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RAPID Flight Operation User Manual - Max-Planck

1. gt Look up RAM Scalar Array table B N LUT 24 bit counters Hg i DPU Command i EPP Control i i Data bus EPP Figure 12 Schematic block diagramm of the electron pre processor EPP Electron input data energy E and direction number D are passed through a sorting process to reduce the data volume 1 41 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py JE IES 60 E 8 IIMS SCENIC 1ES LIMS SCENIC RAPID CLUSTER Figure 13 Orientation of RAPID on the Cluster spacecraft The convention for the direction numbers D is shown for the two sensor systems 1 42 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu 2 0 Telemetry The general structure sequence for the downlink TM words and the uplink TC words telemetry is compare also Annex A 1 chapter 2 Byte Word Bytes per Structure Bit Length Length S C Sampling Sequence TM 8 bit 8 bit 1 MSB first TC 8 bit 16 bit High Byte TC name MSB first Low Byte TC parameter MSB first Details on TC structure see Section 3 2 Down link telemetry modes bitrates Telemetry Mode Bitrate bps adjusted NM 1 NM 2 NM 3 1024 80 BM 1 4620 92 BM 2 1155 23 BM 3 1925 38 NM 1 contains Science Nominal Data BM 1 contains Science Burst Data BM
2. 7 3 3 Monitoring or Activities During Perigee Passage No specific activities are planned for perigee passes The Monitoring is accomplished via nominal telemetry channels on line or off line no special precautions are required 7 3 RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu 7 3 4 Conditioning after Perigee After perigee geocentric radial distance larger than specified in 7 1 1 the instrument will be brought back to the pre perigee configuration P Name Description P18 HVUp HV increase to nominal level Procedure is defined in Annex A 3 2 7 3 5 Constraints Time tagged TCs are acceptable after verification of instrument health during commis sioning Availability of normal telemetry link is acceptable 7 3 6 Resources Normal telemetry link required for preparation of instrument functions before and after perigee 7 3 7 Procedures As described in Section 7 3 2 the instrument will be commanded into Hot Stand by mode and after perigee pass the instrument will be reconfigured in pre perigee mode see Sections 7 3 2 and 7 3 4 for procedure 7 4 Manoeuvers 7 4 1 General Approach For manoeuvers with engine burns the instrument is to be turned OFF 7 4 2 Preparation of the Instrument Before the Manoeuver Normal POWER OFF procedure P Name Description P8 PowerDown Power OFF seque
3. TS 1 1nsec 30 keV 10 TOF nsec s 3 4cm Figure 5 Fraction of the energy time plane covered by the IIMS system The width of the particle traces reflects the variation of the flight path in the SCENIC geometry Energy thresholds A B and C define the lowest energy value accepted the upper limit for linear response and overrange respectively 1 34 YP AE RAPID CLUSTER Issue 3 7194 Flight Operation User Manual Rev 0 Date 17 06 2000 CROSS SECTION of the IES HEAD SHIELDING HU D ACTIVE STRIP AREAS PINSLIT Figure 6 The IES Sensor Concept Multiple look directions are achieved using a single detector with multiple elements place behind a pin slit 1 35 RAPID CLUSTER Issue 3 2A Flight Operation User Manual Rev 0 Date 17 06 2000 DA Py IES 800p DETECTOR PROTON VETO DISCRIMINATOR 4 DPU CONVERSION RANGE OF OPERATION DEPOSITED ENERGY keV 10 20 10 400 10 INCIDENT ENERGY keV Figure 7 Energy range covered by the IES detector system The shaded area indicates unique electron identification 1 36 YH Dz Issue 3 O Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual LEVEL 2 LEVEL 1 Figure 8 Simplified diagrams of a the IIMS and b IES signal conditioning units with emphasis on the signal and data formation data are shown in heavy rounded rectangles
4. 3 0 Control 3 1 Control Philosophy 3 1 1 Introduction Most instrument functions are controlled by telecommand i e the instrument is config ured by a set of TCs which are stored in registers Among others these TCs define the nominal Operational Modes OM and all emergency modes e g deactivating a noisy detector In standard operations the instrument will be configured in steps e POWER ON Instrument in a safe without high voltages but scientifically mean ingful e g all solid state detectors active configuration Full operational capacity can be achieved by a small number of TCs typically 10 20 e TURN ON HV relays e Set HV levels e In case of emergency a POWER OFF POWER ON cycle resets the instrument to the default mode POWER ON mode Emergency situation is defined as an unintended deviation from normal performance We distinguish two categories Serious emergency a HV discharge failure in TC section etc requires immediate action Soft emergency b Noisy detector etc situation must be considered however action not time critical e Functional integrity will be checked continuously with the built in test calibrator IFPS e Internal over current detectors latch up detector will switch parts of the instru ment automatically OFF and ON in case of excessive currents in the DPU seen on ground no action required but inform PI e General approach for instrument control during u
5. TC Function ZERFCLKS Sets clock 1 kHz 16 kHz enables disables FGM interface Baseline 1 kHz Reference Annex A 1 4 5 4 Procedures In case analysis shows inadequate quality of obtained pitch angle data the RAPID team will decide whether or not to disable the FGM interface e When FGM is in calibration mode typically 5 min per orbit the RAP IEL shall be disabled by TC issued by JSOC Procedure P27 Annex A 3 describes the IEL disable enable cycle 4 7 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu 5 0 Commissioning 5 1 Initialization of the Instrument Initialization Commissioning will be executed by RAPID team For the patch codes that are to be uploaded consult Annex A 1 sect 5 3 For the commissioning RAPID requests data from the on board Tape Recorder in addition to real time data acquisition Perigee passage Magnetosheet crossing Solar Wind part of the orbit Magnetosheath and undisturbed SW Note e The maximum stepping speed for MCPHV is 1 step Tspin e The maximum stepping speed for DEFHV is 1 step 2 Tspin e During the commissioning phase lower stepping speeds will be used 5 1 1 Timeline Table 5 1 Commissioning Plan and Timeline Step Description Proc Time Conditions min
6. RAPID CLUSTER Flight Operation User Manual DL mu A 1 CLUSTER RAPID Instrument Users Guide IDA Please click here for Issue 2 Revision 7 from Feb 15 2000 prepared by A M llers R Rathje C Dierker Institut f r Datenverarbeitungsanlagen Technische Universit t Braunschweig A 1 1 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date DA Py 17 06 2000 A 2 TM Parameters Dornier Database The TM parameters are not provided in this electronic version since they are not readily available in electronic form However the same information is to be found in the following text files S C 1 rapid fi tm S C 2 rapid f2 tm S C 3 rapid_f3 tn S C 4 rapid f4 tm A 2 1 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py A 2 2 Issue 3 Rev Date 17 06 2000 YP AE RAPID CLUSTER Flight Operation User Manual A 3 RAPID Command Language RCL Please click here for Issue 4 Revision 1 from June 19 2000 A 3 1 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py A 3 2 Issue 3 Rev Date 17 06 2000 RAPID CLUSTER Flight Operation User Manual DA mu A 4 Def
7. As mentioned above the SCU utilizes an integrated multiplex chip denoted switched charge voltage converter SCVC as the input stage for the analogue signal processing The SCVC contains a total of 16 charge sensitive preamplifiers with a noise at zero input capacitance of 700 electrons rms 6 keV FWHM The total power consumed is about 10 mW only nine preamplifier channels are actually used for IES The essential functions of the SCVC chip are shown in the simplified circuit diagram presented in Figure 8b The charge placed in an active strip of the solid state detector by an incident particle is integrated a stored on the capacitor C2 following the preamp This stored charge is compared with a background value stored on a companion capacitor C1 The difference between these two values of charge is then strobed out and fed into a comparator circuit From the comparator the signal is read into an 8 bit analogue to digital converter ADC The resultant digitized signal represents the pulse height or energy E of the incident particle The charge deposited by the incoming particle can be integrated for periods ranging from 2 to 50 microseconds via a DPU controlled command The use of the shorter time constant lengthens the dead time due to the finite time required to strobe all nine channels but tends to reduce the system noise Depending on counting rate the DPU can optimize the integration time constant The SCVC chip has an offset
8. up AE RAPID CLUSTER iDA Flight Operation User Manual Issue Rev 3 Date 17 06 2000 RAPID CLUSTER FLIGHT OPERATION USER MANUAL DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 List of Contents 1 0 Instrument Description 1 1 A A II Se oe eS ee Ee au 1 1 LLL Bee Ties doe Ade a a ee eke 1 1 L2 NEUERE ee Bc RAR G 1 3 1 2 1 The RAPID Spectrometer 46564 db mad 4e nn 1 3 1 2 2 Signal Conditioning Units SCU 1 8 123 The Digital Processing Un DPU 2 2 24 a4 gi 1 15 1 2 4 The IIMS And IES Science Data 1 19 1o On Board Fe ooe e e SIREN RES ee ea aeg 1 22 Lad AR UIEC DE u a ra ai 1 23 14 Instrument Physical Characteristics 4 4 6 646584 66 be ee es 1 28 1 41 Location on the Spacecraft 1 28 LAS TEE Der ae s sios ERA Dr ENS ES 1 28 143 Physical Properties oe ce s sa bus eG Bae Biel 1 28 Lo PUR ces a ee ee E AA a 1 29 2 0 Telemetry 2 1 21 Monitornne PUS lt 2 2 0 00 ta sone ah ada oe ee es 2 2 22 Benson TT se oe Se pa a a basses 2 2 eel TOME seo esre erraten 2 2 223 do Monitors gt e coco sere DRE OAK Ae Res 2 2 2 23 lemperat re Monitors 44 dus ea dia wk tG pa ha 2 4 224 Instrument MN 2 5 2 2 5 Analogue Parameter Settings 2 5 220 IEL latas and Data ar za ar rer rat ae 2 5 227 List of All UK Parameters 4 2 2 44 44586 aa
9. 1 Bi phenyl actuators none To 35 hours release doors Steps 2 6 on first day of session 2 POWER ON P1 2 Final orbit reached Default Mode 10 11 Payload No constraints Patch Code upload P31 30 Set IES int time 5 us P32 1 IIMS Commissioning A P20 35 As for step 2 IFFT TAC slope variation IFFT 6 Data Evaluation gt 15 WHISPER OFF FGM No constraints Other No constraints T Set IES int time 15 us P33 1 continued 5 1 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu Table 5 1 Commissioning Plan and Timeline continued Step Description Proc Time Conditions min 8 HV Commissioning IIMS P17 460 HV relays ON Mode 19 11 Increment MCPHV to step 3 Increment MCPHV to step 7 Hold step 7 operational level Note S C2 different Step DEFHV to HV step 6 and hold Step DEFHV to HV step 15 10 kV Hold DEFHV step 15 IFFT Step DEFHV to step 0 9 Set IES int time 2 us P28 1 10 Data Evaluation 30 As for step 6 11 Set IES int time 50 us P29 1 12 IMS Commissioning B P22 100 As for step 6 Variations of configurations IFFT Step DEFHV to step 10 and hold Data evaluation IFFT Step DEFHV to step 0 13 IES Commissioning P21 80 Variation of integration time Histogram mode vary int time Int time to 2us IFC ON Data evaluation IFC
10. D STA CHPS on step 8 3 5 kV STO CHPS on step 8 3 5 kV DEFPS on step 7 4 2 kV Comments Temperature T 200C EoL refers to end of life conditions for the Micro Channel Plates MCP CM Configuration Mode 4 2 RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu 4 2 2 High Voltages The instrument has three different high voltage power supplies powered from the internal low voltage power supply LVPS All three HV supplies are independently controlled by TC Power supply Function Range V Steps STA CHPS START Microchannel plate 0 4000 16 STO CHPS STOP Microchannel plate 0 4000 16 DEFPS Deflection voltage 0 10000 16 All high voltages are completely contained in the instrument i e field lines do not extend into free space In flight software safety precautions are taken Limit control stepping control 4 2 3 Conditions The power consumption has a quasi hard relationship with the operational modes OM a In Stand by Modes the power dissipation is within 1 or 2 constant IES creates a minute rate dependence b In all other modes the power consumption can vary by no more than 10 due to the particle flux in IIMS Consult also Section 4 2 1 4 2 4 Monitoring The low voltages 12 V 5 V and the high voltages STA CHPS STO CHPS and the DEFPS are monitored by the respective analogue value in the analogue HK p
11. b Configuration back up of the configuration segment in the main RAM Cycle time is 1 spin This back up is automatically retrieved after a latch up was detected or a watchdog reset has occurred 3 1 3 Modes Operational Modes OM can be changed with no restrictions except for changes in the high voltage levels see Section 6 0 Routine OMs are associated with a certain HV setting obtained from pre flight calibrations However test and or commissioning phases require different HV settings as part of the check out procedure The term test refers to unexpected instrument response which requires detailed examinations with specific adopted test sequences controlled by ground commands Safe operation of the high voltage system requires the following steps if a high voltage level is to be increased e Set a new limit value higher or equal to the intended target value e Enable changing of HV level e Set desired target value e Disable changing of HV level A decrease of the HV value can be achieved by simply stepping down to the new value 3 2 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 3 2 External Telecommands According to EID A chapter 3 3 3 2 telecommands are divided into e Memory Load Commands MLC and e ON OFF Commands OOC 3 2 1 Memory Load Commands MLC A MLC is constructed as a 16 bit word compare details in Annex A 1 chapter 3 3 and EID
12. 1 37 YH Dz Issue 3 O Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual SCENIC DPU processing system 80C86 CLUSTER RAPID Figure 9 Block diagram of the RAPID digital processing unit and its interfaces to the sensors and to the spacecraft 1 38 YH Dz Issue 3 Rev 0 Date 17 06 2000 RAPID CLUSTER Flight Operation User Manual S C Figure 10 Schematic representation of the data processing in the DPU Input data from the IIMS SCU and IES SCU are shown on the left heavy rounded rectangles The sorting and classification processes eventually result in Science Data which in turn are organised in Experiment Data Blocks EDB for transmission 1 39 Issue 3 17 06 2000 MP AE RAPID CLUSTER JA Flight Operation User Manual Rev 0 Date 4 lt Readout every Sector 656 Bin nm Counters for T EA T Bs E fl B f A EA science raw data bo I PAD f BIN Readout P 2 every Spin Toas Direct Event Direct Er ETDS Buffer Sie store Readout every En 2048 64th Spin E Fr Jon Matrix sz E Binay A 4 Counters for Search I MATRIX increment RAPID IPP Figure 11 Diagram of the ion pre processor IPP showing the data flow in the classification process 1 40 DZ mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Date 17 06 2000 O K2 O
13. M and N which refer to three independent functional levels L In flight calibration This function can be activated in parallel to the current operational mode of the instrument M Energy binning parameter This parameter transforms the 8 bit primary accuracy of energy signals into an output signal with lower or equal accuracy The transformations are performed by look up tables LUTs which are different for each unit and which need to be uploaded by patches when the instruments are first turned on or when the power KAL has been lost See Annex A 1 Section 5 3 3 1 LUT 1 Binning from 256 to 12 burst mode or 8 normal mode bins 2 Not used for Cluster I this was a 2nd LUT for a different temperature 3 LUT 3 Histogram mode 1 to 1 binning 8 bit output This LUT is called if full energy resolution is required N Integration time parameter This parameter defines the integration time t in the detector read out system Se lection of an integration time t is dictated by the particle flux In autoswitching mode the integration time is not fixed but changes automatically with count rate 2 Three dimensional Mode Matrix LMN for IES L M N 0 measuring 0 Autoswitching 1 In flight calibration 1 LUT 12 or 8 binning 1 t 2us not used 2 t bps 3 256 bins histogram 3 t lous 4 t 50us 5 Memory dump mode 6 6 DA mu RAPID CL
14. T range extends essentially from 0 nsec to 80 nsec Particles electrons or nuclei with sufficient energy to penetrate the ED detector create a veto signal in the BD detector which results in the elimination of this event from subsequent analysis With reference to Fig 5 the following definitions are used for particle identification Logic State T Range Species Remarks in the E Ch ABC t0 t1 Proton Reduced resolution tl t2 Helium Reduced resolution ABC 2 80 nsec All nuclei Nominal resolution ABC T0 T1 Proton Unique identification T1 T2 Helium Unique identification T gt T2 CNO and heavier No mass resolution 1 6 DL mu RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000 As mentioned earlier the IIMS sensor system is composed of three identical SCENIC heads in a configuration such that contiguous coverage over 180 in the polar angle is achieved the polar angle is defined with respect to the Cluster spin axis The sectored rotation of the spacecraft provides the completing azimuthal coordinate The design features of the SCENIC head combined with the specific lay out of the electronic system lead to performance parameters summarized in Table 1 3 Table 1 3 Characteristic parameter of the IIMS and IES sensor systems IIMS IES Energy Range Hydrogen 46 1500 4000 Helium 76 1500 4000 CNO 98 1500 4000 Electrons 20 40
15. The internal digital processing unit RAPID DPU serves the SCUs and sensor systems IIMS and IES evaluates and compresses the primary event data rate to a level which is compatible with the telemetry capacity and arranges the output data in the format of an experiment data block EDB The present description of the DPU and its func tions is a rather brief extract with strong emphasis on the data manipulation and the final construction of Science Data A more comprehensive report of the DPU will be submitted as a separate publication The simplified DPU block diagram in Fig 9 the following key elements e Interface to the IIMS SCU Ion Pre Processor IPP Electron Pre Processor EPP e Microprocessor system 80086 based e Memory protection and latch up detection safeguard electronics Interface to the Cluster spacecraft Inter experiment link IEL to the magnetometer instrument FGM Low voltage power converter 1 2 3 1 IIMS Event Processing A main task of the DPU is the compression of the enormous data rate received from the IIMS SCU system It was mentioned in the previous section that each fully defined particle event is described by 2 analog signals EAN TAN and a set of 18 digital pulse channels These data are processed in the DPU and eventually transformed into Science Data for nuclei The various data types created in the SCU on the different levels of processing are transferred to the DPU as schemat
16. mu RAPID CLUSTER Issue 3 DA Flight Operation User Manual Rev 0 Date 17 06 2000 Ch No Parameter HK Name Initial Value Function Remark 21 Interval ERDLEDBC 3 EDB counter 24 bits length Counter every 32 spins ERDSPINC 0E hex Spin counter 24 bits length sampled every 32 spins ERDEDBCR 0 EDB counter 6 bit length for IFPS ERDFGMCR 0 FGM counter 7 bit length Received number of vectors in last spin Read out value 62 FGM ON 0 FGM OFF ERDICCNT 0 Invalid TC counter 8 bit length ERDVLCNT 0722 Valid TC counter 8 bit length ERDCECNT 0 TC error counter 8 bit length ERDTOERC 5 Time out error counter 16 bit length can happen during initialisation ERDFRPRT not predictable MP free time 16 bit length 22 IIMS ERDTRIGM 0 Trigger Mode E T Default setting Status ERDIFIND 0 Serial Mode Default setting ERDEDET1 0 Energy Det S1 Default ON ERDEDET2 0 Energy Det S2 Default ON ERDEDET3 0 Energy Det S3 Default ON ERDBDETI 0 Back Det S1 Default ON ERDBDET2 0 Back Det S2 Default ON ERDBDET3 0 Back Det S3 Default ON ERDDMUX1 0 DIR MUX S1 Default ON ERDDMUX2 0 DIR MUX S2 Default ON ERDDMUX3 0 DIR MUX 83 Default ON ERDTMUX1 0 T MUX S1 Default ON ERDTMUX2 0 T MUX 82 Default ON ERDTMUX3 0 T MUX 3 Default ON 1 Value without any memory uploading before 2 The value effect when Patch b is loaded A 4 3 DA Py RAPID CLUSTER Issue 3 DA Flight Operation User M
17. 06 2000 i DL mu 7 6 4 Configuration Control of Patching To the extend it is possible e g a constraint may result from limited telemetry rates the patch will be checked by e special flags in the HK Data functionality e special flags in the Science Data assignment of EDB pattern 7 6 5 Reload of Software after e g Power OFF Patch codes are stored in non volatile RAM keep alive power thus reloading patch codes after POWER OFF is not necessary except patch codes require memory space in the main RAM volatile However after POWER ON chaining may be required 7 6 6 Constraints Uploading chaining of patch codes is generally a critical operation the instrument may end up in an undefined status Specifically we request that all HV voltages be turned OFF during uploading chaining of patches 7 6 6 Resources Reasonable patch code operations are limited by the size of free space in the non volatile RAM max 2 KByte 7 6 7 Procedures Can only be defined with an exact knowledge of the problem to be addressed e g new scientific modes work arounds for software bugs improved content of look up tables LUT or correcting anomalies 7 6 8 Note on the RAP F1 Phoenix F6 F7 and F8 embedded S W 1 A minor inconsistency in module 14 3 ofthe RAP F1 PHOENIX unit s embedded S W see attached S W list was corrected for RAP F6 F7 and F8 RAP F1 requires uploading of Patch Code A
18. 12 14 16 Gt 2 1 20 04 95 6 6 2 changes under 6 1 1 Si Ru 2 1 20 04 95 6 6 3 ref in first sentence Si Ru 2 1 20 04 95 6 6 6 formulation under M 3 Si Ru 2 1 20 04 95 6 6 9 changes of numbers under 2 Si Ru vill DA Py RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000 CHANGE REPORT Iss Rev Date Sec Page Changes Orig 2 1 20 04 95 7 7 1 changes in chapter 7 1 2 and 7 1 4 Si Ru 2 1 20 04 95 7 7 2 changes in chapter 7 2 4 and 7 2 7 Si Ru 2 1 20 04 95 7 7 3 textfloat Si Ru 2 1 20 04 95 7 7 5 changes under 7 5 1 and 7 4 7 Si Ru 2 2 03 11 95 7 7 6 7 6 1 last sentence add Gt 2 1 20 04 95 7 7 7 misspellings Si Ru 2 1 20 04 95 8 8 2 misspellings formulation Si Ru 2 1 20 04 95 8 8 3 changes under 8 3 Si Ru 3 2 03 04 96 A 3 All complete update Rj 2 1 28 02 95 A 1 several see change report of A 1 Rj pages 2 1 03 11 95 A 4 All Changing Table 1 1 Gt ix DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 CHANGE REPORT Iss Rev Date Sec Page Changes Orig 2 1 08 02 99 Cont ix 7 6 9 additional note in List of Contents Gt 2 1 08 02 99 1 1 3 Table 1 1 changes in Science Team Gt 2 1 08 02 99 1 1 14 changes from 2 to 50 us second paragraph second line Gt 2 1 08 02 99 1 1 20 cha
19. 4 6 4 5 Interface to Other Experiments 4 6 AL SRO 6 lea Lu a ee ea 4 6 dos Monitorning EN 4 7 ADS Via cover ra cri Da e a OR are 4 7 ADA Process 24 423 24a mn Das aha as Lens 4 7 5 0 Commissioning 5 1 5 1 Initialization of the Instrument 5 1 SLI Timmele oc oe da de pi daos a ar a he 4 a 5 1 5 12 Operational Constraints lt psa due ee ze a EEE as 5 3 513 OENB rare 5 3 ll Mn ne ok at Ke wae as leet a ee a ee de 5 3 lH Produrre oo s un da o ee nee 5 4 e A UN Oe BO ee De ee ee eS 5 4 5 2 1 Under Experiment Control 5 4 52 2 Active Covers oo Liu 64 bead eb web lan eu 5 4 5 2 3 Environmental Control 5 4 5 24 High Voltages ON 1 44 4 2 gui da dus bed ren 5 4 6 0 Nominal Operations 6 1 6 1 Operational Scenario lt o serer Lame Eau bE A 6 1 GLI Mode Birasture o a se da AM a ae 6 2 02 Opertiongl Procedures 464 44 cms das dd Ba a a er 6 9 0S un a ee sa SOs 6 9 6 4 Modes and Transitions for JSOC lt lt 2 6 10 7 0 Critical Operations 7 1 Tod Short A 7 1 7 1 1 General Approach o da dos a ir ae re 7 1 7 1 2 Preparation of the Instrument ooo aa 0 ee be ea 7 1 7 13 Monitoring or Activities During the Eclipse 7 2 7 1 4 Conditioning after the Eclipse 44 4 as durera 7 2 TLS COnsStraAints o moed med ra en at he g a 7 2 1b Resources aon Goo a eR a Re e
20. 6 4 Modes and Transitions for JSOC The following is the input supplied to JSOC to define the operation modes and the transition commands Expected Operating Modes We presently expect to switch both instruments between high and low fluxes together the neutral mode will be considered to be low The electrons will be high or low as the ions are high or low If IES is run in autoswitching then its mode is independent of IIMS Thus IES Fixed Autoswitching Low flux mode 24 014 24 010 High flux mode 14 011 14 010 ENA mode 25 014 25 010 Standby Modes Cold standby 10 011 Voltage turned off Hot standby 11 011 Voltage on but set to OV Red Hot standby 12 011 Voltage on but set to non zero value Test Modes In flight test modes are 4B LMN and AB 1MN which switch automatically back to the original mode when finished FGM Calibration When FGM is calibrating it is necessary to switch off the IEL Inter Experiment Link This is not a mode change but only a flag change 6 10 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 High Level Mode Names Since the above modes are difficult to remember we define some with English names These are the modes that are used with JSOC commanding and the input to the Master Science Plan JSOC Mode Description AB LMN OFF RAPID is switch off no power 00 000 HIGH High flux rates reduced sensitivity 14 011 or 14 0
21. High Voltage Control gt o s s acos 4 dau ge we nenn 3 4 3 3 3 Parameter Commands 3 4 3 4 On board Calibration Tables Modification 3 4 3 5 On board Software Modification 3 4 3 6 Internal Control and Commands 3 0 3 7 Constraints and Applicability of Telecommands 3 5 4 0 Environment 4 1 AI Thermal i e ce bose es we i a ne ot ed we a bec Bh a 4 1 AL Condena dias a nee ei 4 1 LLE Monitorning 1 4544 2b eH hee ee er ae RES RES 4 1 Mili SOG 2 3 chk ekeni al rn a ee 4 1 4 1 4 Procedures 4 1 A POB cocoa aa Bela Bee AR Ree 4 2 A A E ee en eh 4 2 42 3 ich Vol aaa dut a a a en haha 4 3 173 OMIS lt lt don ds ae a rasen nee 4 3 Bae OIGO 6 Se bh we oe Bee 6 her er D s eee 4 3 en LA ar e N eh a 4 4 4 2 6 Procedures 4 4 43 CoOmmunsllond a a a Rw 4 5 4 3 1 Bit Rates Associated to Each TM And Each Instrument Mode 45 432 Conditions o ss esesss dred BA Eaa pa ie 4 5 daa Monko eea du en ee a ee ee 4 5 ARa Vol sana ie 4 5 Air Procedures iii Lu a e ea RY 4 5 dd Te ee a en e ee ee ea a ee 4 6 dA Condes ose ces La VE era ernten 4 6 ale Momtoring o scoe c pelea a p ae a 4 6 4i TAM ee e a ed 4 6 11 DL mu RAPID CLUSTER Issue 3 DA Flight Operation User Manual Rev 0 Date 17 06 2000 ada Produire oe Vacio ea A Se a
22. The EPP tasks are the provision of a serial command interface to IES and the pre processing of IES event data A simplified block diagram of the electron pre processor is presented in Fig 12 A valid electron event at the EPP input is described by a digital signal duple E D with E 8 bit and D 4 bit denoting the electron s energy and direction of incidence respectively The E D pair serves as an input vector for a bin definition look up table LUT which defines a bin number B 8 bit The bin number B and the current sector number SCT SCT defines 16 azimuthal sectors are concatenated to form an other vector pointing to a RAM SCALER field a RAM based counter array and the selected counter is then incremented The contents of the RAM SCALER serves as the basis for the electron Science Data 1 17 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 The bin definition LUT can be exchanged by telecommand thus allowing arbitrary schemes for binning the energy and direction ranges A set of pre defined LUTs is permanently available in the DPU for the generation of the electron Science Data consult Table 1 4 for definitions 1 E 3DD E PAD m 2 Direct Events DE Look up tables are dedicated to either group 1 or group 2 This implies that in contrast to IIMS the two groups are mutually exclusive since only a single LUT is active at any given time A set of about 16 diffe
23. an azimuthal sector with the sector number SCT SCT IN DEX MOD 16 b The DPU starts the transmission in sector SCT by reading out the contents with decreasing priority Pu u 3 2 1 0 the DPU sequences through the sectors until the number of events equals the maximum number S allowed per EDB More precisely this can be written as SCT 15 0 Y P v mod 16 lt S v SCT u 3 with Py designating the number of events per priority P and sector Pu lt 16 the total number of DE events S per EDB is defined in Table 1 4 A definition of the Science Data together with a brief description of the respective prime scientific value is given in Table 1 4 1 19 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu Table 1 4 The RAPID Science Data Data Particle No of Polar Azimuthal Scientific Type Species E Ch Intervals Sectors Objectiv I SPCT H He CNO 8d i i E spectrum PAD H 2w 3x15 16 Pitch angle distr I 3DD H He CNO 8d 12x15 16 3 d distr high res MTRX all all i i A E A distr d E PAD Electrons 2 w 3x20 16 Pitch angle distr E 3DD Electrons 12 d 9x20 i 3 d distr m Electrons 16 Detector index DE All 256 max 12x15 16 High res direct events SGL na na na var Digital pulse rates narrow differential energy channels w wide energy channels i integral The DPU samples the above data types and constructs an experiment dat
24. by the default values listed in Table A 4 1 in Annex A 4 e Pre set upper limits for the high voltage power supplies CHPS and DEFPS ensure that neither a specified target value nor the actual value can exceed the respective limit e Loss of S C provided sector clock causes the DPU to switch automatically to in ternal artificial sector clock e Other features Consult Section 3 1 1 Internal external source for the sector clock is flagged in the HK parameter ERDSSINT see Annex A 1 A source change for the sector clock has no effect on the Oper ational Mode OM of the instrument no mode change This is particularly important for operations in short eclipses compare Section 7 1 for operation in long eclipses compare Section 7 2 3 7 Constraints and Applicability of Telecommands Constraints and criteria for the applicability of telecommands are addressed in Annex A 1 chapter 3 4 for each TC 3 5 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 4 0 Environment 4 1 Thermal 4 1 1 Conditions No particular requirements for any Operating Mode OM other than the temperatures shall have to be within nominal range for platform mounted units 4 1 2 Monitoring Two instrument powered thermistors described in Section 2 2 3 The HK par
25. command interrupt to prevent data loss Else it tests for incrementing of spin counters and telemetry requests to make sure that the system is still running properly If the test result is negative the DPU program waits in an endless loop for the hardware reset from the watch dog unit INTO The highest priority maskable interrupt is assigned to command receiving Every time a complete 16 bit command word is received the interrupt line goes active and the DPU has to read the data from the command latch of the spacecraft interface Before leaving the interrupt it is made sure that the next word wasn t received meanwhile otherwise it is also read INT1 The next priority is given to timer 0 interrupt This timer is used to generate an artificial sector clock in case of missing clock information from the spacecraft SSC SRP INT2 This interrupt appears every 256 ms It is derived from the spacecrafts spin segment clock SSC and used to divide the whole spin measurement period into 16 equal fields The numbering and position relative to the sun direction can be changed by two telecommands Within this interrupt procedure the measurement dead time timer is started to get the same dead time in all sectors independent of the tasks to be performed here There are spin and sector orientated tasks that must be performed within the interrupt procedure or at least during the dead time before the measurement starts again 1 25 DA mu RAPID CL
26. in Annex A 1 chapter 3 3 e Memory Load Commands MLC No specific time delay 4 4 1 2 TEL Timing No requirements beyond existing specifications 4 4 1 3 Sector Timing Sector timing is critical for the science data it is derived from the Sun Reference Pulse and the Sector Reference Clock SRC In case SRC is not available the instrument switches over to an internal artificial sector clock See also Section 3 6 4 4 2 Monitoring No requirements 4 4 3 Control No requirements 4 4 4 Procedures None 4 5 Interface to Other Experiments 4 5 1 Conditions RAPID has a single IEL interface to FGM The magnetic field data are used for on board pitch angle calculations In case the data on the IEL are not usable or corrupted by interference the DPU can be commanded to disable the IEL interface 4 6 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu 4 5 2 Monitoring The status of the IEL interface in the instrument is monitored by the following HK Parameter HK parameter Function ERDIELIE IEL enabled disabled ERDIELCS IEL clock 1 kHz 16 kHz ERDFGMCR Number of FGM vectors received in the last spin ERIPITCH Quality of pitch angle distribution Proper functioning of the IEL can only be assessed by inspecting science data There is no immediate action required 4 5 3 Control The IEL interface is controlled by TC
27. instrument showing the sensor system IIMS and IES Individual detector heads are indicated by Sn n 1 2 3 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py Figure 2 Key components of the dual sensor spectrometer integrated into the single RAPID boxstructure 1 31 up AE RAPID CLUSTER Issue 3 iDA Flight Operation User Manual Rev Date 17 06 2000 Figure 3 A photograph of the RAPID EM unit The sensor system IIMS is on the left side 1 32 i DL mu RAPID CLUSTER Issue 3 IDA Flight Operation User Manual Rev 0 Date 17 06 2000 DIR 8D MIRROR ie FOL MCP ED mt e eae ts AT hie 5 G Sk El2 12 3 7 UE ma E FE ii Fi s it 712 figs Si i yes ps mn T 219 OS MUO N e RER pen STOP COLL 1 DEFL COLL2 STOP HV DISTR Al203 2cm ta Figure 4 Cross sections of the SCENIC head Two narrow collimators COLL1 and COLL2 and a set of deflection plates DEFL form the entry element The foil FOIL and the solid state detector ED define the time of flight geometry The detector BD is in anticoincidence to ED Microchannelplates MCP detect start and stop secondary electrons 1 33 RAPID CLUSTER Issue 3 i DL mu JA Flight Operation User Manual Rev 0 Date 17 06 2000 4000 keV To Tf hk Ty OVERFLOW 1500 keV
28. is monitored in HK parameter ERDDPUCU see Annex A 1 chap ter 4 2 4 2 6 Procedures Condition Power consumption exceeds 100 for more than 5 min HK parameter ERDDPUCU Action Inform PI Limit checking see Table 8 1 Section 8 3 4 4 DA mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 4 3 Communications 4 3 1 Bit Rates Associated to Each TM And Each Instrument Mode The instrument has four different bit rates bps defined by the telemetry The relation ship between TM bps and operational mode OM is as follows TM mode Bitrate bps OM adjusted NM 1 1024 80 a m NM 2 1024 80 a m NM 3 1024 80 a m BM 1 4620 92 a m BM 2 1155 23 a m BM 3 1925 38 a m a m all modes 4 3 2 Conditions No constraints provided S C operates under nominal conditions 4 3 3 Monitoring The instrument has no provision for monitoring the TM 4 3 4 Control No constraints 4 3 5 Procedures Na 4 5 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 4 4 Timing 4 4 1 Conditions RAPID is time critical but the required time accuracies remain well within the Cluster specifications No specific requirements 4 4 1 1 Command Timing The timing of commanded changes in the instrument is entirely an internal process e Direct Commands DC Execution delayed as specified
29. mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 6 0 Nominal Operations 6 1 Operational Scenario a Routine operations of the instrument along the orbit involve a number of different configuration modes CM see definitions below to cope with drastically different flux levels encountered in the various regions of geospace The following typical scenarios are ordered by the apogee position the intention is to provide a baseline for planning some further fine tuning is probably required when in orbit experience is available Configuration Modes CM describe the internal settings of the instrument sensor systems in flight calibrator integration time etc A detailed description of CMs is given in Section 6 1 1 For the present purpose the code CM n illustrates simply the amount of mode switching expected A Apogee in the magnetotail inside the magnetopause Region in geospace Configuration Mode CM Magnetosheet CM 1 Magnetopause skimming CM 1 Lobe Polar cap CM 2 CM 3 Cusp CM 2 Inner Magnetosphere CM 4 inside 5 Rz B Apogee in the magnetosheath between magnetopause and bow shock Region in geospace Configuration Mode CM Magnetosheath CM 2 Magnetopause crossing CM 1 Lobe Polar cap CM 2 CM 3 Cusp if crossed CM 2 Inner Magnetosphere CM 4 inside 5 Rx 6 1 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Man
30. of RAPID 1 2 Instrumentation 1 2 1 The RAPID Spectrometer Outer envelopes of the RAPID spectrometer with some principal dimensions are shown in Fig 1 The instrument is physically a single structure which contains all major elements shown in Fig 2 the SCENIC and IES sensor systems the front end electronics called SCU and the digital processing unit DPU with the the low voltage power supply LVPS and the spacecraft interface in the back of the box Fig 3 is a photograph of the EM unit 1 3 YP AE RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 The sensor system for nuclei is composed of three identical SCENIC heads the acronym will be explained in Section 1 2 1 1 The positions of the three systems S1 S2 and S3 in the instrument reference system are marked in Fig 1 Each spectrometer head Sy y 1 2 3 is protected by a mechanical door After insertion into the vacuum of space the individual door latches are released by bi phenyl C12H10 operated mechanisms and the doors are rotated into the open position by the action of a spring An opened door and the orifice for the bi phenyl evaporation is sketched in Fig 1 for head 2 This rather straightforward scheme for an one shot actuator is based on the vast difference in evaporation speed of large bi phenyl molecules in air and in vacuum However the obvious simplicity of such a device is somewhat offset by the difficult
31. on the instrument health engineering HK data and information relevant for the instrument performance science HK data are transmitted in the HK telemetry HK TM The type of HK data is listed in Table 2 1 2 2 2 Voltage Monitors a Low voltages LV According to Table 2 1 the HK channels 1 to 6 monitor the 12 V and the 5 V lines for the electronic circuitry and the bias voltage 60 V for the solid state detectors three energy detectors and three back detectors The LV lines are either ON or OFF 2 2 DA Py RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 Table 2 1 Source Ch Nr Parameter Type IIMS SCU 12 V 5 V 5 V 12 V E Bias BD Bias STA CHPS STO CHPS DEF PS Door 1 Door 2 Door 3 HV S A Temp1 Sensor Temp2 SCU GND Ref ppr gt pr gt gt gt gt gt gt r gt gt gt gt gt DPU 17 18 19 20 21 Index Status Command Buffer latchup detect status Internal counter II CC IIMS 22 23 24 25 26 Status Calibration data MCP and HV control HK data Single counts ae IES 27 Rates 2 3 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 Parameter HK Name 5 V ERIP5VRF 5y ERIM5VRF 12 V ERIP12RF 19 ERIM12RF 60 V E ERDEBIAS 60 V B ERDBB
32. operations along an orbit can be expected A Apogee in the magnetotail inside the magnetopause Region in geospace Configuration Mode CM Plasmasheet 14 011 or 14 010 Magnetopause skimming 14 011 or 14 010 Lobe Polar cap 24 014 or 24 010 Cusp 24 014 or 24 010 Inner Magnetosphere 11 011 or 11 010 inside 5 Rx B Apogee in the magnetosheath between magnetopause and bow shock Region in geospace Configuration Mode CM Magnetosheath 24 014 or 24 010 Magnetopause crossing 14 011 or 14 010 Lobe Polar cap 24 014 or 24 010 Cusp if crossed 24 014 or 24 010 Inner Magnetosphere 11 011 or 11 010 inside 5 Rx C Apogee in the solar wind outside the bow shock Region in geospace Configuration Mode CM Solar Wind 24 014 or 24 010 Bow Shock 24 014 or 24 010 Magnetosheath 24 014 or 24 010 Magnetopause crossing 14 011 or 14 010 Cusp 24 014 or 24 010 Polar cap Lobe 24 014 or 24 010 Inner Magnetosphere 11 011 or 11 010 inside 5 Rx Typical number of TC per mode change 5 It is anticipated that the autoswitching mode AB 010 for IES will be applied as much as possible unless commissioning or later experience reveals problems with this feature in which case fixed integration times will be used 6 8 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 2 Routine Operations for 1 Orbit per Month Radial distance R gt 4
33. or pedestal value which is different for each channel The pedestal values are stable over time and temperature but must be handled correctly in analysis of the converted ADC value The output of the IES SCU is a set of nine ADC values corresponding to the signal plus pedestal recorded since the previous readout As indicated in Figure 8b each of the energy measurements is associated with a four digit direction number D to form an E D address pair for the information processing in the follow on Electron Pre Processor EPP in the DPU and accumulation by the microprocessor This permits the DPU to handle the IES data at a sample time equivalent to strobing out the SCVC channels As mentioned the IES is a very compact sensor system Because of this compactness it has not been possible to test the system in the standard manner of electronic pulse stimulation through a charge terminator Instead the full system can be stimulated with a set of radioactive sources which produce a series of gamma or X ray lines in the 20 keV to a few hundred keV region When a set of spectra are recorded from these sources it is possible to calibrate the IES system very accurately demonstrate the linearity of the amplifier gains and observe the effect of the pedestal variation from channel to channel 1 14 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 1 2 3 The Digital Processing Unit DPU
34. p7 HIGHXIEL P5 STANDBY1 pd LOWXIEL P24 LOW p24 LOWXIEL P8 OFF ps LOWXIEL P7 STANDBYO p7 LOWXIEL P5 STANDBY1 pd NLOWXIEL P24 NLOW p24 NLOWXIEL P8 OFF p8 NLOWXIEL P7 STANDBYO p7 NLOWXIEL P5 STANDBY1 pd 6 12 17 06 2000 YP AE RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000 7 0 Critical Operations 7 1 Short Eclipse 7 1 1 General Approach During short eclipses perigee eclipse t amp 50 min RAPID will be operated in Stand by mode see Section 2 4 6 i e the HV generators are turned OFF the pre eclipse opera tional mode remains unchanged reference EID A Section 3 3 3 3 2 and Section 10 2 6 7 1 2 Preparation of the Instrument Two cases are distinguished a Payload remains ON in Eclipse No change in the RAPID pre eclipse configuration mode CM In order to monitor the temperature effects on the IES performance the instrument will be set to the IES histogram mode shortly prior and after the eclipse P Name Description Set up Time P16 IES Test Histogram few minutes Objective IES test at pre eclipse temperature Actual test time before entry into shadow is not critical typically 5 min IES test at post eclipse temperatures Actual test time after the S C emerged from shadow must be as short as possible in order to reflect end of shadow temperature effects IES test after temperature recovery to pre eclips
35. processing in the SCU whereas the duple BDI OVF y is transferred directly to scalers in the DPU Level 1 The signals EAN EDI STA STO DD y are offered to the next stage in the SCU for a first evaluation As sketched in Fig 8 the analog signals EANy and the time signals STA STO y are connected to so called OR MUX devices for selection The DPU can specify the sensor operation by setting the E and T multiplexer to the OR or MUX mode In the OR mode signals are accepted on a first come first serve basis in operational terms this mode is called Parallel Mode PM In the MUX mode sensors Sy are selected sequentially and only signals from a given sensor are accepted at a time in operational terms this mode is called Serial Mode SM An analog EANy signal in the E channel is processed only if the digital EDIy meet some constraints The EDly signals are evaluated in the sE TRIGGER LOGIC sE stands for single EAN to ensure that a single Sy sensor was active The peak detector PD in the analog path can operate on the EAN signal only if exactly one out of the three EDIy lines carries a pulse If this condition is met sE TRIGGER LOGIC creates an ENY pulse to indicate that the EAN EDI y combination concurs with the mentioned requirements In general An EAN signal will not be accepted by the PD circuit if 1 9 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 e its amplitude was
36. see Instrument User s Guide Annex A 3 p 5 4 to update Module 14 3 to version 2 01 2 In order to improve the counting statistics for the data type I 3DD the duty cycle for RAP F6 F7 and F8 was increased to 8 16 spins compared to 1 16 spin for F1 Phoenix See also Instrument User s Guide Annex A 3 p 2 1 and p 2 3 7 7 DZ mu RAPID CLUSTER Flight Operation User Manual Issue 3 Rev 0 Date 17 06 2000 RAPID embedded S W Modules Version Module Description Function 1 0 1 0 task manager tool for organization of management 1 0 2 0 interrupt procedures 1 0 2 1 command interrupt process telecommands 1 0 2 2 sector interrupt spin synchronization 1 0 2 3 artificial sector clock 1 0 2 4 latchup interrupt stores LU source 2 0 2 5 watchdog 1 0 3 0 IIMS sensor handling procedures 1 5 4 0 IIMS classification handling procedures 1 0 5 0 IIMS calibration single calibration shot once spin 1 0 6 0 IIMS IFFT in flight functional test 1 2 7 0 command handling execution of TCs 1 0 8 0 telemetry data transfer procedures 1 2 9 0 HK formatting generation of HK frames 10 0 EDB formatting generation of science data frames Del 10 1 IIMS data 3 0 10 2 IES data new beginning scheme implemen tation Jan 97 2 0 11 0 IIMS classification test procedure to test IIMS classifica tion H W and data formatting 12 0 Instrument conf image save restore intr config 13 0 latchup dete
37. tasks controlled by the job manager have to be performed 1 23 D mu RAPID CLUSTER Issue 3 0 Date 17 06 2000 Flight Operation User Manual Rev The watchdog function is implemented by a hardware that generates a NMI every second This NMI must be responded by the DPU within a given time by a port write command at a specific address with a fixed value f1h to prevent the hardware circuit from generating a RESET pulse for the processor system This port write command will only be executed if the spin counter increases for at least 1 step in about 2 5 spins 1 24 DA mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 The real instrument handling is divided into two parts 1 interrupt procedures to handle asynchronous events like telecommands get timing information like the sun pulse or the sector clock and perform tasks that have to be done at exactly that time as for example the starting of measurement periods 2 tasks that are started from the job manager as soon as possible depending on a fixed given priority scheme 1 3 1 1 Interrupt Procedures NMI The NM is the interrupt with the highest priority It is used for watchdog purposes Because there is no hardware FIFO for received telecommands which could arrive every 240 us the NMI first tests whether it interrupted the command interrupt In this case it returns very quickly to the
38. to form a TCR pulse functionally TCR is formed at this stage but the logic is actually located in the DPU This pulse proves that valid analog energy EAN and time TAN signals are present However it is important to note that the compliance of the EAN TAN pair with the trigger condition specified in the TRIGGER LOGIC has yet to be demonstrated in the Level 2 processing phase When the DIR channel has found a single direction a corresponding sDIR 3S signal is created and the direction is characterized by the duple sDIR Sy DIR x with the ranges y 1 2 3 and x 1 2 3 4 1 10 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 As discussed above a particle s direction of incidence within 180 polar angle is defined by a coarse direction Sy one of the three 60 SCENIC heads Sy and a fine direction DIR x division of Sy in four 15 intervals The coarse direction Sy can be obtained from three different channels From the E channel EDI Sy from the DIR channel sDIR Sy and from the multiplexer system E T DIR MUX by selecting a sensor head Sy The fine direction DIR x on the other hand is extracted only from the DIR channels Of particular interest is the susceptibility of this system to particle pile up in the DIR channel and its dependence on the sensor mode parallel or serial Serial Mode The DPU activates a single sensor head Sy at any given time an
39. 0 ENA 46 100 Mass Classes amu 1 4 12 16 28 56 Mass Resolution A dA 4 Oxygen Field of View 6 x 180 17 5 x 180 Angular Coverage Polar Range Intervals 180 12 180 9 Azimuthal Range Sectors 360 16 360 16 Deflection Voltage kV Range Steps 0 10 16 Geometric Factor cm2 sr Total Differential 24 10 2 107 1 2 107 1 4 107 The response functions of the SCENIC head and likewise of the IIMS sensor system is generally described by a complex family of energy dependent functions parameterized by the particle mass A and the selected type of science data science data SD are described e g in Annex A 1 The conversion from observed counting rates n cts sec to particle flux j in physical units is therefore represented by functions of the form j GF e E A SD l n with GF denoting the geometric factor and e describing the detection efficiency as a function of particle energy E particle mass A and selected Science Data channel SD 1 7 YP AE RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 1 2 1 2 The Electron Detector IES Electrons with energies from 20 keV to 400 keV are measured with the Imaging Electron Spectrometer IES Advanced microstrip solid state detectors having a 0 5 cm x 1 5 cm planar format with three individual elements form the image plane for three acceptance pin hole systems Each
40. 000 DZ mu 1 0 Instrument Description 1 1 Overview The RAPID spectrometer for the Cluster mission is an advanced particle detector for the analysis of suprathermal plasma distributions in the energy range from 20 400 keV and 2 keV nuc 1500 keV for electrons and ions respectively Novel detector concepts in combination with pin hole acceptance allow the measurement of angular distributions over a range of 180 in polar angle for either species The detection principle for the ionic component is based on a two dimensional analysis of the particle s velocity and energy Electrons are identified by the well known energy range relationship The detection techniques are briefly described and selected areas in geospace highlight the scientific objectives of this investigation Keywords Energetic particle spectrometer plasma dynamics reconnection field line 1 1 1 Scientific Objectives Over many years of intense research the Earth magnetosphere has emerged as a highly structured and dynamic magnetically contained body of plasma At times or perma nently parts of the magnetosphere seem to be connected with interplanetary field lines The field topology in the outer regions of the magnetosphere and its time dependence is by a large a result of currents carried by the thermal plasma The supra thermal com ponent on the other hand may be less important for most of the macroscopic plasma quantities but it plays an important role
41. 0000 km CM 24 034 At Apogee CM 55 05N to completion CM 4B 114 for 10 min Radial distance R lt 40000 km CM 10 011 or CM 10 010 The assumption is that mode switching is based on model predictions II Special Operations For 1st month Pedestal Monitoring even orbits and R gt 40000 km CM 24 031 or CM 24 034 odd orbits and R gt 40000 km CM 25 014 all orbits and R lt 40000 km CM 10 011 III Special CM on Demand The detection of energetic neutral atoms ENA requires to configure the RAPID unit on one spacecraft in the ENA mode IIMS CM 15 or 25 in Section 6 1 1 2 The orbital segment in the lobes polar cap is ideal for this purpose low background from ions or penetrating particles 6 2 Operational Procedures Procedures for the change of operational modes OP are given in Annex A 3 6 3 Planning The planning of the operational modes and the transitions between these modes is in agreement with the Cluster science operations as recommended to the SWT In practice this means interfacing with JSOC to define the operational modes and the transition procedures that switch between them For the sake of simplification the JSOC modes are given descriptive names which translate into the more precise modes defined in Section 6 1 1 2 The JSOC input is given in Section 6 4 6 9 DA mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000
42. 03 11 95 Cont xi Cont Annex A 1 Sec 5 App Patch Code Gt 2 1 20 04 95 1 1 4 reference formular Si Ru 2 1 20 04 95 1 1 5 reference last chapter Si Ru 2 1 20 04 95 1 1 6 table 1 2 Si Ru 2 1 20 04 95 1 1 7 table 1 3 changes in two last chapters Si Ru 2 1 20 04 95 1 1 11 misspelling reference Si Ru 2 1 20 04 95 1 1 13 misspellings Si Ru 2 1 20 04 95 1 1 22 grammar Si Ru 2 1 20 04 95 1 1 23 misspelling Si Ru 2 1 20 04 95 1 1 25 misspelling formulation Si Ru 2 1 20 04 95 1 1 26 Si Ru 2 1 20 04 95 1 1 27 es Si Ru 2 1 20 04 95 1 1 28 7 Si Ru 2 1 20 04 95 2 2 1 grammar Si Ru 2 1 20 04 95 2 2 2 table under 2 1 Si Ru 2 1 20 04 95 2 2 5 misspelling Si Ru 2 1 20 04 95 3 3 1 grammar Si Ru 2 1 20 04 95 3 3 2 new item under 3 1 3 Si Ru 2 1 20 04 95 3 3 3 changes in table under 3 2 4 Si Ru 2 1 20 04 95 4 4 1 formulation table under 4 1 4 Si Ru 2 1 20 04 95 4 4 2 changes under 4 2 1 and comments Si Ru 2 1 20 04 95 4 4 4 formulation changes under 4 2 6 Si Ru 2 1 20 04 95 4 4 5 misspelling Si Ru 2 1 20 04 95 4 4 6 Si Ru 2 1 20 04 95 5 5 1 2 item under 5 1 Si Ru changes table timeline point 5 2 2 03 11 95 5 5 1 2 item under 5 1 patch code Gt 2 3 19 04 96 5 5 1 table 5 1 1 Timeline Gt Procedures and Durations in Step 2 5 Gt 2 1 20 04 95 5 5 2 table timeline Si Ru 2 2 19 04 96 5 5 2 Procedures and Durations in Step 6 8 10
43. 10 LOW Low flux rates full sensitivity 24 014 or 24 010 NLOW Neutral particle mode for ions low flux 25 014 or 25 010 HIGHXIEL Same as HIGH but with IEL turned off LOWXIEL Same as LOW but with IEL turned off NLOWXIEL Same as NLOW but with IEL turned off STANDBYO Cold standby power on but HV off 10 01N STANDBY1 Hot standby power on and HV on 11 01N The procedures referred to in the 2nd column of Table 6 1 are those defined in Annex A 3 Mode switching Table 6 1 JSOC Modes and Procedures Initial Mode Procedures Final Mode IBMD Procedure Any P8 OFF p8 OFF P6 Previous p6 OFF P1 STANDBYO pl STANDBYO P8 OFF p8 STANDBYO P2 P34 ies_hi HIGH cld_hi STANDBYO P2 P34 ies_lo LOW cld lo STANDBY1 P8 OFF p8 STANDBY1 P18 P34 ies_hi HIGH hot_hi STANDBY1 P18 P34 ies_lo LOW hot_lo HIGH P14 P34 ies_lo LOW hi_lo HIGH P14 P25 P34 ies_lo NLOW hi_nlo HIGH P8 OFF ps HIGH P7 STANDBYO p7 HIGH P5 STANDBY1 pd 6 11 DA mu RAPID CLUSTER Flight Operation User Manual Issue Rev 3 0 Date Table 6 1 JSOC Modes and Procedures continued Initial Mode Procedures Final Mode IBMD Procedure LOW P13 P34 ies_hi HIGH lo_hi LOW P27 LOWXIEL p27 LOW P25 NLOW p25 LOW P8 OFF p8 LOW P7 STANDBYO p7 LOW P5 STANDBY1 p5 NLOW P26 LOW p26 NLOW P26 P13 P34 ies_hi HIGH nlo_hi NLOW P27 NLOWXIEL p27 NLOW P8 OFF ps NLOW P7 STANDBYO p7 NLOW P5 STANDBY1 pd HIGHXIEL P24 HIGH p24 HIGHXIEL P8 OFF ps HIGHXIEL P7 STANDBYO
44. 2 contains same data format as NM 1 BM 3 contains same data format as BM 1 plus additional check bytes compare also Section 6 1 1 1 2 1 YP AE Issue 3 RAPID CLUSTER JA Flight Operation User Manual Rev 0 Date 17 06 2000 2 1 Monitoring Philosophy All monitoring is through the RAPID housekeeping telemetry HK telemetry The HK TM contains data which monitor the technical status of the instrument e g temperatures and voltages and data which allow a quick judgement on the functional performance The latter type of data has also significance for the interpretation of the information in the science telemetry OBDH monitoring S C thermistor in RAP Position Operational RAP Out of Limit Parameter Proc Range Status Actions SCU 30 lt T lt 445 ON T gt 45 RAP OFF ERAP_T P8 T lt 30 No action OFF T gt 45 No action T lt 30 RAP ON if possible Pl 2 2 Housekeeping TM The DPU Software Users Guide Annex A 1 is the reference document for the RAPID HK parameters A A 1 provides a detailed definition of the parameters and specifies the position in the HK telemetry frame at interface to OBDH The document A A 1 is the principle source for Annex A 2 which shows the same information in the context of the HK telemetry down link telemetry A A 2 provides also calibration curves for analogue parameters 2 2 1 Introduction Important information
45. A chapter 3 3 3 2 1 MLCs can be organized as single word commands discrete commands or DC or as multiple word commands block command or BC MLCs are listed and defined in Annex A 1 chapter 3 3 RAPID DC commands are coded ZER BC commands are coded BER 3 2 2 Command Execution Delay DC commands are executed after a pre defined time delay Delay times are specified in Annex A 1 chapter 3 BC commands have no defined delay time activation requires a separate DC 3 2 3 ON OFF Commands The instrument has no internal ON OFF commands 3 2 4 High Voltage Control Critical Commands DC and BC commands which control high voltages or sensitive instrument functions are considered critical Commands of this nature are Telecommand Function Criticallity ZERALEVS Set STA CHPS voltage level Potential danger of discharges ZERPLEVS Set STO CHPS voltage level ZERDLEVS Set DEFPS voltage level s BERIOWRS Write into hardware port Extreme care required 3 2 5 Parameter Commands All DC Commands are Parameter Commands see Section 3 2 1 3 2 6 Alphabetic List of DC and BC Commands Annex A 1 contains listings for both BC commands chapter 3 3 3 and DC commands chapter 3 3 4 3 3 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 un 4 mu 3 3 Reflection of TCs on TM Section 3 4 in Annex A 1 provides a detailed description for each extern
46. A DE SRR Re eA RS 7 2 HAT Peel 1 a eae a we dede 7 2 Pa a A 7 2 72 1 General AMOR ete ROE ai AA 7 2 7 2 2 Preparation of the Instrument Before the Eclipse 7 2 7 2 3 Monitoring or Activities During the Eclipse 7 2 Tad Conditioning alter Eclipse 44 44 4 2 sh va has ae 7 2 IH COMES ee A t he NE pue 7 2 T20 Resources a anna de mue en av ae de E 7 3 111 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 e 0 RE 7 3 7 3 Perigee Passages 4 de be amp Mau de we we a an 7 3 Tal General Approach s us css ah unten 7 3 7 3 2 Preparation of the Instrument Before Perigee 7 3 7 3 3 Monitoring or Activities During Perigee Passage 7 3 7 3 4 Conditioning after Perigee 7 4 EL MI Demi es 7 4 T 30 Resources lt ce a les ee OS HEE RA 7 4 Lal DRAM 22 2 14 as cuite de 7 4 TA Mer oc cere du ara a Dr ARA EES 7 4 7 4 1 General Approach LL 4 4 Sc as d au me eh 7 4 7 4 2 Preparation of the Instrument Before the Manoeuver 7 4 7 4 3 Monitoring or activities during Manoeuver 7 4 7 4 4 Conditioning after the Manoeuver 7 5 Tee RA lt lt Lan ee hei 7 5 A oe Bee eee ERROR eee ea 7 5 EA RR 7 5 To Boundary Crees we du pa die dope Re nie 7 5 Tod Tuner Kress gt iore pee de LUS rear A 7 5 TO P
47. HK telemetry 2 2 5 Analogue Parameter Settings With reference to Table 2 1 only HK parameters 7 8 9 are controlled by dedicated TC all other analog HK parameters are set by RAPID power ON OFF TC 2 2 6 IEL Status and Data The IEL status is monitored by the following parameters Parameter HK Name IEL interface ON OFF ERDIELIE Number of received FGM vectors ERDFGMCR Details are given in Annex A Al 2 2 7 List of all HK Parameters Reference lists of all HK parameters are given in e Annex A 1 chapter 4 1 and 4 2 at RAPID OBDH interface e Annex A 2 A 2 1 A 2 2 down link telemetry 2 2 8 Parameter Short Description Short parameter descriptions are part of reference lists specified in 2 2 7 2 3 Initial Settings 2 3 1 Introduction HK parameters are subcommutated with varying commutation depth After a POWER ON command the following prescription shall be applied e Check HK parameter ERDHKFCR Frame counter or HK set counter This rotat ing 5 bit counter starts at value 0 and increments with every new frame HK set e The first 8 HK sets shall be discarded since the values may not be consistent due to internal settling time 2 5 RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu 2 3 2 Instrument Status The POWER ON command causes the DPU to activate instructions stored in program memory which define the initial c
48. IAS Detailed definitions of the LV related HK parameters and calibration curves are given in Annex A 2 b High Voltages HV According to Table 2 1 the HK channels 7 8 and 9 monitor the adjustable high voltages for the START channelplates STA CHPS the STOP channelplates STO CHPS and the deflection voltage DEFPS Parameter HK Name Range kV STA CHPS ERISTAHV 0 4 5 STO CHPS ERISTOHV 0 4 5 DEFPS ERIDEFHV 0 10 0 Detailed definitions of the HV related HK parameters and the calibration curves are given in Annex A 2 Activation of the high voltage power supplies setting a HV level or stepping the voltage requires special procedures compare Annex A 3 2 2 3 Temperature Monitors Two instrument powered thermistors are used in RAPID ID HK Name Location T 1 ERISTREF IIMS sensor T 2 ERIHKTRF HK board An additional S C powered thermistor is not covered by this document Details of the temperature HK parameters and calibration curves are given in Annex A 2 2 4 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu 2 2 4 Instrument Status The instrument configuration status is generally reflected in the status information of the control logic DPU All analogue parameters Table 2 1 can be used for independent verification of commanded settings or configurations Accepted as well as rejected TCs are reflected in the
49. OFF 14 Modification of Default Setting P23 30 As for step 6 Rephasing of SRP pulse Store new configuration 15 FGM IEL Test P27 5 FGM ON TEL ON default FGM avail on ground IEL OFF WHISPER OFF IEL ON P24 Other No constraints Region M Sheet Inner MSPH 16 Listening Mode 30 FGM ON CM 14 011 WHISPER ON Other No constraints 17 IES test 2us P16 40h 5 As for step 16 continued RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 DL mu Table 5 1 Commissioning Plan and Timeline continued Step Description Proc Time Conditions min 18 IIMS in CM 24 011 P14 30 As for step 16 Listening Mode for IIMS 19 Resetting to CM 14 011 P13 Payload No constraints 20 21 22 Setting as step 19 Data to be recorded for rest of orbit 23 Final adjustments 60 1 week later End of Commissioning Note e All data collected during times with no real time contact should be recorded to improve knowledge about the functional integrity in as many different regions of geospace as possible e Definition of procedures see Annex A 3 e Following POWER ON the instrument assumes full functionality after a delay time of 120 sec In this interval no HK data are produced see also Section 3 6 5 1 2 Operational Constraints Only one instrument at a time Real time HK telemetry must be available High voltage turn on Door position not criti
50. R Flight Operation User Manual DA Py DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 List of Figures E CON MD OF wm 11 12 13 Mechanical configuration of the RAPID instrument 1 30 Key components of the dual sensor spectrometer 2 2 22222200 1 31 A photograph of the RAPID EM unit 1 32 Cross sections of the SCENIC head 1 33 Fraction of the energy time plane covered by the IIMS system 1 34 The IES Sensor Concept 2 2 4 4 4 4 4 4 44e ea de gi 1 35 Energy range covered by the IES detector system 1 36 Simplified diagrams of the IIMS and IES signal conditioning units 1 37 Block diagram of the RAPID digital processing unit 1 38 Schematic representation of the data processing in the DPU 1 39 Diagram ul the ion pre processor IPP 54 ey ua a ees 1 40 Schematic block diagramm of the electron pre processor 1 41 Orientation of RAPID on the Cluster spacecraft 1 42 vil DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 CHANGE REPORT Iss Rev Date Sec Page Changes Orig 2 1 20 04 95 Cont viii 7 1 2 title changed Si Ru 2 1 20 04 95 Cont x misspelling Si Ru 2 1 20 04 95 Cont xi A 3 new arrangement footnote A 2 Si Ru 2 2
51. RO 5W oo AA RA AA AAA RA 7 6 LOL General Approach s Le amp dure ra bo HEE HHO 7 6 oe Lo the Path gt e Li eee ar RAA a e 7 6 7 6 3 Validation and Verification 7 6 7 6 4 Configuration Control of Patching 7 7 7 6 5 Reload of Software after e g Power OFF 7 7 TOGO DIE a Lu 4 4 a ee AE dede Der ce 7 7 e une net ee nd el d nue 7 7 7 6 8 Note on the RAP F1 Phoenix F6 F7 and F8 embedded S W 7 7 8 0 Contingency Operations 8 1 8 1 Failure Analysis FMECA or 2 ee ee ORS ps Be Mad ia 8 1 81 1 G n ral Failures 4 4 4 4 b 2 45 6 au a a da ned ra 8 1 512 High Voltage System 2 ea 4 du da bus dede de et 8 1 ALA Detectors MOP SEDI ji ae nein Vb ed aan 8 1 8 2 Instrument Failure Recovery 8 2 8 2 1 General Recovery Procedure 8 2 9 2 2 Redundancy Draft 224 AA 8 2 8 2 3 TM Parameters Monitored 8 3 8 24 Troubleshooting Chart 4 2 1 zu ceo de os 8 3 8 3 Contingency Recovery Procedures 22 58 24 bee wee ah due 8 3 A 1 Instrument Users Guide A 1 1 lv di AE RAPID CLUSTER Issue IJA Flight Operation User Manual Rev Date 17 06 2000 A 2 TM Parameters Dornier Database A 2 1 A 3 1 A 4 1 A 3 RAPID Command Language RCL A 4 Default Settings Following POWER ON TC Issue 3 Date 17 06 2000 Rev RAPID CLUSTE
52. USTER Flight Operation User Manual Issue 3 Rev 0 Date 17 06 2000 3 Major Configuration Modes LMN Principle IES CMs C C C C C M L 10 Autoswitching mode M L 3N High resolution mode 6 1 1 3 Operational Modes OP Modes M L 11 High flux mode fixed integration time 2us M L 14 Low flux mode fixed integration time 50ys M L 5N Memory dump mode verifies stored pedestal values RAPID operational modes are constructed from IIMS and IES configuration modes Operational Modes are coded OP AB LMN The OP modes will be used for normal NM and burst BM telemetry Short Description of Major Configuration Modes Mode AB IIMS LMN IES POWER ON 10 014 default mode Stand by 10 OMN Hot stand by 11 OMN Nominal operation Low flux mode Fixed int time 24 014 Autoswitching 24 010 High flux mode Fixed int time 14 011 Autoswitching 14 010 In flight Cal 4B 64 sec IMN ENA 15 or 25 LMN ENA Energetic neutral atoms TAutoswitching or fixed times to be decided at commissioning 6 7 RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu I Routine Operations 1 Routine Operations for each Orbit Routine operations of RAPID are largely driven by the ambient particle flux i e the region in geospace Ordering the orbits by the apogee position as in section 6 1 the following routine
53. USTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 increment of the sector number send sector information to the EPP readout of single counters readout of IIMS direct events readout of IIMS classification counters readout of IES classification counters increment spin counters copying of data to the scratch memory latchup detector measurement in sensitive mode in sector 5 IIMS single shot calibration in sector 9 INT3 The IIMS classification parity error interrupt This interrupt disables the classifi cation and starts new table calculations if the tables are corrupted by SEUs INT4 Timer 1 interrupt is used for the dead time period and the switching of IIMS detector heads in serial operating mode INT5 This interrupt should become active if a latchup is detected by the instrument Then the microprocessor has to read the latchup source from a register and write it into the permanently powered latchup free Marconi RAM INT6 This interrupt serves all telemetry inputs Such a low priority interrupt can be used because all signals are buffered by FIFOs or the time until the next event is very long 1 spacecraft RESET pulse signifies a new acquisition frame On that signal the HK FIFO is cleared and a new HK block of 40 bytes is written into the FIFO 2 read complete FGM vector from the spacecraft interface 3 12 bit 3 bit range code 1 trigger b
54. a block EDB as the basic unit for the data transmission to the ground The EDB period T 4 sec is defined by the spacecraft telemetry system however the data structure varies with the telemetry mode Table 1 4 shows the distribution of the Science Data in an EDB for operation in the telemetry nominal mode NM The EDB structure is the ultimate definition of the science return from RAPID Finally it should be noted without details that SCU and DPU provide also valuable information in two other data fields which support the interpretation of the Science Data in a significant way The first set comprises analog and digital housekeeping HK data which reflect the actual operational configuration of the instrument and the health of all subsystems in an engineering sense These data are transmitted in a dedicated telemetry channel The second data set comes from the IIMS built in precision pulse generator used to monitor and characterize the performance of the IIMS SCU and to some extent of the DPU as well The calibrator system operates in two different modes e The In Flight Particle Simulator IFPS A calibrating E T pulse pair is injected into the front end SCU electronics once per spin and with a fixed phase The DPU varies the pulse amplitudes by cycling through a pre programmed sequence which generates these simulated particle events such that an even coverage in A E A space is achieved The IFPS is permanently active and cannot be switc
55. al telecommand in alphabetic order Effects of TCs are reflected in the Returns section of each command description Annex A 1 chapter 3 4 consult also chapter 3 2 3 3 1 Direct Commands Block Commands Compare Section 3 3 3 3 2 High Voltage Control Compare Section 3 3 3 3 3 Parameter Commands Compare Sections 3 2 5 and 3 3 3 4 On board Calibration Tables Modification On board calibration tables cannot be modified by TCs 3 5 On board Software Modification Commands for patching S W are included in Annex A 1 To include patchcode into the running software involves the following commands Telecommand Function BERPLADS Set program load address BERMLDCS Memory load ZERPDISE Enable patches BERJOBS Store job in job manager Patching procedures will be provided when needed Generic procedure for changing on board software e g changing values in look up ta bles See Procedures P 26 in Annex A 3 3 4 DL mu RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000 3 6 Internal Control and Commands The following internal control functions are available e POWER ON commands In the first 120 sec following POWER ON the instrument is in an idle state and is exclusively responding to telecommands as a safeguard for unforeseen deadlock effects The DPU configures the instrument automatically in the POWER ON RESET mode characterized
56. ameters are defined in Annex A 1 chapter 4 Telemetry specifications loca tion etc limits and calibration curves are given in Annex A 2 Reaction in response to deviations in POWER ON condition Limits and required action is described in Annex A 2 HK parameter ERIHKTRF and ERISTRF 4 1 3 Control The instrument has no active thermal control hardware The only means for temperature control by TC is to turn the instrument power ON or OFF 4 1 4 Procedures Condition RCP Function Action T 1 gt 400C P8 power turned off inform experimenter T 2 lt 400C Pl power turned on inform experimenter Procedures RCP are to be executed by ground operations only Procedures see Annex A 3 4 1 DA mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 4 2 Power 4 2 1 Profiles The power for the DPU the SCU and the high voltage power supplies is taken from the 12 V and the 5 V lines Typical values are given in the following table reference line 28 3 V 80 efficiency The power is not mode OM dependent Variation between units 8 5 Condition CM Raw Power Raw Power F 1 mW mW No particles 1000 particles sec Power ON Stand by 3962 3990 HV Relay OFF Mode HV Relay ON Hot Stand by 3990 4018 HV ON Y Operational 4160 4188 Mode 4216 4216 All HV on EoL max Level Operational 4302 4302 Mode
57. anual Rev 0 Date 17 06 2000 Ch No Parameter HK Name Initial Value Function Remark 22 ERDDWISP 6 Dir window STP 5 bits static ERDDWIST 3 Dir window STA 5 bits static ERDEWISP 14 Energy window STP 5 bits static ERDEWIST 6 Energy window STA 5 bits static ERDFLAP1 0 Flap 1 status 0 closed 1 open ERDFLAP2 0 Flap 2 status 0 closed 1 open ERDFLAP3 0 Flap 3 status 0 closed 1 open ERDHMASK 7 Head selection default ERDTCFAC 00 TAC slope default 0 ERIPITCH 66 HEX Look direction for I PAD FGM OFF data formatting 66 HEX FGM ON Value unpredictable 23 Calibration ERICALEN n a Cal energy value varying values ERICALTF n a Cal TOF value varying values 24 MCP HV ERISAREF n a HV disable Reading depends on S C Control control disable connector ERDRELS2 0 HV relay OFF default value all HV voltages OFF 25 HK Data n a 26 Single ERIENYCP not predictable Counting rate SSD 8 bit length compressed Counter Counting rate depends on particle flux ERIENYLB not predictable Counting rate SSD Low Byte 8 bit ERISTACP lt 10 IFC counts HV OFF IFC counts ERISTALB lt 10 IFC counts HV OFF IFC counts ERISTOCP lt 10 IFC counts HV OFF IFC counts ERISTOLB lt 10 IFC counts HV OFF IFC counts 27 Rates ERERATE1 unpredictable IES noise level Det quality ERERATE2 before IES noise level Det quality ERERATE3 ZERELUTS IES noise level Det quality ERERATE4 commands IES noise level Det quality ERERATES IES noise level Det quality ERERATE6 IES noise leve
58. arameters the setting of the high voltage levels is reflected in the HK telemetry 4 3 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 Function HK Parameter A TC HK Parameter D 12 V ERIP12RF 12 V ERIM12RF 5V ERIP5VRF 5V ERIM5VRE STA CHPS ERISTAHV ZERALEVS ERDSTMHC STO CHPS ERISTOHV ZERPLEVS ERDSPMHC DEFPS ERIDEFPS ZERDLEVS ERDDPHCL Definitions of HK parameters and telecommands are provided in Annex A 1 Location in the HK telemetry limits required action and calibration curves are given in Annex A 2 Note For monitoring of the above HK parameters some delay time for the respective parameter has to be taken into account Delay times in the order of a few seconds correspond to time constants in the HV system 4 2 5 Control The power consumption of the instrument is determined by the operational mode OM activated by TC Power consumption for Stand by and Hot Stand by is shown in Sec tion 4 2 1 Excessive power consumption due to latch up leads to an automatic partial power OFF ON cycle Instrument reaction on latch up recovery e DPU powered down for 2 sec except control circuitry e Automatic power up for DPU e Resuming pre event instrument configuration i e operational mode including HV settings remain unchanged by latch up event e Event is flagged in HK parameter ERDLRES Nominal instrument
59. art detection techniques the large energy range for nuclei and electrons and the complete coverage of the unit sphere in velocity space lead to the following capabilities e Remote sensing of local density gradients over distances comparable with parti cle gyroradii Species dependent structures in gradients can be studied gradient motions can be resolved to one spin period T 4 sec e Determination of major ion species H He CNO in the energetic plasma compo nent A special operational mode allows the identification and analysis of energetic neutral atoms ENA e Characterization of magnetic field line topologies using the fast motion of energetic electrons These observational features allow detailed studies in all regions of geospace visited by Cluster The RAPID instrument uses two different and independent detector systems for the detection of nuclei and electrons The IIMS imaging ion mass spectrometer identifies the nuclear mass of incident ions or neutral atoms from the kinetic energy equation A time of flight and energy measurement determines the particle mass One dimensional images of spatial intensity distributions result from the projection principle The IES imaging electron spectrometer is dedicated to electron spectroscopy The well known energy range relationship is used to identify electrons over a limited energy range The RAPID Science Team listed in Table 1 1 is the primary user of the RAPID data Cl
60. ation in the memory To activate the patch code another telecommand is necessary to change a pointer in the non volatile ram to point to the new code instead of the old code in the PROM or to store a job in one of the job managers levels to call the new code See also Section 3 5 1 4 Instrument Physical Characteristics 1 4 1 Location on the Spacecraft RAPID is mounted on the instrument platform the viewing direction is radially outward The instrument position and the angular range of the two sensor systems IIMS and IES is shown in Fig 13 1 4 2 Flight Covers a The three SCENIC heads in the IIMS sensor system are protected by flight covers which are released by an autonomous bi phenyl actuator Release time Approxi mately 30 hours after launch b The three IES detector heads are protected by non flight covers containing desiccant for humidity control These covers are removed shortly before launch leaving the small entrance holes unprotected during launch 1 4 3 Physical Properties Dimensions mm LxWxH 391 x 200 x 208 doors open Weight kg 5 615 Power W 4 500 1 28 3 17 06 2000 Issue Rev 0 Date RAPID CLUSTER Flight Operation User Manual DA Py 1 5 Figures RAPID CLUSTER Issue 3 DA Flight Operation User Manual Rev DA Py Date 17 06 2000 N ISOLATING FEET Figure 1 Mechanical configuration of the RAPID
61. ault Settings Following POWER ON TC A 4 1 i DL mu RAPID CLUSTER Issue 3 DA Flight Operation User Manual Rev 0 Date 17 06 2000 Table A 4 1 Default Settings Following POWER ON TC Ch No Parameter HK Name Initial Value Function Remark 17 Index ERDHKFCR 0 Frame counter counting 18 Status ERDTMMOD 00 TM NM static ERDSSINT 0 Int sectorclock OFF static ERDIELIE 1 IEL interf ON static ERDRAMCK 0 RAM check OFF static ERDSCMXS n a S C MUX n a ERDSCMEM 0 Scratch mem off static ERDSPPOS 7F HEX Sun pos in Sun sector static ERDPATAC 0 Patch OFF static ERDSPSEC 0 Sun sector static ERDDEADT 0 Deadtime static ERDWATEN 1 Watchdog ON always 1 ERDCMDER 0 TC error static ERDCMDIV 0 Invalid TC static ERDCMDVD 0 Valid TC static 19 Command ERDECODE 0000 Errorcode static Buffer ERDLVCMD FF 44 hex Last valid TC static ERDSVCMD _ FF 45 hex Second last valid TC static ERDLICMD FF Last invalid TC static 20 Latch up ERDLUSEN 0 Sensitive mode OFF changes to 1 ON Detector after 32 spins ERDLUDE1 0 LUD MPB OFF ERDLUDE2 0 LUD MPB MEM OFF change to 1 ON ERDLUDE3 0 LUD Counter OFF after 32 spins ERDLUDE4 0 LUD CLASMEM OFF ERDLUMS1 0 LUD MPB Sensitive OFF ERDLUMS2 0 LUD MPB Sensitive OFF change to 1 ON ERDLUMS3 0 LUD MPB Sensitive OFF after 32 spins ERDLUMS4 0 LUD MPB Sensitive OFF 1 Value without any memory uploading before 2 The value effect when Patch b is loaded A 4 2 DA
62. below the lower threshold A no EDI created e the particle energy was sufficiently high to stimulate the back detector BD and the resulting BDI signal disabled the EDI pulse e more then one EDI pulse was detected by the sE TRIGGER LOGIC The T OR MUX circuit in the T channel selects a STA STO pair in a similar manner as the EAN signal is selected in the E channel The time to amplitude converter TAC transforms the pair into an analog signal called TAN T analog with an amplitude proportional to the observed flight time T and issues a digital TAC pulse to indicate the detection of a valid TAN signal In the DIR channel a device marked SEDILO Fig 8 converts the pulse pattern on the DDy lines three times four lines in signals and codes characterizing the status and contents of the direction measurement 1 A sDIR 3S pulse is issued if only a single active x direction was found in all three detector heads 2 The sDIR Sy pulse defines the stimulated detector head Sy y 1 2 3 3 The DIR x x 1 2 3 4 code defines the four look directions in Sy In summary the Level 1 processing leads to the following products A new multiple of digital pulses STA STO TAC ENY is established reflecting that START and STOP pulses are selected and a valid TAN signal is produced an EAN signal from a single detector is received and the signal sampling in the S amp H circuitry is initiated As indicated in Fig 5a ENY and TAC are combined
63. ble before the instrument is config ured after the eclipse 7 2 7 Procedures See Section 7 1 2 7 3 Perigee Passages 7 3 1 General Approach It is expected that the ion sensor IIMS in RAPID will be exposed to rather high counting rates due to both high forward fluxes and penetrating particles when the spacecrafts travel through the inner parts of the ring current region As a result the scientific value of the data may be reduced by background contamination furthermore the high rates may present a lifetime problem for the microchannel plates MCP As a precaution RAPID will be put into the Hot Stand by mode e STA PS STO PS and DEFHV are set to 0 V the power supplies remain ON e The IES sensor remains fully active the integration time constant for IES will be optimized for a high flux environment the solid state detectors in IIMS are active but no TOF measurement Criterion for switching into the Hot Stand by Mode Geocentric radial distance below 5 Rz geocentric Note The commissioning test phase will be used to establish actual counting rates for perigee passes This data base will be used to assess the actual hazard for MCPs and the optimum settings for IES operations A modification of predefined perigee procedures may result 7 3 2 Preparation of the Instrument Before Perigee Before perigee the instrument will be configured in Hot Stand by Mode P Name Description P7 StandBy HV down HV relays OFF
64. boundaries and may result in a modification of the CM table in 6 1 1 3 Special campaigns may require special mode settings 7 5 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 7 6 Patching SW 7 6 1 General Approach There are two possibilities for patching software e Up loaded subroutines are included into the running s w by the embedded job manager e Software hooks can be used to include up loaded program codes Details and procedures will be provided by the experimenter when needed Consult also Annex A 1 sect 5 3 7 6 2 Loading the Patch General procedure e Definition of a target address see command BERPLADS in Annex A 1 e Uploading Patch Code using command BERMLDCS see Annex A 1 Comment The actual amount of commands is defined by the required patch code driven by the detected anomaly 7 6 3 Validation and Verification General approach e Acceptance of the commands defined in Section 7 6 2 verified as described in Annex Al e RAM check to verify positioning and contents of the uploaded code Definition of the RAM check start address uses command BERRCADS Annex A 1 Switching ON OFF RAM check is done by command ZERIRCKS Annex A 1 e Chaining of the patch selection of the chain procedure depends on details of the detected anomaly 7 6 RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17
65. cal no restriction for HV operation 5 1 3 Constraints Regional constraints in GEOSPACE for the commissioning HV turn on Low flux environment preferred IES check out Region not critical but not close to perigee FGM interface Inside magnetosphere WHISPER interference All regions high and low plasma density 5 1 4 Resources On the spacecraft Nominal power and bitrate At ESOC Experiment EGSE and 1 ESOC workstation per spacecraft 9 3 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 5 1 5 Procedures A description of procedures is given in Annex A 3 The procedure used for the commis sioning phase is P3 5 2 Mechanisms 5 2 1 Under Experiment Control The IIMS doors are opened by bi phenyl actuators no TC required Timing Temperature The doors will be released about 35 hours after lift off if the spacecraft temperature is about 20 C Higher temperatures will accelerate the opening process whereas lower temperatures lead to delays It is a single shot release mechanism 5 2 2 Active Covers None 5 2 3 Environmental Control None compare comments in Section 5 2 1 5 2 4 High Voltages ON See initialization procedure in Sections 5 1 and 5 1 5 After successful completion of the commissioning phase the high voltages are routinely turned on and off by applying pro cedures P2 and P7 described in Annex A 3 5 4 DL
66. ctor serving fine strobing of LU circuits 2 0 14 0 EPP handling 1 0 14 1 table calculation calc and load classification tables into EPP 1 0 14 2 test procedures procedures to test EPP H W and data formatting 2 01 14 3 IES automatic mode change 7 8 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 8 0 Contingency Operations 8 1 Failure Analysis FMECA 8 1 1 General Failures Failures in the low voltage area of the electronics DPU SCU are possible but not very likely Procedures for a failure analysis will be provided in case the principle function of the instrument is in question the large variety of possibilities does not warrant any effort at this stage 8 1 2 High Voltage System The high voltage system of the instrument comprises the high voltage generators STA PS STO PS and DEFHV the high voltage distribution and the interior of the sensor systems The HV generators demonstrated short proof capabilities in addition they are protected by internal current limiters In case of a catastrophic failure in one of the three HV generators the unit in question can be disabled without effecting the functions of the remaining generators Impact on instrument operation Consult Section 8 2 8 1 3 Detectors MCP SSD The detectors used in the instrument are e Microchannel plates MCP for the START and STOP systems in IIMS e Solid State D
67. d cycles through the sensor heads Sy y 1 2 3 in a preprogrammed sequence A unique coarse direction y is therefore imposed for all events A fine direction DIR x will be issued by SEDILO only if the DDy code from the DIR channel shows unambiguous direction information Invalid DDy codes two or more lines show high levels due to multiparticle interaction or charge splitting between read out modes disable SEDILO and the triple sDIR 35 sDIR Sy DIR x will not be generated However the DPU accepts the remaining digital signals for accumulation in COUNTER ARRAY but the classification is restricted to MTRX data as will be discussed in Annex A 1 Parallel Mode All three sensor heads are active and particles are accepted on a first come first serve basis The direction of incidence y x is obtained from measured quantities only The unbiased sensitivity over 180 makes this mode attractive in low flux environments but this advantage is increasingly qualified by the susceptibility to multi particle events if the flux exceeds a certain critical level The response to ambiguous directional measurements can be presented in a convenient form by using the definitions 1 11 i DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 e DDu 2 DIR detector in sensor head Su shows two active anodes due to multi particle interaction or charge splitting the DIR detectors from the other heads are ass
68. da man 2 5 228 Parameter Short Description lt c zu 44 2a bee etaa 2 5 e ee 4 Les aan ira naar hans 2 5 241 o ASI Lie a ee ae a 2 5 24 2 ISRAEL Stat s 2 sree 4 RAR A die 2 6 2 3 3 Analog Parameter or Sara una Re ee EE 2 6 2 4 Important Parameters for Prime Instrument Modes 2 6 221 TOR e ra esera dioa oe een ie green 2 6 242 Test and Gommissioning Phase 2 454 255 66654 aa sut 2 6 2 4 3 Technical Mode Memory Dump Mode 2 7 244 DEN Mode ss Leu ss peake toeg fahe a eus 2 7 24 5 Hol oily Mode oc e sesser ana Ress 2 7 240 Nominal Mile s sec e D Le aps ARS aa Es 2 7 3 0 Control 3 1 SL Control Philosophy aus ss le Les dei au merk ans 3 1 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 ALL als A 3 1 312 Parameters 2 2 das mer a a en nn 3 2 ae Modes soea 4 deu 2 En a re 3 2 3 2 External Telecommands s lt e u 0a u an Liu ui aa ei a 3 3 3 2 1 Memory Load Commands MLC 3 3 422 Commend Execution Delay e os a sec so pornos 3 3 329 ON OFF Commies ic r ss ee anea ibea 3 3 3 2 4 High Voltage Control Critical Commands 3 3 3 2 5 Parameter Commands 3 3 3 2 6 Alphabetic List of DC and BC Commands 3 3 3 3 Reflection of TCs on TM 3 4 3 3 1 Direct Commands Block Commands 3 4 3 3 2
69. dle a maximum event rate of roughly 50000 sect 1 16 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 The final product of the classification is the construction of high resolution A E A vectors which are used to address 1 a 16 x 64 matrix counter field and 2 a bin definition field The selected matrix counters are incremented the contents of this counter field represents the IIMS part of the Science Data MTRX The output of the bin definition field is a bin number B which defines 41 bins in the A E A plane The bin number combined with the direction number D addresses the bin counter array and the respective bin counter is incremented The contents of the bin counter array is the basis for the Science Data I SPCT I PAD and I 3DD This process reduces the A E A matrix from a total of 1024 to 41 elements which cover the same area in A E A space with a coarser resolution The above description of the classification process refers essentially to E T D events with valid values for all three parameters Events with missing parameters are processed according to the following scheme missing parameters are shown as 0 E T D Classification 0 T D yes E 0 D no E T 0 MTRX only 0 T 0 MTRX only 1 2 3 2 Electron Pre Processor EPP According to Fig 10 signals from the IES SCU are transferred to the electron pre processor in the DPU
70. e 17 06 2000 1 2 4 The IIMS And IES Science Data The final data products resulting from the DPU are called Science Data According to Fig 10 the main body of the Science Data contains ion data I SPCT I PAD I 3DD electron data E PAD E 3DD m and MTRX data Each one of these data types is obtained from the classification process in IPP and the bin sorting in EPP Two more types of Science Data are provided for IIMS e SGL Data The DPU samples the 45 accumulators in COUNTER ARRAY with specified frequencies and forms single parameter rates called SGL Data e DE Data A fraction of unprocessed E T D events is selected to bypass the clas sification for transmission to the ground so called direct events DE The selection of DE events is based on a four step priority P which is assigned to the bin number B this assignment can be changed by telecommand default is P const for all B of a given particle species Priority P 3 refers to high priority particles With this definition priorities are assigned as follows Priority P 0 1 2 3 Species ep He CNO Si group A maximum of 16 DEs per priority is accepted in each of the 16 azimuthal sectors on a first come first serve basis and written into a 4x 16 x 16 event buffer Events are selected for addition to an EDB by applying the following prescription a At any given time the four least significant bits of the spin counter INDEX designate
71. e As a result little practical value will be put on these modes e The coincidence condition in Mode 2 has a reasonable efficiency but the accepted event structures have clearly a mixed distribution e The double coincidence in Mode 4 is lower in occurrence rate than Mode 2 but it creates clean distributions with acceptable efficiency This mode is therefore the preferred operational mode e Modes 5 and 6 are implemented merely for the case of drastic failures in either the energy or the time channel The E and T ADC in the DPU start the conversion in binary codes if the analog pair EAN TAN meets the coincidence requirement set in TRIGGER LOGIC and the event now represented in an all digital form is ready for the classification process in the DPU 1 2 2 2 The IES Signal Conditioning Unit Figure 8b shows the principal features of the IES signal conditioning unit The initial am plifier stages for the nine energy channels and a multiplexer are implemented in monolithic technology This chip a development of the Rutherford Appleton Laboratory Oxford UK is physically integrated into the sensor housing The second part of the SCU accepts the serialized output signals from the chip for amplification in a single amplifier chain and subsequent digitization This part of the SCU is designed with standard electronic components 1 13 vr AE RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000
72. e of DEFL is to protect the instrument from overloads due to large fluxes of low energy particles e g solar wind plasma Some selected technical parameter of the SCENIC head are listed in Table 1 2 1 5 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu The relative high gain of the active collimator approx 10 allows efficient separation of energetic neutral atoms ENA from ions for energies up to 100 keV This energy band is generally considered important for magnetospheric neutrals produced in the ring current region Table 1 2 Technical parameter of the SCENIC head Flight path s mean 34 mm Field of view total 12 x 60 Polar angles 4 x 15 E Detector ED Area Thickness 5 x 15 mm 300 y B Detector BD Area Thickness 5 x 15 mm 300 u START foil nominal Al Lexan Al ug cm 17 10 17 Deflection voltage 0 10 kV The fraction in E T space covered by the SCENIC head is shown in Fig 5 together with calculated loci of major magnetospheric nuclei or groups of nuclei The width of the particle traces reflects the effect of flight path variations over the 60 opening of the SCENIC head The energy E scale from 0 keV up to 4000 keV is partitioned by discriminators B and C which define a lower threshold for energy measurements at 30 keV an upper limit of the linear range at 1500 keV and an overflow limit at 4000 keV respectively The time
73. e value Test at t 50 min after eclipse b Payload has to be turned OFF in Eclipse The following procedures apply P Name Description Set up Time P8 POWER DOWN Power off sequence few minutes P6 POWER UP Power on sequence 10 minutes to pre eclipse CM The required procedures are given in Annex A 3 7 1 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 7 1 3 Monitoring or Activities During the Eclipse The instrument status and behaviour is monitored by the normal HK channels no special activities are foreseen 7 1 4 Conditioning after the Eclipse See Section 7 1 2 a and b 7 1 5 Constraints None 7 1 6 Resources It is assumed that nominal power for the instrument can be provided 7 1 7 Procedures See Section 7 1 2 7 2 Long Eclipses 7 2 1 General Approach See specifications in EID A Sections 3 3 3 3 2 and 10 2 6 7 2 2 Preparation of the Instrument Before the Eclipse Same as Section 7 1 2 7 2 3 Monitoring or Activities During the Eclipse During long eclipses no activities are planned monitoring is not required 7 2 4 Conditioning after Eclipse See Section 7 1 2 7 2 5 Constraints None 7 2 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 7 2 6 Resources Nominal spacecraft power and bitrate must be availa
74. er D 0 11 which defines twelve unique directions within the 180 polar range of the instrument with the counting convention specified in Fig 13 In case the sDIR 3S pulse fails to indicate the presence of a high resolution directional measurement positive identification of a single direction out of the 12 polar angular intervals the DPU determines a coarse y direction from the EDI y pattern and assigns to these the direction numbers D 12 13 14 inspect Fig 13 for the counting convention The event E T D is now prepared for the classification process in the follow on ion pre processor or IPP in Fig 11 The objective is to extract from the E T pair the particle mass A and the energy per mass ratio E A with high precision In addition the A E A space is subdivided into a coarse bin field which is then combined with high resolution direction information This leads to a substantial reduction in the required data rate without the necessity to reduce resolution in time and direction The DPU initiates the classification process upon the appearance of at least one of the trigger signals Es and Ts The E A ratio is established in a straightforward single table look up technique since this quantity is obtained from the measured flight time T directly The particle mass A on the other hand depends on energy E and flight time T A 4 step successive approximation in an E f T A table is applied to obtain the mass A This process can han
75. etectors SSD ion implant single active volume detectors IIMS e Solid State Detectors SSD ion implant microstrip detectors IES All detectors are very delicate objects with some sensitivity to particle flux SSD or extracted total charge MCP Detectors are usually bottlenecks i e loss of a detector leads to the loss of an entire data channel there is no redundancy in the detector system but the degradation of instrument functions is reasonably weakly dependent on detec tor failures due to the number of systems used Impact of detector loss is detailed in Section 8 2 8 1 DA mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 8 2 Instrument Failure Recovery 8 2 1 General Recovery Procedure In case a catastrophic failure is detected in either the HV system or in a detector MCP or SSD the instrument will be commanded into an operational mode which eliminates the use of the suspected detector or component A certain loss of data is an inevitable result of this recovery process however in most cases the remaining science data are not expected to show degradation in quality 8 2 2 Redundancy Concept As already mentioned above RAPID has no redundancy in the detector or HV system but a few precautionary steps were taken to reduce the science loss due to a single failure in this area DEFHV Single unit failure can result in loss of deflection voltage the inst
76. execution every spin execution in next spin execution every 64th spin execution in next 64th spin D N Q A WO N FR execution immediate with lowest priority All normal measurement tasks are implemented as jobs in level 2 or 5 Command exe cution is done with level 4 stepping of high voltages is implemented as level 6 job IIMS classification test is done with a level 9 job Jobs could be added or deleted to these tables and FIFOs at any time by telecommand 1 27 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 1 3 1 3 On Board Software Modifications During flight new program code or parameters for table calculations can be sent to the RAPID DPU details on program patches and table patches are addressed in Section 7 1 For this purpose some commands are defined to select the physical memory address or for parameter loads a logical memory address where the the new bytes should be stored Most likely this will be an address in the permanently powered ram area where the new bytes are kept available even in non operating periods of the instrument for the next power on situation After transmitting of the target address to the DPU the bytes themselves are sent They are collected in a buffer until the complete block has arrived Then CRC checking is performed and the result is echoed in the HK frame If the CRC is ok than the block will be moved to the right loc
77. he IES detector heads develops excessive noise no recovery action is possible Dependant on the noise level the system either tolerates the malfunction or the data are corrupted to a point which makes them unusable IES cannot be powered down separately 8 2 3 TM Parameters Monitored No special arrangement required all functions will be monitored through the normal HK channels by instrument and technical HK checks by ESOC compare Annex A 2 2 8 2 4 Troubleshooting Chart The nature of a failure dictates the amount of troubleshooting required to identify the kind of failure and to develop means to recover instrument functions Most of the conceivable failure modes described in Section 8 2 2 are likely to be discovered in the HK data or in the science data A need for additional troubleshooting may or may not arise 8 3 Contingency Recovery Procedures Table 8 1 summarizes all analog digital HK parameters for which a specified action is required in case the parameter exceeds deviates from prescribed ranges values The column Action describes steps to be taken by the ground operator in proportion to the severity of the deviation observed Table 8 1 HK Parameter Analog range Action Identifier Digital Value ERDSSINT 1 Inform PI ERDBBIAS 8 3 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py A 0 4 Issue 3 Rev 0 Date 17 06 2000
78. hed off A comparison of the simulated event pattern with the image obtained by the DPU reveals irregularities in the analog and digital signal processing IFPS results are transmitted with full resolution in a dedicated area of the EDB not included in Table 1 4 and contribute to science data I SPCT MTRX and SGL rates 1 20 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 un 4 mu e The In Flight Functional Test IFFT This routine must be initiated by telecom mand and the instrument resumes the pre test operational mode automatically after completing the test The IFFT monitors threshold positions and amplifier linearity in the SCU It should be noted that the transmission of science data is incomplete during operation of the test routine The distribution of the Science Data in an EDB is defined in the Instrument User Guide Chapter 2 on Annex A 1 1 21 YP AE 4 Flight Operation User Manual Rev 0 Date 17 06 2000 RAPID CLUSTER Issue 3 1 3 On Board Software Instrument Software Tasks IIMS sensor handling procedures A collection of small procedures to handle the interface hardware to the IIMS SCU and the stepping of high voltages IIMS classification handling procedures Procedures to calculate classification ta bles control the classification state machine and readout the results Furthermore a test program to verify that the hardwa
79. ically shown in Fig 10 The multitude of IIMS signal channels shown on the left side of Fig 10 is divided into three groups The first group includes the 18 digital pulse channels A subset TAC EDI y sDIR Sy DIR x is passed through a logic to expand the TAC and EDI y pulses into channels with higher directional resolution This process leads to pulse types of the form TAC y TAC yx and EDI yx These pulses and the set STA STO BDI y OVF y ENY sDIR 35 are offered to COUNTER ARRAY Fig 10 to increment appropriate scalers 1 15 YP AE RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 The second group is essentially a duplication of direction relevant information from the DIR and E channels sDIR Sy sDIR 3S DIR x EDI y and the overflow indicator OVF y This subset is used for consistency checks in a precursing process before the analog signals EAN and TAN in the third group are accepted for digitization and classification Events showing overflow in the energy channel E gt 4 meV and or inconsistent direction information in EDI y and sDIR Sy are discarded For all other events the two ADCs can be enabled by the trigger signals Es and Ts At the same time the DPU processes the event related direction information sDIR Sy DIR x and synchronizes it with the digitized E T pair to remove dynamic phase shifts The DPU also converts the SCU direction code y x into a serial numb
80. it for the scratch memory 3 fill telemetry FIFO with next 512 bytes block INT7 Timer 2 is used to generate the timing of IFFT shots to the IIMS SCU 1 26 DA mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 1 3 1 2 Job Manager Tasks The job manager is a program to manage event triggered software execution that means every time a special event has occurred for example the begin of a sector or a spin a signal is sent to the job manager Then it looks whether there are procedures to be executed at this event and eventually starts them There is always only one task active at a time but this task must be interrupted by a task which is more urgent So it s easy to understand that all sector related jobs must be completed before spin orientated jobs because the latter could be completed at any time during the 4 s spin period whilst sector jobs must end before the next sector starts 250 ms sector period To solve this problem a fixed priority scheme is implemented Furthermore the job manager can handle two different types of tasks those that have to be executed once function pointers to these tasks are stored in FIFOs and tasks to be performed every time the signal is received stored in tables For RAPID there are 9 priority levels execution immediate highest priority execution every sector execution in next sector execution after receiving a command byte
81. l Det quality ERERATE7 IES noise level Det quality ERERATES IES noise level Det quality ERERATE9 IES noise level Det quality ERDIESIE 1 IES interface ON default value ERIPADTS 0 IES pitch angle format default EPAD formatting method ERECMDRT 0 IES TC answer default setting 2 us LUT 1 t 2 psec LUT 1 binning integration time 2 usec default value EREFXLUT 0 Autoswitching Default fix bit Autoswitching ON A 4 4
82. mode stand by power is required from KAL at all times Lack of stand by power results in the loss of memory and will require extensive memory loading procedures following each POWER ON command b Science Burst Mode BM RAPID can operate under three burst modes with different accelerated bit rates BM 1 Nominal telemetry mode for high speed data taking BM 2 Identical to NM 1 BM 3 Read out of RAPID scratch memory BM 1 EDB format plus check bytes Compare also Section 2 0 6 1 1 2 Configuration Modes IIMS and IES are largely independent subsystems of RAPID with different internal set up structures called Configuration Modes CM Configuration modes emergency modes are not considered are conveniently represented by Mode Matrices 6 3 i DL mu RAPID CLUSTER Flight Operation User Manual Issue Rev 3 Date 17 06 2000 a IIMS Configuration Modes AB 1 Definition of A B The configuration parameter A and B refer to two independent functional levels in the internal control system of the instrument The parameter A defines sensor and or DPU operations parameter B defines the HV conditions in the instrument A B 0 OFF 0 HV OFF relay OFF is 1 HVON STA 0V STO 0V DEF OV 2 P 2 HVW ON STA r STO s DEF t 3 SWG 3 HVON STA R STO S5 DEF T 4 IFFTON 4 HVON STA R STO S DEF 0V 5 DPU Test 5 HV ON STA R STO 5 DEF 10 kV Comments DPU Test RAM ROM dum
83. n and signal processing on different levels An important task of the SCU is to ensure that signals generated in the IIMS sensor system are indeed caused by a single incident particle Within limits the SCU detects and excludes events which involve two or more particles arriving at the sensor system within a defined time window The following is a description of major electronic SCU components and the sequential signal processing on different levels 1 8 RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu Level 0 A particle passing through a SCENIC head Sy is analysed with respect to its flight time T or equivalently to its velocity to its energy E and to its direction of incidence DIR Accordingly the SCENIC head generates a set of signals analog and digital in the energy E the time T and the direction DIR channel with the following definitions CH SIGNAL DEFINITION E EAN Analog signal from the energy detector ED EDI OVF Digital pulses from the lowest A and highest C thresholds in the ED amplifier chain Overflow indicator BDI Digital pulse from the back detector BD BDI inhibits EDI and OVF T STA STO START and STOP signals DIR DD One out of four direction signals The signal multiple EAN EDI OVF BDI STA STO DD y obtained from the head Sy represents an event at level 0 The subset EAN EDI STA STO DD y is used for further
84. nattended periods Automatic monitoring of a minimum number of parameters e g S C powered thermistor in RAP a Critical for instrument health b Critical for scientific quality 3 1 YP AE RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000 Execution of an external TC is generally delayed until the beginning of the next spin rotation although some TCs are associated with longer delay times consult Annex A 1 chapter 3 3 3 1 2 Parameters Parameters may be changed at any time by single TCs or by sequence of TCs For example changing a high voltage level requires typically 4 TCs Operational Modes OM are defined with nominal settings of the high voltages but without changing the OM other HV levels may become desirable to adjust for gain changes Similarly selected detector heads can be omitted from the measurements or the TAC slope can be changed to compensate for changes in the electronic system After sending a POWER ON command the DPU configures the instrument according to information stored in a PROM A multitude of configurational parameters variables can be stored in the non volatile RAM keep alive line powered Two storage modes are implemented a The current instrument configuration can be frozen in the RAM by TC ZER CFGSS parameter 0 This set of parameters can be loaded into the volatile main RAM at any later time by TC ZERCFGSS parameter 1
85. nce 7 4 3 Monitoring or activities during Manoeuver N a since instrument is not powered 7 4 YP AE RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000 7 4 4 Conditioning after the Manoeuver Configuration procedure for normal operation P Name Description P6 PowerUp Standard Power ON sequence boot sequence IES T 2 usec autoswitching ON 7 4 5 Constraints None 7 4 6 Resources Full telemetry link for instrument commanding 7 4 7 Procedures Instrument operations before and after manoeuvers involve procedures defined in Sec tions 7 4 2 and 7 4 4 definitions are given in Annex 3 2 7 5 Boundary Crossings 7 5 1 General Approach The in orbit operations for RAPID are based on the principle minimal mode changes Along trajectory the instrument modes are driven by the particle flux encountered Final decisions on routine mode changes can only be taken after the commissioning phase Potential mode sequences and switching criterion see Section 6 1 1 3 I Mode changes along an orbit are subject to a critical review after the commissioning phase The intention is to minimize the number of routine mode changes Crossings of boundaries such as the magnetopause bow shock etc may require mode changes 6 1 1 3 Experience gained during the Commissioning Phase will establish a baseline for routine mode switching at
86. nges in Table 1 4 E 3DD Electrons 12 d Gt 2 1 08 02 99 1 1 21 removal of Table 1 5 Science Data in an EDB Gt 2 2 08 02 99 6 6 6 changes in 1 LUT1 and 2 LUT2 2 256 to 12 Gt binning 2 2 08 02 99 7 7 5 changes in 7 4 4 boot sequence IES T 2 us Gt 2 2 08 02 99 7 7 7 7 6 9 new Note concerning embedded S W Gt 2 0 08 02 99 7 7 8 new RAP embedded S W Modules Gt 2 6 21 05 99 Anx 1 all see separate change report PWD 3 4 08 02 99 Anx 3 all see separate change report PWD DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 CHANGE REPORT Iss Rev Date Sec Page Changes Orig 3 0 17 06 00 all all Repackage sources for electronic version new PWD header uniform issue and revision number for all pages spelling and other cosmetic fixes 3 0 17 06 00 1 1 3 Revise list of Co Is PWD 3 0 07 03 00 5 5 1 Revise commissioning plan PWD 3 0 17 06 00 6 2 6 6 6 9 Change mode descriptions for single LUT and PWD autoswitching 3 0 17 06 00 6 6 10 Include JSOC input PWD 2 7 15 02 00 A 1 all see separate change report PWD 4 0 11 03 00 A 3 all see separate change report PWD xi Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py 0 12 RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2
87. on its own rights due to peculiarities in the physics of energetic particles Acceleration processes in the magnetosphere of still un known nature energize particles elsewhere in the magnetosphere to hundreds of keV The relatively fast motion of these particles can carry information about the energization pro cess over significant distances to an observing platform Studies of the intensity profile the energy distribution and the ionic mass and charge composition can provide important clues on the nature of the process Furthermore the kinetic properties of these particles can be used as a tool to trace out plasma structures over distances as large as an Earth radius by utilizing the particle s gyroradius Information can even be transmitted over global distances by the rapid drift of energetic particles in field gradients or even more important by field aligned swift electrons travelling with speeds comparable with the speed of light In tail like field configurations these particles can transmit over very large distances almost instant information on changes in the field topology 1 1 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 DL mu The Cluster polar orbit 4 x 19 Rg provides excellent opportunities for energetic particle studies The physics at the magnetopause the bow shock and the near earth magnetotail are key regions of interest for the RAPID investigation The state of the
88. onfiguration of the instrument Details of the initial pa rameter settings see Annex A 3 Procedures procedure P 1 and related default settings shown in Table A 4 1 in Annex A 4 2 3 3 Analog Parameter The POWER ON command configures the analogue parameters as follows Parameter HK Name Raw Value STA CHPS ERISTAHV 128 STO CHPS ERISTOHV 128 DEF PS ERIDEFHV 128 For all other parameters consult default settings listed in Annex A 4 Table A 4 1 2 4 Important Parameters for Prime Instrument Modes 2 4 1 Introduction The instrument can be operated in a large variety of modes or configurations A small sub set of these modes defines the so called Operational Modes OM described in Section 6 0 all other potential modes are activated only in the case of unexpected malfunctions or functional flaws these modes will not be described in this document 2 4 2 Test and Commissioning Phase Parameters will be checked in dependence on telecommand sequences see Section 5 0 virtually any parameter can be considered relevant in this phase Consult Annex A 3 Procedures procedure P 3 2 6 RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 i DL mu 2 4 3 Technical Mode Memory Dump Mode Required only on specific request by experimenter requested only if data indicate un explained peculiarities In such a case selected RAM fields will be checked The re
89. ose collaboration with the other Cluster teams is essential to bring to bear the wealth of information expected from this multi spacecraft mission which indeed offers an un precedented scientific tool for studies of long standing problems in the magnetosphere 1 2 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 Table 1 1 The RAPID Science Team Principal Investigator B Wilken MPAe Lindau FRG Co Principal Investigators P W Daly U Mall MPAe Lindau FRG Co Investigators J B chner A Korth MPAe Lindau FRG S Livi J Woch ii T A Fritz Boston Univ Boston USA M Grande C Perry RAL Chilton UK M Carter J B Blake J F Fennell AC Los Angeles USA F Sorass K Aarsnes UoB Bergen Norway D N Baker LASP Boulder USA H Borg I Sandahl IRF UmeA Sweden R D Belian G D Reeves LANL NM USA K Mursula UoO Oulu Finland S McKenna Lawlor SPC Maynooth Irland F Gliem IDA Braunschweig FRG K Kecskem ty KFKI Budapest Hungary E T Sarris UoT Thrace Greece Z Y Pu Beijing Univ Beijing China Associated Members Sir W I Axford MPAe Lindau FRG V M Vasyliunas M Schulz Lockheed Lab Palo Alto USA P Tanskanen UoO Oulu Finland M Scholer MPE Garching FRG The following sections describe the detection techniques employed in IIMS and IES and expand on specific aspects of the signal processing and data generation in the two seg ments
90. p HV step r s t arbitrary step numbers between 1 and 16 HV step R S T fixed step numbers defined by ground calibration 2 Two dimensional Mode Matrix AB for IIMS A B 0 1 2 3 4 5 00 10 20 30 40 50 Ol amp D Fr 11 12 13 21 22 23 31 32 33 41 42 43 91 52 53 14 24 34 44 54 15 25 39 45 99 6 4 DA mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Date 17 06 2000 3 Principal IIMS Modes CM 00 POWER OFF CM 1B SERIAL Mode the 3 SCENIC heads are activated in a standard 1 2 3 sequence only 1 SCENIC head is active at a time CM 2B PARALLEL Mode the 3 SCENIC heads are all active at the same time Particles will be processed on a first come first serve basis CM 3B SWG Mode SWITCHING Mode the 3 SCENIC heads are sequenced in a pre scribed pattern selected by TC As in SERIAL Mode only 1 SCENIC head is active at a given time CM 4B IFFT inflight calibrator ON Activated by TC upon completion of test sequence instrument returns to the pre test configuration automatically CM 5B DPU Test Mode DTM Verifies stored coefficients for particle mass determination 6 5 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 b IES Configuration Modes LMN 1 Definition of L M N The operation of the IES subsystem requires three parameters L
91. quired command sequence is described in Annex A 3 Procedures procedure P 4 HK parameters to be monitored HK Name Value ERDRCHKL Lower RAM address ERDRCHKU Upper RAM address ERDRAMCK Memory Dump ON OFF 2 4 4 Standby Mode In this mode the instrument is configured in any of the Operational Modes OM described in Section 6 0 with the high voltage power supplies TURNED OFF Required parameter settings See Section 2 4 5 2 4 5 Hot Standby Mode In this mode the instrument is configured in any of the Operational Modes OM described in Section 6 0 but the high voltages STA CHPS STO CHPS and DEFPS are set to the lowest level U 0 V Required command sequence is described in Annex A 3 procedure P 5 HK parameters to be monitored Mode Parameter HK Name Value Hot Stand by 1 Relays ON ERDRELS2 1 ON Stand by 0 Relays OFF ERDRELS2 0 OFF 2 4 6 Nominal Mode Routine operational modes are called Nominal Modes NM with defined HV settings and sensor configurations For all Nominal Modes the following parameters are considered most important Parameter HK Parameter Value STA CHPS ERISTAHV see Section 6 0 STO CHPS ERISTOHV id DEFPS ERIDEFHV 2 2 7 Issue 3 Date 17 06 2000 Rev RAPID CLUSTER Flight Operation User Manual DA Py YP AE RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000
92. re is working correctly IIMS calibration Software to stimulate the sensor electronics so that they generate test events that can be processed by the classification unit in the DPU There are two calibration modes the always running single shot calibration and the in flight functional test IFFT that is only executed on command command handling Administration of the command buffers and FIFO checking of the commands and execution of them Return codes of commands are sent to the HK frame generating software save and restore of the instrument configuration Automatically every spin the actual instrument configuration is stored in the NV ram to get the ability to restore the instrument status after switching off because of a detected latchup Additionally you have the chance to store the actual configuration at any time and reconfigure to this state later on telemetry 1 HK formatting 2 EDB formatting 1 22 RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 DA mu 1 3 1 Architecture RAPID DPU software is completely written in 80C86 assembler It consists of a short main program the NMI procedure to control the watchdog functions and an event trig gered task manager called job manager The main program only initializes the DPU hardware and software variables on power up Then it stays in an infinite 1 ms loop to determine free processor time when no interrupt driven
93. rent LUTs is required to cover the entire range in energy and direction for the high resolution direct events in group 2 1 2 3 3 On Board Pitch Angle Computation The RAPID spectrometer is connected to the magnetic field instrument FGM via an inter experiment link IEL FGM sends 64 uncorrected magnetic field vectors Bx By Bz per spacecraft rotation T 4 sec Vector components are offered in digital form with a width of 12 bits each The objective is to determine for each of the 16 azimuthal sectors which look direction in the IIMS and IES fan respectively is perpendicular to the current B vector the DPU uses the second B vector received in a given sector as the reference vector The DPU implements this 90 pitch angle determination by applying the following al gorithm in each sector Vectors D v 0 11 for IIMS and v 0 8 for IES with normalized magnitude are introduced to describe the boresights of the detector look direc tions A software routine calculates the 12 9 vector products D e B and determines the vector D for which the product assumes a minimum value i e the direction D corresponds to 90 pitch angle The number of events accumulated with the direction number D n are part of the I PAD E PAD Science Data together with events from detectors with the fixed direction numbers D 0 and D 11 D 0 and D 8 for IES 1 18 DL mu RAPID CLUSTER Issue 3 Flight Operation User Manual Rev 0 Dat
94. rument works perfectly well with no deflection voltage in the collimator MCPHV The high voltage bias for channel plates is provided by two independent power supplies The START plates are driven by the STAPS and the STOP plates are drive by the STOPS Loss of one system results in the loss of atomic mass information from all three IIMS sensor heads the sensor heads continue to function as particle counters without mass identification 300 V The low voltage power supply provides also the 300 V bias for the three microstrip SSD in the IES heads The 300 V line has no independent control but is current limited in case of a short The total loss of IES can result if the 300 V is lost or pulled down significantly START MCP Substantial increase of dark current in one START channel plate can be tolerated by the STAPS the sensor system in question can be totaly disabled should crosstalk lead to unacceptable interference STOP MCP Same as for START MCP E DET Energy detectors in IIMS E Det n n 1 2 3 Any noisy detector can be eliminated by TC Result Loss of atomic mass information from one sensor head 8 2 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 B DET Back detectors in IIMS B det n n 1 2 3 Any noisy detector can be disabled by TC Result Loss of high energy response in the affected sensor head IES Det If one of the three microstrip detectors in t
95. system divides a 60 segment into 3 angular intervals A schematic cross section of an IES pin hole camera is presented in Fig 6 Three of these detectors arranged in the configuration shown in Fig 1 provide electron measurements over a 180 fan The 800 micron thick ion implant solid state devices are covered with a 450 g cm Si eq absorbing window which eliminates ions up to 350 keV through the mass dependent range energy relationship The principle energy range for IES is shown in Fig 7 The 9 individual strips on the three focal plane detectors are interrogated by a multi channel switched charge voltage converter SCVC in monolithic technology The SCVC provides for each particle coded information on the strip number and particle energy This primary information is transferred to the DPU for further evaluation 1 2 2 Signal Conditioning Units SCU The general lay out of the RAPID instrument in Fig 2 shows that either of the two sensor systems is followed by a dedicated circuitry called signal conditioning unit or SCU The primary task of the SCU is to provide proper analog amplification and signal shaping event definition logic control functions for configuring the detector system and to interface with the digital processing unit or DPU 1 2 2 1 The IIMS Signal Conditioning Unit Fig 8 is a simplified representation of the SCU which is intended to amplify essential components and their role in the complex signal generatio
96. ual Rev 0 Date 17 06 2000 C Apogee in the solar wind outside the bow shock Region in geospace Configuration Mode CM Solar Wind CM 2 Bow Shock CM 1 Magnetosheath CM 2 Magnetopause crossing CM 1 Cusp CM 2 Polar cap Lobe CM 2 CM 3 Inner Magnetosphere CM 4 inside 5 Rz Typical number of TC per mode change 5 b Monitor and Housekeeping Box N A c Once per orbit the in flight calibration CM 3 will be activated in a low flux envi ronment lobes After completion of the IFFT cycle about 240 sec the instrument returns to the pre test configuration 6 1 1 Mode Structure Telemetry Configuration and Operational Modes Operational Modes OM The RAPID operational modes OM are formed by the telemetry mode TM normal and high bitrate see Section 2 0 and the internal instrument configuration mode CM OM TM CM 6 2 DL mu RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000 6 1 1 1 Telemetry Modes The RAPID telemetry modes and bitrates are shown in Sections 2 0 and 4 3 1 a Science Nominal Mode NM For RAPID all NM are equal NM 1 NM 2 NM 3 The instrument will operate more than 90 of the time in an unattended telemetry mode NM 1 Energetic ions and electrons are analysed and processed on board by look up tables contained in EPROM devices or by LUTs generated from uploaded TCs In the POWER OFF
97. umed inactive e 2DD DIR detectors from two different heads Su and Sv show valid single direc tions the third detector is assumed inactive e EDI y Single s or multiple m y directions active and by referring to the DPU description SENSOR SEDILO DPU EDI y DDy sDIR 3S sDIR Sy DIR x CLASSF CTR ARRAY s m DDu 2 I MTRX Yes S valid Yes EDI Sy Yes no Yes s m 2DD sDIR Su v no Yes Level 2 The digitization of the EAN and TAN amplitudes in the analog to digital converters actually located in the DPU depends on precise coincidence conditions The circuitry TRIGGER LOGIC imposes commandable trigger modes and time windows on the event pattern EAN TAN sDIR with sDIR 3S abbreviated to sDIR Trigger Mode Accepted Event Type 1 E Tx sDIR E T sDIR 0 T sDIR 2 E T E T E 0 0 T 3 Ex TxsDIR E T sDIR 4 Ex T E T 5 E E T E 0 6 T E T 0 T 1 12 YP AE RAPID CLUSTER Issue 3 IJA Flight Operation User Manual Rev 0 Date 17 06 2000 The above trigger conditions lead obviously to a digital filter function with effects on the overall detection efficiency of the spectrometer The following is a qualitative assessment of the filter effect e The coincidence conditions in Mode 1 and 3 lead generally to a rather low rate of occurrence This is even amplified by the relatively low probability for creating a sDIR 35 puls
98. utation A E V or by statistical analysis in two dimensional V E space with the mass A as the sorting parameter Actually the velocity detector measures the flight time T the particle needs to travel a known distance in the detector geometry 1 4 DL mu RAPID CLUSTER Issue 3 JA Flight Operation User Manual Rev 0 Date 17 06 2000 Fig 4 shows cross sections of the SCENIC detector telescope drawn to scale A particular feature is the triangular structure with a 60 opening angle The energy measuring solid state detectors SSD are mounted in the apex at the rear of the system A group of two SSDs an energy detector ED and a back detector BD is combined in an anti coincidence condition for high energy electron detection The flight time T measuring system is the entry element of the telescope It is essentially composed of a thin foil see Table 1 2 and the front surface of detector ED The distance between the foil and detector ED along the line of symmetry is the nominal flight path s for the T measurement Particles passing through the telescope release secondary electrons SE from the entry foil The SE are accelerated and directed to a microchannelplate MCP for detection The MCP output signal constitutes the START signal for the T measurement Details of the isochronous SE transfer to the START MCP are shown in the upper cross section of Fig 4 Upon impact of the particle on detector ED secondar
99. y electrons are ejected from its surface as well These SE are transferred to the STOP MCP by a technique similar to the start electrons The STOP signal completes the T measurement The energy E of the incident particle reduced by the loss in the START foil is measured in detector ED For sufficient high energies the particle is able to penetrate detector ED and to strike the back detector BD This leads to the elimination of the event from analysis as described in Section 2 2 Fig 4 shows the START foil as an elongated rectangle The design of the START system is such that the SE transfer to the MCP is not only isochronous but also position preserv ing Four read out anodes behind the START MCP not shown in Fig 4 correspond to four contiguous segments on the entry foil and each of these forms a 12 by 15 viewing cone with the ED detector in the back of the system In a sense this geometry can be considered a degenerated case of a projection camera with only one pixel in the back plane In this special case the virtual image plane coincides with the entrance foil Incident particles are strongly collimated before they reach the T E telescope Two microchannel collimators COLL1 and COLL2 in Fig 4 define a highly anisotropic field of view FOV with 12 lateral and 60 polar opening A set of plates between the collimating elements with potentials 0 and Udef forms a linear electrostatic deflector DEFL The primary purpos
100. y to predict with some reliability the accurate release time due to the uncertainties in the knowledge of the bi phenyl temperature during the launch phase Measurements in the laboratory suggest a delay time of about 30 to 40 hours for the doors to be released after launch The electron detector IES is composed of three identical sensor heads as well however the detection technique differs entirely from the principle used in SCENIC Again the apertures are protected by bi phenyl operated closures but in this case the mechanism is rather simplified The tiny entry holes of the IES heads are closed by bi phenyl plugs which leave the holes open after evaporation in space The positions of the heads Sn are shown in Fig 1 as well 1 2 1 1 The Nuclei Detector SCENIC The center piece of the IIMS sensor system is the so called SCENIC detector head The acronym stands for spectroscopic camera for electrons neutral and ion composition In essence SCENIC is a miniature telescope composed of a time of flight TOF and energy E detection system The novel aspect is the imaging of flux distributions and the capability to identify energetic neutral atoms ENA in a certain energy band The particle identifying function of the SCENIC spectrometer is obtained from a two parameter measurement The particle velocity V and the energy E are measured as independent quantities the particle mass A is then uniquely determined either by comp

RAPID Flight Operation User Manual - Max-Planck

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