for canceling the CFP or for anyone s failure to receive actual notice of cancellation Cancellation may be followed by issuance and synopsis of a revised CFP if that is appropriate Guidelines for Participation in the Instrument Program ce 5 9 a CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 5 3 7 Proposal Forms Proposal Title Page Proposal Reference No To be filled in by USRA TITLE OF PROPOSAL ABSTRACT SOFIA INSTRUMENT DEVELOPMENT PROPOSAL SUMMARY Principal Investigator Organization Phone J Fax J Email Type of Organization e g profit non profit educational small business minority woman owned etc Identification of other organizations if any that are currently evaluating a proposal for the same efforts Instrument Type Detector Type Detector Format Wavelength Range Resolution Pass Bands Funds Requested from USRA for Duration of Project and the Desired Starting Date Figure 5 1 Proposal Form Proposal Title Page 5 10 eA Guidelines for Participation in the Instrument Program CHAPTER 5 SOFIA SI Proposal and Review Process SOFIA IHB 0 0 Budget Summary From To USRA USE ONLY 1 Direct Labor salaries wages and fringe benefits 2 Other Direct Costs a Subcontracts b Consultants c Equipment d Supplies e Travel 1 Domest
253. vestiga tors deployments including ferry flights maintenance and holidays blocked out In addition to this there will be intermediate and operating schedules for each mission The intermediate sched ule for a mission is prepared by the Operations Control Center 90 days before the start of a mis sion showing dates and approximate take off times for the flights in the series This schedule will 4 2 77 1 Yearly Scheduling of the SSMOC mper HN EP CHAPTER 4 SSMOC Operations and SOFIA Observing SOFIA IHB 0 0 also have an estimate of the number of investigators who will participate and their approximate arrival and departure times this includes the members of the PI team At this stage a contingency plan is developed as a back up in case the science instrument for the mission is not found to be ready during its scheduled reviews The operating schedule for the mission is prepared by the Operations Control Center 30 days in advance of the series with details such as the flight plans including flight take off and landing times the investigators including their dates of arrival and departure the logistics requirements e g cryogens and shipping and telescope configuration requirements e g tertiary mirror A readiness inspection of the PSI s and SSI s will be made either by a visit by a SSMOC scientist to the PI s institute or through a report by the PI showing the SI s performance characteristics If the science instrument is n
254. vide title of project sponsoring agency and ending date 5 3 3 5 Vitae Vitae and publications together are limited to a minimum of one page per individual for the PI and Col s and the individual publications are limited to the five most relevant to the proposal plus five others that the PI or CoI may wish to include 5 3 4 Certifications The Certifications provided in the Attachments should be filled out and attached to the original copy of the proposal This will reduce the amount of time required to process grants 5 3 5 Additional Guidelines for Foreign Proposers And Proposals With Foreign Participation In this Call for Proposals USRA is not soliciting proposals for instrument development from PI teams from non U S institutions Should such a non U S PI team wish to develop an instrument for use on SOFIA USRA will provide them with the same technical information made available to U S proposers Such non U S teams may then propose for time on SOFIA with their instru ment on a future Call for Proposals Should a U S proposal with non U S participation be selected USRA will arrange with the non U S sponsoring agency for the proposed participation on a no exchange of funds basis in which USRA and the non U S sponsoring agency will each bear the cost of discharging its respective responsibilities U S proposals which include non U S participation must be endorsed by the respective government agency or funding sponsoring ins
255. vided by the TMC chassis A second table is needed to list 1 whether the TMC is driven internally or externally 2 the range of frequencies used when driving the TMC externally 3 sample waveforms when driving either the TTL or analog inputs and 4 whether the internal phase reference is also used and the range of phase offsets expected All schematics and tables are needed for the pre ship review and should be updated for completion of the post flight review TA SI 05 Instruments requiring the telescope counter balance weight science instrument rack need to note when they desire to install their equipment in the limited number of racks available All SOFIA provided racks are available when the instrument arrives in the SSMOC Assembly of science instrument equipment in the SOFIA racks should be completed prior to the pre install instrument review A schematic and table is required that list the equipment equipment dimen sions the equipment weight the locations within the rack when assembled for installation on the TA and any cabling between the counter balance rack and the science instrument This material is needed for review prior to the pre ship review All rack weights are verified prior to the pre install instrument review SOFIA Science Instrument Commissioning eua 2 69 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 12 3 MCCS ICDs MCCS_SI_01 Instrument teams requiring an approved modified KAO PI instrument
256. w Final vibration levels will be available after SOFIA initial flight tests Telescope Mounting flange x m 2 21 CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 Focal Plane Acceleration 0 16 s i 1 1 nne A 1 1 s H 1 I l i e H 1 i mem dim St r t a i P i ide me ems 3 1 E i i 1 a Cumulative RMS m s 4 1 i J 1 1 D aea aca ah tara car rm acus at ad sas sarta ra BA aa tartar e iius ii ais D 1 Frequency Hz Figure 2 18 Science Instrument Accelerations in the U V and W Directions 2 5 Science Instrument Envelope The SOFIA science instrument envelope controls the spatial interface with the aircraft and tele scope The interface control document Global 09 defined 3 envelopes that follow the science instrument installation process During each of these phases the telescope motions are specified While mated to the telescope s science instrument flange the science instrument volume begins at the vertical plan of the flange and extends forward The science instrument volume also includes a volume segment that extend aft of the flange and fits within the telescope s Nasmyth tube while not extending aft of the gate valve The three science instrument envelopes are 2 22 uA Science Instrument Envelope CHAPTER 2 SOFIA Science Instrument ICDs SOFIA IHB 0 0 2 5 1 The Installat
257. ward of the telescope assembly These seats are installed close to the forward face of the P I instrument racks For this reason these seats have both lap belts and shoulder harnesses TBV The shoulder harness must be used with the lap belt during takeoff and landing The same seat belt configuration is used in the PI Console next to the Telescope Operator s Console and on the two seats facing outboard at the data analysis consoles These latter two seats must be swiveled to face aft for landings and take off Additional unassigned seating is located in the forward cabin these will have normal lap belt seat belts required for take off and landing During turbulence all must be seated with their lap belts fastened A typical research flight is long 8 hours two small ovens a refrigerator and cold drinking water are available for passenger use in the forward galley area Two lavatories are located in the forward area aft of the aircraft stair well Life vests life rafts oxygen supplies fire extinguishers and other safety equipment are distrib uted throughout the cabin All passengers will be thoroughly instructed in safety procedures prior to each flight series Additional aircraft safety information is provided at the end of Section 3 TBD General Description of Observatory Working Environment i ce 1 7 CHAPTER 1 SOFIA Design and Operation SOFIA IHB 0 0 1 2 4 Observatory Personnel The SOFIA 747 SP flight crew cons
258. y the PI team with review and signoff by certificated SSMOC technicians This entire procedure should take no longer than 2 3 hours since it would have been demonstrated in the TA MCCS simula tor Once the installation is complete and the SI is operational the two installation technicians will place the TA balancing weights required for three dimensional rotational balance of the TA SI package This will be done by connecting strain gauges between the aircraft and telescope assem blies rotating the telescope to several elevations and using associated MCCS based software to solve for a unique static solution After the TA weights have been added the RIS Rotation Isolation System or TA bearing will be activated and the telescope will be unbraked with the telescope at 40 degrees elevation Then as the telescope moves through all its angular degrees of freedom the cable drape and floor clear ances will be checked for interferences The balance will be checked through the full elevation range of the telescope For SI s using the instrument rotator plate the balance of the telescope will be checked for all SI rotation positions with respect to the telescope For SI s using the rota tor plate it is required that their center of gravity will be sufficiently close to their rotational axis that the TA fine balance system can compensate for SI rotation The entire balancing procedure should take no longer than about 1 hour After the tele

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