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ISS Russian Segment User Manual

1. 140463 c gt Ne Fig 6 6 8 The arrangement of containers in the cargo compartment of the Progress spacecraft 1140463 Wis 181 E H ol ea T S Tier III containers Tier II containers No III 1 III 2 III 3 III 4 No II 1 II 2 II 3 Tier I containers N 2 N 1 1 ENS SAE j mA Reo Spacecraft assembly 5 N 5 installation envelope 1 5 ul A gt No Spacecraft assembl installation envelope Fig 6 6 9 Dimensions of cargo containers of the Progress spacecraft 140463 7 9 No Payload l IV a closet accommodation area closet eer 7 5 Ne 2 BG payload accommodation area a couch gt FL ol 2 e T S equipment 2 The payload is only placed in container No 6 when a two seater version of the of the spacecraft is used Fig 6 6 10 The container and locations for accommodating additional cargo inside the orbital module of the Soyuz TMA spacecraft Note 1 In containers 1 5 7 9 the cargo to be delivered is placed in addition to the
2. 140463 on the deliverable cargo list 1 several identical cargoes are delivered one technical data sheet specifying their quantity 15 published Fig 6 6 6 shows the reference coordinate system of the spacecraft Fig 6 6 7 shows the cargo compartment of the Progress spacecraft Fig 6 6 8 shows the arrangement of containers in the cargo compartment of the Progress spacecraft Fig 6 6 9 shows dimensions of cargo containers on the Progress spacecraft Fig 6 6 10 shows the container and locations for accommodating additional cargo inside the orbital module of Soyuz TMA spacecraft Fig 6 6 11 shows cargo container in the descent vehicle of the Soyuz TMA spacecraft LLLA 1140463 178 Center of mass 11 1 lan e rr gt FL ol 2 e T S Fig 6 6 6 Reference coordinate system of the spacecraft r 140463 Docking unit Access hatch Docking unit cover envelope m LUC 547 WX 7 Access hatch m Payload containers Pavload E ne HHHH S P E gt c3 eo ca
3. gt 2 e T S Table 6 1 3 3 5 1 Spacecraft compartment Descent vehicle during escape tower operation Descent vehicle during cargo return 1140463 112 Loads in the X axis direction Accelera Number Pulse tion g of duration impacts ms Loads in two other mutually perpendicular directions Accelera Number Pulse tion g of duration ms Table 6 1 3 3 5 2 Spacecraf Mission t Exposure Frequency subranges Hz phases compart duration s ment 20 50 50 100 200 500 1000 10 200 500 1000 2000 0 Vibration acceleration spectral density g Hz Ascent to Orbital 10 02 10 02 10 02 10 05 0 05 0 025 orbit module 0 05 0 025 10 013 cargo compart ment 0 02 0 02 0 02 0 01 0 01 10 005 0 02 10 02 0 02 0 008 0 004 480 0 008 0 004 0 002 Orbital Orbital 0 004 10 004 10 004 10 004 10 004 0 004 flight module 0 002 cargo compart ment 0 004 10 004 10 004 0 004 0 01 0 01 D D pen Spacecraf Mission t Exposure Frequency subranges Hz phases compart duration s 20 50 50 100 200 500 1000 100 200 500 1000 2000 ment Vibration acceleration spectral density g Hz 0 004 10 004 10 004 0 004 0 41 0 01 pee 0 08 10 2 0 4 0 4 0 16 0 08 Loads vary linearly with frequency within
4. 2 2 2 58 4 4 Mini Research Module 1 1 2 4 66 4 5 Multipurpose laboratory module 70 SC areo ceralicatioli OPER esse DU 89 5 1 Documents used the course of 9 5 2 scientiic equipment 92 6 Specifications for experimental equipment delivered to ISS 102 6 1 Specifications for equipment transported in Russian spacecraft Progress and gt AL ol Z m T 6 4 A typical crew day plan during implementation of the standard mode 159 6 5 Acoustic environment in the ISS RS 160 6 6 Carso MeO Fallon cc 166 Attachment Ski vb 186 E 140463 1 Introduction This Manual provides basic information that designers of experiments and payloads that are proposed to be conducted and installed in the Russian Segment of the International Space Station ISS RS need to know in order to correctly state specifications when drawing up statements of work for space experiments and scientific equipment as well as to conduct a preliminary feasibility analysis of the experiments proposed for ISS RS It provides general
5. 1711771170 Deed documentation Uplinking a preliminary radiogram from Physical integration of the cargo to be returned into the descent vehicle _ Docking of the next spacecraft y Descent vehicle tandins Fig 6 5 5 The process of integration of cargo to be returned to Earth into Soyuz spacecraft 6 6 7 Documentation requirements 6 6 7 Requirements for the outline and installation drawing The outline and installation drawing 1s a drawing of a cargo a kit a cable in _ transportation position The outline and installation drawing shall cover the following data 1 name 2 drawing number gt E m 3 mass 4 coordinates of the center of mass with tolerances 1140463 smi os 5 moments of inertia with tolerances 6 unit drawing configuration 7 outline dimensions with tolerances of the cargo specifying dimensions of all protruding elements 8 locations of connectors monitoring or control panels toggle switches 9 coordinates of the unit attachment points and dimensions of fastener holes for cargoes with a mass of more than 8 10 kg 10 instructions for the unit orientation du
6. a EBERT 100 om I E 0 1 1 10 100 1000 10000 100000 f MHz Fig 6 2 4 2 7 Electric field strength outside ISS RS 1140463 Field strength may vary from 134 dBmicroV m to the specified value depending on the device location The radiated signal 15 modulated in amplitude with 1 kHz frequency and 50 depth of modulation 6 2 4 2 3 Requirements for radio receivers radio transmitters and AFD Specifications of radio receivers radio transmitters and antennas meet the requirements of Radio Regulations and recommendations of International Radio Consultative Committee IRCC Specifications of radio receivers radio transmitters and antennas are checked for compliance with the standards of Radio Regulations using procedures which meet the requirements of IRCC Recommendations E A 5 z zi 1140463 6 2 5 Labeling 6 2 5 1 Special labeling for ISS In addition to the labeling usually used by the equipment developer or vendor alphanumeric and barcode labels must be applied Equipment delivered in a package shall have the proper labeling on the package 6 2 5 1 1 Alphanumeric labeling Alphanumeric labeling in two languages the types and methods of labeling specifics of using R
7. D LI TT TIT m gt 0 2 2 gt 5 quil 7 yz cd Q ra zc Tl z me S n K S E 9 3 z ae o dr RC s 3 le mL 228 mm porthole Fig 4 1 5 SM interior view starboard mg 027 z ol S Lo a LI 1140463 O gt H ol S 7 X L E 22 2 im t m ME Xo gt ya 1 f z ON po 111114 _ _ ___ Xm E 228 mm porthole Lm We me Multipurpose biotechnology thermostat TUM SEEI eo pr 19 426 mm porthole Fig 4 1 6 SM interior view port side en a SICUT 1140463 100 J WIS D v Sr jejsouuoq ASo ougoojorq esodundn n A
8. JO Auesseoau 0140 aunpa peoped unge Jol SM i z JE SATRIA AEREA 01 5599 2 OF 32 p sun Dunes 115001910 11794 B GT 0Jo sun SUKETE 2500 x SIGEIBAE uoneziuags pue 0 SNCpseZeL auge Bun i JO SUBELU pue xpouly LO BU gee jusuidinba S xoge o m 5 gt p1eoquo juouidmbo y10ddns 0018510 Jo sonsuojoeeu 21481 pi An Lus O pauco purs oup jo doo stp cuui EJU LU NANDE A I 5 SE EQUI JOJU JELE 945458 Ip 5 1 Jac segue Sod Jo 545095 Aiddns 46 o qe reA SOOINOSOI C V 21991 E 4 5 Multipurpose laboratory module MLM Characteristics launch mass kg 20700 kg pressurized volume m 70 0 volume for scientific equipment m 8 0 power for scientific equipment kW up to 1 0 kW daily average inside the pressurized cabin and up to 1 5 kW daily average outside the pressurized cabin maximum daily average rejection of heat from the hardware included in the MPF kW up to 1 0 launch v
9. T a 1140463 5 2 3 Acceptance tests are done to check the equipment against the requirements of the documentation approved by RSC Energia The procedure for conducting acceptance tests 1s determined by the contract requirements 5 2 4 Tests at the checkout and testing facility within the flight model of the spacecraft ISS RS module are conducted in order to check mechanical electrical and software interfaces between the equipment and the spacecraft module Interfaces with the spacecraft are checked 1 the course of spacecraft processing at the checkout and testing facility interfaces with an ISS RS module are checked in the course of joint tests of scientific equipment with the electrical model of the module at the checkout and testing facility Tests within the flight model of the spacecraft at checkout and testing facility and at the processing facility are conducted when interfaces are available by agreement with RSC Energia 5 2 5 Incoming inspection of the equipment at the processing facility is conducted per agreed procedure after its transportation to the processing facility Incoming inspection operations include inspection of external appearance and a check for missing items equipment operational integrity check 1f need be E gt gt ol 2 2 T 5 2 6 Program of qualification and acceptance tests Requirements for equipment tests are de
10. averaged over time intervals of 100 s do not exceed the levels shown in Fig 1 Higher levels at frequencies ranging from 0 8 Hz to 5 Hz are due to the operation of solar array actuators and US segment radiators SARJ TRRJ crew exercise on treadmill and stationary bicycle maximum amplitudes of transient accelerations caused by individual sources do not exceed 10000 micro g along each axis At frequencies of 10 Hz to 300 Hz requirements are met at distances of no less than 1 meter away from the most powerful sources of disturbance which include 140463 in particular compressors for example in air conditioning systems electric pumps in the heating and cooling loops toilet control moment gyros Requirements may be updated for specific equipment locations 6 2 3 2 Requirements for the equipment to maintain microgravity conditions In order to comply with microgravity requirements for ISS RS and for ISS as a whole during microgravity modes of the ISS flight 180 days per year periods stretching for 30 days each every piece of equipment shall meet the following requirements the equipment shall not produce quasi stationary forces of more than 4 grams acting for long periods of time exceeding 30 seconds the equipment operation shall not cause accelerations with frequencies of up to 10 Hz in ISS RS modules that are in excess of 10 of the levels shown in Fig 6
11. Software II lest program Working compartment POI E Earth radiation belt protons P ISS RS International Space Station Russian Segment PC MKC P RF command and communications system RF equipment Descent vehicle 1140463 ox Onboard measurement system service Module DC 1 Docking Compartment COL PCI COTP Thermal control system Telephone and telegraph communications system _ Power supply system TepMocrar MBHT Multipurpose Biotechnological Hig
12. FL A Q requirements of Tables 1 and 2 but included in the payloads scientific equipment shall be blow those given in Tables 1 and 2 depending on the duration of their activation In order to evaluate the effect of the additional No equipment in each specific case an acoustic analysis 15 conducted of the mission phase which includes this source and all the other significant sources levels allowable per sanitary and hygienic standards during crew active duty and even during sleep along with other adverse spaceflight factors results 1n higher crew fatigue and loss of hearing acuity This circumstance and increasingly of noise The noise exposure through an entire multi day mission which exceeds the 140463 No difficult recognition of voice commands and audio warning signals against the noise background also affect flight safety 6 5 1 Acoustic environment in the SM SM 1s designed in such a way as to allow the crew to continuously reside 1n it and in particular this module has crew quarters cabins where crew members can sleep After a number of measures have been implemented to reduce levels of noise from these noise sources which included installing various devices noise suppressors vibration insulators sound absorbent mats vibration damping coatings at present noise levels in
13. Q j lt 5 gt e e EH uo preoquo Jo sjop ino pue peo Aed Jo suoneooT cC p 914 1140463 977 977 IN 0 ui9So 1 e 7 j k 8 I 1 i gt T A 4 His b Lo 5 2 o 1140463 speuiuie up gsn egz Su Lio JOJU aj dn sjeudsouge erp ul 35 1415 LRM 1860 008 hA 5 1 JOH 35 IWS LAM 008 UO ____________ i suoggeoM 5 gt juouidmbo 200125 Jo 10 592110521 JOA D C 91981 4 3 Mini Research Module 2 MRM2 Characteristics launch mass kg 3670 50 kg pressurized volume m 12 5 storage volume for cargoes and scientific equipment 0 2 in particular for scientific equipment 0 1 power for scientific equipment kW up to 0 1 maximum daily average rejection of heat from the hardware included the MPF through the air loop of the thermal control system up to 0 1 launch vehicle Soyuz FG external appearance 1s shown in Fig 4 3 1 Advanced cargo boom on the passive base point Micro meteorid A shield 1 ai Mi NS X 5 gt B Ee H E
14. B3aM H e ol T S scientific equipment units Location of external deliverable multi purpose workstation 2 and its TI EE 1140463 e gt A I ut ta A Basepoint un E gt gt 2 Un A 5 3 4 5p gt Lus eO 5 d c D 3 D gt O O c EX lt d x gt zs Ss E E gt 5 o eb 5 e co Ob SOLU see I EI jS Ur ac Oe mE JS 520 EAA un paseqi m da uo T 70d ELIO ET us 3uisuudinba DY OLE bs Jo sse E4303 Sup BY sog udnr oe A BULELE jo qur UO WELL 71124 Ed 12 pg i sod 240445 Addins SpLELULUCO o Ju SL jo E39 h uongdunsuoe AER sod SUOqE Ss spo juouidmbo JO uoned8ojur 592110591 TWAN LU
15. ON gt _ c 5 9 9 dm p e im 8 OQ wv gt 8 z O 5 9 zi Q H n 2 5 72 20 Automatic airlock 1s intended for removing payloads from the MLM pressurized adapter and placing them on the outer surface of the space station receiving payloads from ERA robotic arm and moving them into the internal volume of the airlock and on to the MLM pressurized adapter conducting scientific experiments in the internal volume of the airlock conducting scientific experiments outside the airlock on the extended table and at a specially prepared station Key specifications of the airlock airlock mass kg up to 1050 maximum power consumption with a payload kW 1 5 gas volume 2 1 maximum payload mass on the payload handling device kg 150 maximum payload dimensions mm 1200x500x500 the number of vacuum pumping cycles during flight tests no less than 200 allowable internal pressure kg cm 1 3 residual pressure after vacuum pumping mm Hg 107 gt Ht A External view of the airlock 1s shown in Fig 4 5 3 _ __ oL Do __ LL 1140463 OO N ooueTeodde 814 A quiosse SUIAOW peo
16. 140463 Hin along X axis 44 3 along Y Z axes 1 5 Operating values for quasi static loads taking into account the low frequency dynamic component for payloads secured in transportation position which do not have with the effects of transportation fixtures taken into account any normal modes within the frequency range of up to 30 Hz or have normal modes 1 the said frequency range while having a Q factor for the cargo fasteners system of no more than 10 are 7 15 1n any of the three mutually perpendicular directions occurring non simultaneously Duration of exposure to linear and quasi static loads up to 600 s Vibration loads in 3 mutually perpendicular directions in the form of sine vibration are given in Table 6 and at frequencies above 20 Hz in the form of random vibration are given in Table 5 Shock loads are in accordance with Table 1 Operational acoustic loads on the spacecraft acoustic noise levels total acoustic pressure during ascent to orbit are outside spacecraft up to 145 dB The acoustic noise spectrum inside the payload fairing of the launch vehicle 15 E A 5 z given in Table 7 Duration of exposure 20 30 s inside cargo compartment and the orbital module up to 135 dB No The acoustic noise spectrum 15 given in Table 8 Qualification levels are presented duration of exposure
17. 77 sjopno Jomod oN We q 1140463 oN 8H spEjno dj urge 2 pezunssedd ud 008 SRUUEUS 940499 T seoE EL LINNEA 1140463 BUES A WAG 101 eul SUO QEN 09 n 996504 511 T 2 S53 ua BIAS p 957 cec 58 5 COb S 54 JOLI SSp Sd see Lut LO Jo SLUM Ors e3o O M BUGSO PSH DOE uondunsuo ___ 0 5 2 momoa eeodndapy juouidmbo orpuoros JO 5 WS D TD AQL SHOES 0 esodangd niruu Jo H gt ol e a B3aM ol ea S Deliverable Multipurpose Workstation Passive payload adapter Active payload adapter 17 600 1152A 0 7 600 1151A 0 E Payload adapter Deliverable multipurpose 17KC 600101150A 0 Workstation s 1 17 600 1501A 0 Platform with adapters kJ 17 600 1501A 210 Retaining plate 21 17 600 1501 45 Passive basepoint Pd Mating device Active Base 04 j Point 27KCM 152IO 7110 0 Base NM Retaining plate 20 0 17
18. delivery Manifest 1s updated 1f necessary 4 months before the spacecraft 15 launched final outline and installation drawings of the deliverable cargos are to be submitted to the RSC Energia specialists on the spacecraft 3 months before the launch the specialists on the vehicle publish layout drawings for cargo accommodation inside the cargo compartment of the spacecraft and perform a preliminary engineering analysis of mass center of gravity and inertial characteristics of the spacecraft Published 1 5 months before the launch of the spacecraft are engineering drawings and documentation on cargo installation and the results of the analysis of cargo mass inertial and center of gravity properties of the spacecraft 1140463 m No later than 1 month before the launch the cargo 15 to be delivered to the processing facility where it will then be physically integrated into the vehicle Fig 6 6 1 shows the process of deliverable cargo integration into Progress spacecraft F Cargo data submitted and LN Tee 15 apud for gt cargo accommodation in the eme mem 9 CA to E facility E Physical D 1 of the iod MEM IBN i 111 E P process o cargo integration into Progress spacecraft gt ol Z e T
19. limits specified in Fig 6 2 4 2 3 Above 30 MHz compliance with the limits shall be assured for both horizontally and vertically polarized waves gt ol Z e T S E 1 1 it H E El bah 140463 Hin Measurement band shall be at least kHz the range of 0 01 to 0 15 MHz 10 kHz in the range of 0 15 to 30 0 MHz 100 kHz in the range of 30 to 1000 MHz MHz above 1000 MHz These requirements do not apply to RF noise generated by emissions from radio transmitter outputs 6 2 4 2 2 Immunity of equipment to electromagnetic noise 6 2 4 2 2 1 Low frequency noise Peak voltage values for low frequency noise the 28V power supply circuits of the module are given in Fig 6 2 4 2 4 Upeat V gt ol Z e T S 6 2 4 2 2 2 Industrial RF noise Peak voltage values for industrial RF noise in the 28V power supply circuits of the ISS RS modules are given in Fig 6 2 4 2 5 E Fig 6 2 4 2 4 Low frequency noise Else 140463 Upeakl dB uV ee mg _ M 32444 LLL LLLI d BIER Ht 80 0 0 4 10 100 1000 f MHz Fig 6 2 4
20. ol 2 e T 140463 p PUNS 9AISSEq VAA 20 oseg SN MdlA oouereodde WTN LU Sp 914 o ouj rod LN MdW aAISSEq EN Md IN 6 SN MdIN 1140463 ooueTeodde WTN C S v 914 VN MdlA 9N MdlN lt Ues 1 4 ZN Md VAA aseg VAA JUIOg oseg 1140463 For installing scientific equipment outside the MLM pressurized cabin the following External Multi Purpose Workstations EMPWS are provided EMPWSI EMPWS2 based on a passive fastener 77 810 2600 0 located outside the MLM instrumentation and cargo compartment 3 along Plane I Installation of scientific equipment onto EMPWSI EMPWS2 is effected by means of payload adapter 77 600 2200 0 EMPWS3 based on a passive fastener 77KMJI 810102600 0 located outside the MLM instrumentation and cargo compartment 3 between Plane II and III Installation of scientific equipment onto EMPWS3 15 effected by means of payload adapter 77KMJI 600102200 0 EMPWSA based on a passive fastener 77KMJI 810102600 0 located outside the airlock Installation of scientific equipment onto EMPWSA 15 effected by means of payload adapter 77KMJI 600102200 0 EMPWSS based on a passive base point 27KCM 152107200 0 locat
21. gt gt ol 2 2 T requirements of 99 a foreign organization follows contract requirements for conducting the space experiment scientific equipment certification 1s conducted in order to verify its following integral properties safety strength fire safety electrical safety toxicological safety radiation safety etc A Russian organization develops scientific equipment accordance with TE 1140463 89 equipment compatibility with spacecraft and ISS RS systems equipment compliance with requirements in the Specifications Depending on the specific kind of equipment certification 15 performed as follows safety and compliance with the specified requirements are verified for all types of equipment equipment compatibility with the spacecraft and ISS RS systems are verified for the equipment that has interfaces mechanical electrical software telemetry with the spacecraft and operating on board the spacecraft 5 1 Documents used in the course of certification 5 1 1 Documents used in certification of scientific equipment are defined in Russian technical standards documents used for the development of rocket and space technology products Certification documents attesting to certification of an individual piece of equipment are logbook data sheet label hereinafter referred to as logbook included in the accompanying documents flightworthiness sta
22. 0 MOYO 1140463 3 4 ISS RS consisting of SM MRM2 MRM1 and MLM Resources allocated to the MPF include allocated working volume of up to 1 m on SM up to 0 2 m on 2 up to 3 m on MRMI and up to 8 m on MLM power supply on SM and DCI up to 0 3 kW daily average and up to 1 kW for 2 days with continuous additional normal power supply to ISS RS from the US segment in accordance with operational documentation on up to 0 1 kW daily average on MRMI up to 0 1 kW daily average on MLM up to 1 0 kW daily average inside the pressurized cabin and up to 1 5 kW daily average outside the pressurized cabin heat rejection capacity on SM and MRM2 up to 0 3 kW daily average on MRMI up to 0 1 kW daily average on MLM up to 1 0 kW daily average after deployment of an additional radiative heat exchanger the number of workstations on the outer surface 4 pcs on the SM 8 pcs when deliverable Multi Purpose Workstations MPWs taken into account 5 pcs on MRM2 7 pcs when deliverable Multi Purpose Workstations MPWs E gt Z T taken into account 9 pcs on the MLM 13 pcs when deliverable Multi Purpose Workstations MPWs are taken into account payload data downlink capacity maximum via TM IU unit up to 2 MB per a Session ISS attitude control mode nomin
23. 600 1501A 350 Fig 4 1 8 Deliverable multipurpose workstation sample fields of view of scientific equipment installed on the SM multipurpose workstation are given in the following figures Fig 4 1 9 field of view of scientific equipment installed on the axis of sight aimed at zenith Fig 4 1 10 field of view of scientific equipment installed on the VPM H3 axis of sight pointed towards zenith Fig 4 1 11 field of view of scientific equipment installed on the VPM H3 axis of sight pointed towards nadir Fig 4 1 12 field of view of scientific equipment installed on the YPM H4 axis of sight pointed towards zenith Fig 4 1 13 field of view of scientific equipment installed on the VPM H4 axis of sight pointed towards nadir TI 1140463 H gt ol e Fig 4 1 9 field of view of scientific equipment installed on the 1 axis of sight aimed at zenith 140463 49 1140463 180 170 170 field of view of scientific equipment installed on the VPM H3 axis 4 1 10 Fig of sight pointed at zenith a _____ 1140463 470 480 170 field of view of scientific equipment installed on the VPM H3 axis Fig 4 1 10 of s
24. Atmospheric temperature during unmanned missions Temperature outside pressurized compartments in open space 150 to 125 C 6 2 1 5 Humidity Relative humidity 30 70 up to 95 for short periods of time up to 3 hours per day Dew point temperature 4 4 15 6 C in the living area 18 28 C in the instrumentation area 10 40 C during manned missions and 0 40 C 140463 6 2 1 6 Aerosol content Aerosol content in the atmosphere no more than 0 15 mg m for particles ranging from 0 5 to 300 micron 6 2 1 7 Medical and technical requirements for microbiological content Requirements for the allowable number of microorganisms are given in Table 6 2 2 Table 6 2 2 Source sampling time Number of bacteria Number of fungi no more no more than Air colony prior to flight 300 50 forming units m __ w NN Internal surface prior to flight 5 0 0 1 colony forming units m 0 8 NL NN There should be present no pathogenic bacteria or fungi gt ol Z e T S 6 2 2 Mechanical loading conditions Equipment loading and microgravity conditions and requirements given below apply to the loads occurring during storage and operation of the equipment in orbit within ISS RS Requirements for other operational phases are defined separately in accordance with the documenta
25. E 5 gt AIP SS 5 gt hatch with hol Deliverable MPWS gress hatch with a porthole on the passive base point Fig 4 3 1 MRM2 external appearance LT 1140463 Special features that MRM2 provides for conducting scientific experiments capability to install hardware on the outer surface of MRM2 for observations of the upper hemisphere and the plane of the local horizon availability of a porthole with capability to sight the hardware in the horizon plane capability to place hardware inside pressurized cabin for short periods of time for conducting space experime nts and to store it only for the periods between EVAs on board systems resources for scientific equipment on the external surface are mostly borrowed from the SM Passive base point 27KCM 152107200 0 Payload mass kg It is used for installing SE or MPWS D Quantity pcs Multipurpose workstation Deliverable analog of 17KC600101501A 0 Payload mass kg 150 The use of MPWS D makes it possible to increase up to three the uanti CS 9 p number of work stations gt ol e T Fig 4 3 2 Characteristics of standard external workstation adapters for installing configuration are shown in Fig 4 3 3 resources used for integration of scientific equipment are listed Table 4 3
26. t 21481 1140463 sample fields of view of scientific equipment installed on the MRM2 BPB multipurpose workstation are given in the following figures Fig 4 3 4 field of view of scientific equipment installed on the PBP axis of sight aimed at zenith Fig 4 3 5 field of view of scientific equipment installed on the PBP2 axis of sight aimed at zenith 90 00 H gt ol e a lt 480 1709 Fig 4 3 4 field of view of scientific equipment installed on the axis of sight aimed at zenith 140463 s 1140463 Fig 4 3 5 field of view of scientific equipment installed on the PBP2 axis of sight aimed at zenith a _____ In addition to MPW structural elements handrails can also be used for scientific equipment integration on the outer surface of MRM2 Examples of scientific equipment installation on MRM2 handrails and fields of view for scientific equipment are shown in Figures 4 3 6 4 3 7 Radiators on the USOS Radiators on the USOS c lt x H resupply spacecraft Fig 4 3 6 An example of scientific equipment installation on MRM2 handrails B3aM E ol ea 7 1140463 _ Fig 4 3 7 Fields of view
27. No 6 3 2 7 3 Touch temperature Surfaces having temperature of 40 to 45 with which the crew may come into an inadvertent contact shall have appropriate caution plates Surfaces with temperatures above 45 shall have protective devices or insulation to prevent crew contact Surfaces with temperatures below 5 with which the crew may come into contact shall have protective devices or insulation to prevent such contact as well as caution plates 140463 6 3 2 7 4 Spherical radii of outer corners and edges The SE hardware shall have rounded corners and edges or means of protecting the corners in accordance with Table 6 3 2 7 4 Table 6 3 2 7 4 Spherical radii of outer corners planes and edges structural Radius mm Holes panels covers 6 4 3 0 Preferable corner radii in the panel 3 0 1 5 Minimal plane moms Bp Note Open edges 1 thickness of 2 0 gt 1 0 mm and more full radius Minimal thickness of Smoothed 0 5 to 2 0 mm out or 3 thickness of less rounded off than 0 5 mm Small pieces of hardware 1 0 Minimal manipulated by hand wearing a spacesuit glove Note Instead of a spherical radius a chamfer 45 by 1 5 mm minimum with gt ol Z e T S smoothly beveled edges The chamfer width shall be selected in accordance with approximate values for spherical radii describ
28. Number of pixels in the CCD matrix 437664 752x582 gt FL ol 2 The imaged area on the ground 23 2x18 4 Field of view deg 3 3x2 38 H ol ea T To 1140463 At present the video system does not have the optics which would meet the quality requirements for Earth imaging for the purposes of Earth Remote Sensisng 3 9 2 HDTV video system Specifications Table 3 9 2 1 list HDTV system performance data during Earth imaging from the altitude of 400 km using the lens HJ15x8B IAS the lens 1s currently available onboard ISS RS Table 3 9 2 1 The HDTV system specification Focal distance max mm 120 240 without with extender extender Field of view deg 4 6x2 6 2 3x1 3 The imaged area on the ground 32x18 4 16x9 2 ci gt Ht 5 A 5 z The owner of the HDTV video system is NASDA however at present after consultation with the Japanese it can be used as the ISS RS system equipment Its further use must be agreed with NASDA with participation of Rosaviacosmos From the technical standpoint the HDTV video system 15 the next generation video equipment with respect to the LIV system the resolution of the HDTV camera 15 4 times that of the LIV camera In addition to this HDTV provides more color information about th
29. __ _ ___ __ __ 1140463 _ H ol ea a EH oO lt H Fig 4 5 6 field of view of scientific equipment installed on the EMPWS4 axis of sight pointed towards nadir T 1140463 JIucr 1140463 Fig 4 5 7 field of view of scientific equipment installed on the EMPWSS axis of sight pointed towards nadir E _ S H 90 Fig 4 5 8 field of view of scientific equipment installed on the 56 axis of sight pointed towards nadir J f _ _ __ 1140463 is c ol ea 80 90 oov Fig 4 5 9 field of view of scientific equipment installed on the EMPWS7 axis of sight pointed towards nadir 1114 _ _ ___ 1140463 5 gt O 2 5 O Q dum D DD Gy oe 9 x a 2 o 5 9 8 E om D 2 o 2 e 2 5 n wn Ee 5 4 C
30. ol ea S TI 1140463 66 Included in the MPF is the mission payload equipment necessary for providing onboard an extended range of services in support of Russian commercial experiments Set up in the pressurized cabin are 5 multi purpose workstations MPWs equipped with mechanical adapters and mission payload equipment modular shelves up to 4 pcs Glovebox C hardware with retractable glove box shelf MBLTT thermostat MBHTT thermostat multipurpose vibration isolation platform MVIP Slots for modular Arch frame shelves Modular shelf frame 50 Pull out shelf Tau Payload attachment slots GR 7 Ve Special bolts SN S 500 4 Handle 27 5 Velcro pads E gt ol Z e T Fig 4 4 2 Mechanical payload adapter Key specifications maximum payload unit dimensions 600x400x600 mm maximum number of retractable shelf modules 4 payload attachment to shelf modules anchor bolt attachment elastic fasteners Velcro fastener pud 11 T i 140463 rr LORETSU e guede LOQEJGIA By o an Jo seu 35 0 z Dube sp Bopiq 3 119911
31. 8 2 Temperature when 6 1 2 2 delivered to the processing facility eT 8 3 Temperature in flight 6 1 2 2 for spacecraft The tests for thermal stability are conducted 8 4 Thermal cycle Requirements of Subjected to the tests is scientific equipment specifications for the operating unpressurized compartments under scientific equipment exposure to cyclically varying temperature LoH f Verified requirements Test verification subparagraph in Qual Note Section 6 test 8 5 Acoustic noise 6 1 3 3 for spacecraft The tests are conducted if the equipment 15 6 2 3 3 for ISS RS considered critical with respect to acoustic noise exposure as well as in the cases where the root mean square value of the acoustic pressure on the hardware in the locations where it 1s installed in the spacecraft module exceeds 130 dB 8 6 High low pressure tests 6 1 2 4 for spacecraft The tests are conducted in order to check 6 2 1 3 for ISS RS operational integrity of the equipment under exposure to extreme pressure values 8 7 Pressure drop rate tests 6 1 2 4 for spacecraft t Subjected to the tests 1s scientific equipment built in the form of a pressurized unit or a vented container used inside the descent vehicle or orbital module of Soyuz spacecraft Pressure drop rate 15 100 mm Hg s 9 Radiation stability tests 6 1 2 5 for spacecraft The test 1s run for the kinds of equipmen
32. Materials shall not be capable of maintaining combustion either on their own or when integrated into another product or system Fire prevention measures all the circuit boards shall be covered on both sides with silicon or another approved material if they not completely enclosed a metal container and if they are not otherwise accepted by the Russian side all transformers or coils are fully enclosed 1 a metallic material an approved potting compound Exceptions from this rule must be specifically approved by the Russian side all the wires are covered with Teflon all wires and cables are protected or routed in such a way as to rule out any possibility of wire damage which may cause sparks or short circuits circuit protection shall be provided in order to avoid possible circuit overheating in off nominal situations for example short circuit as a result of an abrupt change or a delay 1140463 insulation of power cables shall be heat resistant connectors that do not have such protection shall be shielded with housings made of nonflammable materials 6 2 7 2 Materials toxicity It 1s forbidden to use for the hardware structure any toxic or hazardous materials which may release gases detrimental to the crew in concentrations dangerous to the crew Materials of the equipment located on the outer surface of ISS shall meet the standards for outgassing in vacuum with respect to loss of mass no mo
33. S Physical integration of deliverable cargos The process of physical integration of cargoes is determined by the technical plan of spacecraft processing at the processing facility and the launch pad Fig 6 5 2 shows the process of physical integration of cargos into Progress spacecraft Else 140463 L25 ei os ts L2 ta Days _ E TO T e T T T T d nu additional deliverable LTEM Losing adt M adidas iui at Cn anch pad TE 1 The a __ Fig 6 6 2 The process of physical integration of cargo into Progress spacecraft The major portion of physical integration of deliverable cargo into the cargo compartment of the spacecraft 1s performed 25 12 days before the launch of the spacecraft Specific schedules for loading cargo within the specified interval of time and the number of days allocated for physical integration 1s determined by the technical plan for specific spacecraft processing Within the time period of 8 5 days before the launch of the spacecraft during final operations after the spacecraft has gone through the filling station and payload unit assembly it 1s possible by the decision of the technical management to perform additional physical integration additional loading of deliverable cargoes of a
34. are 4 5 ayz 6 0 m 82 x 0 2 rad 32 eyz 0 7 rad 82 For the equipment having a natural frequency of the attachment below 20 Hz operational values of linear and angular accelerations can be as high as the following values 22 0 m s ayz 16 0 10 52 x 1 3 rad s yz 7 0 rad s When determining design loads the safety factor shall be set equal to 2 If need be these accelerations can be updated for an individual piece of equipment to take into account its specific attachment stiffness values dynamic characteristics of the primary structure of the equipment and its location on the ISS RS structure The structure of the equipment installed inside ISS RS modules in the crew transfer path 1n addition to inertial loads see paragraph 0 2 1n accordance with the requirements of approved document SSP 41163 shall withstand operational loads of 556 N design value of 778 N caused by the crew knocking directly against the equipment The force shall be applicable in any direction to any spot on the equipment accessible to the crew The structure of the equipment installed on the outer surface of the ISS RS in close proximity to the crew transfer path in addition to inertial loads see gt ol Z e T paragraph 0 2 in accordance with the requirements of approved document SSP 41163 shall withstand operational loads of 50 kgf 490 5 caused
35. as well as crew intravehicular and extravehicular activities In addition to inertial loads there are loads generated by forces directly applied gt ol Z e T by cosmonauts astronauts In addition to the above loads the equipment installed on the outer surface of the modules 15 subjected to the following loads Jet plume impingement loads loads produced by a crew tether when the tether 1s fastened to the equipment Inertial loads for the equipment are given in the form of operational linear and angular accelerations of the center of gravity and about the center of gravity of the equipment in the OXYZ coordinate systems which are defined as follows r 1140463 SM X axis of the OXYZ coordinate system is parallel to the Xgs axis and 15 pointed in the same direction Y axis 1s perpendicular to the X axis 1s parallel to the Yrs axis and is pointed in the same direction Z axis completes the right handed coordinate system located on the docking port Xpc axis of OpciXpciYpciZpci coordinate system 15 parallel to the axis and is pointed in the opposite direction axis is perpendicular to the Xpc axis is parallel to axis and is pointed in the opposite direction Zpci axis completes the right handed coordinate system MRM2 located on the docking port Xmrm axis of the 2 24 2 coordinate system is pa
36. specifications for the scientific equipment the scientific equipment 1s most sensitive under given conditions 17 EMC test 6 1 2 5 for spacecraft 6 2 6 for ISS RS LoH f Verified requirements Test verification subparagraph in Section 6 flight units of self contained power sources except the ones of the tablet type are subject to tests The tests include visual inspection recording physical characteristics taking measurements of storage voltage and operating voltage leakage test cycling 18 Tests of self contained charge discharge power supplies and chargers Tablet type self contained power sources are tested within operating equipment Flight units of chargers are tested under normal operating conditions Self contained power sources and chargers that have passed the tests within the equipment are not subjected to tests within this scope 001 Notes 1 Symbols this test must be conducted p these requirements can be verified through calculation analysis tests checks are not conducted 2 It 1s acceptable with the agreement of RSC Energia not to conduct certain types of tests specified 1n the table In that case the equipment compliance with the requirements shall be verified through analysis 6 Specifications for experimental equipment delivered to
37. subrange gt 1140463 Table 6 1 3 3 5 3 For all Exposure spacecraft Frequency subrange Hz duration s compartments Mission phases 5 25 25 200 200 800 800 1500 1500 2500 Vibration acceleration amplitude ps gp o pe i B Loads vary linearly with frequency within subrange Table 6 1 3 3 5 4 gt Table 6 1 3 3 5 5 Center frequency of the octave frequency subrange Hz No Maximum root mean square level of acoustic pressure dB nop mimm 1140463 115 6 1 3 3 6 Autonomous transportation of equipment and hardware For autonomous transportation of equipment and hardware by all types of transportation the recommended accelerated test modes are given in Table 6 1 3 3 6 Table 6 1 3 3 6 The number Shock Total of impacts pulse Transportation vehicle Pulse duration number of per minute acceleratio axes ms impacts no more than 6 1 3 4 Safety factors 5 strength analysis of deliverable cargoes including their fasteners 1s done based on design overloads defined as the product of operating overloads and the safety factor f The same safety factors f ar
38. 15 120 s inside descent vehicle up to 125 dB 6 1 3 3 3 When Soyuz emergency rescue system escape tower operates off nominal situation Operational values for linear loads a during descent vehicle escape manuever n 15 exposure duration is 5 s 1140463 107 n 8 exposure duration is 2 s n 13 1 Hz vibration t 30 s b during ballistic descent of the descent vehicle after launch vehicle failure n 27 exposure duration 15 9 s 5 exposure duration is 13 s n 1 exposure duration 1 6 s Vibration loads in three mutually perpendicular directions applied to the escaping part as random vibration per Table 5 Shock loads are in accordance with Table 4 Operational acoustic loads on the spacecraft Acoustic noise levels total acoustic pressure during operation of the emergency rescue system operation time 1s 4 s are outside the spacecraft up to 160 dB inside the orbital module up to 150 dB inside the descent vehicle up to 140 dB 6 1 3 3 4 In orbital flight 1 operating values for quasi static loads taking into account the low frequency dynamic component for payloads secured in transportation position which do not have with the effects of transportation fixtures taken into account any normal modes within the frequency range of up to 30 Hz or have normal modes in the said frequ
39. 2 3 1 The operation of the equipment shall not cause accelerations with frequencies in the range of 10 Hz to 300 Hz that are excess of 10 of the levels shown Fig 6 2 3 1 at the equipment attachment point the operation of the equipment shall not cause non stationary accelerations with E A 5 z amplitudes exceeding 1000 micro g at the equipment attachment point 6 2 3 3 Noise level limit requirements for the equipment No During its operation no piece of equipment shall generate noise excess of 55 dB at the distance of 1 m from the source LLLA 1140463 g 100000 10000 minimi im et 1000 LLL Tz micro g 1 3 octave RMS value 0 01 0 1 1 10 100 1000 Frequencies Hz Fig 6 2 3 1 6 2 4 Electrical requirements 6 2 4 1 Basic requirements 6 2 4 1 1 On board power supply E A 5 z Power is supplied to the equipment from a DC power source of the Electrical Power Supply EPS system of ISS module at nominal voltage of 28 5 0 5 V across the EPS output terminals Steady state supply voltage at the hardware input lies within the 23 29 V range The hardware shall operate normally when exposed to sudden changes in supply voltage by 4 5V with a frequency no higher than 1 Hz and duration of no less than 0 1 ms In that case the vo
40. 2 5 Industrial RF noise 6 2 4 2 2 3 Pulse noise The effect of the pulse noise 1s characterized by the following parameters amplitude and duration of a test pulse are given in Tables 6 2 4 2 1 and 6 2 4 2 2 pulse edge durations are no more than 5 of the pulse duration pulse rate is 1 Hz for a period of 1 minute or for a period of time needed to evaluate performance Table 6 2 4 2 1 Characteristics of pulse noise between power buses Pulse duration 50 100 300 500 microseconds gt ol 2 e T Pulse amplitude V PIS 15 10 10 15 15 10 10 Table 6 2 4 2 2 Characteristics of pulse noise between each of the power buses and the case Pulse duration 50 100 200 300 microseconds NH MEL T 1140463 Im Pulse amplitude V Peak values of electric field strength inside 155 RS modules are given in Fig 6 2 4 2 6 Ep dB uV 0 LEER _ Jmm Fig 6 2 4 2 6 Electric field strength inside the module 6 2 4 2 2 4 Radiated RF noise outside ISS Peak values of electric field strength outside ISS RS are given in Fig 6 2 4 2 7 gt ol Z e T S dB uV EHWCEHHEIEEREEHIEHINEHUT LE Ee 120 ea 34
41. 2 Environmental conditions 6 1 2 1 Gas medium Composition of the gas medium inside Cargo Compartment Descent Vehicle and Orbital Module in volume percentages through all the phases of free flight up to the docking with the space station oxygen 21 40 at partial pressure of 120 350 mm Hg 1140463 m carbon dioxide up to 3 hydrogen up to 2 helium up to 0 01 nitrogen the rest Gas media composition in Cargo Compartment Descent Vehicle and Orbital Module after docking with the space station and opening of the transfer hatches 15 the same as the composition of the atmosphere inside the space station pressurized cabin 6 1 2 2 Temperature In production and storage rooms 5 30 C Ground transportation 50 C Assembly and testing 0 40 C On the launch pad for cargoes 0 40 C Orbital flight for cargoes when the crew is not present 0 40 C for cargoes when the crew is present 18 4 25 C for cargoes outside pressurized compartments from minus 150 to 125 C After spacecraft landing for cargoes 50 C gt ol Z e T S Ls Temperature is allowed to rise up to 30 C and drop down to 410 for no more than 3 hours a day 140463 6 1 2 3 Humidity at temperature 20 In production and storage rooms 20 8
42. 5 E A 5 z Barcode labeling 1s done by affixing special labels carrying a barcode duplicated in alphanumeric format Barcode labels must not cover any existing inscriptions on No the cargo The locations for onboard data sheets and labels are determined by the developer drawing If the cargo is not subject to barcode labeling a barcode is not to be installed entry shall be made in the dimensional installation drawing Photographs of the delivered cargo are taken separately prior to installation on the spacecraft as well as after its installation on the spacecraft Deliverable cargoes are loaded into the spacecraft and checked for labeling per design documentation requirements a person in charge of the cargo and are specified in its dimensional installation 140463 6 1 6 Requirements for cargo mechanical properties Mechanical properties shall be consistent with the cargo delivery and disposal conditions The cargo shall be able to go through the spacecraft hatches The cargoes to be delivered are loaded into Progress spacecraft through the hatch in the docking assembly inside diameter of 800 mm and through three loading hatches inside diameter of 470 mm in the cargo compartment Inside diameter of the boarding hatch in the orbital module of Soyuz is 660 mm the diameter of the manhole hatch in the Soyuz descent v
43. 6 exposure duration is 20 s n 7 1 exposure duration is 20 s a ballistic descent of the descent vehicle off nominal situation ny 0 10 n 0 1 600 s including n 10 exposure duration is 20 s 1 exposure duration is 20 s a normal descent of the descent vehicle nominal conditions r 1140463 Variation of operating values of loads with time 1s approximated by a sine half wave with half period equal to the exposure duration c during parachute system operation during drogue chute operation n 10 in any direction exposure duration 1s 10 s during main chute operation n 8 exposure duration is 15 s 4 exposure duration is 15 s during re hooking 5 in any direction exposure duration 1s 5 s d touch down with failed soft landing thrusters off nominal situation at first impact 100 a deviation of loading direction of 15 is possible ny 7 50 direction of loads in transverse plane is arbitrary Variation of loads with time 1s approximated by a sine half wave with half period 20 30 ms 2 vibration loads in three mutually perpendicular directions on the descent vehicle during reentry in the form of random and sine vibration accordance with Tables 6 1 3 3 5 2 6 1 3 3 5 3 3 shock loads are in accordance with Table 6 1 3 3 5 1 E A 5 z No LLLA 1140463 ui
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45. EE RA European robotic arm 140463 REVISION LOG Total number of number of Document accompanyin modified replaced new deleted pages in the number 5 document documentati on and date Revision Signature O gt 1140463 EN 189 189
46. Test verification subparagraph 11 Section 6 6 Safety review safety analysis includes safety assessment in general and specialized fields strength materials safety toxicological and radiation safety etc as well as an integrated assessment of the hardware safety 7 Mechanical loads tests The tests are performed to check the strength of 7 1 Vibration load bearing elements of the hardware that has 7 2 Shock loads a mechanical interface rigid attachment with 7 3 Linear accelerations the spacecraft module as well as 1f need be to check the functional integrity of the hardware The tests shall be performed in transportation 6 1 3 for spacecraft 6 2 2 for ISS RS and working configurations of the hardware under the types of loading which correspond to these configurations for example in a bag package fastened in a way similar to the standard attachment to the spacecraft If the hardware was tested at levels different from those currently established the issue of Verified requirements Test type Test verification subparagraph in Qual Note Section 6 test extending the applicability of these results needs to be coordinated with RSC Energia The accuracy of humidity measurements 1s to EN 8 Environmental tests E 8 1 Humidity 6 1 2 3 for MURS 6 2 1 5 MURS ISS RS be agreed with RSC Energia
47. acceptable risk the duration of a period within an expedition to orbit during which acceptable risk standards apply must be additionally defined gt 2 e T S LLLA 1140463 121 Table 6 2 1 Maximum acceptable content of harmful trace contaminants in the space station atmosphere Compound Russian MAC values US SMAC values for for 360 days in orbit 180 days in orbit methane 3300 20 Tas formaldehyde 0 05 0 05 acetaldehyde aliphatic aldehydes 1 4 to 8 benzaldehyde fous zi Compound Russian MAC values US SMAC values for for 360 days in orbit 180 days in orbit mg m mg m 1 0 Russian Maximum Allowable Concentrations MAC are stated in the national standard GOST P 50804 95 US Maximum Allowable Concentrations SMAC are stated in the document dichloromethane 1 2 dichloroethane Freon 218 compounds are grouped into structural classes Maximum Allowable Concentrations for individual contaminants in spacecraft atmosphere JSC 20584 6 2 1 3 Atmospheric pressure The total nominal pressure onboard the space station is maintained within 734 770 mm Hg the minimal pressure 15 no less than 700 mm Hg 6 2 1 4 Atmospheric temperature gt ol Z e T S
48. and DVCAM formats It is also possible to downlink video and audio signals via the switch of the LIV video complex signals are compressed in MPEG2 format used in ground digital HDTV channels as well as in Blu ray disk recorders Viewfinder Electronic color Combined 12x optical zoom lens The camcorder has a system of color filters and balance of white as well as an amplifier and an electronic shutter Possible use video recording the progress of the experiments within experimental setups video recording inside SM to provide information to general public video recording of Earth video recording from Soyuz during re docking operations backup capability for TV broadcasts when primary LIV system is unavailable or out of order Fig 3 9 3 Video camera HDV Sony 21 Built in portable LCD display for viewing the recordings The video camera uses Sony s Memory Stick The camera image sensor has three 1 3 inch CCD matrixes with a total of 450 000 pixels Characteristics of the 12 x zoom lens match 1 3 inch CCD system The optical stabilizer is Super SteadyShot M which uses independent determination of horizontal and vertical motion A prism system in front of the lens effectively compensates camcordershaking when filming without a tripod Black and white LCD viewfinder with 180 000 pixels provides horizontal resolution of 500 TVL which simplifies manual focusing control Video d
49. by the crew inadvertently knocking against the equipment The force shall be applicable in any direction to any spot on the equipment accessible to the crew In accordance with requirements of the approved document SSP41163 a structure on the equipment which may serve as an attachment point for the hook of a crew tether shall be capable of withstanding the design load of 200 1962 r 140463 applied at the tether attachment point and acting any direction accessible to the crew In accordance with requirements of the approved document SSP 41163 the structure of the equipment installed on the ISS RS outer surface with the exception of solar arrays and radiators shall be capable of withstanding the folowing local operational pressures generated by the thruster jets normal pressure of 16 7 kgf m circumferential pressure of 3 91 kgf m The surface area to which these pressures are applied up to 0 25 m When equipment is installed on solar arrays and radiators the values for operational pressures are to be additionally defined Safety factor for operational pressures generated by thruster jets is to be set equal to 2 Operational number of the equipment loading cycles in the orbital phase of the mission during docking control system operation as well as during intra and extravehicular activities for evaluating fatigue strength when the equipment operational life 1s 15 years 1s
50. gt ol Z e T S of this hazard exists In those cases where the loss of function may result in a critical hazard no single failure shall result in the loss of this function 6 3 1 3 4 2 A function which if inadvertently triggered may result in a catastrophic hazard shall have at least three independent inhibits for the entire time while the likelihood of this hazard exists There shall be a capability to monitor the status of at least two of the three required inhibits In those cases where the loss of function may result 1 a catastrophic hazard two failures shall result 1n the loss of this function 1140463 151 6 3 1 3 5 Caution and warning devices In those cases where the occurrence of a hazardous situation requires urgent action on the part of the crew fire depressurization toxic release etc devices shall be used for providing a timely warning to the crew about these hazardous situations and or for switching off the SE system hardware 6 3 1 3 6 Special procedures Procedures supporting the SE safety shall contain Safety instructions for equipment handling procedures to be followed in case of possible SE failures 6 3 2 Design requirements 6 3 2 1 Materials Materials used in SE structure including packaging shall meet the following safety requirements a Toxicity The materials 1n use that are in contact with the spacecraft environment shall
51. information about ISS RS resources at different stages of its deployment as well as about resources of its individual elements Special attention 1s given to the issues related to payload delivery and in orbit operation and returning experimental results to earth All the payloads installed on ISS RS Scientific Equipment SE are included into the Mission Payload Facility MPF The Manual describes the ISS RS MPF architecture and provides a brief description of its components It provides a description of workstations for accommodating scientific equipment mission payloads that support the conduct of space experiments resources provided for SE the principles of SE control and methods of downlinking data from the SE It describes the SE operational environments within the ISS RS modules and within gt Ht A 5 z the transportation vehicles Soyuz and Progress E 140463 2 Ground rules To meet the necessary requirements for SE development testing delivery accommodation and functioning a Mission Payload Facility 15 established onboard 155 RS Included in the MPF are scientific equipment mechanical adapters Science support equipment cables In order to achieve the most efficient use of resources provided by the space station for conducting research throughout its life during which time some research objectives may become irrelevant t
52. minute communications session ci Ft A 5 z E 140463 3 6 Trajectory and navigation support for space experiments ISS together with the ISS RS 15 continuously normally operated in the orbital coordinate system The accuracy and stability of maintaining the ISS in the OCS ISS OCS attitude control accuracy 10 angular minutes ISS angular rate stabilization accuracy 0 005 deg s Additional requirements for payload accuracy and stabilization during a program of experimental tests shall be met through the use of additional specialized or multipurpose equipment working in conjunction with the operating mission payload equipment 155 can perform programmed pitch and roll maneuvers within 15 degrees this constraint 15 imposed due to the lighting conditions of the thermal control system panels on the US orbital segment Installed at present on one of the on board crew support computers 1s the Sigma program for displaying the trajectory and navigation flight environment which makes it possible to perform the following tasks continuous real time display on the screen of the space station position current orbit track coverage areas of the nearest ground stations the start and end times of the next communications session with Earth lighting environment in orbit mission elapsed time etc Used to display
53. not release into the environment any toxic and noxious chemical substances in concentrations constituting a threat to the life of the crew and spacecraft operation Care must be taken to avoid the use in the SE hardware of any chemical E A 5 z substances which do not come into direct contact with the environment but may pose toxicity threat 1f they leak into the spacecraft atmosphere for example may cause crew skin or eye irritation or affect spacecraft equipment If nevertheless No they need to be used requirements of paragraph 6 3 1 3 shall be met accordance with the hazard level b Fire safety Materials used under normal operating conditions and in case of cabin depressurization shall not become a source of fire or explosion shall be heat resistant and shall not sustain combustion neither by themselves nor when used within hardware assemblies and systems shall not release flammable gases and form combustible or explosive mixtures 140463 c Microbiological safety The materials use shall not be a source of microbiological contamination of the spacecraft atmosphere and structural elements and shall not create a propitious environment for microorganism development and shall be resistant to biodegradation d Operation in vacuum SE located outside the pressurized cabin of the spacecraft shall be resist
54. of scientific equipment installed on MRM2 1140463 4 4 Mini Research Module 1 1 Characteristics launch mass kg 7900 pressurized volume 17 4 storage volume for cargoes and scientific equipment m 5 in particular for scientific equipment 3 0 power for scientific equipment kW up to 0 1 maximum daily average rejection of heat from the hardware included the MPF through the air loop of the thermal control system kW up to 0 1 Jaunch vehicle Space Shuttle Orbiter MRM I external appearance is shown in Fig 4 4 1 RGF Airlock Radiative heat echang Docking target Docking TV camera P lt LAM d A 7 i f iU 4 5 ont X Ww 5 M1 v gt a E mm E 7 7 gt 5 Qv gt PE Y b 1 al gt e e lt 4 a 4 3 D A 2 arid ww gt 7 i I EC PVGF gt a MA 3 E 2 t gt p 4 W Acti docki it c H 7 Fig 4 4 MRMI external appearance B3aM
55. safety both for the crew and for other hardware on the vehicle 6 3 1 2 During its operation and storage the SE shall not crate dangerous situations or the risk of such situations occurring shall be minimized The dangerous situations as applied to SE are classified according to the hazard level as follows Critical Hazard The hazard which if it occurs may result in such damage to the vehicle equipment as does not preclude its further operation or in a nondisabling injury to the crew or in the need to use unplanned procedures which affect the operation of onboard systems of the Russian spacecraft Catastrophic Hazard The hazard which if it occurs may result in the loss of the vehicle or in a disabling or fatal injury to the crew 6 3 1 3 Development of SE and its utilization operations shall meet the following requirements in order to minimize the risk of occurrence of hazardous situations 6 3 1 3 1 Tolerance to failures resulting 1 dangerous situations SE shall be designed in such a way that no combination of two failures or two operator errors or one failure and one operator error can result in a catastrophic hazard no single failure or single operator error can result in a critical hazard 6 3 1 3 2 Design for Minimum Risk This requirement consists in assuring selecting the necessary safety factors scope of developmental and verification tests to assure high strength properties survivability resistance to va
56. standard CENE 1140463 m Container cover S amp in open position SSS gt N 880 100 470 INL Pa 300 Container cover Fig 6 6 11 Cargo container in the descent vehicle of the Soyuz TMA spacecraft in open position 320 E H ol ea T a _ f f 1140463 Attachment A obligatory List of Acronyms OI TS Onboard information and telemetry system Onboard cabling system BKC soon _ Trajectory and navigation support IU Interface Unit b TM IU Telemetry array interface unit b b C bHO P Passive Basepoint K H C j T Payload Basepoint Multipurpose vibration isolation platform EVA Extraveh
57. the SM working compartment generated by the continuously operating onboard equipment according to in flight acoustic measurement results are in the central station area 65 67 dBA in the wider part of the working compartment 64 65 dBA in crew cabins with fully closed doors 52 55 dBA It should be kept in mind that the controlled noise levels shall correspond to a mode where only continuously operating onboard equipment 15 working in normal operational mode in the absence of noises from intermittent sources and in the absence of any noise generated by crew members It should be noted that the noise generated by crew activities 1s not controlled in any way at all 6 5 2 Acoustic environment in DC DC design allows the crew to stay in it for short periods of time Based on the results of ground pre flight acoustic tests the noise level in the central part of was 70 dBA There were no plans to implement measures to reduce levels inside 1 In flight acoustic measurements produced lower values 140463 66 68 dBA which may be due to a change in acoustic properties of the internal volume of the module resulting from the fact that 1t 1s partially cluttered up with various objects especially soft objects During ground tests the module was empty 6 5 3 Acoustic environment in MRM2 MRM2 design allows the crew to stay it for short peri
58. to study the feasibility of its accommodation onboard the spacecraft a documentation package 1s to be submitted which contains 6 6 1 1 For all cargoes E A 5 z envelope and installation drawing transportation safety data package accompanying documentation No with agreements between RSC Energia and the cargo owner on its integration and delivery including electrical interface including electrical consumption heat release cargo operations timeline special requirements activation telemetry etc Requirements for envelope and installation drawing are given in paragraph 6 7 1 6 6 1 2 For active cargoes additional documentation 15 provided in accordance 140463 No Requirements for transportation safety data package are given in paragraph 6 7 2 Requirements for accompanying documentation are given in paragraph 6 7 3 The cargo owner 15 responsible for validity of provided data and for cargo compliance with the specified requirements Cargo delivery removal and return are only performed in case of positive results of RSC Energia s studies of cargo compliance with the requirements and feasibility of their accommodation and fastening The studies are conducted on the basis of the documentation provided by the cargo owner curator 6 6 2 Project Man
59. to be set in accordance with Table 6 2 5 3 E Table 6 2 5 Equipment cyclic loading spectrum Operational number of acceleration gt Acceleration level 2 cycles 100 90 100 gt 90 80 200 80 70 700 2 70 60 800 60 50 950 50 40 1 150 5 40 30 1 500 E 30 20 6 49E 6 1 40E 7 5 E 2 1140463 Operational number of acceleration Acceleration level cycles 15 10 Dal fear 10 2 5 9 05 7 In this case 100 percent loading level is to be assumed to be equal to the maximum loading level specified paragraph 6 2 2 1 2 As the equipment operational life increases the number of loading cycles rises 1n proportion to the increase in operational life 6 2 3 Microgravity 6 2 3 1 Microgravity environment in RS modules In accordance with Basic Requirements for ISS RS 27 0000 during ISS microgravity flight modes which per specification SSP41163 shall be maintained for 180 days per year in continuous 30 day intervals RS modules provide the following microgravity environment quasi static accelerations frequencies 0 01 Hz of no more than 4 microg Quasi static acceleration in excess of NASA requirements is due to a disadvantageous position of the RS research modules with respect to the ISS center of gravity root mean square vibration acceleration levels in 1 3 octave frequency subranges gt ol Z e T
60. um En trie 1140463 5 Cargo certification One of the essential conditions for integrating scientific equipment into Russian spacecraft and ISS RS 15 to certify the scientific equipment the scientific equipment hardware delivered by Russian transportation spacecraft to ISS RS shall be certified for transportation functioning onboard the spacecraft and use onboard ISS RS that 1s the hardware shall comply with the current requirements levied upon the hardware by the Russian spacecraft and ISS RS All the activities on the implementation and verification of compliance with the current requirements for the scientific equipment and proving its flightworthiness are subdivided into the following groups which correspond to the step by step process of development verification and certification of the scientific equipment a development of scientific equipment to meet the specified requirements b verification of the scientific equipment to check and confirm that requirements specified for the equipment have been met Verification includes tests calculations analyses etc Requirements for hardware are given in paragraph 5 5 c analysis of verification results verification of equipment characteristics compliance with the specified requirements evaluation of hardware flight readiness development and publication of certification documents E
61. 5 Transportation up to 90 Assembly and testing 20 80 On the launch pad for cargoes 20 65 Orbital flight for cargoes when the crew 15 not present 20 80 Orbital flight for cargoes when the crew 15 present 30 75 After descent vehicle landing for cargoes up to 98 A rise up to 90 for as long as 3 hours a day 15 possible 6 1 2 4 Pressure Absolute pressure of the gas medium inside pressurized compartments through all the phases of ground processing 15 the atmospheric pressure and through all the mission phases it may vary within 450 970 mm Hg The vacuum outside the spacecraft in the cargo compartment of Progress spacecraft when conducting experiments requiring its depressurization or when cargoes are located on the outer surface of the spacecraft is at 107 10 mm Hg In case of depressurization of the cargo compartment or the descent vehicle of Soyuz the cargo may stay at a pressure as low as 10 mm Hg for as long as 10 gt ol Z e T S hours The maximum pressure drop rate is 100 mm Hg s 1140463 6 1 2 5 Radiation exposure Radiation exposure requirements for Progress and Soyuz spacecraft are defined in SSP 50094 Subsection 3 6 To evaluate exposure to external radiation sources the following values are assumed to characterize the protection during Progress missions for elements inside the compart
62. 6 2 3 Sine wave vibration modes gt 2 e T S Vibration acceleration Time of application in Frequency range Hz amplitude 2 each direction s Notes 1 The modes listed in the table correspond to the qualification test levels 2 Vibration acceleration values vary linearly between frequencies 3 The time of application of vibration acceleration frequency subranges 15 specified in the tests using the method of smooth variation of frequency T 140463 Table 6 2 4 Random vibration modes Frequency Hz Time of each Vibration acceleration spectral density g Hz direction s Notes 1 The modes listed in the table correspond to the qualification test levels 2 The values for spectral densities between the above frequencies vary linearly with logarithmic scale for frequency and spectral density If need be the above vibration modes for an individual piece of equipment can be updated to take into account its specific location on the ISS RS 6 2 2 1 2 Dynamic and cyclic loading of the equipment during in orbit storage and operation within ISS RS The structure of the equipment installed inside and outside the ISS RS modules shall be capable of withstanding inertial loads caused by forces acting on the ISS structure contact forces from dockings and undockings of various spacecraft forces generated by operation of control system effectors
63. 7 pcs when deliverable Multi Purpose Workstations MPWs taken into account payload data downlink capacity maximum via TM IU unit up to 2 MB per a session E gt Z T 155 attitude control mode nominal Orbital Coordinate System 5 ISS OCS attitude control accuracy 10 angular minutes ISS angular rate stabilization accuracy 0 005 deg s the number of telemetered parameters up to 212 SM up to 50 MRM2 and up to 36 1 the list of electrical interfaces available RS 232 RS 422 only on SM RS 485 only on SM 1 140463 Ethernet USB HF with wave impedance of 75 Ohm and 50 Ohm only on SM discrete control commands on SM and MRM2 the number of vaccumization interfaces for MPF 1 pc on MRM2 and 1 pc on MRMI The MPF cargo traffic to ISS RS 15 planned based on the following assumptions delivery of cargo to ISS RS onboard Progress M M1 logistics spacecraft on average up to 600 kg per year return from ISS RS of up to 110 kg of payloads per year The external appearance of ISS RS in the above configuration 1s shown in the figure ci Ft A 5 z E 140463 IWAN TWAN WS JO Sunsisuoo uonemsruoo SA SSI STA VIAL 21406 5524804 55946044 eLel
64. ISS 6 1 Specifications for equipment transported in Russian spacecraft Progress and Soyuz 6 1 1 General These requirements are applicable to all the cargoes delivered to ISS in Progress and Soyuz spacecraft to all the waste and cargoes removed from the station for disposal inside Progress cargo compartment or Soyuz orbital module as well as to cargoes returned to Earth inside Soyuz descent vehicle The document contains requirements for all the phases of transportation and for the spacecraft ground processing phase the transported cargoes shall meet the requirements of the normal operating conditions described in this Section In off nominal situations including depressurization cargoes shall remain fire and explosion safe nontoxic leakproof gases liquids biological samples and preserve its mechanical integrity meet safety requirements for crew and spacecraft equipment There are no requirements to assure cargo functioning after an off nominal situation In accordance with the conditions required onboard spacecraft for cargo delivery all the cargoes are subdivided into E A 5 z active cargoes which require for their transportation connections to the spacecraft onboard systems power supply system thermal control system No telemetry etc passive cargoes which do not require for their transportation any connections to the spacecraft onboard systems 6 1
65. Lens Nikkor 14 24 mm Telephoto lens AF S Nikkor 600mm f 4 Telephoto lens AF S Nikkor 400mm f 2 8 Telephoto lens Nikon TC 14E Telephoto lens Nikon TC 20E Telephoto lens Nikon TC 17E SM FOTO D3 X TC 17 10 1 2 3 4 5 p Flash lamps Flash lamp Nikon SB 800 SM FOTO D2X U03 Battery chargers Battery charger for camera Nikon D2X SM FOTO D2X U05 Battery charger for camera Nikon D200 SM FOTO D200 U05 Power supply units Storage battery Nikon EN EL4 SM FOTO D2X U06 6 E gt Z T Storage battery Nikon EN EL4a SM FOTO D2X U06 Accessories L T T 140463 Remote control cable SM FOTO D2X 02 Flash lamp synchronizer 5 SM FOTO DI1 X U08 Adapter SM FOTO D1X U09 2 for the bracket PC CARD ADAPTER PCMIA adapter Photographic equipment cleaning kit SM FOTO DI UI2 Battery handle for SM FOTO D200 U06 01 camera Nikon D200 MB D200 SM FOTO D1X U10 2 Power supply units container SM FOTO D200 U04 2 Stereo adapter PENTAX SM FOTO D200 SA 1 PENTAX A bracket for stereo imaging through a SM FOTO D200 BR Adapter ring stereo adapter SM FOTO D200 SA R porthole Photographic equipment 15 self contained and 1s not connected to the onboard power supply line Chargers for storage batteries of the Nikon camera are hooked up to connectors on the LIV video system S
66. R Z1 SM HDV U0O1 Camcorder Sony HVR Z7 SM HDV U10 2 Lens Fujinon HAs18x7 6BRM 137mm SM HDV U11 Adapter ACM 17 SM HDV U12 Camera light Sony HVL LBP SM HDV U14 2 Wide angle attachment x0 8 Sony VCL SM HDV U02 HG0872 EE Battery Sony NP F970 SM HDV U03 1 1 1 1 1 1 Video cassettes Sony PHDVM 63DM SM HDV U04 14 1 i 1 1 1 1 1 7 10 5 E gt Z T 2 18 Adapter BNC BNC 1 T7 140463 J Q lt Bem uo Adapter to bracket LIV 106 20 From LIV 106 20 to LIV video camera Adapter iLink for MRU SM HDV UI5 Cable iLink 6p 4p 2m SM HDV 11 External appearance characteristics and possible uses of the above video camera are given in Fig 3 9 3 3 9 4 Video camera Sony DSR PD150P External appearance characteristics and possible uses of the above video camera are given in Fig 3 9 4 E gt AL ol 2 T 140463 Ne Camcoder Sony 71 contains a high resolution video camera with 3 CCD matrices and HDV video recorder It can be installed onto a bracket for securing it to the SM handrails The camera can be equipped with a wide angle attachment x0 8 Sony VCL HG0872 The camcoder can work in PAL and NTSC systems as well as in HDV DV
67. S P Korolev Rocket and Space Corporation Energia ISS Russian Segment User Manual E gt ol Z e T 2011 Table of Contents DENCE OG NC CO MR 8 3 Z Ground 4 3 General data on the ISS RS resources at different stages of its deployment 5 3 1 ISS RS consisting of SM and 5 3 2 ISS RS consisting of SM and 2 8 3 3 ISS RS consisting of SM DC1 MRM2 and 11 3 4 ISS RS consisting of SM MRM2 MRM1 14 3 5 Characteristics of communication links and downlinking 17 3 6 Trajectory and navigation support for space experiments 19 3 7 The list of photographic and video equipment onboard ISS RS 22 3 8 Equipment for still photography 23 35 9 Video dE 30 4 Capabilities supporting scientific equipment operation 155 RS modules 37 service module C MD o RU 37 4 2 Docking compartment No 1 54 4 3 Mini Research Module 2 2
68. SM and up to 0 2 m on 2 power supply on SM and DCI up to 0 3 kW daily average and up to 1 kW for 2 days with continuous additional normal power supply to ISS RS from the US segment in accordance with operational documentation on up to 0 1 kW daily average heat rejection capacity up to 0 3 kW daily average the balance 15 achieved taking into account the heat loss through the SM hull the number of workstations on the outer surface 4 pcs on the SM 8 pcs when deliverable Multi Purpose Workstations MPWs are taken into account 5 pcs 7 pcs when deliverable Multi Purpose Workstations MPWs taken into account payload data downlink capacity maximum via TM IU unit up to 2 MB per a Session ISS attitude control mode nominal Orbital Coordinate System OCS ISS OCS attitude control accuracy 10 angular minutes ISS angular rate stabilization accuracy 0 005 deg s the number of telemetered parameters up to 212 SM and up to 50 MRM2 gt AL ol Z T the list of electrical interfaces available for RS 232 RS 422 only on SM RS 485 only on SM Ethernet USB HF with wave impedance of 75 Ohm and 50 Ohm only on SM discrete control commands the number of vaccumization interfaces for MPF 1 pc on MRM2 140463 8 The MPF cargo traffic t
69. a way that the normal to the line connecting the centers of cross sections of the two central handrails is slanted at an angle of 47 from plane I towards plane II The scientific equipment 15 fastened onto the handles with special locks each of the workstations VPM H3 15 formed by four threaded M12 holes with the base of 400 x x200 mm located in the payload fairing supports on the outer surface of the SM along planes II and IV between frames 8 8a respectively Scientific equipment 15 installed using adapters the Deliverable Multi Purpose WorkStation DMPWS 17KC 600IO 1501A 0 is installed on VPM H3 DMPWS consists of a base 17KC 600IO 1501A 100 with pP T 11 T 140463 PBP and a platform 17KC 600IO 1501A 200 with three passive parts of scientific equipment adapters 17 600 1150A 0 and a mating device 27KCM 152IO 7110 0 for installation onto a PBP Normals of the three passive adapters installed on the platform shall be aligned with axes Y sm and Zsm Installed on the VPM H4 under flight test conditions can be a deliverable workstation developed with the use of design solutions implemented in the design of the DMPWS The following volumes are reserved for installation and connection of scientific equipment inside the pressurized cabin of the Service Module on the backside of panel 407 YPM4 3 zone for scientific equipment with dimensions of up to 175x400x60 mm behind panel 305 YPM4 2 zone for scient
70. agement Cargo integration project management consists of the following steps 1 reviewing and approving the documentation package on the cargoes manifested for delivery on a specific spacecraft active cargoes require matching the interfaces 2 engineering analysis development of the configuration for cargo accommodation in the compartment meeting the requirements for mass centering and inertial properties of the spacecraft and conditions for cargo delivery fastening in flight attitude etc and the conditions stipulating that the equipment in the compartments shall not interfere with the crew operating controls and using life support equipment 3 physical integration building up kits accommodating and securing cargoes in the spacecraft compartment 6 6 3 Cargo accomodation 6 6 3 1 General The cargos are arranged within the compartments in such a way as to meet the requirements and constraints of the vehicle and of the cargoes themselves and this arrangement is covered in the vehicle design documentation Cargoes are installed onboard the spacecraft using RSC Energia drawings and design and operational documentation contingent upon availability of certificates _ __ __ __ 1140463 for transportation and operation and the installation 1s covered in the onboard documentation for the vehicle the operations to service and process the deliverable cargoes at the processin
71. al Orbital Coordinate System OCS ISS OCS attitude control accuracy 10 angular minutes ISS angular rate stabilization accuracy 0 005 deg s 140463 the number of telemetered parameters up to 212 SM up to 50 MRM2 up to 36 MRM1 up to 323 MLM the list of electrical interfaces available for MPF RS 232 RS 422 on SM and MLM RS 485 on SM and MLM Ethernet USB MIL STD 1553B only on MLM HF with wave impedances of 75 Ohm and 50 Ohm on SM and MLM discrete control commands SM MRM2 and MLM the number of vaccumization interfaces for MPF 1 pc on MRM2 1 pc MRMI 2 pcs on MLM the number of thermostatting interfaces for MPF 2 pcs on MLM The MPF cargo traffic to ISS RS is planned based on the following assumptions delivery of cargo to ISS RS onboard Progress M M1 logistics spacecraft on average up to 600 kg per year return from ISS RS of up to 110 kg of payloads per year The external appearance of ISS RS in the above configuration 1s shown in the Figure gt ol Z aal T 140463 WTN Pue TIWAN TWAN WS JO 3011515000 uoneansirjuoo SY SSI VIAL 2n amp oq VIAL 21406 1140463 552180414 0 MOYO 3 5 Characteristics of communication links and downlinking The preliminary design calls for e
72. al characteristics of the spacecraft Published 1 5 months before the launch of the spacecraft by specialists on the spacecraft are engineering drawings and documentation on cargo installation and the results of the analysis of cargo mass inertial and center of gravity properties of the spacecraft No later than 1 month before the launch the cargo is to be delivered to the processing facility where it will then be physically integrated into the vehicle E A 5 z Fig 6 5 3 shows the process of deliverable cargo integration into Soyuz spacecraft No 140463 Cargo data are submitted and DD yer is developed for cargo accommodation in the spacecraft Tories emen m to 979 processing facility Physical rmm M of aa WW Fig 6 6 3 The process of iube cargo into Soyuz spacecraft Physical integration of cargoes into Soyuz spacecraft Fig 6 5 4 shows the process of physical cargo integration into Soyuz spacecraft _ en the main load of en E NR cargoes additional deliverable cargos iji B Loading additione Mn nd t the la bends unch pad E gt FL ol 2 e T Fig 6 6 4 The proc
73. ant to exposure to heat and vacuum and shall not be a source of contamination of the space around and inside the module under normal environmental conditions Non metallic materials as well as coatings used for sealing and insulating electrical circuits shall be tested for mass loss and volatile matter content under exposure to heat and vacuum and have mass loss of no more than 1 and volatile matter content of no more than 0 1 Thermooptical properties of the surfaces of the SE located outside the pressurized cabin of the vehicle shall not affect the vehicle safety exceed the allowable thermal conditions as well as create glare or flood exposure of light sensitive elements of the vehicle E A 5 z 6 3 2 2 Structure 6 3 2 2 1 SE structure shall be designed taking into account actual loads and safety factors accepted for the vehicle No 6 3 2 2 2 Materials used for the SE structural elements including fasteners shall be reviewed for corrosion cracking under stress fatigue strength As far as possible alloys with high resistance against stress corrosion cracking shall be used 6 3 2 2 3 SE structure shall be designed for maximum differential pressure occurring during ascent descent or activities involving emergency depressurization and subsequent re pressurization of the vehicle ISS The vents in the vented compartments shall have such surface areas as to assure structural integri
74. ata are recorded on cassettes One cassette holds 40 minutes of recording Fig 3 9 4 Video camera Sony DSR PD150P 4 Capabilities supporting scientific equipment operation on ISS RS modules 4 1 Service module CM The following interfaces with the module are used during integration of the scientific equipment into the SM mechanical interface electrical interfaces including power interface telemetry interface data interfaces thermal interface vacuum interface connection to external environment The SM design provides for a number of areas for installing the scientific equipment in orbit which have structural support for mechanical attachment and connections of the scientific equipment to the ISS support systems Such areas outside the SM are the workstation located on the SM outer surface along plane III of the Working Compartment 1 between frames 3 4 Installed on the SM body on the transition plate 17KC 300101573 0 as a mechanical device for fastening scientific equipment if a Passive Base Point PBP 27KCM 152107200 0 Scientific gt A 5 z Equipment 15 installed by an operator during EVA onto PBP using an adapter which includes an Active Base Point ABP 27KCM 152107100 0 workstation VPM H2 formed by a system of handrails 25x25 mm in cross section on the body of SM Working Compartment 2 between planes I and in such
75. ated FL A outside 155 RS for which radiation hardness parameters are specified the form of spectral characteristics No 6 2 6 2 Absorbed doses of space electrons and protons for materials and equipment located inside ISS RS per 1 year of flight tests for various values of mass thickness of a spherical shielding under exposure to omnidirectional irradiation solid angle 47 are listed in Table 6 2 6 2 1140463 Table 6 2 6 2 Mass Absorbed dose rad year 3 0E 01 5 0E 01 7 0E 01 1 0E 00 2 0E 00 3 0E 00 5 0E 00 1 0E 01 2 4E 03 1 1E 03 5 9E 02 2 4E 02 9 0E 00 1 6E 00 1 0E 00 6 2E 01 2 5 03 1 2E 03 6 5E 02 3 0E 02 5 8E 01 4 4 01 3 5E 01 2 4E 01 6 2 6 3 Absorbed doses of space electrons and protons for materials and equipment installed outside ISS RS per 1 year of flight tests for various values of mass thickness of a spherical shielding under exposure to unidirectional irradiation solid angle 27 are listed in Table 6 2 6 3 Table 6 2 6 3 Mass Absorbed dose rad year FL A 4 0E 05 7 3E 04 9 3E 03 5 2E 03 2 8E 03 8 7E 02 1 8E 02 4 3 05 7 4E 04 9 4E 03 5 3E 03 2 8E 03 9 1E 02 2 0E 02 6 2 6 4 All radiation doses shall be recalculated for the specified duration of flight tests of instruments and equipment assuming
76. c Solar cosmic MeV cm mg minimum flux averaged over an rays total rays peak orbit particles cm days flux flux particles cm particles cm d ays 7 0E 01 7 5E 08 1 6E 02 1 6E 02 9 0E 01 6 0E 09 1 4E 03 1 4E 03 Table 6 2 6 5 provides differential energy spectra for protons Table 6 2 6 5 Differential energy spectra for proton sources Earth radiation belts at Earth radiation belts at Solar cosmic rays solar minimum flux solar minimum peak peak flux averaged over an orbit flux at SAA protons cm day M protons cm day MeV _ protons cm days MeV eV 9 2 05 1 1 06 1 1E 06 8 4E 05 5 5 05 2 6 05 3 5 04 4 8E 03 FL A 6 2 7 Requirements for materials The below requirements apply to all materials listed 1n the full list of nonmetallic materials The full list of nonmetallic materials which are in contact with the pressurized cabin atmosphere includes structural materials used in fabrication of casings fasteners circuit boards covers sheathes etc varnishes paints compounds adhesives insulating materials for wires cables harnesses The list has the official document status and must be signed by a responsible representative of the international partner 6 2 7 1 Materials fire safety Materials shall not be capable of spontaneous ignition
77. ce of 1000 Ohm use shall be the subject of a special discussion and agreement with RSC Energia 6 3 2 5 Living space safety SE shall not be the source of elements contaminating internal compartments of the vehicle To assure the cleanliness of the living space inside the compartments 6 3 2 4 Radiation safety All the SE elements which produce ionizing radiation shall be identified and their LE ug _ S S 1140463 liquid loose and paste like substances shall be contained within a reliable sealed package The SE structure shall guarantee that the amount of outgassing will not exceed maximum allowable concentrations that 15 the gas composition will not be disturbed SE shall not be a source of strong smell The acceptable noise level during SE operation shall not exceed 65 dBA at the distance of 1 m 6 3 2 6 Non ionizing radiation The use of SE containing sources of laser radiation as well as containing permanent magnets shall be agreed with RSC Energia 6 3 2 7 In flight handling safety 6 3 2 7 1 SE shall have interlocks to prevent inadvertent operation or a change in configuration caused by crew actions during handling For example locking of switches can be achieved by means of protective covers If need be onboard documentation instructions for the crew shall be prepared E A 5 z 6 3 2 7 2 SE external structure and packaging shall have no sharp or protruding elements
78. ce with the transportation environments and transportation safety requirements the owners of these cargoes need to prepare a transportation safety data package to reflect compliance with requirements of Section 2 5 Information about cargo hazards is considered complete if each hazard in the transportation safety data package has hazard description measures to prevent the hazard methods of safety verification and documentation with verification results Cargo ground processing safety is reviewed separately from transportation safety therefore it shall not be covered in the transportation safety data package 6 6 7 3 Requirements for accompanying documentation E A 5 z Accompanying documentation 1s submitted to RSC Energia in Russian and in English No Accompanying documentation contains technical data sheet cargo processing instructions 1 need be instructions for the crew 1f need be The list of accompanying documentation for an active cargo 15 TBD in consultation between RSC Energia and the country supplying the cargo The technical data sheet contains the name the drawing number the serial number the useful life as well as confirms that cargo has been fully processed and is operational verification report complies with specifications and 15 ready for flight operation within the ISS The technical data sheet 1s published for each item
79. d clearly defining its functions To be checked are logic functions of the device as a user of a data network controller or slave device the impossibility for the user to corrupt formats and data content in an interface unrelated to the user correctness of the user response to the set of commands contained in the interface software interfaces between newly added equipment and the user providing protection of RS systems against off nominal situation To be checked in such an interface belonging for example to a laptop computer are hardware protection against false and invalid commands and operator s instructions The equipment shall be checked in real onboard environment in order to obtain actual measurement results from the flight model of the onboard cabling against the background of active operation mode of the onboard systems over applicable E A 5 z interfaces In verifying compliance with data security requirements a special emphasis No should be placed on standard interchangeable components and storage medium containing installation or autorun software cartridges hard drives floppy disks be in place to guard against their unauthorized use in the RS equipment To be checked 15 whether the protection 1s in place against unauthorized launch of software and its installation in RS computers corruption of basic software of the RS equipment supporting control system
80. dow on the display screen to promptly calculate predict when and how well a specified area on the Earth surface 1s going to be visible from the space station within the interval of time covering the next 16 orbits to a week Coordinates of a region can be specified by means of an arbitrary point immediately on the screen itself on the map or selected from any pre prepared list of objects The trajectory and navigation support software includes lists on the following subjects ecology geology etc Selecting an item on these lists can be done by typing the name of the desired item on the keyboard The visibility can be calculated for several targets at the same time with subsequently displaying the data on what targets are visible during the current orbit Also calculated are the coverage areas of the specified ground stations to evaluate reliability the level of likelihood of detecting and identifying the known feature a group of features or a sector of the terrain in the observed region taking into E gt Z T account geographic and meteorological observation conditions The evaluation takes region under observation The cloud cover intensity 1s automatically evaluated based on monthly average values or is set manually based on real time data Evaluated automatically 1s also the number of observations which need to be planned in order to identify the desired feature
81. e ventilation system air conditioning system system for filtering harmful contaminants from the air thermal control system Immediate sources of continuous noise are such elements of these systems as fans pumps compressors electrical drives for various purposes mechanically operated controllers etc There are no international standards for noise levels inside habitable compartments of spacecraft In Russia there 1s a currently operating standard GOST R 50804 95 Crew Habitable Environment in a Manned Spacecraft General Medical and Technical Requirements recommendations of which as applicable to the International Space Station became a constituent part of Russian US standard Joint NASA RSA Document On Specifications And Standards For The ISS Russian Segment SSP 50094 which was put in force in 1996 Used as the unit for evaluating human exposure to noise usually 15 the level L4 measured in decibels with scale A correction dBA which corrects for non uniformity 1n an average human s hearing acuity for sounds with the same level at E A 5 z different frequencies within the audible range It should be noted that the noise level L4 does not always give a precise characterization of the noise perception and only serves as its approximate criterion For missions lasting more than 30 days SSP 50094 establishes maximum methods of their measurement According to SSP 50094 noise f
82. e also taken into account during qualification tests Minimal safety factors are set in accordance with Table 6 1 3 4 When the structure 1s exposed to a combination of forces for the loads increasing the strength gt ol Z e T S margin the safety factor is set at f 1 Loads increasing the strength margin determined during strength analysis 1140463 Table 6 1 3 4 Loads per paragraphs Value of safety factor f no less than 6 1 3 3 1 1 5 6 1 3 3 2 1 4 6 1 3 3 3 1 3 6 1 3 3 4 2 0 6 1 3 3 5 a b c 1 5 In the course of strength analysis an additional coefficient K 1s introduced which is a multiplier for the safety factor for fasteners for example bolts screws taking into account a pre torque 1 25 for critical fasteners having a complex geometric shape for example brackets fittings 1 25 when using materials having a high spread in strength properties or a significant anisotropy for example engineering plastics K 1 2 6 1 3 5 Vibration and acoustic tests 6 1 3 5 1 Vibration and shock qualification tests are conducted at levels that are at least as high as those given in paragraph 6 1 3 gt ol Z e T S 6 1 3 5 2 It is allowed to replace random vibration tests per Table 5 with sine tests are increased by no less than 3 dB and the exposure duration by no less than a factor of 4 but no l
83. e or aperture having higher priority and manual Optical exposure measuring area Matrix centrally weighted spot measurement TRO Bracketing mode 2 9 frames with incremental steps of 1 3 2 3 or EV 00000 Poser Dmeim 0 NNNM E gt AL ol 2 T 140463 Additional characteristics external appearance and purpose of the above cameras are shown in Fig 3 8 1 1 3 8 1 2 gt FH Z T Fig 3 8 1 1 External view of still camera Nikon D3 Nikon D3X IL 140463 Ton FL x gt No Fig 3 8 1 2 External view of still camera Nikon D2 _ __ Ll _ _ __ 1140463 3 9 Video equipment 3 9 1 LIV system specification LIV system is based on professional equipment operating in analog format BETACAM SP Fig 3 9 1 1 shows the video camera included in this system and Table 3 9 1 1 LIV system performance data for Earth imaging f rom the altitude of 400 km using the lens Fujinon 16 9 28 the lens is currently onboard ISS RS Fig 3 9 1 1 Overall view of the LIV system video camera Table 3 9 1 1 LIV system specification
84. e scene which 15 important during interpretation and analysis of the features on the ground The overall view of the HDTV camera 15 given in Fig 3 9 2 1 E 140463 It should be noted that the filming results can only be returned to Earth on a recording medium HD video cassettes The existing capacities of the ISS RS RF links do not support downlinking of the filming results At present the Russian side has neither the equipment for ground processing of the information nor the capabilities to review and copy video materials obtained in the course of the HDTV system operation c H Fig 3 9 2 1 Overall view of the HDTV camera No 3 9 3 video system The video system 15 intended for performing the following tasks video recording of the experiments video filming inside the SM video filming of the Earth The equipment includes camcorders Sony HVR Z1 and Sony HVR Z7 of the HDV digital format Using an adapter to the bracket LIV 106 20 the camcorders can be To 1140463 installed on the bracket order to fasten them to the SM handrails The kit also includes a wide angle attachment x0 8 Sony VCL HG0872 Sony batteries NP F970 a lamp Sony HVL LBP video cassettes Sony PHDVM 63DM set of cables and adapters The list of equipment Table 3 9 3 1 Table 3 9 3 1 Camcorder Sony HV
85. ed above 6 3 2 7 5 Screws and bolts Bolts and screws with threaded parts may protrude by 2 3 mm but by no more than 1 turn of the thread and have means of protection which do not interfere with installation or removal of the bolt or the screw Fasteners shall be captive 140463 6 3 2 7 6 Moving parts Moving parts fans belt drives turbine wheels etc which may cause crew injury or damage to SE through inadvertent contact or capture shall have guard rails or other protective devices 6 3 2 7 7 Pitch or capture points Controls locks and other similar devices shall be designed and positioned in such a manner as to prevent them from pinching parts of the crew spacesuit If need be protective covers or enclosures shall be used SE hardware located outside habitable compartments which during its operation may produce a gap of less than 3 5 mm between the hardware and adjacent structures shall be designed in such a manner as to prevent pinching or capture of parts of spacesuit of a crew member performing an EVA 6 3 2 7 8 SE installation Internal and external SE located along the crew translation paths and installed in the working areas shall be able to withstand loads caused by crew activities including EVA E A 5 z 6 3 2 8 Chemical power sources batteries and storage batteries electrochemical cells No The s
86. ed outside the MLM instrumentation and cargo compartment 3 along Plane III Used for installing scientific equipment onto EMPWSS5 is a mating device ABP 27KCM 152107110 0 It is possible to install onto EMPWSS a multipurpose platform 17KC 600101501A 210 with active adapters 17 600 1151 0 allowing simultaneous installation of three payloads Used for installing scientific equipment onto the platform are passive payload adapters 17KC 600101152A 0 EMPWS6 based on a passive base point 27 152 7200 0 located outside the MLM instrumentation and cargo compartment 3 along Plane I Used for E gt ol 2 e T installing scientific equipment onto EMPWS6 is mating device 27KCM 152107110 0 It 1s possible to install onto EMPWS6 a multipurpose platform 17KC 600101501A 210 with active adapters 17 600 1151 0 allowing simultaneous installation of three payloads Used for installing scientific equipment onto the platform are passive payload adapters 17KC 600101152A 0 gp 1140463 EMPWS7 based on a support 77 600 1006 100 located outside the MLM pressurized adapter between Plane III and IV Installation of scientific equipment onto EMPWS7 is effected by means of a base for installing the scientific equipment onto a support 77 600 1006 200 EMPWSS based on a support 77 600 1006 100 located outside the MLM instrumentatio
87. ehicle Proton M LV To support scientific equipment installation MLM has provisions for installation of payloads inside pressurized cabin of MLM 16 internal multipurpose workstations with the total volume of the accommodation areas of no less than 8 m including a workstation equipped with a porthole for installing units of scientific equipment installation of no less than 12 simultaneous payloads outside the MLM pressurized cabin mechanical interfaces vacuum interfaces interfaces to provide thermostatic control for scientific equipment interfaces to supply scientific equipment with power from the MLM On board Equipment Control System command and data interfaces between scientific equipment and the MLM On board Equipment Control System payload operating conditions in required modes when conducting space experiments storing original materials and obtained results In addition to this to support a long term program of scientific and applied research MLM provides the following equipment vibration isolation platform 11 T i 1140463 glove box thermostats In order to minimize EVAs when installing scientific equipment on external workstations the following robotic equipment 15 provided ERA robotic arm automatic airlock AL The MLM external appearance is shown in Figures 4 5 1 and 4 5 2 External view of the airlock 1s shown in Fig 4 5 3 gt
88. ehicle is 620 mm The dimensions of the cargoes are determined during approval of the dimensional installation drawings for these cargoes Cargoes to be delivered can be secured inside Progress and Soyuz by means of flanges and bolts bands and straps putting cargoes inside containers Mass dimensions inertia properties of the cargoes to be delivered shall conform to the outline drawings approved by the Russian side 6 1 7 Packing requirements The packing used in flight shall preserve cargo integrity during transportation and storage within the transportation spacecraft The packing material used in flight shall comply with SSP50094 paragraph 4 3 4 gt ol Z e T S 1140463 6 2 Specifications for the equipment stored and operated onboard ISS RS 6 2 1 Medical and technical requirements for habitable environment 6 2 1 1 Atmospheric composition Maximum content of major components in the space station atmosphere in orbit volume 94 nitrogen up to 78 no more than 600 mm Hg oxygen up to 24 8 carbon dioxide up to 3 methane up to 0 5 hydrogen up to 2 0 helium up to 0 01 water vapor up to 3 up to relative humidity of 90 6 2 1 2 Harmful trace contaminants content The maximum content of harmful trace contaminants shall comply with Table 6 2 1 Russian standards correspond to zero risk US standards correspond to
89. ency range while having a Q factor for the cargo fasteners system of no more than 10 are in longitudinal direction nx 0 3 in lateral direction nx 1 2 in transverse direction 2 1 2 simultaneous exposure for 12 minutes 2 vibration loads for all spacecraft compartments in 3 mutually perpendicular directions in the form of sine vibration are given in Table 6 1 3 3 5 3 and at frequencies above 20 Hz in the form of random vibration are given Table 52 3 shock loads are given in Table 6 1 3 3 4 2 140463 4 operational loads for dynamic loads during docking with ISS are given in Table 6 1 3 3 4 3 Table 6 1 3 3 4 1 In the X axis direction In two other mutually Pulse duration perpendicular directions Load Number of Load Number of mes me 40 2 40 2 vehicle orbital module and cargo compartment gt 2 e T S r 140463 Table 6 1 3 3 4 2 Loads in the X axis direction Loads in two other mutually perpendicular directions Spacecraft Accelerat Numb Accelerat Numbe Pulse duration compartment The number Cycle ofloading duration cycles ms 6 1 3 3 5 During Soyuz descent and landing gt ol Z e T S 1 operational values for linear accelerations ny 0 6 n 0 1 duration 600 s including n
90. ent installed on the EMPWSS axis of sight pointed towards nadir of sight aimed at zenith Fig 4 5 5 field of view of scientific equipment installed on the EMPWS3 axis gp 140463 Fig 4 5 8 field of view of scientific equipment installed on the EMPWS6 axis of sight pointed towards nadir Fig 4 5 9 field of view of scientific equipment installed on the EMPWS7 axis of sight aimed at zenith Fig 4 5 10 field of view of scientific equipment installed on the EMPWSS axis of sight pointed towards nadir Fig 4 5 11 field of view of scientific equipment installed on the EMPWS9 axis of sight pointed towards zenith 08 90 oov 100 H gt ol e a Fig 4 5 3 field of view of scientific equipment installed on the 5 axis of B3aM sight pointed towards nadir ol ea S 111114 _ _ ___ 1140463 _ 1140463 sight pointed towards nadir _ __ ___ c H Fig 4 5 5 field of view of scientific equipment installed on the EMPWS3 axis of sight pointed towards nadir _
91. equivalent scale A corrected sound levels for continuous noise in the habitable compartments of manned spacecraft Mission duration of Sound pressure levels dB in octave Equivalent more than 30 days frequency bands noise levels and sound gt Z e T levels These noise levels are given as rounded values calculated for octave frequency bands expressed in dBA Center frequencies 63 12 25 50 Ik 2k 4 8k Hz 5 0 0 1140463 _ Taking into account additional intermittent noise sources the total level of sound per day measured in dBA and duration of exposure to it per day shall not exceed acceptable levels given in Table 2 with the equivalent level for the crew active period not exceeding 60 dBA gt 2 e T S r 140463 Table 6 5 2 Maximum acceptable sound levels over a 16 working period in habitable compartments and in locations where the crew stays for short periods of time during operation of additional noise sources depending on the time of exposure to them Maximum exposure time hours Total acoustic pressure level dBA over a 16 hour working period Acoustic pressure levels in octave frequency bands from additional noisy equipment delivered onboard the manned spacecraft not covered by e
92. ess than 120 s 6 1 3 5 4 G load qualification tests are conducted taking into account safety factors per paragraph 6 1 3 4 vibration per Table 6 6 1 3 5 3 Operational acoustic loads applied to the spacecraft during qualification 1140463 6 1 3 6 Microgravity Active cargoes that operate continuously or in the microgravity mode shall meet the requirements for microgravity conditions specified in paragraph 6 2 3 6 1 4 Electrical conditions and requirements for electrical equipment Electrical conditions and requirements are given for active cargoes which require connection to the spacecraft onboard power system Active cargoes are connected to the spacecraft onboard power system via four pin connectors to outlets rated at Progress LOA and 20 using a circuit breaker 6 1 4 1 Onboard power system voltage The spacecraft onboard power system provides DC power at 27 V 6 1 4 2 Bonding to protect against static electricity In order to assure that all the conducting parts of the cargo and the spacecraft have the same electrical potential all the electrically conductive structural elements need to be bonded that is have reliable electrical interconnections with E A 5 z contact resistance of no more than 2 5 mOhm No 6 1 4 3 Insulation resistance 20 MOhm at relative air humidity of 45 80 within the tem
93. ess wu cargo into m spacecraft The major portion of physical integration of deliverable cargo into the orbital module and the descent vehicle of the spacecraft 1s performed 30 12 days before the launch of the spacecraft Specific schedules for loading cargo within the El bah 140463 specified interval of time and the number of days allocated for physical integration is determined by the technical plan for specific spacecraft processing Within the time period of 8 5 days before the launch of the spacecraft during final operations after the spacecraft has gone through the filing station and payload unit assembly it 1s possible by the decision of the technical management to perform additional physical integration additional loading of deliverable cargoes of a limited mass and volume 2 1 days before the spacecraft launch it is possible by the decision of the RSC Energia General Designer to load additional kits of a limited size through the side loading hatch on the spacecraft The need to integrate cargo during that time period shall be stated when the cargo delivery request is submitted for inclusion the Manifest 6 6 4 3 Safety documentation submittal deadlines Deadlines for submitting transportation safety data packages for review are 3 months before launch for the first category cargoes non hazardous cargoes and second category cargoes the cargoes that are hazardou
94. fined in OCT 92 5100 89 and SSP 50094 A typical list of tests and verification activities under the programs of qualification tests and acceptance tests of the equipment 15 given in Table 5 2 1 For each type of tests a test procedure 1s developed OO O 1140463 Verified requirements Test Testtype Test verification subparagraph in Section 6 1 Check for missing items Requirements of design documentation for the scientific equipment 2 Inspection of the external Requirements of design appearance documentation for the scientific equipment 3 Dimensions check Requirements of design documentation for the scientific equipment 4 Checking mass and position Requirements of design of the center of gravity documentation for the scientific equipment 5 Packing check Requirements of design documentation for the scientific equipment Checks delivery set for missing items and completeness of technical and operational documentation The external appearance of the equipment 1s checked against outline drawing and it 15 checked whether logbooks and certificates are available and completely filled out To be checked are outline dimensions of the hardware center to center distances of mounting holes mounting holes dimensions Mass and center of mass position are checked against the developed outline drawings Verified requirements
95. g facility are only conducted subject to availability of proper instructions agreed with RSC Energia and under the supervision of its responsible representatives 6 6 3 2 Conditions for placing cargoes onboard Progress spacecraft The owner curator of the cargo shall keep in mind that after the cargo 1s stowed in the vehicle and until it is unstowed onboard the station there will be no access to it The duration of the above period depends on the conditions for stowing and installing cargoes onboard the vehicle Deliverable cargoes are stowed in containers designed for them and in free areas within the cargo compartment As a rule cargoes with a mass of 8 10 kg are stowed in the spacecraft containers if there are no special transportation requirements and cargoes with a higher mass are installed in special transportation racks for which purpose the deliverable unit shall have mounting fixtures The need to develop special mounting fixtures and packaging adapter racks shock E A 5 z absorbers thermal insulation moisture proofing etc is stipulated when the contract 1s concluded No 6 6 3 3 Cargo accommodation onboard Soyuz spacecraft are set aside for them As a rule cargoes with a mass of up to 5 kg are stowed in the spacecraft containers if there are no special transportation requirements and cargoes with a higher mass are installed in special transportation racks f
96. h Temperature Thermostat MBLT Multipurpose Biotechnological Low Temperature Thermostat 3 Heavy charged particles Ressuply spacecraft Phone Ultra short waves Ft A y MPW Multi Purpose Workstation MECTO PW Multi Purpose Workstation VPM I Deliverable Us System interface device y Passive restraint FGB Functional cargo module C Mission payload H Payload data Mission Control Center i M Moscow FE 140463 gt 2 e T S WK Airlock
97. he research methodology may change and scientific equipment may fail or become obsolete the MPF 15 based on the principles of unification and integratedness The unification principle calls for the use of replaceable payload technology which implies that virtually any kind of scientific equipment can be delivered and put into operation immediately in orbit In order to implement such technology the MPF will support installation adaptation of delivered SE built to meet the relevant requirements from the standpoint of mechanical electrical data and other interfaces SE control data support temperature control and vacuumization onboard ISS RS provided by the onboard support systems that are not included into MPF E gt 2 e T 140463 3 General data on the ISS RS resources at different stages of its deployment 3 1 ISS RS consisting of SM and DC1 Resources allocated to the MPF include the working volume allocated at SM and DC1 up to 1 power supply up to 0 3 kW daily average and up to 1 kW for 2 days with continuous additional normal power supply to ISS RS from the US segment in accordance with operational documentation heat removal capacity up to 0 3 kW daily average the balance 1s achieved taking into account the heat loss through the SM hull the number of workstations on the outer surface 4 pcs on the SM 8 pcs w
98. hen deliverable Multi Purpose Workstations MPWs are taken into account payload data downlink capacity maximum via TM IU unit up to 2 MB per a Session ISS attitude control mode nominal Orbital Coordinate System OCS ISS OCS attitude control accuracy 10 angular minutes ISS angular rate stabilization accuracy 0 005 deg s the number of telemetered parameters up to 212 the list of electrical interfaces available for MPF RS 232 RS 422 RS 485 gt AL ol Z T Ethernet discrete control commands the number of vaccumization interfaces for 1 pc The MPF cargo traffic to ISS RS 15 planned based on the following assumptions delivery of cargo to ISS RS onboard Progress M M1 logistics spacecraft on average up to 600 kg per year return from ISS RS of up to 110 kg of payloads per year USB HF with wave impedance coefficients 75 Ohm and 50 Ohm 140463 E gt AL ol 2 T external appearance of ISS RS in the above configuration is shown in Fig 3 1 140463 EN WS Jo 01515002 uonemnsruoo SA 55 T E SIA VIAL 2n amp og WW ss24804d 1140463 5 404 INS W SSa18 01g 3 2 ISS RS consisting of SM DC1 and MRM2 Resources allocated to the MPF include allocated working volume of up to 1 m on the
99. iclular Activity Ft A Pressurized adapter NEN Payload fairing r Galactic cosmic rays Cargo compartment KIIH MPF Mission Payload Facility Flight tests Information system A Space experiments II T r 1140463 ox LEI Linear energy transfer Mini Research Module 2 2 1 Mini Research Module 1 1 MLM Multi purpose Laboratory MJIM Module Micro meteorid shield SE T i PL O M M Message collecting module scientific Equipment M3 CC HA Ground tracking station Off nominal situation Orbital Coordinate System Instrumentation Cargo Compartment safety data package Software Payload Ft A
100. ific equipment with dimensions up to 220x350x300 mm The SM external appearance 1s shown in Figures 4 1 1 and 4 1 2 External multi purpose workstations on the SM for installing units of scientific equipment are shown in Figures 4 1 3 and 4 1 4 SM interior view locations of portholes laptops and mission payloads are shown in Figures 4 1 5 4 1 6 and 4 1 7 SM resources used for integration of scientific equipment are listed in Table 4 1 1 gt ol 2 e T 140463 MOIA WS SIA S 0 WS C Uv Sl 4 1140463 44 1M is ML 4 Be zr da EN 1H MPW N2 gt ol e T 2 4 Fig 4 1 3 External MPWS for installing scientic equipment units SM B3aM Ne 8 4 Lo E M or a Lx 2 EIL A 4 m us 140463 z ol S WS uo spun juouidimnbo ormuoros Sur ejsur 107 SM dW p Dp 914
101. ight pointed at zenith pO _____ 170 4gg 170 Fig 4 1 11 field of view of scientific equipment installed on the VPM H3 axis H gt ol e a of sight pointed towards nadir el e m z ise ea e EA H o H FL 1140463 2 5 fic equipment installed the axis 1140463 1 O om 2 5 z p amp un e 8 E lt D p A a Ri z ep 20 e WN 5 I 53 talled on the axis N 5 eO dem un gt 9 4 ET E x 5 2 U gt a Oo amp 2 n o a F E th gt D E 4 2 Docking compartment No 1 DC1 Special features that provides for conducting scientific experiments are capability to install hardware on the outer surface of MRM2 for observing the plane of the local horizon availability of a porthole with a capability to sight the hardware 1n the horizon plane capability to place hardware inside pressurized cabin for short periods of time for conducting space experiments and to store it onl
102. limited mass and volume 2 1 days before the spacecraft launch it is possible by the decision of the RSC gt ol Z e T S loading hatch on the spacecraft The need to integrate cargo during that time period shall be stated when the cargo delivery request is submitted for inclusion in the Manifest 6 6 4 2 Deliverable cargo integration into Soyuz spacecraft The work to integrate cargoes into Soyuz spacecraft starts 4 months before the scheduled launch of the spacecraft and 1s based on the cargo delivery Manifest Energia General Designer to load additional kits of a limited size through the side El bah 140463 4 to 3 5 months before the spacecraft 1s launched cargo outline and installation drawings are submitted to RSC Energia for approval Based on the results of the approval process for the cargo outline drawings the feasibility of delivering cargo onboard the spacecraft 1s determined and cargo delivery Manifest 1s updated 1f necessary 3 month before the spacecraft 1s launched final outline and installation drawings of the deliverable cargos are to be submitted to the RSC Energia specialists on the spacecraft 2 5 to 2 months before the launch the specialists on the spacecraft publish layout drawings for cargo accommodation inside the cargo compartment of the spacecraft and perform a preliminary engineering analysis of mass center of gravity and inerti
103. ll be provided by taking the following measures bonding the equipment that 1s providing a secure electrical connection between the cases of the devices and the body of the ISS RS modules removing static electricity from the operator during electronic equipment installation using an antistatic wristband connected to grounding points available in the ISS RS modules removing static electricity from onboard cables during their connection to electronic equipment by using a multipurpose device 17KC 300109052 0 6 2 8 2 Hardware bonding is provided by means of bonding straps equipped with which must be casings of the devices to be installed inside pressurized compartments The bonding is established by connecting a bonding strap to the device casing and to the body of the pressurized compartment by means of a fastener a screw or by mating disconnectable bonding straps E A 5 z It 15 acceptable to bond devices via an electrical interface with the ISS RS onboard systems where one of the electrical circuits which has galvanic coupling with the pressurized compartment body 15 assigned to serve as a bonding wire No 1140463 149 No 6 3 Safety requirements 6 3 1 General requirements 6 3 1 1 General requirements are applicable to SE design and development and are aimed at assuring the required level of SE
104. ltage at the hardware input shall remain within the 23 29 V range The on board automatic equipment of the module provides bipolar switching of the primary power supplied to the hardware as well as protection of power lines against possible overcurrent loads and short circuits the cabling and hardware El bah 140463 To assure an optimal selection of elements for power switching overload protection and of power cabling parameters the following inputs from the users are needed the number of power feeders and their purpose timeline for applying and removing power in each feeder under nominal and off nominal situations characteristics of each power feeder including the nature of the load resistive inductive capacitive power consumption watt ampere timelines for the equipment under all operational modes taking into account possible input voltage variations within specified limits parameters of possible inrush currents transient modes including inrush current amplitudes and their durations Acceptable values for inrush currents and their durations are additionally specified in each individual case and are agreed during development of electrical schematics for the equipment interfaces with the module control system In general inrush currents must not exceed the maximum steady state operating current multiplied by a factor of five In that case the duration of the current
105. ment located near to the hull 1 g cm during Soyuz missions inside compartments near the hull 1g cm and under the couches in the descent vehicle 3 g cm Radiation from the internal source inside the descent vehicle 1s a flux of gamma ray photons with energies of up to 9 7 MeV The dose rate does not exceed 0 1 rad day at the distance of 0 6 meters from the source the area under the couches 6 1 3 Mechanical loads 6 1 3 1 Coordinate systems Ground transportation X axis 1s parallel to the direction of transportation Positive direction of the axis 1s against the transportation direction Y axis is perpendicular to X axis The positive direction of the axis is up E A 5 z Z axis is perpendicular to axes Y and completes the right handed coordinate system No Orbital insertion and flight X axis 1s the longitudinal axis of the vehicle Positive direction 15 towards maximum loads during ascent Attachment 2 Y axis 1s perpendicular to X axis Z axis 15 perpendicular to axes X Y and completes the right handed coordinate system The XYZ coordinate system 15 rotated around X axis by 135 with respect to X Y Z coordinate system Descent vehicle reentry and landing X axis The positive direction 1s towards maximum loads DIT EE 1140463 denon 105 Y axis 15 perpendicular to X axi
106. n and cargo compartment 3 along Plane II Installation of scientific equipment onto EMPWSS 15 effected by means of a base for installing the scientific equipment onto a support 77 600 1006 200 EMPWSO based on a support 77 600 1006 100 located outside the MLM instrumentation and cargo compartment 3 along Plane IV Installation of scientific equipment onto EMPWSO 15 effected by means of a base for installing the scientific equipment onto a support 77 600 1006 200 EMPWS based on a passive fastener 77KMJI 820107360 0 located on the in and out table of the airlock Installation of scientific equipment onto EMPWSA 15 effected by means of payload adapter 77KMJI 600102200 0 The in and out table of the airlock also provides structural elements for securing payloads when conducting experiments in the extended position of the table sample fields of view of scientific equipment installed on the MLM multipurpose workstation are given in the following figures Fig 4 5 3 field of view of scientific equipment installed on the EMPWSI axis of sight pointed towards nadir E gt ol 2 e T Fig 4 5 4 field of view of scientific equipment installed on the EMPWS3 axis of sight pointed towards nadir Fig 4 5 6 field of view of scientific equipment installed on the EMPWS4 axis of sight aimed at zenith Fig 4 5 7 field of view of scientific equipm
107. n is impractical for digital data transmission and 15 assigned a backup status Exchange of data at 4 8 kbps over the phone 2 channel of RF C amp CS Regul OS via the flight model of IU makes it possible to downlink up to 100 KB of data during a 5 minute communications session Exchange of data at 16 kbps over the phone 3 channel of RF C amp CS Regul OS the forward uplink channel 15 working normally but the downlink for the time being 1 140463 provides no more than 150 KB of data over a 5 minute communications session If larger files need to be downlinked a series of several consecutive communication sessions can be used Besides as the next phase in its upgrade there are plans to switch to after proper testing 15 completed 32 and 64 kbps transmission modes for the phone 3 channel of Regul OS The maximum amount of payload data that can be downlinked via TM IU over telemetry channel per one communications session 1s 2 MB with other users not being able to use this communications channel while the payload data are being downlinked In early 2011 a Radio Data Transmission System RDTS 15 to be deployed on the SM of the ISS RS which 15 to provide additional data downlink capacity RF link with up to 100 Mbps throughput downlink receiving data over HotLink from the payload installed on the outer surface of the SM for its direct transmission The RDTS system allows downlinking no less than 3 7 GB of data during a 5
108. o ISS RS 15 planned based on the following assumptions delivery of cargo to ISS RS onboard Progress M M1 logistics spacecraft on average up to 600 kg per year return from ISS RS of up to 110 kg of payloads per year The external appearance of ISS RS in the above configuration 1s shown in Fig 3 2 c C H X o X z E 140463 EZ TWAN OG WS Jo 801518000 uogemsruoo SY 551 T E SIA 2n amp oq 552180414 1140463 904 VIAL 21406 55218044 gt 6 3 3 ISS RS consisting of SM DC1 MRM2 and MRMI Resources allocated to the MPF include allocated working volume of up to 1 m on SM up to 0 2 m on MRM2 and up to 3 on power supply on SM and DCI up to 0 3 kW daily average and up to 1 kW for 2 days with continuous additional normal power supply to ISS RS from the US segment in accordance with operational documentation on up to 0 1 kW daily average on MRMI up to 0 1 kW daily average heat rejection capacity on SM and up to 0 3 kW daily average the balance is achieved taking into account the heat loss through the SM hull on MRMI up to 0 1 kW daily average the number of workstations on the outer surface 4 pcs on the SM 8 pcs when deliverable Multi Purpose Workstations MPWSs taken into account 5 pcs on
109. o ISS onboard Russian vehicles 6 6 6 Integration timeline for cargoes to be returned to Earth Defined at 3 months before spacecraft undocks from the space station 1s which cargoes to be returned to Earth are to be integrated into the descent vehicle of the spacecraft in orbit Defined at 2 5 to 2 months before spacecraft undocks from the space station 1s the configuration of the hardware to be returned in the order of priority Submitted to RSC Energia shall be final documentation packages only for those cargoes E A 5 z which were delivered to ISS onboard the transportation vehicles of the Partners 1 5 to 1 month before the spacecraft undocking RSC Energia specialists on the No vehicle define the layout for cargoes to be returned to Earth These materials are the basis for updating onboard documentation The configuration and from MCC after the Soyuz spacecraft has docked with the space station but no later than 5 days before the scheduled landing of the descent vehicle provided the cargo safety package 15 available in consultation with RSC Energia Fig 6 6 5 shows the process of integrating cargoes to be returned to Earth into Soyuz spacecraft accommodation of the equipment to be returned can be updated using a radiogram 1140463 Submission of the manifest and the cargo data package DAN EMI Se rie pete ee oe
110. ods of time MRM 2 geometry and configuration of its continuously operating onboard equipment are similar to Based on the results of ground pre flight acoustic tests the noise level in the central part of MRM2 was 70 dBA 6 5 2 Acoustic environment in MRM1 MRM I design allows the crew to stay it for short periods of time Based on the results of ground pre flight acoustic tests the noise level in the central part of MRMI was when averaged along the length of the working compartment 72 dBA gt 2 e T S 1140463 6 6 Cargo integration 6 6 1 General Progress and Soyuz spacecraft deliver to the space station dry cargoes in pressurized compartments In addition to this Progress can deliver to the station liquids and gases If need be cargoes can be placed outside the pressurized compartment Cargoes transported by the vehicles shall meet requirements set fourth in this document Documentation shall be drawn up for all the cargoes including the packing used in flight to state that the cargoes are allowed to be stored and operated onboard the International Space Station and transported onboard the spacecraft as well as to certify the flight safety of the cargo The cargo accompanying documentation and technical manuals must be approved by RSC Energia In order for RSC Energia to perform work on integration of the cargo and
111. operation etc The use of such elements onboard shall be tightly controlled and measures shall 140463 Protective warning labeling must be made and applied to interchangeable components to limit the list of devices where these could be installed 6 2 4 2 Electromagnetic compatibility 6 2 4 2 Electromagnetic interference generated by scientific equipment 6 2 4 2 1 1 Low frequency noise Peak voltage values for low frequency noise Upeak generated by equipment in the 28V power supply circuits of the ISS RS modules shall not exceed the values given in Fig 6 2 4 2 1 jn Upeac dB uV E A 5 z No Fig 6 2 4 2 1 Low frequency noise Where f 1s the frequency kHz Measurement band shall be at least 10 Hz 1n the range of 30 Hz to 1 kHz 100 Hz in the range of 1 to 10 kHz 140463 6 2 4 2 1 2 RF noise Peak voltage values for RF noise shall not exceed values given in F1g 6 2 4 2 2 Upeak dBuV gal gi 1 10 100 f MHz Fig 6 2 4 2 2 RF noise Measurement band shall be at least kHz the range of 0 01 to 0 15 MHz 10 kHz in the range of 0 15 to 30 0 MHz 100 kHz in the range of 30 to 100 MHz 6 2 4 2 1 3 Electric field strength of radiated RF noise Equipment installed onboard ISS RS shall not generate noise exceeding the
112. or which purpose the deliverable unit shall have mounting fixtures Deliverable cargoes are stowed the areas within the cargo compartment that 140463 The need to develop special mounting fixtures and packaging adapter racks shock absorbers thermal insulation moisture proofing etc 1s stipulated when the contract 1s concluded The main place for accommodating payloads returning to Earth 1s the container under the middle seat In the two seater version of the spacecraft returning payloads are also stowed in a special container installed into the right hand seat Returning payloads shall be capable of being loaded through the payload container cover dimensions 170x470 mm The decision on the feasibility of returning a cargo to Earth is made based on the results of RSC Energia study 6 6 4 Deliverable cargo integration timeline 6 6 4 1 Deliverable cargo integration into Progress spacecraft The work to integrate cargoes into Progress spacecraft starts 6 months before the scheduled launch of the spacecraft and is based on the cargo delivery Manifest 6 to 4 months before the spacecraft is launched cargo outline and installation drawings are submitted to RSC Energia for approval Based on the results of the approval process for the cargo outline drawings the feasibility of delivering cargo onboard the spacecraft is determined and cargo E A 5 z
113. perature range of 15 35 and no less than 1 MOhm at relative air humidity of 95 and 20 temperature Insulation of primary current carrying circuits from the device case and between any electrically 1solated circuits shall be able to withstand a test voltage of 200 V effective or DC voltage for 1 s Insulation resistance of electrical circuits in active cargoes shall be no less than 1140463 m 6 1 4 4 Design features Design of high voltage elements in active cargoes shall rule out any possibility of corona discharges and short circuiting at low pressure inside compartments All current carrying elements in active cargoes having non insulated electric conductors located the air flow shall be securely protected against contact with small objects using airtight covers 6 1 4 5 Noise immunity and electromagnetic compatibility Requirements for electrical and RF equipment to provide noise immunity and electromagnetic compatibility when exposed to inadvertent interference finding its way into the equipment in a typical noise environment are given in paragraph 6 2 4 2 6 1 5 Cargo labeling requirements The cargoes to be delivered or removed are to be labeled with onboard data sheets and barcode labels as well as photographed and filmed on video Deliverable cargoes shall have onboard data sheets and barcodes to make them identifiable per requirements of paragraph 6 2
114. pulses E A 5 z must not exceed 20 ms when input power voltage varies within 23 29V Primary power circuits of the equipment shall have conductive coupling with neither the case of the device nor with the telemetry circuits The equipment must remain operational in case a primary power bus inadvertently comes into contact with the device case Loads devices having individual protected power feeders must not have any conductive coupling between themselves via the primary power plus buses As a rule each device must be powered via a separate connector Its type and pin assignment are additionally defined during development of electrical schematic for interfaces between the device and the onboard automatic equipment 140463 6 2 4 1 2 Electrical insulation resistance Resistance of electrical insulation between primary power supply circuits both positive and negative and equipment case shall be no less than 20 MOhm at relative humidity of 45 80 percent and ambient temperature of 15 35 deg C no less than 1 MOhm at relative humidity of 95 3 percent and ambient temperature of 207 5 deg C Insulation resistance measurements are taken at 30V DC 6 2 4 1 3 Electric strength of the insulation Resistance of insulation between primary power circuits both positive and negative and the case of the equipmen
115. r phase a certificate was published for an earlier successfully completed flight safety certificate is not published for that item for that particular phase 5 2 Scientific equipment tests 5 2 1 Generally scientific equipment 1s subjected to the following kinds of tests qualification tests QT acceptance tests AT tests at checkout and testing facility within the flight model of the spacecraft ISS RS module incoming inspection at the processing facility tests at the processing facility within the flight model of the spacecraft ISS RS module the tests and operations to service and process the scientific equipment at RSC Energia and the processing facility are only conducted per RSC Energia approved instructions and under supervision of its responsible representatives The instructions shall contain all the information that 15 necessary to handle the equipment E gt gt ol 2 2 T 5 2 2 Qualification tests are conducted by the equipment developer on the which is built per documentation for the flight model of the equipment The prime task of qualification tests 15 to check the equipment against specification or contract requirements under exposure to environments which are as close to operational environments as possible and if need be under heavier duty test modes qualification model of the equipment which 15 not intended for operation but
116. rallel to the axis and 15 pointed in the same direction axis 1s perpendicular to the 2 axis 15 parallel to the Zgs axis and is pointed in the same direction Zug axis completes the right handed coordinate system MLM X axis of the OXYZ coordinate system is parallel to the axis and is pointed in the same direction Y axis 1s perpendicular to the X axis 1s parallel to the axis and is pointed in the same direction Z axis completes the right handed coordinate system E A 5 z The following notation 1s used ax acceleration in the X axis direction ayz acceleration in any transverse plane parallel to the OYZ plane angular acceleration about X axis to the OYZ plane and goes through the X axis Recommended stiffness of fasteners for installed equipment shall correspond to natural frequencies of no less than 20 Hz Operational linear and angular accelerations of the center of gravity and about the center of gravity of the equipment located inside and outside ISS RS modules with rigid attachment at interface points to the ISS RS in 6 degrees of freedom yz angular acceleration about any transverse axis which lies in a plane parallel 140463 that 15 having the natural frequency of the attachment 220 Hz taking into account the stiffness of the attachment point
117. rbit etc To assure normal operation of the trajectory and navigation support software provisions have been made for daily uplinks of the orbital trajectory data predictions New versions of the software with the updates reflecting crew comments are delivered to the space stations on removable hard disk drives onboard Soyuz TMA spacecraft E gt AL ol 2 T 140463 3 7 The list of photographic and video equipment onboard ISS RS Currently available onboard ISS RS 1s equipment still photo video cameras which can support within certain limits the tasks of Earth remote sensing Tables 3 7 1 and 3 7 2 provide the lists of photographic and video equipment onboard ISS RS respectively Table 3 7 1 The list of photographic equipment onboard ISS RS Equipment name Major accessories Still camera Nikon D2X Nikkor autofocus lenses Still camera Nikon D3 Nikkor autofocus lenses Table 3 7 2 The list of video equipment onboard 155 RS Video system LIV Telescopic Fujinon 16 9 28 HDV videocamera The camcoder contains a high resolution Sony 71 and Sony HVR Z7 video camera with 3 CCD matrices and video recorder Video camera Sony DSR PDI150P 12x zoom lens matches the 1l 3 inch Ht A 5 z system Optical stabilizer Super SteadyShot M equipment are gi
118. re than 1 and the amount of condensing substances no more than 0 1 determined per GOST P50109 92 or another standard similar to ASTMES95 6 2 7 3 Microbiological stability of the materials Equipment destruction to a limit posing a threat to health and life 1s not allowed Microbial resistance must be specified for each listed material Equipment and its container must be disinfected at the launch site unless otherwise specified by the Russian side Usual methods of hardware disinfection include the use of liquid hydrogen E A 5 z peroxide and radiation This usual processing applies to all external surfaces This method can be revised if there is any danger of damaging the hardware Disinfectant resistance shall be specified for each listed material No non metallic materials analysis Assessed on a regular basis shall be devices intended for multiple use in flight as well as items and materials which are used as samples as defined by the Russian side Periods of time during which the properties of the materials remain preserved shall be specified for each listed material 6 2 7 4 Aging of materials An estimate of the equipment susceptibility to ageing shall be made by means of 1140463 6 2 8 Protection against static electricity 6 2 8 1 Protection of electronic equipment against static electricity during its installation and hookup to onboard cables sha
119. ring transportation onboard spacecraft with respect to the flight g load direction if there 1s such a constraint subsection 0 11 instructions concerning the feasibility of the unit delivery inside a spacecraft container or on the spot accommodation 12 special requirements for transportation conditions onboard the spacecraft if need be 13 lifting points for cargoes with a mass above 20 kg 14 bar code location If during transportation onboard the spacecraft the cargo is staying inside its gt 5 A 5 packaging or it has temporary protective elements covers the outline and installation drawing shall reflect the cargo 1n packaging and with its protective COVCTS Outline and installation drawings of the cargoes shall be approved by specialists on the same type of spacecraft in the past no additional approval of the outline and installation drawing 1s required on the spacecraft RSC Energia In case of repeated multiple deliveries of a cargo that has already been delivered 1140463 176 6 6 7 2 Requirements for the safety data package In accordance with SSP 50146 cargo safety information shall be presented in the form of a safety data package General requirements for the safety data package contents and format as well as cargo classification by category are defined in SSP 50146 Attachment D In order to certify cargoes for complian
120. rious kinds of loads Safety factors and scopes of testing are determined by standards depending on the types of equipment and r r r 1140463 _ specifics of its use Typical examples of the use of the design for minimum risk are selection of safety factors of safety margins when analyzing the structural strength of the body of sealed pressurized vessels of load bearing structural elements 6 3 1 3 3 Safety taking into account vehicle ISS services 6 3 1 3 3 Safety without taking into account vehicle ISS services SE shall be capable of taking care of its safety by itself without any servicing on the part of the vehicle ISS even in case of a contingency onboard the vehicle ISS 6 3 1 3 3 2 Safe With Vehicle Services If requirements of safety without servicing paragraphs 6 3 1 3 3 1 or 6 3 1 3 3 2 are difficult to implement for technical reasons the requirement of safety with servicing on the part of the vehicle must be met In this case the overall safety of the SE together with the vehicle equipment that is being used shall meet the requirements of paragraph 6 3 1 3 1 or 6 3 1 3 2 of this document with respect to hazardous situations 6 3 1 3 4 Hazardous functions control 6 3 1 3 4 1 A function which if inadvertently triggered may result in a critical hazard shall have two independent inhibits for the entire time while the likelihood
121. rom continuously operating sources 15 restricted to the limiting acoustic pressure spectrum in dB in octave frequency bands with their geometric average values ranging from 31 5 to 8000 Hz as well as to integral sound levels L4 and equivalent sound levels L4 equ measured on the A scale in dBA By equivalent noise level La equ 1s meant a value that 1s equal to the constant noise level L4 which has the same energy With continuously operating noise sources the acceptable noise pressure allowable acoustical levels in habitable compartments of the spacecraft and 1140463 m levels in octave frequency bands acoustic levels and equivalent acoustic levels in habitable compartments of the Russian Segment of the International Space Station established separately for the crew working and sleeping modes are listed in Table 6 5 1 With the joint operation of the primary continuous and additional intermittent noise sources the aim 1s to make sure that the equivalent noise level for the period of active crew operations 16 hours does not exceed 60 dBA And all the cases where the equivalent sound level exceeds 60 dBA taking into account additional intermittent noise sources the noise from all these sources shall be limited by operating time parameters of the additional equipment per Table 6 5 2 Table 6 5 1 Acceptable sound pressure levels in octave frequency bands and
122. s The positive direction 1s towards maximum loads Z axis 1s perpendicular to axes X Y and completes the right handed coordinate system 6 1 3 2 Types of mechanical loads types of loads can be grouped as follows shock loads of short duration occurring during transportation launch vehicle and spacecraft engine firings and shutdowns separation of the spacecraft from the launch vehicle spacecraft separation during reentry etc vibration loads produced by acoustic and mechanical effects during operation of propulsion systems and atmospheric turbulence linear and low frequency dynamic loads Cargoes that are highly susceptible to shock and vibration loads shall be installed on shock absorbers by the developer 6 1 3 3 Loads 6 1 3 3 1 When the spacecraft 15 transported within the processing facility When the spacecraft 15 transported by rail within the processing facility the operational loads are n l 1 5 1 1 40 25 0 2 gt ol Z e T S When lifted carried and installed onto supports in horizontal position 0 1 150 5 0 1 vertical position 1 gt 1 0 1 gt 1 1 0 1 6 1 3 3 2 During ascent to orbit Operational values for linear loads for cargoes without taking into account the low frequency dynamic component are ee
123. s but prevention measures are obvious 4 months before the launch for the first and second category cargoes which require developing special fixtures for securing them onboard the spacecraft 6 months before the launch for the cargoes of the third category highly technical cargoes posing a great hazard during delivery installation and operation gt ol Z e T S a transportation safety data package containing all the currently available information on potential hazards of the cargo must be submitted The final complete transportation safety data package shall be submitted within the timeframe established for the first and second category cargoes Note Deadlines for submitting transportation safety data package for review are different from deadlines for submitting inputs for assessments and analyses 140463 6 6 5 Integration timeline for cargoes to be disposed of Considering the need to analyze and approve documentation packages for cargoes delivered to ISS onboard the transportation vehicles of the Partners cargo documentation packages shall be submitted to RSC Energia from the cargo owners curators for approval 1 month before spacecraft undocking from the space station approved 15 days before the undocking No documentation packages need to be submitted for the cargoes that were delivered t
124. stablishing on ISS RS intercomputer digital data exchange links with MCC M via RF links of the standard SM systems Telephone and Telegraph Communications System TTCS RF communications and control system RF C amp CS Regul OS TV System TVS and onboard telemetry system OI TS 2 12 with data throughput of 1 2 kbps via the Telephone amp Telegraph System Interface Unit TTS IU and the TTCS VHF link up and down linking 2 4 4 8 kbps via interface units IU or TM IU and RF link phone 2 of RF C amp CS Regul OS up and down linking 16 32 64 kbps via interface units IU or TM IU and RF link phone 3 of RF C amp CS Regul OS up and down linking 51 2 102 4 kbps via TM IU and RF link of the OI TS 2 12 system subsystem B in the data array transmission mode downlinking 16 32 64 kbps altogether up to 96 kbps via user channels 1 2 of RF C amp CS Regul OS when using Zveno B hardware up and down linking Out of the abovementioned communications links currently implemented onboard SM and available for digital data exchange are the TTCS VHF link with 1 2 kbps capacity via TTS IU unit RF C amp CS Regul OS RF link phone 2 with 4 8 kps capacity via IU unit RF C amp CS Regul OS RF link phone 3 with 16 kps capacity via IU unit E gt Z T The TTCS link 1s mostly used for communications with the crew has a low bandwidth and for that reaso
125. t as well as between any electrically isolated circuits shall comply with requirements for electrical insulation resistance after application to these circuits of a 200V test voltage effective or constant value The test voltage shall not exceed allowable test voltages for components used in the equipment 6 2 4 1 4 Requirements for data interfaces with the ISS RS systems The equipment which has data interfaces with ISS RS systems shall be safe for the Russian hardware and control systems that are sharing the interfaces The equipment to be used onboard RS shall be classified by the presence of the gt ol Z e T S following interfaces electrophysical interfaces which determine parameters of interfacing with electrical circuits for data transmissions Such an interface must be subjected to the following operations device connectors shall be mated to the actual on board cabling to check their wiring electrical circuit parameters shall be measured in the actual onboard cabling and evaluated to make sure they lie within tolerances for data transmission lines MIL STD1553B ETHERNET etc LE ug 40463 performance tests shall be run via connected interfaces per user s manual for the device information and logic interfaces determining protocols for data transmissions in the network to which the new user 1s connected an
126. t that 6 2 6 for ISS RS are radiation exposure critical Test verification 10 Leakage tests 11 Thermal vacuum test 12 A check of electric circuit LoH f Verified requirements subparagraph in Section 6 Requirements of specifications for the scientific equipment 6 1 2 2 for spacecraft 6 2 1 4 for ISS RS Requirements of specifications and design documentation for the scientific equipment Subjected to the tests is the equipment that has a pressurized volume an enclosure a vessel containing gas liquid test tubes with biological samples etc Before and after strength tests the equipment must be tested for leakage Before filling the flight unit must be tested for leakage Subjected to tests is the equipment that operates in open space in unpressurized compartments It is recommended that the tests be combined with thermal stability tests see paragraph 8 3 A check of electrical circuits continuity and Isolation Verified requirements subparagraph in Test verification Section 6 13 Insulation and insulation breakdown tests 6 1 4 for spacecraft 14 Inrush current test 6 2 4 for ISS RS E 15 Power consumption check 16 Functional test Requirements of Acceptance tests are performed at nominal supply voltage while qualification tests are performed at those extreme voltages to which
127. tement safety certificate 5 1 2 Logbook E gt gt ol 2 2 T The logbook 15 intended for identifying a piece of equipment recording its key The logbook 15 published for each piece of equipment by its manufacturer vendor in accordance with the current requirements for shop floor documentation In some particular cases for example for certain foreign made equipment purchased items when there 15 no logbook meeting the established requirements the organizational unit in charge of that item publishes a document functionally similar to a logbook characteristics and contains a flightworthiness statement for that particular unit E PN 1140463 5 1 3 Flightworthiness statement Flightworthiness statement is intended as an assertion by the developer supervisor company organizational unit that the current requirements of the Specification or a document which replaces it supplement to a contract etc The Statement shall attest to the completion of the scheduled developmental testing to the fulfillment of the current requirements for scientific equipment and contain a permission to fly the equipment The Statement is the primary certification document published by the developer based on the results of a series of activities aimed at analyzing developmental testing and confirmation of the scientific equipment readiness for flight flight testing per requiremen
128. that they are proportional to the duration of flight tests Dosage safety factor with respect to the listed data or data 1 1 1140463 Moan obtained by recalculation for other operation life for the developed purchased equipment shall be no less than 2 6 2 6 5 In case the hardware is reused guaranteed in orbit operation time 1s determined by taking into account the total planned duration of flight tests 6 2 6 6 Ionizing radiation responsible for soft and hard failures in the ISS RS equipment is characterized by integral spectra of linear energy transfer for heavy charged particles and differential energy spectra for protons Table 6 2 6 4 provides integral spectra of linear energy transfer for heavy charged particles Table 6 2 6 4 Linear energy Linear energy transfer for the heavy charged particles source transfer Galactic cosmic rays at solar solar cosmic Solar cosmic MeV cm mg minimum flux averaged over an rays total rays peak orbit particles cm days flux flux particles cm particles cm d Ft A ays HEN 40463 _ 145 Linear energy Linear energy transfer for the heavy charged particles source transfer Galactic cosmic rays at solar solar cosmi
129. the running view of the current location under the flight path are Earth surface maps of various scale ranging from coarse mapboard type E gt Z T maps to detailed 1 200000 As all the maps are bitmap images on cylindrical the same format provide real time simulations of the future prediction or the past position of the space station Selected as variable simulation parameters can be year month day hour and second of the flight as well as the number of the orbit and the number of days into the mission When the simulation 1s run forward the latest available orbital data are extrapolated when the simulation is run backwards the history of orbital and attitude projection it 1s also possible to use any other set of maps or color photos prepared in X 140463 data is used There 15 a fast motion mode for displaying the space station position In addition to this the space station position can be frozen in its orbital track on the screen at any desired moment in time review all the available electronic maps the geographic atlas mode and determine geographic coordinates of any area on the Earth surface to automatically determine on the e maps the names of a region a country a water area 1 a sea a bay a sound or an area of the Russian Federation which is being overflown by the space station and output these data in a specified win
130. till cameras specifications Table 3 8 1 2 gt AL ol Z m T CCD matrix dimensions 23 7 15 7 mm Recording medium Compact Flash and Microdrive memory cards Light sensitivity Equivalent to 100 800 ISO speed Table 3 8 1 2 Digital still camera Nikon D2X MI 140463 Kun LCD display 2 5 inch 232000 with adjusted Lenses Autofocus lenses Nikkor and SIGMA Viewfinder field of view 96 of the frame area Optical exposure Automatic software controlled with time of exposure or aperture having higher priority and manual Optical exposure measuring area Matrix centrally weighted spot measurement Bracketing mode 2 9 frames with incremental steps of 1 3 1 2 2 3 or 1 EV mmi Power Hentai BELA TV Battery charger ET SM FOTO DI X U05 Digital still camera Nikon D3 Nikon D3X CCD matrix dimensions 36 0x23 9 mm 35 9x24 0 mm Light sensitivity Equivalent to 200 6400 ISO speed 25600 ISO 100 1600 Recording medium Compact Flash and Microdrive memory cards gt AL ol Z m T RAW EF and EG o LCD display 3 inch with 920000 pixels with MI 140463 adjusted brightness 100 frame coverage Lenses Autofocus lenses Nikkor and SIGMA AF 300 800 f 5 6 Optical exposure Automatic software controlled with time of exposur
131. tion currently in effect In particular conditions and requirements for launching with the use of Soyuz transportation spacecraft and LE ug 40463 Progress logistics spacecraft and for returning cargo using Soyuz are given in Section 6 1 of this document If the equipment meets the below requirements it can be stored and operated as far as mechanical loading conditions go in any ISS RS module If need be mechanical loading modes for a specific piece of equipment can be updated to take into account its specific location on the ISS RS 6 2 2 1 Loads 6 2 2 1 1 Vibration loading Vibration modes are specified by means of vibration acceleration amplitudes within the up to 20 Hz frequency range and vibration acceleration spectral density values in the frequency range above 20 Hz For the up to 20 Hz frequency range the modes are listed in Table 6 2 3 Random vibration modes within the 20 2000 Hz frequency range are given in Table 6 2 4 The modes are specified for three mutually perpendicular directions Modes listed in Table 6 2 3 and 6 2 4 do not apply to the equipment located inside and outside propulsion compartments of spacecraft SM and other modules when propulsion systems located inside these compartments are operating Mechanical loading modes for such equipment are specified separately in accordance with the documentation currently in effect Table
132. tructure materials and electrolytes used in the chemical power sources shall meet requirements of paragraphs 6 3 1 and 6 3 2 1 of these requirements Chemical power sources and or devices which use them shall have protection against charging discharging overcurrents excessive temperature and devices preventing discharges of electrolyte into the atmosphere of the vehicle The use of chemical power sources with more than 120 watt hour capacity or having especially toxic electrolytes such as theonylchloride lithium is only allowed upon agreement with RSC Energia 1140463 m f the standard mode lon 0 lementat imp ing crew day plan duri Ica 6 4 A typ SA SS 9 SIA 1140463 05 p34 _ logo ____ mm L O m ___ LL LL w ___ HL LLLLLLLLLERLLLLLLsL m Lo 3 kerete oze SELLO 68L sunt aar Nu Ti EN 6 5 Acoustic environment in the ISS RS modules ISS modules are filled with noisy equipment which operates continuously or for long periods of time throughout the day and constitutes the backbone of the life support systems Such systems includ
133. ts of Russian technical standards The Statement 15 published for the scientific equipment for which a permission to fly 15 sought for the first time newly developed or structurally modified equipment and which 15 used under the Russian program of scientific and applied research The Statement s scope shall cover the flight of scientific equipment inside a particular type of a transportation spacecraft and its use within an ISS RS module 5 1 4 Safety Certificate The Certificate attests to the scientific equipment compliance with the current safety requirements The Certificate 1s published based on the results of analysis of E gt gt ol 2 2 T the equipment safety characteristics and measures taken to prevent hazardous attachment to the certificate which together with the certificate constitute a single Safety Data Package SDP The safety certificate 1s published for scientific equipment of foreign organizations for the phase of its transportation on a Russian spacecraft and for the phase of its use and storage on board ISS RS situations The results of such an analysis presented in the form of report O O J 1140463 for Russian scientific equipment for the phase when it 1s used and stored onboard ISS RS and the phase when it 1s transported onboard a foreign spacecraft If the scientific equipment 15 a re flight item for a particula
134. ty while providing the maximum rate of change for the pressure 140463 6 3 2 2 4 Open surfaces on SE shall be smooth and have no burrs 6 3 2 2 5 The structure of the SE and the packing used in flight shall have no breakable materials or shall preclude fragments of such materials spreading beyond casings or packing of the SE hardware in case of failures both under normal environmental conditions and in case of cabin depressurization 6 3 2 3 Electrical safety SE electrical circuits shall be protected against possible overloads and short circuits and potential ignition by correct choice of wire gauge wire insulation circuit breakers etc etc There shall be no electrical contact between the vehicle body and electrical circuits of the SE SE hardware shall be designed in such a way as to protect the crew against an inadvertent contact with electrical circuits In case the SE uses voltages above 30 V measures shall be taken to protect the crew against electric shock per catastrophic hazard level Leak current during contact with the SE being serviced shall not exceed 0 07 mA DC for a normal contact with a human being No two electrically conductive surfaces within the reach of a member of the crew shall have a voltage difference exceeding 40 mV at frequencies of 1000 Hz or gt ol Z e T S lower measured across the resistan
135. usian and English are described in the joint standard SSP 50094 Section 4 6 7 6 2 5 1 2 Barcoding In order to set up inventory accounting of every piece of equipment and cargo both delivered to ISS RS and returned disposed of from the space station the ISS Cargo Traffic and Inventory 1s used Each item included into block by block list and into cargo traffic shall have a description following a pre defined data set which is entered into and then stored in the information system ISS Cargo Traffic and Inventory To automate the inventory keeping processes barcoding is used therefore all the items intended for use onboard ISS shall have barcode labels of one of the sizes with different information content barcode only also duplicated in numerical format gt ol Z e T S name and barcode duplicated in numerical format system designation name and barcode duplicated in numerical format 1140463 6 2 6 Ionizing radiation 6 2 6 1 Integral energy spectra of electrons and protons in Earth radiation belts at solar maximum are given in Table 6 2 6 1 Table 6 2 6 1 Electron energy Electron stream Proton energy Proton stream 3 9E 06 2 3E 06 2 0E 06 1 7E 06 1 6E 06 1 4E 06 1 2E 06 5 9 05 6 9E 04 8 2E 03 3 7E 02 Note These data are used to evaluate integrity of materials and elements loc
136. ven in sections 3 8 and 3 9 A more detailed description characteristics and external appearance of the above E 140463 3 8 Equipment for still photography Specifications Currently available onboard ISS RS are still cameras Nikon D2X Nikon D3 and Nikon D3X see Table 3 8 1 1 which make it possible to take high resolution photos of the Earth surface and other through ISS portholes mostly portholes No 6 No 7 and No 8 The still cameras come with accessory lenses which are listed below and are intended for different tasks Table 3 8 1 1 Russian photographic equipment onboard SM Still cameras Still camera Nikon D3X SM FOTO D3X U01 Still camera Nikon D3 SM FOTO D3 U01 N901 still camera Nikon D2X SM FOTO D2X UO01 Lenses Lens AF DX Nikkor 10 5 mm SM FOTO D1 U02 07 Lens AF S Nikkor 14 mm SM FOTO D1X U02 03 Lens AF S Nikkor 17 35 mm SM FOTO D1X U02 01 Lens AF S Nikkor 17 55 mm SM FOTO D1 U02 06 E gt AL ol 2 T JI SM FOTO D200 U02 06 s Lens AF S Nikkor 28 70 mm SM FOTO D1X U02 02 SM FOTO F5 1 U02 Lens AF S Nikkor 80 200 mm SM FOTO D1X U02 05 1 Lens AF VR Zoom Nikkor 80 400 mm f 4 5 5 6 _ __ Ll _ _ ___ _____ 1140463 SM FOTO D3 U02 Ne2 99 Lens SIGMA AF 300 800 1 5 6 SM FOTO D3 X U02 08 1 The lens for ultra close up photography SM FOTO D200 U02 09 Micro Nikkor f 105 mm
137. with the specified level of reliability to simulate in real time a segment of the Earth surface and or of the celestial sphere which is visible through the specified porthole To simulate the celestial sphere Pulkovo observatory catalog 1s used 5050 brithest stars recalculated for 2003 into consideration the presence of cloud cover intensity on the scale of 0 to 10 over the 140463 also continuously calculated are positions of the Sun and solar reflection from the Earht surface the Moon and planets Other SC for which orbital parameters are available There 1s a mode for the automatic selection of that porthole which 1s the best suited for observing the specified feature on the Earth surface or the celestial sphere In addition to the actual portholes there 1s a virtual porthole which simulates the view forward or backward along the flight path to simulate the space station rotation in coordinates bound with the specified window This makes it possible even when there are no available data on the current attitude to determine the actual attitude by manually bringing into coincidence the electronic model of the porthole and the actual image visible through the porthole using in the process such visual cues as the horizon line the Sun the Moon and bright stars to receive voice messages about various events beginning and end of a communications session orbital sunsets and sunrises a new o
138. y for the periods between EVAs on board systems resources for scientific equipment on the external surface are mostly borrowed from the SM On the DC external surface possible areas for deploying payloads are magnetomechanical latches 77KC 1 1940 100 located on the cylindrical part and on the central sphere passive base points 27KCM 152IO 7200 0 2 pcs located on the cylindrical part used for accommodating cargo booms brackets 240 2200 101 for the latch of the outboard workstation placed 4 pes each on the flange of the exit hatches Locations on of external multipurpose workstations based electromechanical latches are shown in Fig 4 2 1 Locations of payload equipment windows and electrical outlets are shown in Fig 4 2 2 gt ol 2 e T DCI resources used for integration of scientific equipment are listed in Table 4 2 1 pum 140463 Micro meteorid shield 1 Electrical connector Eu Se 7 Wm O gt H IE an Electrical connector Micro meteorid shield 2 Fig 4 2 1 Locations of external MPWS on 1 No Micro meteorid shield 3 5 gt lt NN EN 1140463 ol S W

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