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Power SCOE Spec.

1. cccccsscssessseesseesecesscesecesecesecsseeceeceeeseeseeeseeeseeesseeeeesees 23 5344 Output current measurement eee ete nt ER EVENIRE UM Eee ee yo yt dne esee t einen due 23 5 3 5 Solar Array Simulator SAS Output impedance inner 24 Page 2 77 Power SCOE Spec European Space A e spatiale europ Date 24 06 2013 Issue1 Revo Agenc ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 3 6 Solar Array Simulator SAS Shunt regulator ss 24 5 3 7 Deleted 4 err teer UEFA iere ia eie OFEN REI EYE T cu sente vs ERE 24 5 3 8 Solar Array Simulator SAS Current sensing and monitoring esee 24 5 3 9 Solar Array Simulator SAS Sunlight eclipse transitions 24 5 3 9 1 Solar Array Simulator SAS Transitions TIME 25 5 3 9 2 Solar Array Simulator SAS Transitions management 25 5 3 10 Solar Array Simulator SAS Thermistors simulation 25 5 3 11 Solar Array Simulator SAS Over voltage protection ss 25 5 3 12 Solar Array Simulator SAS Over current protection ss 25 5 3 13 Solar Array Simulator SAS Safety LOOP inner 26 5 3 14 Solar Array Simulator SAS High Priority Commands eese netten 26 5 4 Power SCOE Launch Power Supply LPS High Level Functional Requirements 26 5 4 1 Launch Power Supply LPS Main Ta
2. Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 4 5 Launch Power Supply LPS Sensing capability VA EQ T The Launch Power Supply LPS shall provide the capability to sense and display the on board Battery voltage and temperature plus the Main Bus output voltages 5 4 6 Moved to section 5 3 14 5 4 7 Launch Power Supply LPS Over voltage protection VA EQ T The Launch Power Supply LPS shall provide an over voltage protection mechanism at the user interface with adjustable level for the voltage output lines Default value triggering the over voltage protection shall be adjustable in the range from 18 V to 22 V 5 4 8 Launch Power Supply LPS Over current protection VA EQ T The Launch Power Supply LPS shall provide an over current protection mechanism at the user interface with adjustable level for the current outputs lines Default value triggering the over current protection shall be 3 A 5 4 9 Launch Power Supply LPS Safety loop VA EQ T The Launch Power Supply LPS shall a Safety Loop to manage the situation in which a failure on one of the power supply is detected over voltage over current the safety loop interface shall switch off the power outlets of all power supplies in error condition The safety loop response time shall be 1 ms the safety loop threshold shall be adjustable between 28V and 33V and finally the on LPS only the safety loop could be disabled by the operator vi
3. 4 Power SCOE Test Points VA EQ T Test points shall be foreseen for each critical signal in order to allow calibration integration operation and maintenance as well as surveying of signals at the interfaces level 6 4 1 Power SCOE Test Points characteristics VA EQ T The test points shall be short circuit protected or secured by other means 6 4 2 Power SCOE Test Points connectors VA EQ T Page 46 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC All the Power SCOE test points shall be provided using the same connector type ex 4 mm banana jacks or BCN connectors in order to allow easy use of measurement probes and commercial laboratory equipment In any case the connectors shall be of standard types Page 47 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 4 3 Power SCOE Test Points accessibility VA EQ T Test points shall be accessible without dismounting and disconnecting any equipment or parts of Power SCOE 6 4 4 Power SCOE Test Points availability VA EQ T Test points shall be provided for every critical signal to allow 1 Easy isola
4. 6 7 3 Exchanged messages format eninestienenennennenetesnestenennennentiennennenenese 49 6 7 4 Exchanged messages contents eese esee eee eene enses stans tnss inse tas s tasa inse inse inse pass sa setas spas spas stas spass tasso 49 7 POWER SCOE OPERATIONAL REQUIREMENTS ee ee eese ee esee esee eoe a eese oso sese oso so noe 51 71 Power SCOE Testing capability sise 51 7 2 Power SCOE Main capabilities sise 51 7 2 1 Battery Conditioning Equipment BCE Main capabilities 51 7 3 Power SCOE POWT OM osian eere enr lat tent ERE Ya ERE HEEL NE qa E ENERO CL Ee RE RONDE LH ELS o eR eO Eee dogs 52 7 3 1 Power SCOE Status after Power OM ccccccssccsssccesecssscsscecsssecssaecsssecsseecesasecesseceseecesaeesseeessaeeceseeesaees 53 7 4 Power SCOE Operative modes e eiceecee cete eene een aoro atn en koe en n kon enn E 53 FAA Power SCOE Local Mode ni sanitaire 53 7 4 9 Power SCOE Remote Mode 5 n nane RR IU ERES 53 7 4 3 Power SCOE Manual Mod ren eee e eea Eee S eonia aE eSEE 53 7 4 4 Power SCOE Emergency shut down button sis 54 7 4 5 Power SCOE Operative Modes switching ss 54 7 4 6 Operative Modes Switching commands ss 54 7 4 7 Power SCOE Remote Control cccsccsssscsssscesssccsscccsssecsseecssseecsesecssecsseeesseeeesesesseseceseecssaeesseeessaeecseneseneees 54 7 4 8 Power SCOE Commands neret iced ves
5. 75 77 Power SCOE Spec Date 24 06 2013 Issue 1 Rev o EGSE CHASSIS GROUND il European Space Agency Agence spatiale europ enne ESA UNCLASSIFIED For Official Use 2esa Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC ANNEX 2 SPACECRAFT INTERFACES Spacecraft connectors interfacing the Power SCOE and pins function TBD Page 76 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC ANNEX 3 CCS INTERFACES The Power SCOE shall be able to interface with the CCS node via a 100 Mb s Ethernet Local Area Network using the standard TCP IP protocol The communication with the CCS shall be based on a Packet oriented protocol where the packets format is the same defined for the ones exchanged with the Spacecraft Page 77 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne
6. Not Applicable Page 74 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use ANNEX 1 GROUNDING Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC e The insulation between any output terminal and the AC power line shall be higher than 10 MO e Aground terminal shall be foreseen on the equipment for grounding connections e For equipment racks used in clean room areas a grounding bridge shall be provided to allow ground connection either to the main safety ground or facility ground The EGSE grounding concept shall be the following e All signal lines are floating ones with respect to S C I F e With respect galvanic insulation the electronic components of the EGSE side must be referenced to EGSE ground e With respect galvanic insulation the electronic components of the S C side within the EGSE must be referenced to the S C ground primary or secondary ground e The umbilical signals which are referenced to the S C primary ground respectively to the secondary ground shall be processed in EGSE by electronic unit referenced to the S C primary ground respectively to the S C secondary ground and shall be isolated from EGSE ground mm rs Q T eU Vi 4 i Equipment Nor GND A mi rat it sabe Equipment 2 UUT STRUCTUFE 7 i EGSEground Primary ground Star Point Secondary ground Page
7. Power Supply Power Control and Distribution ProtoFlight Model PayLoad Module Remote Terminal Unit Solar Array Simulator Special Check Out Equipment Spacecraft Satellite SerVice Module Telecommand Telemetry European Space Agency Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 3 GENERAL DESCRIPTIONS 3 31 Mission Description VA I O Euclid is an optical near infrared survey mission designed to understand the origin of the accelerating expansion of the Universe It will use cosmological probes to investigate the nature of dark energy dark matter and gravity by tracking their observational signatures on the geometry of the Universe and on the cosmic history of structure formation Euclid has been approved by ESA and delegated bodies for a planned launch in 2020 in the frame of the Cosmic Vision 2015 2025 plan The target orbit is a large amplitude libration orbit around the night side Lagrange point of the Sun Earth system L2 The launch service shall be provided by the Soyuz 2 1b Fregat from Kourou with direct insertion into the target orbit 3 2 Power SCOE general description VA I O Power SCOE will be used either during Euclid AVM FM Service Modules test activities and also at Spacecraft level verification including environmental testing up to the launch campaign when LPS making part of the overall COTE
8. Space Ag Date 24 06 2013 Issue1 Revo ace Spatial eu ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 5 9 Battery Conditioning Equipment BCE Over voltage protection VA EQ T The Battery Conditioning Equipment BCE shall provide an over voltage protection mechanism at the user interface with adjustable level for the voltage output lines Default value triggering the over voltage protection shall be 26 V protection intervention time shall be 50 seconds 5 5 10 Battery Conditioning Equipment BCE Over current protection VA EQ T The Battery Conditioning Equipment BCE shall provide an over current protection mechanism at the user interface for the current outputs lines Default value triggering the over current protection shall be 2 of the maximum current protection intervention time shall be 50 useconds 5 5 11 Battery Conditioning Equipment BCE Over temperature protection VA EQ T The Battery Conditioning Equipment BCE shall provide an over temperature protection mechanism based on the battery temperature monitored via the thermistors The outputs of the Battery Conditioning Equipment BCE shall be switched off at an adjustable upper temperature limit of around 35 C 5 5 12 Battery Conditioning Equipment BCE Safety Loop VA EQ T The Battery Conditioning Equipment BCE shall provide a Safety Loop to
9. dere AE ae dendi aeneae 36 6 1 2 Battery Simulator BS Interfaces ccc cescsscesseessceccesccesecssecesecsseseseceseceseceseseseseseceseceaeesaeseaeseaeseseseneees 36 6 1 3 Solar Array Simulator SAS Interfaces rss 36 6 1 4 Battery Conditioning Equipment BCE Interfaces ss 36 Page 3 77 Power SCOE Spec European Space A Agence spatiale europ Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 1 5 Launch Power Supply LPS Interfaces sise 37 Gm DJ deeem etes tique 37 6 2 Power SCOE Cable length eeeeseessssececceeesseeececceseseseeececeessssesecceceessseceeecenessseseseceesseseseeeeesensseaeeeees 38 6 2 1 Cable between Power SCOE and Spacecraft seen 38 6 2 2 Cables between SAS LPS SCOE and TM TC DFE cccsscsssssssceseceseceecsseceseseseeeseceseeeseseseeeseeeseseseeeneees 38 6 2 3 Launch Power Supply LPS cables sine 40 6 2 3 1 SAS LPS Cables For AIV Activities cccccsscssscssscssscssececcssessseceseceseceseseseceseeeseseseseaeeeseseaeseaeseeeseseseneees 40 6 2 3 2 LPS Cables On Launch Site n nana aenea na RI UH ERES 40 6 2 4 Cables naming orte sondes pase g ora io oe gore poc qose ooo eos pos Gare ooa o se pos dore E eg ko POE aree DE e ER e se GRE ed que seuss 41 6 3 Power SCOE Connectors and pins function serrer 41 6 51 Deleted 5 onion encanta
10. ee devi iai 41 6 3 2 Deleted etie RO ER RR RR GR Tse Ba EGG RS 41 6 3 9 Deleted ER EP I EE EU EEE a E SR ET 41 6 3 4 BS LPS SAS Connection Configuration 42 6 3 5 Deleted ease ae coner etie ade edi pb e iba et etes eir 44 6 3 6 LPS Connection Configuration s scssi EG 44 6 3 7 Battery Conditioning Equipment BCE Connection Configuration 45 6 3 8 BATTJ67 pins Bion TO CETERI m 46 6 4 Power SCOE Test Polnts aedes ree rase etc tertie PE GNE nine esee beu ete ear cosh ERENT 46 6 4 1 Power SCOE Test Points characteristics nine 46 6 4 2 Power SCOE Test Points connectors cscccsssccsssecessccssseceseccsssecsssecssaecsseecesaseceseecesuecesaecssaeeeeaseceseeesaees 46 6 4 3 Power SCOE Test Points accessibility ss 48 6 4 4 Power SCOE Test Points availability iii 48 6 4 5 Grounding CONCEPE cccssciscccsscisccdenctecciscebeccesscbeccesncbeccascessccesccnsecescansecescsnsecestensecescinsecescansecescsnsecestensbcnnsebnncees 48 6 5 Power and Signal ground separation eeeseescesccecceeeseeeccecceseeseeecceceeseeseeeaceaeeseesceeceeseeseeeseaeeaeeseeeeeeaees 48 6 6 External powering sn init 48 6 7 Power SCOE to CCS Interfaces him nan Annee 49 6 7 1 Communication Control for Power SCOE inner 49 6 7 2 Communication Link Start Wp sessc ssccssctssccsseessevsecesceudoe cascaocnaceuacecancvzocegceabecasevaocnaceuacesanevaoceaceuabecacevveaesteves 49
11. eee eene eene esee eee ee eene esso soe o eene 71 rii V rification responsibility ooo eerte x Re ins ONERE SEN nette ERE PSE SENS KURSE SER nier onde etes este 71 1i 2 Veritication purposed tee ttem pec ve cased ceauash Gest ete Capit pues cals Guo ete esse ed eaa aa nn nie denses en tee es eat es 71 11 3 Power SCOE Acceptance 5 eee totae iet etie tin vealed ca P EUER E EET 71 11 3 1 Power SCOE Acceptance Performance tests sise 72 11 4 Final Power SCOE Acceptance documentation approval and witnessing eese 73 11 5 Verification methods Lin tea Het rere eve tore nie tt pure ka PESEK PERS ex EORR ERE CES PER 74 ANNEX 1 GROUNDING e cese aeo rera se eren on rene heo Fa Uo ee svoo Pe EN oae Fe Ue vo ae eO e Ue Lea E reed ne Uo e sse E ese sea eee te 75 ANNEX 2 SPACECRAFT INTERFACES ecce eee eee ee ee eee eene rente ses h sees ee sese tese o soe o eese eee oe o 76 ANNEX 3 CCS INTERFACES cesse ee rna ea ee Pape De LES aha Eae ro ba Oe ae aree eae ea obe popa Penes en ses ee dede 8e se 77 Page 6 77 Power SCOE Spec European Space A ence spatiale europeenne Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 1 INTRODUCTION This documents contains all the requirements necessary for the design the development and the manufacturing of the Power SCOE that will be used during all
12. functions at TM TC DFE side are reported here below TM Primary NRZ L PIN Name Direction Level Description 1 IF GNDI Interface Ground 1 2 Not Connected 3 Not Connected 4 TMSCP_CLK_T From S C RS 422 Primary TM Clock true signal 5 TMSCP_DAT_T From S C RS 422 Primary TM Data true signal 6 Not Connected 7 LOCK Keying pin 8 TMSCP_CLK_C From S C RS 422 Primary TM Clock comp signal 9 TMSCP_DAT_C From S C RS 422 Primary TM Data comp signal Page 38 77 Power SCOE Spec uropean Space Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC TM Redundant NRZ L PIN Name Direction Level Description 1 IF GNDI Interface Ground 1 2 Not Connected 3 LOCK Keying pin 4 TMSCR_CLK_T From S C RS 422 Redundant TM Clock true signal 5 TMSCR_DAT_T From S C RS 422 Redundant TM Data true signal 6 Not Connected 7 Not Connected 8 TMSCR_CLK_C From S C RS 422 Redundant TM Clock comp signal 9 TMSCP_DAT_C From S C RS 422 Redundant TM Data comp signal Page 39 77 Power SCOE Spec Date 24 06 2013 Issue 1 Revo eus i ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contrac
13. including the final system tests 11 2 Verification purpose VA N A The POWER SCOE Contractors shall have to demonstrate with proper documentation and with a dedicated acceptance tests campaign that Bd The developed Power SCOE design conforms to the requirements amp The developed POWER SCOE item hardware and software comply with the design in terms of manufacturing and performances Bd The developed Power SCOE is free of workmanship errors and is fully functional Adequate test equipment and simulators shall be made available to support the equipment verification process This test equipment is not deliverable and may therefore be recruited from the supplier s laboratory inventory Of particular importance are the simulation of the communication interface with the CCS and the simulation of the interfaces with the on board systems The acceptance tests shall verify under nominal operational conditions only that the electrical and mechanical performances of the equipment meet the requirements of the specifications In particular electrical tests shall include application of expected voltages impedance s frequencies pulses and waveforms at the electrical interface of the equipment including all primary and redundant circuits All the Power SCOE electrical interfaces with the on board equipment shall be tested during acceptance test campaign before the first connection to the real Spacecraft in order to verify that there are no hazardo
14. manage the situation in which a failure on one of the power supply is detected over voltage over current the safety loop interface shall switch off the power outlets of all power supplies in error condition 5 5 13 Battery Conditioning Equipment BCE Under voltage Protection VA EQ T Page 34 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ ESA UNCLASSIFIED For Official Use esa Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC The Battery Conditioning Equipment BCE shall provide an under voltage protection mechanism at the user interface with adjustable level for the voltage output lines Default values triggering the under voltage protection shall be 15 V protection intervention time shall be 50 usec Page 35 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 POWER SCOE INTERFACES REQUIREMENTS 6 1 Power SCOE electrical and functional Interfaces 6 1 1 Deleted 6 1 2 Battery Simulator BS Interfaces VA EQ T The Battery Simulation Equipment BS shall interface the Satellite via the harness at battery level and shall provide at least the following interfaces two separate cables 1 Battery power simulation interface 2 Thermi
15. on board High Priority commands addressed to the PCDU to turn ON and OFF two on board Battery Discharge Regulators 5 4 Power SCOE Launch Power Supply LPS High Level Functional Requirements 5 4 4 Launch Power Supply LPS Main Task VA EQ T The main task of the Launch Power Supply LPS shall be to provide via Umbilical link to the Spacecraft during all integration and testing activities including launch campaign 1 Nominal and redundant Main Bus power lines 6 SAS sections 2 Two Battery support power lines via on board PCDU battery charger The use of a mechanical relay is required at the power feeding outputs in order to galvanically isolate the Power SCOE from the Satellite Page 26 77 Power SCOE Spec European Space Date 24 06 2013 Issue1 Revo Agence s ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 4 2 Launch Power Supply LPS Power Requirements VA EQ T The Launch Power Supply LPS shall be able to provide Nominal and Redundant Main Bus support current loops each providing 0 to 3 Amps to the Spacecraft PCDU via the umbilical connector Protection to ensure that the S C to SAS I F voltage does not exceed 30 8 Volts Current limit setting accuracy shall be better than 1 FSD Each current loop impedance at the PCDU shall be R lt 2 50 C o 5uF and L lt 75uH Each current loop shall be compatible with S3R b
16. operator shall be able to operate on an easily accessible Emergency power off switch latching located on the front panel 7 4 5 Power SCOE Operative Modes switching VA EQ T It shall be possible to externally intervene on the equipment in order to change the operative mode of the Power SCOE The operational mode transition shall be independent from the Local Remote configuration The transitions from Local to Remote control and viceversa shall not affect the current configuration and setting of the SCOE 7 4 6 Operative Modes Switching commands VA EQ T While the transition between Local and Remote Mode shall be possible using dedicated keyboard commands available both to local user and remotely from the CCS the transition to from Manual Mode shall be possible acting on a knob key located on the SCOE front panel 7 4 7 Power SCOE Remote Control VA EQ T The Power SCOE shall be able to be remotely controlled and monitored by the CCS to execute commands like Operational mode Local Remote transition Start stop the running Software Assignment of values to SCOE internal variables Commutation between main and redundant interfaces Acquisition transfer of data from to the CCS Deleted Other DX gd D The same commands and primary functions shall also be available to the Power SCOE user directly acting on local keyboard i e when the SCOE is not remotely controlled by the CCS Local mode Note for Battery C
17. over voltage protection shall be 29 volts protection intervention time shall be 50 useconds 5 3 12 Solar Array Simulator SAS Over current protection VA EQ T Page 25 77 Power SCOE Spec European Space Ag Date 24 06 2013 Issue1 Revo ace Spatial eu ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC The Solar Array Simulator SAS shall provide an over current protection mechanism at the SAS module before the impedance matching circuit with adjustable level from 0 to 3 5 A for the current outputs lines Default value triggering the over current protection shall be 3 5 Amps protection intervention time shall be 50 micro seconds 5 3 13 Solar Array Simulator SAS Safety Loop VA EQ T The Solar Array Simulator SAS shall provide a Safety Loop to manage the situation in which a failure on one of the power supply is detected over voltage over current the safety loop interface shall switch off the power outlets of all power supplies in error condition The safety loop response time shall be lt 1 ms the safety loop threshold shall be adjustable between 28V and 33V Moreover Battery Simulator BS Umbilical I F module and Solar Array Simulator SAS shall be linked one to the other 5 3 14 Solar Array Simulator SAS High Priority Commands VA EQ T The SAS shall provide to both local and remote operator the capability to send 4
18. set by the CCS if working under in Remote control 7 6 Power SCOE Self test VA EQ T The POWER SCOE shall provide a full self test capability in order to support failure investigation down to individual drawer or module level In case of Self Test failure ex one instrument is not available for whichever reason a warning message shall be sent to the user and depending on the type of detected failure it shall be possible to keep on using the Power SCOE in a reduced performance configuration Page 56 77 Power SCOE Spec European Spa Date 24 06 2013 Issue1 Revo Agence spatiale ei ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 6 1 Interface behaviour during Self test VA EQ T During the self test execution special attention shall be paid to the interfaces connecting the Power SCOE with the Spacecraft i e the self test shall prove that all these interfaces are in a well defined status and guarantee that no hazard is caused no signal shall be sent to the Spacecraft 7 6 2 Self test activation VA EQ T The Power SCOE shall provide the capability to initiate at any time the self test either from local keyboard or remotely by the CCS In any case the self test shall be automatically performed at power up of the Power SCOE Note for Battery Conditioning Equipment BCE only this requirement is not applicable for BCE for what conce
19. sveevsvenegevesaveavasencusnceateteoedeecuevebasedsuedeosueve aces eines en cite ee ut 55 7 5 Power SCOE Off line and On line mode definition 56 7 5 1 Off line mode Interfaces status inner 56 7 5 2 On line mode Interfaces status 56 7 5 3 On line mode Interfaces setting 56 Page 4 77 Power SCOE Spec uropean Space Agency Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 6 Power SCOE Self testion tep aara iaun ea a e Ea EE EE A Ea n AE E ARENE EEE EN aaa REN 56 7 6 1 Interface behaviour during Self test ss 57 7 6 9 Self test aCHyaltlon toe e ore ren erre ieiet es PER NOE Pe ENSE FE EN EP Respon P bes E oen rH detente tete 57 7 0 3 Self test logging ssc neii 57 7 7 Power SCOE Archiving capability for Battery Conditioning Equipment esee 57 7 7 1 Battery Conditioning Equipment BCE Archive files naming esee nnne 58 7 7 2 Battery Conditioning Equipment BCE Archive files management 58 7 7 3 Battery Conditioning Equipment BCE Archive files storage on local disk 58 7 7 4 Battery Conditioning Equipment BCE Local disk unavailability for archiving 58 7 8 Power SCOE Logbook capability 0 eee escsscsesceseeseeeccesceseeeceeceeseeseseceeaeeseeseseaeeaeeseeseeeeeesessessaseaeea
20. the Integration and Test activities performed on Euclid Satellites starting from the AVM and finally on the FM Spacecraft up to the launch This specification covers the functional and the performance requirements for the SCOE and specifies the interfaces with the S C and with the overall EGSE The Power SCOE will constitute part of the Euclid Electrical Ground Support Equipment and will be composed of the following main functional blocks Solar Array Simulation Battery Simulation Battery Charge discharge Main Bus Voltage Monitoring Launch Power Supply making part of the COTE PONE Each one of the mentioned functional blocks can also be considered as a specific SCOE but the ones listed in bullets 1 4 and 5 that will be part of the same equipment 1 1 Document structure The Power SCOE Specification document is organised as briefly depicted here below Lists of the documentation to be applied or kept into account during the design and implementation phases of the Power SCOE are reported in Section 2 followed by a brief summary description of the foreseen mission and of the Power SCOE configuration used during different Integration and Test phases Section 3 General descriptions of the possible major tasks of these EGSE items can be found in Section 4 Inside Section 5 the detailed functional and operational requirements are contained including the type of data information the Power SCOE shall be in charge to manage Interface
21. the capability to adjust the battery output voltage between o V and 30 V at the user interface 5 2 11 Battery Simulator BS I V characteristic adjusting VA EQ T The Battery Simulator BS shall provide the capability to adjust the static I V characteristics over the entire battery voltage range Page 19 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 2 12 Battery Simulator BS Maximum voltage VA EQ T The Battery Simulator BS shall control the battery output so that the maximum voltage shall never exceed 26 V at the user interface 5 2 13 Battery Simulator BS Regulation capability VA EQ T The Battery Simulator BS shall provide regulation capability using voltage sensing lines at the spacecraft interface to achieve better than 0 5 setting accuracy at the spacecraft interface 5 2 14 Battery Simulator BS Output Impedance VA EQ T The battery simulator impedance at the spacecraft interface shall be 50mQ 10 with an inductance of between 1 and 3 uH 5 2 15 Battery Simulator BS Output Voltage sensing VA EQ T The Battery Simulator shall have the capability to sense the output voltage at the user interface and shall regulate the SCOE output accordingly see para 6 1 2 5 2 16 Battery Simulator BS Battery temperature sensing VA EQ T The Ba
22. 0xxxxxx 13 NL GLC The Power SCOE shall generate and maintain local logbook files containing organised in chronological order and time stamped at least the following information 1 General test data ex Start end time and date of test 2 Configuration information HW and SW 3 Error diagnostic and warning messages 4 System events error messages simulation messages 5 Deleted 6 Command execution results 7 Power SCOE status changes 8 Allmessages exchanged with the CCS 9 Deleted 10 Other Note for Battery Conditioning Equipment BCE only bullet 5 of this requirement is not applicable for BCE for what concern the reception of remote commands from the CCS and bullet 8 is not applicable at all 7 8 1 Logging task activation VA EQ T The log function shall start automatically when the Power SCOE reaches any automatic operating mode i e when the relevant On line software is started and running 7 8 2 Logbook files organisation and naming convention VA EQ T The logbook files shall be identified by names containing the creation date and time and stored in proper sub directories also organised by date 7 8 3 Logbook files management P HP ASPI 1 SP 0045 3 3 1 2 GRQT 0090 VA EQ T Log files shall be crated and closed in such a way to avoid too big files In case big amount of data should be logged the files have to be closed when their size reach reaches 1MB On the contrary whenever only few data are to
23. 4 9 Power SCOE general description eee re rhet RR ERR RESP ES ERE rna eR EE RES ERES ee tiens es 11 4 GENERAL REQUIREMENTS e eeee eese eese ense suse hase ss etse etus etes sees essa senes sese so sesso soto soe u 15 44 Power SCOE main TI k iada rtr etr hehe a ecu te det a cutee abc rese Ee fe ER EHE 15 4 1 1 Power SCOE Controller main functions sise 15 4 1 2 Power SCOE Solar Array Simulator SAS main functions 15 4 1 3 Power SCOE Battery Simulator BS main functions 15 4 1 4 Power SCOE Launch Power Supply LPS main functions 16 4 1 5 Power SCOE Battery Conditioning Equipment BCE main functions 16 5 POWER SCOE HIGH LEVEL FUNCTIONAL REQUIREMENTS eee eese eene enne nnne 17 5 1 Power SCOE Umbilical Interface Module High Level Functional Requirements 17 5 2 Power SCOE Battery Simulator BS High Level Functional Requirements eese 17 5 2 1 Battery Simulator BS Main task ss 17 5 2 2 Battery Simulator BS Operational modes sense 17 5 2 3 Battery Simulator BS Battery charge discharge ss 18 5 2 4 Battery Simulator BS Battery discharge current ss 18 5 2 5 Battery Simulator BS Battery charge current ss 18 5 2 6 Battery Simulator BS Crossing between source and sink mode ees 18 5 2 7 Battery Simulator BS Initial battery Charge status ss 18 5 2 8 Battery Simulator BS Pe
24. Battery Conditioning Equipment BCE Charge cycle setting esee 31 5 5 4 Battery Conditioning Equipment BCE Battery discharging 32 5 5 4 1 Battery Conditioning Equipment BCE Discharge current 32 5 5 4 2 Battery Conditioning Equipment BCE Discharge cycle setting eere 32 5 5 5 Battery Conditioning Equipment BCE Battery capacity determination accuracy 32 5 5 6 Battery Conditioning Equipment BCE Output sensing eeeeesesseeeeeeeee teen enne 32 5 5 7 Battery Conditioning Equipment BCE Battery monitoring 33 5 5 8 Battery Conditioning Equipment BCE Automated operation 33 5 5 8 1 Charge discharge configuration set up ss 33 5 5 9 Battery Conditioning Equipment BCE Over voltage protection essere 34 5 5 10 Battery Conditioning Equipment BCE Over current protection 34 5 5 11 Battery Conditioning Equipment BCE Over temperature protection 34 5 5 12 Battery Conditioning Equipment BCE Safety Loop ss 34 5 5 13 Battery Conditioning Equipment BCE Under voltage Protection 34 6 POWER SCOE INTERFACES REQUIREMENTS eee eese eene e eese ee nne n notes tese sos a onse nnn 36 6 1 Power SCOE electrical and functional Interfaces 36 6 13 Deleted 55 iere ree etse pe Dan Gack
25. C via Umbilical connector Provide charge capability for the battery Manage the interface between the SCOE and the S C Umbilical connectors Provide signals Test points Monitor and display signals coming from the S C Sense and display battery voltages of the on board battery Sense and display Main Bus voltage Provide Over voltage Over current protections Simulate and monitor separation switches Manage the flashing light indicating S C is ON 4 1 5 Power SCOE Battery Conditioning Equipment BCE main functions VA EQ T The Battery Conditioning Equipment shall be used in standalone configuration i e it will be not connected to the CCS on the SCOE LAN as the other EGSE items it shall be able at least to Provide controller capability to manage the standalone configuration Charge the current source for the whole battery Taper charge source Discharge current sink for the whole battery Provide over voltage over current protections Provide under voltage protection Provide over temperature protection Allow the user to define different computer controlled charge discharge current profiles Monitor and archive whole battery voltage current and temperature Simulate sections output capacity Page 16 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 POWER SCOE HIGH LEVEL FUNCTIONAL REQUIRE
26. ESA UNCLASSIFIED For Official Use e 2esa CC YE estec European Space Research and Technology Centre Keplerlaan 1 2201 AZ Noordwijk The Netherlands T 31 0 71 565 6565 F 31 0 71 565 6040 www esa int DOCUMENT Power SCOE Requirements Specification Prepared by Reference EUCL EST RS 2 001 Issue 1 Revision o Date of Issue 24 06 2013 Status Approved Applicable Document Type SD Distribution European Space Agency Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC Table of contents 1 INTRODUCTION 7 i1 Document Structure onem P SRI ERRORES PRENDE SEE IRARIRENENESESESERERARE INNER REN RESRE USER ER RU es eee 7 2 DOCUMENTS AND STANDARDS eee eese eese eene ennt ente hates setas esses stesse s esses enne sns u 8 241 APPLICABLE DOCUMENTS 5 tiere eee rere svecehcuonssebsnasecendestevssadcacedceseeustdagvecessnavedebcetesGensasnptonceees 8 2 2 REFERENCE DOGCUMBENTIS i iet ree cos RH EEEE WEE ERA ste E MEE YE ERE rae Ere bar a HEE ER EE PeE es 9 2 Applicable Standards tisser ae EE EEK ARERR 9 2 4 ACLODVITIS 5 E E T A E euupecveussivespuunsessaoeyeeyss 10 3 GENERAL DESCRIPTIONS ssesessoeesesoseceeoesoseoeeooeeesoosesesoseoeeoesoseseeooseoeooseoseoseoseeesoseeceeoseo 11 ui Mission Descriptio seien eret non den anne dire et dent een EAR EY Eu Fuer eden 11
27. GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 3 4 BS LPS SAS Connection Configuration VA EQ T The harness of the BS LSP SAS to perform the AIT activities shall be realised as follows Connectors type and pins function are provide in Annex 2 Page 42 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 30 mt cables length 4 Skin connectors SK01B J09 gt Batt HRNS connector J03 gt Batt HRNS connector J04 Skin connectors SK01B Same connectors type CBSAI1JOI CBSA11J02 SAS 1 to 30 CBSAI12J01 fo CBSA13J01 Temperature simulation CBSA13J02 CBSA14JO1 CBSA14J02 CBSA20J01 CBSA20J02 TM TC DFE Connectors Imt LPS Umbilical 1 Umbilical 2 H S C to PWR SCOE connections for Euclid AIT configuration Page 43 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 3 5 Deleted 6 3 6 LPS Connection Configuration The LPS harness for launch AIT activities shall be realised as following Connectors type and pin function are provide in Annex 2 15 mt cables length except for TLM and TLC lines Umbilical 1 Umbili
28. LICABLE DOCUMENTS The here below listed documents in the latest issue form part of this specification to the extent specified herein In the event of conflict between the contents of this document and the contents of applicable documents listed below the conflict shall be brought to the attention of the Prime Contractor for clarification AD 1 Deleted AD 2 Deleted AD 3 Deleted AD 4 Deleted AD 5 Deleted AD 6 Deleted AD 7 Deleted AD 8 Deleted AD 9 Deleted AD 10 Deleted AD 11 Soyuz CSG User s Manual Dated March 2012 AD 12 Deleted AD 13 Deleted AD 14 Deleted AD 15 Deleted AD 16 Deleted Page 8 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale et ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 2 2 REFERENCE DOCUMENTS The here below listed documents have to be considered in their latest issue RD 1 Deleted RD 2 Deleted RD 3 Space Engineering Software ECSS E 40B RD 4 Deleted 2 3 Applicable Standards ECSS E ST 10 02C Verification Issue 2 06 March 2009 ECSS E ST 10 03C Testing dated 1 June 2012 ECSS E ST 20 C Electrical and electronic Issue 2 31 July 2008 ECSS E ST 20 07C Electromagnetic compatibility Issue 1 Rev 1 7 February 2012 ECSS Q ST 30 02C Failure modes effects and criticality analysis FMEA FMECA 6 March 2009 ECSS E ST 50 03C Space da
29. MENTS VA EQ E Regardless the operating mode the Power SCOE shall be able to provide the required power to the Satellite during test activities from AVM integration up to the final tests performed during Launch campaign It shall be able to simulate the real behaviour of the batteries and Solar Array panels The Battery Conditioning Equipment shall be used in standalone configuration whenever is required to perform a battery conditioning cycle 5 1 Power SCOE Umbilical Interface Module High Level Functional Requirements Moved to Section 5 4 10 and Section 5 4 11 5 2 Power SCOE Battery Simulator BS High Level Functional Requirements 5 2 1 Battery Simulator BS Main task VA EQ I O The Battery Simulator BS main task shall be the simulation of the Li Ion battery behaviour installed on the Spacecraft 5 2 2 Battery Simulator BS Operational modes VA EQ T The Battery Simulator BS shall be able to work in several different operational mode e Nominal mode Sun presence e Charge mode e Discharge mode e Taper charge mode Page 17 77 Power SCOE Spec irop 1 Sp Date 24 06 2013 Issue 1 Revo ngence spaumn ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 2 3 Battery Simulator BS Battery charge discharge VA EQ T The Battery Simulator BS shall be able to simulate the battery charge and discharge cycles ove
30. SE functional architecture Page 13 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Page 14 77 Power SCOE Spec Appendix 2 to ESA AO 1 7612 13 NL GLC ESA Contract No 4000xxxxxx 13 NL GLC TM TC Video signals Amplifier SCOE Battery Umbilical Controller SCOE DFE LAN IS LAN 4 Station Data Archive Y Experiment EGSE Figure 3 2 2 Euclid EGSE Launch configuration functional architecture Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 4 GENERAL REQUIREMENTS 4 1 Power SCOE main tasks VA EQ T The Power SCOE shall be built around the following main functional blocks SCOE Controller Solar Array Simulator Battery Simulator Launch Power Supply Battery Conditioning Equipment PPE SE 4 1 1 Power SCOE Controller main functions VA EQ T The Power SCOE Controller shall be able at least to e Perform command and control of the SCOE functions Communicate with the CCS for data transfer and mode control except for BCE Perform a self test at power on and on CCS request Provide archiving capability BCE only Provide logging capability 4 1 2 Power SCOE Solar Array Simulator SAS main functions VA EQ T The Solar Array Simulator shall be able
31. Safety Loop VA EQ T The Battery Simulator BS shall provide a Safety Loop to manage the situation in which a failure on one of the power supply is detected over voltage over current the safety loop interface shall switch off the power outlets of all power supplies in error condition VA EQ T The safety loop response time shall be 1 ms the safety loop threshold shall be adjustable between 28V and 33V VA EQ T Moreover Battery Simulator BS Umbilical I F module and Solar Array Simulator SAS shall be linked one to the other 5 2 20 Battery Simulator BS Battery Protection switch VA EQ T The battery Isolation relay will be introduced in between the Battery and the PCDU at the spacecraft external interface with the following requirements the following requirements shall be applicable at each contact of the Battery protection switch e The maximum peak current shall be 120 Amps for approximately 1s while connected e DCvoltage drop at Spacecraft connector interface less than 0 7 Volts at 30 Amps e Switch configuration shall be single failure tolerant to both ON and OFF switching actions double back to back independent changeover configuration e Remote monitoring of the relay assembly input and output power terminal shall be provided so that voltage equalization within 1 volt may be achieved e Battery side impedance lt 60mQ and 11H e PCDU side impedance 4000uF 20mQ and 50uH e Battery voltage range 15V mini
32. Simulation ON OFF su id e 62 7 10 4 On line mode Test execution c cccssccesssccsssccsssccesseesssscesseecsssecsssecesaecsseecesasecsasecsauseesaeessaeeesaeessauesenaees 63 7 10 5 On Line software Further capabilities ss 63 7 10 6 On Line software Acquisition and Monitoring 63 FAO mM Perso Sri d 63 7 10 6 2 Monitor WINdOW c ess 64 7 10 7 On Line software Termination cccccssccssssccsssecssccsssscsseecesseecsssecssescssseessesessasecseuecsseecesasesseeessasecsaneseneees 64 7 3 Off Im e ACU Vite eintreten ied ama ana di ae 64 7 11 1 Battery Conditioning Equipment BCE Stored data retrieval 64 7 11 2 Test results post DroCessIng sisone erinrar nee E eere YE RR e SER PEE nt ES E Ne axe n EXE POR e RR Eea e EH ee eR S Epe SERES 64 7412 Fil exChAnpe sisi int E 65 8 POWER SCOE HARDWARE AND SOFTWARE CONFIGURATION ecce ecce esee enne 66 84 PowerSCOE Architecture sinistres ERR eg Pe dee PEE PETS ERA EUER USE e leider 66 8 2 Power SCOE software organisation 66 8 3 Power SCOE MOUSE RE c Ge tte teet diets se tiU 66 8 3 1 Solar Array Simulator amp Launch Power Supply SAS LPS housing 66 8 4 Power SCOE Controller characteristics inner 67 9 POWER SCOE PERFORMANCES eee eeee esee e eene eene n estne shes hostes eet s esee sese ses
33. a a dedicated command 5 4 10 Launch Power Supply LPS Monitor and Display Capabilities VA EQ T Page 28 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC The Launch Power Supply LPS shall be able to acquire with an accuracy better than 1 at least the here below listed signals coming from the Spacecraft to monitor their value and to display them to the operator e Battery voltage e Battery voltage sensors lines 1 for Voltage control and one for Battery protection 5 4 11 Launch Power Supply LPS Separation Switches Simulation and Monitoring VA EQ T The Launch Power Supply LPS shall provide the capability to simulate separation switches behaviour Relevant switch status shall also be monitored and displayed 5 4 12 Flashing Light VA EQ T The LPS shall be able to detect that the Satellite is powered ON and shall command the flashing light this information will be taken from the Umbilical lines 5 4 13 SAS LPS Charge array disable link simulation and monitoring VA EQ T The SAS LPS shall provide a capability to simulate nominal and redundant switches to short circuit Solar Array sections during battery SAFE ARM connectors mating activities as shown in Figure 5 4 13 1 Relevant switch status shall also be monitored and dis
34. ak Output power e eeeeseeseeseeseeseeeeee enne nnne nnenne nnne nne tne tn enne enne 19 5 2 9 Battery Simulator BS Battery thermistors simulation 19 5 2 10 Battery Simulator BS Output voltage adjusting eeeeeeeeeseseeseeeeeee teen enne nnne 19 5 2 11 Battery Simulator BS I V characteristic adjusting enne 19 5 2 12 Battery Simulator BS Maximum voltage sise 20 5 2 13 Battery Simulator BS Regulation capability ss 20 5 2 14 Battery Simulator BS Output Impedance ss 20 5 2 15 Battery Simulator BS Output Voltage sensing ss 20 5 2 16 Battery Simulator BS Battery temperature sensing 20 5 2 17 Battery Simulator BS Over voltage protection sise 20 5 2 18 Battery Simulator BS Over current protection ss 21 5 2 19 Battery Simulator BS Safety LOOP ii enne enne nnenne tne trennen enne nn ennen 21 5 2 20 Battery Simulator BS Battery Protection switch ss 21 5 3 Power SCOE Solar Array Simulator SAS High Level Functional Requirements 23 5 3 1 Solar Array Simulator SAS Main task 23 5 3 2 Solar Array Simulator SAS I V characteristic adjusting 23 5 3 3 Solar Array Simulator SAS Output power
35. at least to Simulate the 30 solar array sections by individual independent current sources Have individually adjustable source current and open loop voltage per section Simulate section output capacity Have over voltage and over current protection to avoid any damage to the Spacecraft Sense and display of the section currents and voltages Simulation of Sunlit to Eclipse and Eclipse to Sunlit transitions Simulation of the Solar Array temperature sensors 4 1 3 Power SCOE Battery Simulator BS main functions VA EQ T The Battery Simulator BS shall be able at least to Simulate the flight Li Ion battery in nominal mode sun presence Simulate the flight Li Ion battery in discharge mode eclipse Simulate the flight Li Ion battery in charge mode sun presence after eclipse Simulate the flight LI Ion battery in Taper charge Simulate the source impedance Simulate the Li Ion battery temperature Provide Over voltage over current protections Provide sense and display capability for battery currents and voltages Page 15 77 Power SCOE Spec uropean Space Agency Date 24 06 2013 Issue 1 Rev o Ag SPRRAISLERNSPS ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC e Provide Battery PCDU protection switch 4 1 4 Power SCOE Launch Power Supply LPS main functions VA EQ T The Launch Power Supply shall be able at least to Provide power to the S
36. be logged files can be closed on daily basis 7 8 4 Logbook files storage on local disk VA EQ E Page 59 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC The Power SCOE shall be equipped with sufficient disk space to allow the storage of logbook files for at least one month of test activities 7 8 5 Local disk unavailability for logging VA EQ T In case no more disk space is available for logbook files storage the operator shall be notified in advance with dedicated warning and error messages in order to avoid loss of data 7 8 6 Logbook files directories VA EQ T Logbook files shall be stored in proper distinct and dedicated directories Logbook files format shall be chosen in such a way to allow the users to easily read from them the required data the normal Operating System capabilities can be used for this purpose Page 60 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 9 Power SCOE Errors and Failures management 7 9 1 Error Detection Mechanism VA EQ E The Power SCOE system shall be able to provide a strong and complete error detection mechanism aim
37. ble also to Execute charge discharge cycles as programmed by the operator Archive Test result during charge discharge cycles Retrieve and post process data archived Other De Nor Page 51 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europeenne ESA UNCLASSIFIED For Official Use 2esa Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 3 Power SCOE Power on VA EQ T After the Power on the Power SCOE shall be in a well known and predefined operating mode such that no hazard is caused to the Spacecraft Page 52 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 3 1 Power SCOE Status after Power on VA EQ T After the Power SCOE power On the On line software shall be correctly running but its status shall be Off line the self test shall be completed and the SCOE shall be in Remote operating mode Note for Battery Conditioning Equipment BCE only after the self test completion the BCE shall be Local mode 7 4 Power SCOE Operative modes VA EQ T The Power SCOE shall allow the run time activity to operate in three different operative modes i e Local Mode Remote Mode and Manual Mode Note for Battery Conditioning Equipment BCE only Rem
38. cal 2 S C to PWR SCOE connections for launch configuration Connectors provided by ARIANESPACE Page 44 77 Power SCOE Spec Date 24 06 2013 Issue 1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 3 7 Battery Conditioning Equipment BCE Connection Configuration VA EQ T The harness of the BCE to perform the all the AIT activities shall be realised as following Connectors type and pins function are provide in Annex 2 For what concerns BATTJo7 connector pins function refer to next paragraph 6 3 8 5 mt cables length 1 BATTERY BATTIOI BATTJO2 BATTJ03 BATTJO4 BATTJO7 Voltage monitoring BCE to BATTERY connections Page 45 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Y s NN NN SN Cesa Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 3 8 BATTJO7 pins function Pins function for BATTJo7 Telemetry for Battery positive and negative voltage and mid string voltage is shown here below R a Equipment Interconnection WT Mai Siring Sem Tw isi a am ie EE TE ETS 2 EN D CN ES S IX o Ne R mm SS S N ma NN NN Lis Dumas Teen T 02 T M I I I E L3 I I I I I I X PX Dui wl TER ICTECT IRI ICI SICERICCCIC CIC ICI C7 IC Pr ey SE Ga 1 Dependent on monitoring system 6
39. ce to real sections characteristics as defined here after 5 3 2 Solar Array Simulator SAS I V characteristic adjusting VA EQ T The Solar Array Simulator SAS shall provide the capability to adjust the static I V curve characteristics Moreover the open circuit voltage shall be adjustable in the range from 0 0 to 60 V while the short circuit current shall be adjustable in the range from 0 0 to 3 0 A measured at Spacecraft connector level 5 3 3 Solar Array Simulator SAS Output power VA EQ T The Solar Array Simulator SAS shall provide the output power as defined in predefined default I V characteristics applicable to all 30 sections These characteristics shall be programmable by the user In particular at Spacecraft interface connector the following values shall be guaranteed e Current shall be in the range from 0 to 3 0 A for each section The use of a mechanical relay is required at the power feeding outputs in order to galvanically isolate the Power SCOE from the Satellite At I F connector with S C the voltage will be in the range 29 to 33 V for information only 5 3 4 Output current measurement VA EQ T Page 23 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue 1 Revo Agence Spatiale europ ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC The Solar Array Simulator SAS shall be able to provide a current measur
40. e esses e esses nose ee 68 9 1 Continuous OperaLtlons tees NE YE ERES Fe pear RN nee rege eee Ebert esee PERENA E 68 9 2 Performances at user interface cscccssccessscesssccsssecessccsssecesaeecsssecssascesseessescesaeecsaseceseecssaecsseeeesasecensecenaees 68 9 3 Launch Power Supply LPS Launch site configuration 68 EBD CN T P 68 0 5 JTafe We NE E CR EE RU RE RE EE ha ld a SEL e SNR 68 9 6 Operational condition eseesesscessccesecesecesecesccesecsseceseceseceseceseseaeceseceseceseceseeeseseaeseseseaeceaeseaeseseseaeseseseneees 69 9 7 Periodic MAINTENANCE 2 552 s00c6senesssdecseoesssansseocdcavveddsnneseotecactessseacsensdenseeddcuavoesdacaceedsseevoansdcaveedstenvoneddcactesdtess 69 9 8 EMC Compatability oss cscs coi at nets eee 69 Page 5 77 Power SCOE Spec uropean Space Agency Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 9 9 European Safety Standards sccscccscssecssscssssssessssssssssesssesssesssasssesssesssasssasssasssnessesssasssesssesssesssesssessoesses 69 10 POWER SCOE SPECIAL REQUIREMENTS csccscecsccsceccccccccccccsccccsceccccscscccscsccsceseseees 70 IDEM E E 70 10 2 Product Assurance Requirements esse 70 11 POWER SCOE VERIFICATION REQUIREMENTS ee ee
41. e files BCE only shall be stored in dedicated disks or partitions distinct from the one ones where System and Base Software will be installed 8 3 Power SCOE housing P HP ASPI 1 SP 0045 3 5 2 3 GRQT 0900 VA EQ T All to the maximum possible extent the boxes equipment making part of the Power SCOE shall be housed inside standard 19 racks 8 3 1 Solar Array Simulator amp Launch Power Supply SAS LPS housing VA EQ E The Solar Array Simulator and the Launch Power Supply functionality will be provided by the same SCOE housed inside 3 racks More in details one SAS LPS SCOE will be housed in standard 19 normal racks while for the other 2 SCOE s 2 anti seismic racks for parts common to LPS plus one normal rack for the other SAS equipment s shall be used In any case this means that all the boxes equipment making part of the Launch Power Supply LPS shall be housed inside suitable anti seismic 19 racks provided by the facility able to survive to the ambient environment unmanned Bunker subject to shock vibrations and acoustic noise during Launch phase Refer to AD 11 Page 66 77 Power SCOE Spec urope Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 8 4 Power SCOE Controller characteristics VA EQ T The Power SCOE will be equipped with a Controller for MMI and Test Preparation Execution equipped a
42. ed to monitor the behaviour of its internal software and composing hardware and to promptly notify to the user the relevant error messages The main categories of system errors refer to Hardware malfunctioning Operating system Commercial software Subcontractor provided software Interface errors towards CCS Communication problems with CCS Resources unavailability Other SO SON Er Es pur m The diagnostics mechanism shall be exhaustive i e no error condition shall remain undetected and or not notified by the system to the user Note for Battery Conditioning Equipment BCE only bullet 5 and bullet 6 of this requirement are not applicable for BCE 7 9 2 Failures detection VA EQ T The Power SCOE shall not propagate failures to the on board units Failures in the SCOE must not damage or even stress on board equipments 7 9 3 Self diagnostic capability VA EQ T The Power SCOE shall provide a self diagnostic Software which allows the easily identification of SCOE H W failures Page 61 77 Power SCOE Spec European Space Agency Agence spatiale europ enne Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 9 4 Errors reporting and management VA EQ T In case of any failure the Power SCOE shall be capable to report the error and to take adequate actions to ensure that no damages are provoked propagated to
43. eeseeeeeaees 58 7 8 1 Logging task activation eesesseseseeeseeseeeeee enne teet ne nne nnetne tnnt nne tret ne tse He enne tse rettet tns ieie eeren etse aaier 59 7 8 2 Logbook files organisation and naming convention ss 59 7 8 3 Logbook files manageMment csccsscssecssecssscssecssecssessecssessscesseesenesseessaessassenssseessnesenessesssaessaesseesseesoesses 59 7 8 4 Logbook files storage on local disk 59 7 8 5 Local disk unavailability for logging ses 60 7 8 6 Logbook files dir ctories esee eene aote P e Ue e EE RL ERE Ey ve ene PIER 60 7 9 Power SCOE Errors and Failures management serrer 61 7 9 1 Error Detection Mechanism ccscccsssccssscssssscsssscessecssnecssseessseessesecseuecssecssasesseeessauecssaesesaeessasessenecsnaees 61 7 0 9 Failures Gere ct OM s ee cosee nn sein vene Pe eere seen PE eae vae xe ANERE EREET DL NR TR oian 61 7 0 3 Self diagnostie capability iir tee te eet nte de E aa OKEE Ee PEL Pg RUE Na E Aba Posee eR een SEES 61 7 9 4 Errors reporting and management ceeescescescecceseeececcecceseeseeecceaeeseeseeecceaeesessceaeeseesesaseaeeaeeseeeeeeaees 62 730 On line Activities ert ER a ea ET ERE NE FR eves e eee ee E e es ere pesed oe cepere pee einer pee ee SUPER ES 62 7 10 1 Test Session start up Auxiliary information input 62 7 10 2 Test Session Start Up time sioe ite iere dert feed Pe se ide eo Pe eee Rente ebbe de Uere Ree ERE Ee eroe Ee TREE TERES 62 710 3
44. ement accuracy better than 1 at user interface level 5 3 5 Solar Array Simulator SAS Output impedance VA EQ T The SAS shall simulate the output impedance of each Solar Array sections at user interface i e at the end of the SCOE cables as follows e The effective inductance shall individually adjustable between 4uH and 8uH including cable The SCOE shall be delivered with all inductances set at 5H e The effective capacitance shall individually adjustable between 2uF and 10uF including cable The SCOE shall be delivered with all capacitances set at 5uF The length of the SAS SCOE cables 30 meters shall to be taken into account during SCOE design in order to fulfil above mentioned impedance requirements 5 3 6 Solar Array Simulator SAS Shunt regulator VA EQ T The Solar Array Simulator SAS shall be able to cope with dynamic shunt current regulators on any segments or a combination of them 5 3 7 Deleted Deleted 5 3 8 Solar Array Simulator SAS Current sensing and monitoring VA EQ T The Solar Array Simulator SAS shall provide the capability sense each output current line with a measurement accuracy less than 196 5 3 9 Solar Array Simulator SAS Sunlight eclipse transitions VA EQ T The Solar Array Simulator SAS shall provide the capability to simulate at the same time for all sections Page 24 77 Power SCOE Spec European pace Agency Date 24 06 2013 Issue 1 Revo Agence spatiale
45. ents concerning output voltage current or impedance at the user interface level ie at the point where the SCOE cable connectors are attached to the flight hardware respectively EGSE 9 3 Launch Power Supply LPS Launch site configuration VA EQ T The Launch Power Supply LPS when used during the pre launch Test activities shall be able to provide the required signal with correct electrical characteristic at the Satellite side Moreover the Controller located in different area from the Launch Tower shall be able to command and control the LPS Rack located in the Ariane 5 Launch Table 9 4 Disks Space VA EQ E The Power SCOE shall be equipped with enough space in order to guarantee that Simulation Configuration files Logbook and Archive files Archive files for BCE Only can be stored and maintained at the same time in well identified and distinct disks partitions directories 9 5 Lifetime VA EQ A The Power SCOE will be designed in such way to guarantee it shall be fully operative for 1 years after the Acceptance Review of the Spacecraft Page 68 77 Power SCOE Spec European Spa Date 24 06 2013 Issue1 Revo Agence spatiale et Agency eenne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 9 6 Operational condition VA EQ A Deleted 9 7 Periodic maintenance VA EQ E The Power SCOE shall be designed in such away t
46. europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 1 The transition from sunlight to eclipse 2 The transition from eclipse to sunlight 5 3 9 1 Solar Array Simulator SAS Transitions time VA EQ T The Solar Array Simulator SAS shall allow the user to adjust the transition time specifying it with 1second steps between 1 and 256 seconds 5 3 9 2 Solar Array Simulator SAS Transitions management VA EQ T The Solar Array Simulator SAS shall allow the user to hold or stop a transition in whenever needed the reached current level shall be maintained until a new request from the user 5 3 10 Solar Array Simulator SAS Thermistors simulation VA EQ T The Solar Array Simulator SAS shall be able to simulate Thermistors for the Solar Array sections In particular e Number 6 of ROSEMOUNT 118F 2KO 100 150 C The Temperature sensors will be simulated by 3 fixed values that the user can manually select from SCOE 5 3 11 Solar Array Simulator SAS Over voltage protection VA EQ T The Solar Array Simulator SAS amp LPS shall receive the Prime and redundant spacecraft bus voltage sensors provided through the Umbilical interface and provide a main bus over voltage protection mechanism at the user interface with adjustable level between 28 V to 31 V for the voltage output lines Default value triggering the
47. ge monitor signals 2 positive and 2 negative each connected to the main bus via a 100k 0 0526 resistor The spacecraft provides two battery voltage monitor signals 2 positive and 2 negative each connected to the battery via a 100k 0 05 resistor Refer to Annex 2 6 1 6 Deleted Page 37 77 Power SCOE Spec European S pace Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 2 Power SCOE Cable length 6 2 1 Cable between Power SCOE and Spacecraft VA EQ T The cables connecting the Power SCOE panels to the on board units shall be 30 meters long except the BCE cables that shall be 5 meters long Cables shall be manufactured as straight lines avoiding as much as possible octopus configurations In the schematics reported in next paragraphs showing all SCOE cables connections octopus cables are to be intended only due to drawing limitations and not as a mandatory requirement 6 2 2 Cables between SAS LPS SCOE and TM TC DFE VA EQ T The cables connecting the SAS LPS SCOE panels to the TM TC DFE in order to provide the Telemetry and Telecommands direct link Bypass shall be 30 meters long They will be built using DEMAOP connectors type at TM TC DFE interface while at Spacecraft side connectors Umbilical 1 amp 2 type is defined in Annex 2 The relevant pins
48. hat periodic maintenance of the hardware component shall be reduced to minimum possible frequency 9 8 EMC compatibility VA EQ E The Power SCOE shall be designed to support system level EMC tests This implies that the SCOE shall be able to withstand system susceptibility tests without malfunction 9 9 European Safety Standards VA EQ E The Power SCOE shall be designed taking into account the applicable European safety standards in addition to any specific Spacecraft related safety requirements in particular the Power SCOE shall conform to the C regulations plus other rules for example relevant to the Launch site Page 69 77 Power SCOE Spec European Spa Date 24 06 2013 Issue1 Revo jence sp ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 10 POWER SCOE SPECIAL REQUIREMENTS 10 1 Deleted 10 2 Product Assurance Requirements Not applicable in this context Page 70 77 Power SCOE Spec uror Date 24 06 2013 Issue1 Revo Agence spatiale ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 11 POWER SCOE VERIFICATION REQUIREMENTS 11 1 Verification responsibility VA N A The Power SCOE Contractors shall be responsible for the inspection verification integration and system testing of each delivered equipment of firmware and software packages up to and
49. mum to 26V maximum Page 21 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC Switch mounting distance from body of spacecraft at lease 3m Possibility to extend link to 30m via an extension lead during spacecraft environmental testing Provide status indication Provide rough current measurement indication GO NOGO The Switch will be connected to the S C to the connectors SKo1BJo9 and SKo1J10 Figure 5 2 20 1 provides an overview of the expected connections the switch will be connected to the connector SKo1BJo9 or SKo1BJ10 or to both connectors Pins function and connector type is provided in Annex 2 Lines l ton SKOIBJ10 Figure 5 2 20 1 Battery Isolation Switch connections Page 22 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 3 Power SCOE Solar Array Simulator SAS High Level Functional Requirements 5 3 1 Solar Array Simulator SAS Main task VA EQ T The Solar Array Simulator SAS main task shall be the electrically representative simulation by individual current sources of the each one of the 30 sections of the Solar Array panels Solar Array Sections shall be simulated in accordan
50. n the HOLD mode The Battery Simulator shall filter out current ripple emitted from the spacecraft in the frequency range 10Hz to 200kHz at an amplitude of 3 Amps peak to peak 5 2 7 Battery Simulator BS Initial battery Charge status Page 18 77 Power SCOE Spec uropean Space Agency Date 24 06 2013 Issue1 Revo genes specus curopesnns ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC VA EQ T The Battery Simulator BS shall allow the operator to select a Voltage value that when reached is used by the SCOE itself as a trigger to start the battery charge process 5 2 8 Battery Simulator BS Peak Output power VA EQ T The Battery Simulator BS shall provide for the simulated battery an output power of 465 Watts for 30 minutes in the voltage range from 14V to 27 V Moreover the use of a mechanical relay is required at the power feeding outputs in order to galvanically isolate the Power SCOE from the Satellite 5 2 9 Battery Simulator BS Battery thermistors simulation VA EQ T The Battery Simulator BS shall simulate 4 thermistors of Fenwall 526 31BS12 153 15 KO at 25 C type for the Li Ion battery VA EQ T Temperature sensors will be simulated by 3 fixed values that the user can manually select from SCOE 5 2 10 Battery Simulator BS Output voltage adjusting VA EQ T The Battery Simulator BS shall provide
51. ned at a constant level by regulating Voltage 5 5 3 1 Battery Conditioning Equipment BCE Charge current VA EQ T The Battery Conditioning Equipment BCE shall provide an adjustable charge current source the value of the charge current shall not exceed 9 0 A for nominal charge mode while a constant voltage shall be maintained during Taper charge 5 5 3 2 Battery Conditioning Equipment BCE Charge cycle setting VA EQ T The Battery Conditioning Equipment BCE shall allow the operator to select beside the charge current value also the voltage Default value shall also be provided on the BCE Page 31 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo Agence spatiale europeenne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 5 4 Battery Conditioning Equipment BCE Battery discharging VA EQ T The Battery Conditioning BCE shall provide the capability to discharge the Li Ion battery in Normal mode only i e the whole battery only can be discharged In order to reach the minimum voltage VEOD of 18 V VEOD min 14 75 V proper dedicated loads electronic or resistive loads will be used for the discharge capability The operator shall be notified with an Alarm message when Vgop equals to 18 V and Battery discharge process needs to be aborted when VEOD equals to 15 V also in this case proper message shall be notified to the
52. o 4000xxxxxx 13 NL GLC The On Line software shall foresee at least a Logbook window it shall contain with the relevant time stamp notification of all the events occurring during the current Test Session including both error messages and normal operational information ex Power SCOE status changes All messages displayed inside the Logbook window will be stored inside the Logbook file 7 10 6 2 Monitor window VA EQ T The On Line software shall provide besides the Logbook window a dedicated Monitor window in which the ongoing test information peculiar Power SCOE data and parameters cyclically acquired shall be listed and their measured set values kept updated together with the relevant time stamps Each displayed value shall be clearly identified by its name and description its type analogue digital and its status in case operational limits are defined 7 10 7 On Line software Termination VA EQ T In order to terminate the On line application currently running a dedicated command shall be foreseen It will be in charge to stop in the right order all the running tasks and processes 7 11 Off line Activities 7 11 1 Battery Conditioning Equipment BCE Stored data retrieval VA EQ T The Battery Conditioning Equipment BCE shall provide to the user the possibility to retrieve data from the Archive files produced during On line test activities 7 11 2 Test results post processing VA EQ T The Power SCOE shall pr
53. o try to establish the connection with it 6 7 3 Exchanged messages format VA EQ T The communication with the CCS shall be based on a Packet oriented protocol where the packets format is the same defined for the ones exchanged with the Spacecraft Refer to Annex 3 Dedicated APID have already been defined for EGSE they range from 2016 to 2046 Refer to Annex 3 6 7 4 Exchanged messages contents VA EQ T Page 49 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Ag ale europei ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC The main types of data travelling from the Power SCOE Controller to the CCS beside the handshaking messages used to establish and control the communication link shall be Periodic packets containing vital data acquired by the SCOE Non periodic packets containing the answer to a CCS issued command ex Status request Asynchronous packets containing special events or errors warning notifications Other DU que While the Power SCOE will mainly receive from the CCS always with packet formats specific commands to get particular parameters values or to change the operational mode and Telecommand requests Note for Battery Conditioning Equipment BCE only BCE will not receive any remote commands from the CCS and will not deliver to CCS any packet Page 50 77 Power SCOE Spec European S
54. onditioning Equipment BCE only this requirement is applicable for BCE only for what concerns the availability of keyboard commands Page 54 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use 7 4 8 Power SCOE Commands VA EQ T Deleted Page 55 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo es e 2 23 fi eSa Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC e European Space Agency Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 5 Power SCOE Off line and On line mode definition VA EQ T The Power SCOE On line software shall support two distinct operational modes i e Off line mode and On line mode 7 5 1 Off line mode Interfaces status VA EQ T When in Off line mode all power and signal interfaces to the Spacecraft shall be galvanically separated i e neither power nor other signals shall be provided at the Spacecraft interface 7 5 2 On line mode Interfaces status VA EQ T When operating in On line mode all the Power SCOE interfaces to the Spacecraft shall be connected 7 5 3 On line mode Interfaces setting VA EQ T The interface setting shall be in accordance with the configuration locally set if in Local mode and with the configuration
55. operator 5 5 4 1 Battery Conditioning Equipment BCE Discharge current VA EQ T The battery conditioning equipment shall provide a discharge current sink 5 5 4 2 Battery Conditioning Equipment BCE Discharge cycle setting VA EQ T The Battery Conditioning Equipment BCE shall allow the operator to select beside the discharge current value also the voltage limits for the whole battery Default values shall also be provided on the BCE 5 5 5 Battery Conditioning Equipment BCE Battery capacity determination accuracy VA EQ T The Battery Conditioning Equipment BCE shall provide the capability to measure the battery capacity with accuracy better than 2 5 5 6 Battery Conditioning Equipment BCE Output sensing VA EQ T The Battery Conditioning Equipment BCE shall sense the voltage and current at the user interface and shall regulate the SCOE output accordingly Page 32 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 5 7 Battery Conditioning Equipment BCE Battery monitoring VA EQ T The Battery Conditioning Equipment BCE shall provide the capability to acquire to monitor and to archive inside dedicated archive files at least the following parameters during both charge or discharge cycles e Battery overall
56. ote mode is not required for BCE 7 4 1 Power SCOE Local Mode VA EQ T In Local mode the SCOE controller shall assure the whole functionality of the Power SCOE i e the SCOE shall be fully programmable and managed by the local Software and controlled by means of the commands entered using the local keyboard only 7 4 2 Power SCOE Remote Mode VA EQ T In Remote mode the whole functionality of the Power SCOE shall be assured by the SCOE controller as in Local mode but it shall be controlled by means of remote commands coming from the CCS Note for Battery Conditioning Equipment BCE only this requirement is not applicable for BCE 7 4 3 Power SCOE Manual Mode VA EQ T In Manual Mode the SCOE user shall be able to change all adjustable levels manually acting on the front panel knobs switches the actual adjusted level shall be displayed screen LCD pointer reading etc Moreover the operator shall be allowed to program all circuits power supplies manually to default values previously agreed with the Sub Contractor acting on the front panel with a single knob switch Page 53 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 4 4 Power SCOE Emergency shut down button VA EQ T Regardless the currently selected operational mode the
57. ovide to the user the capability to easily retrieve from logbook messages data test results stored during a Test Session and analyse them with proper tools Operating System standard function can be used for this purpose Page 64 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 12 File exchange VA EQ T The Power SCOE shall be able to provide to the user the mean to exchange data files with external users via FTP or NFS Page 65 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 8 POWER SCOE HARDWARE AND SOFTWARE CONFIGURATION 8 1 Power SCOE Architecture VA EQ A The Power SCOE shall be built to the maximum possible extents using off the shelf equipment wherever is possible custom made hardware and software development shall be minimised 8 2 Power SCOE software organisation VA EQ T The Power SCOE shall provide the capability to store in separated disks or partitions the various kind of Software In particular the Software developed and provide by the Subcontractor the user developed Software command configuration files the Logbook and the Archiv
58. pace Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 POWER SCOE OPERATIONAL REQUIREMENTS 7 1 Power SCOE Testing capability VA I O The Power SCOE shall provide the capability to perform tests through test software installed in the SCOE controller this test software shall receive commands and inputs either from local keyboard or from the CCS 7 2 Power SCOE Main capabilities VA EQ T The Power SCOE shall provide at least the following main capabilities available during either off line or on line mode 1 Preparation of configuration data for the test 2 Preparation and editing of commands files 3 Deleted 4 Execution of command files 5 Logging of test activities operator actions and test results 6 Error detection and relevant messages management 7 On line help for operation failure investigation removal 8 Display of self test results and status parameters 9 Messages exchange with CCS including also data transfer and mode control 10 Off line test result evaluation of data retrieved from logbook files 11 Other 7 2 1 Battery Conditioning Equipment BCE Main capabilities VA EQ T In addition to the capabilities listed in previous requirement with the exception of the Message exchange with the CCS bullet 8 the Battery Conditioning Equipment shall be a
59. played Page 29 77 Power SCOE Spec European Space Ag Date 24 06 2013 Issue1 Revo i in ESA UNCLASSIFIED For Official Use CSa Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC BUS RTN BUS RTN Fonc Figure 5 4 13 1 Charge array disable link Page 30 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 5 5 Power SCOE Battery Conditioning Equipment BCE High Level Functional Requirements 5 5 1 Battery Conditioning Equipment BCE Main task VA I O The Battery Conditioning BCE main task shall allow the conditioning of the Euclid battery 5 5 2 Battery Conditioning Equipment BCE Configuration VA EQ T The Battery Conditioning Equipment BCE shall work in standalone configuration i e without the remote control from of the CCS 5 5 3 Battery Conditioning Equipment BCE Battery charging VA EQ T The Battery Conditioning BCE shall provide the capability to charge the Li Ion battery with a selectable constant current value up to the Nominal End of Charge Voltage VEOC of 25 2 V Taper Charge shall be applied when a voltage of 25 5 V is reached Taper charge definition when the Battery reaches the maximum voltage level the charge has to be maintai
60. r the voltage range 14 to 28 Volts In order to speed up the charging discharging process the Battery Simulator operator shall be able to select a current value in the allowed range and the SCOE shall automatically calculate the required charge discharge time interval It shall be possible to pause the simulator at any time and suspend the discharge characteristic simulation It shall then be possible to continue the simulation It shall be possible to pause the simulator at any time and suspend the charge characteristic simulation It shall then be possible to continue the simulation 5 2 4 Battery Simulator BS Battery discharge current VA EQ T The Battery Simulator shall support a Battery discharge current value equivalent to o 280W over the entire battery voltage range 5 2 5 Battery Simulator BS Battery charge current VA EQ T The Battery Simulator shall provide a sink for battery charge currents of up to 10 A maximum over the entire battery voltage range 5 2 6 Battery Simulator BS Crossing between source and sink mode VA EQ T The Battery Simulator BS shall allow an uninterrupted transition from charge to discharge source and sink mode and vice versa without interruption and without the need of user intervention It shall be possible to alternate between any allowed charge and discharge rate and the battery simulator shall maintain the simulated state of charge The simulation shall be suspended i
61. rchive files shall be identified by names containing the creation date and time and stored in proper sub directories also organised by date 7 7 2 Battery Conditioning Equipment BCE Archive files management P HP ASPI 1 SP 004543 3 1 1 GRQT 0050 VA EQ T Each data file shall be closed when its size reaches a defined limit ex 1GB a new file shall be automatically opened in order to ensure no data loss during the whole test activities On the contrary whenever only few data are to be stored files can be closed in order to contain all the data relevant to a complete charge discharge cycle 7 7 3 Battery Conditioning Equipment BCE Archive files storage on local disk VA EQ E The Battery Conditioning Equipment BCE shall be equipped with sufficient disk space to allow the storage of archive files for at least 20 complete charge discharge cycles 7 7 4 Battery Conditioning Equipment BCE Local disk unavailability for archiving VA EQ T In case no more disk space is available for archive files storage the operator shall be notified in advance with dedicated warning and error messages in order to avoid loss of data 7 8 Power SCOE Logbook capability P HP ASPI 1 SP 004543 3 1 2 GRQT 0060 VA EQ T Page 58 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo AGENCE spauere europeenne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 400
62. requirements are listed in Section 6 where all the interface are considered both towards the Spacecraft and towards other EGSE components e g CCS External interfaces like power from the facility and grounding concepts are also mentioned Operational requirements are depicted in Section 7 while some guidelines for Power SCOE Hardware and Software configurations to be provided by the Contractor are contained in Section 8 Performance requirements to be satisfied by the Power SCOE in order to make it suitable to support all Integration and Test activities are described in Section 9 Finally Verification Requirements are contained in sections 10 and 11 of this Power SCOE Specification document Page 7 77 Power SCOE Spec European Space A Agence spatiale pee Date 24 06 2013 Issue1 Revo Agence spatiale europe ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 2 DOCUMENTS AND STANDARDS In the following sub paragraphs several documents classified in two major categories Applicable and Reference documents are listed More in details e Applicable documents or single paragraphs or sub paragraphs which will be mentioned in this document must be considered as a part of it e Reference documents have been taken into account to prepare this document but it is not mandatory to comply with them they help to clarify and detail specific requirements 2 1 APP
63. rns the activation of self test remotely from the CCS 7 6 3 Self test logging VA EQ T The self test activation shall be logged together with the results of its execution so that these information will be available for later investigation The self test results plus diagnostic messages in the case of unsuccessful execution shall be both locally displayed and reported to the CCS Note for Battery Conditioning Equipment BCE only this requirement is not applicable for BCE for what concerns the diagnostic messages transfer to the CCS 7 7 Power SCOE Archiving capability for Battery Conditioning Equipment VA EQ T The Battery Conditioning Equipment BCE is the only item belonging to Power SCOE where it is required the capability to archive in separate and distinct archive files whose format shall be compatible with the CSV files the following type of data 1 Auxiliary information Date time operator remarks 2 Type of cycle charge discharge 3 Cycle definition set up 4 Battery parameters set up 5 Battery monitored parameters raw and calibrated Page 57 77 Power SCOE Spec European Spa Agence spatiale et Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 Others 7 7 1 Battery Conditioning Equipment BCE Archive files naming VA EQ T The Battery Conditioning Equipment BCE a
64. sk ss 26 5 4 2 Launch Power Supply LPS Power Requirements ss 27 5 4 3 Launch Power Supply LPS Umbilical connection 27 5 4 4 Launch Power Supply LPS Umbilical parameters acquisition eee 27 5 4 5 Launch Power Supply LPS Sensing capability ss 28 5 4 6 Moved to section 5 9 14 3 n emere retro HEP EU ele a EE Tee pe EYE bO eK Ea eK eve voe ael UNE RES 28 5 4 7 Launch Power Supply LPS Over voltage protection e ss 28 5 4 8 Launch Power Supply LPS Over current protection ss 28 5 4 9 Launch Power Supply LPS Safety loop sense 28 5 4 10 Launch Power Supply LPS Monitor and Display Capabilities eese 28 5 4 11 Launch Power Supply LPS Separation Switches Simulation and Monitoring 29 5 4 12 Flashing PI HEERERURERURERORHTERT 29 5 4 13 SAS LPS Charge array disable link simulation and monitoring eere 29 5 5 Power SCOE Battery Conditioning Equipment BCE High Level Functional Requirements 31 5 5 1 Battery Conditioning Equipment BCE Main task 31 5 5 2 Battery Conditioning Equipment BCE Configuration eeeeeeseeseeeeeeeeee ener 31 5 5 3 Battery Conditioning Equipment BCE Battery charging enne enne 31 5 5 3 1 Battery Conditioning Equipment BCE Charge current 31 5 5 3 2
65. stor interfaces for battery Refer to Annex 2 6 1 3 Solar Array Simulator SAS Interfaces VA EQ T The Solar Array Simulator SAS shall provide at least the following interfaces e Power outlets for solar array panel simulation to the flight interface Solar Array connection e Temperature sensors simulation interface Refer to Annex 2 6 1 4 Battery Conditioning Equipment BCE Interfaces VA EQ T The Battery Conditioning Equipment BCE shall interface directly to the Battery connectors and shall provide at least the following interfaces 1 Power input output interface to Battery power connector 2 Interface to battery test connector to monitor overall battery 3 Thermistors interfaces to Battery monitor connector Page 36 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC Refer to Annex 2 6 1 5 Launch Power Supply LPS Interfaces VA EQ T The Launch Power Supply LPS shall provide at least the following interfaces 1 2 3 a Power lines 6 sections 3 A max R 1 loop Interface to Battery Voltage Monitor lines Umbilical interface for Main Bus Voltage acquisition Bus monitor lines and separation switches status Battery temperature Umbilical interface for analogue data acquisition The spacecraft provides two main bus volta
66. t No 4000xxxxxx 13 NL GLC TC Primary NRZ L PIN Name Direction Level Description 1 IF_GND2 Interface Ground 2 2 TCSCP_CLK_T To S C RS 422 Primary TC Clock true signal 3 TCSCP_DAT_T To S C RS 422 Primary TC Data true signal 4 TCSCP_ENA_T To S C RS 422 Primary TC Bypass Enable true signal 5 LOCK Keying pin 6 TCSCP_CLK_C To S C RS 422 Primary TC Clock comp signal 7 TCSCP_DAT_C To S C RS 422 Primary TC Data comp signal 8 TCSCP_ENA_C To S C RS 422 Primary TC Bypass Enable comp signal 9 Not Connected TC Redundant NRZ L PIN Name Direction Level Description 1 IF_GND2 Interface Ground 2 2 TCSCR_CLK_T To S C RS 422 Redundant TC Clock true signal 3 TCSCR_DAT_T To S C RS 422 Redundant TC Data true signal 4 TCSCR_ENA_T To S C RS 422 Redundant TC Bypass Enable true signal 5 Not Connected 6 TCSCR_CLK_C To S C RS 422 Redundant TC Clock comp signal 7 TCSCR_DAT_C To S C RS 422 Redundant TC Data comp signal 8 TCSCR_ENA_C To S C RS 422 Redundant TC Bypass Enable comp signal 9 LOCK Keying pin 6 2 3 Launch Power Supply LPS cables 6 2 3 1 SAS LPS Cables For AIV Activities VA EQ T The SAS LPS will interface with the Spacecraft during AIV activities with 30 mt length cables 6 2 3 2 LPS Cables On Launch Site VA EQ T The LPS will power the Spacecraft already mo
67. t least with 1 Stand alone boot capability2 Colour Screen with high resolution 3 American keyboard 4 Mouse 5 CD reader 6 Local printer to produce a hard copy of the locally displayed data and for local files outputs 8 4 1 Launch Power Supply Controller location VA EQ E The Launch Power Supply LPS shall be designed in such a way that its controller can be located in a manned room 20 Km far from the racks Moreover the LPS shall be designed to have a hot redundancy for the LAN between its controller and the rack 8 5 Interchangeability P HP ASPI 1 SP 0045 3 5 2 3 GRQT 03 10 VA EQ E All hardware components design shall be done in such away to be easily replaced without the need of special adaptation work special tool and procedure required Page 67 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 9 POWER SCOE PERFORMANCES 9 1 Continuous Operations P HP ASPI 1 SP 0045 3 3 5 1 GRQT 0300 VA EQ T The Power SCOE shall be able to run a test session continuously over 20 days 24 hours a day without stopping or losing any data and without the need of restarting rebooting or resetting the system or its components during that time 9 2 Performances at user interface VA EQ T The Power SCOE shall be able to satisfy all requirem
68. ta links Telemetry transfer frame protocol Is 2 31 July 2008 ECSS E ST 50 04C8 Space data links Telecommand protocols synchronisation and channel coding Is 2 31 July 200 ECSS E ST 50 12C SpaceWire Links nodes routers and networks Is 2 31 July 2008 ECSS E ST 50 13C Interface and communication protocol for MIL STD 1553B data bus on board spacecraft Is 1 15 Nov 2008 ECSS E 70 41A Ground systems and operations Telemetry and telecommand Packet Utilization 30 January 2003 CSG RS 10A CN CSG Safety Regulations Volume 1 CSG RS 21A CN CSG Safety Regulations Volume 2 Part 1 CSG RS 22A CN CSG Safety Regulations Volume 2 Part 2 Page 9 77 Power SCOE Spec European Spa gency Date 24 06 2013 Issue1 Revo Agence spatiale europeenne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 2 4 Acronyms APID AVM BCE BS CCS CCU COTE CDMU EGSE HK I amp T ISC IST LPS PCDU PFM PLM RTU SAS SCOE S C S L SVM TC TM Page 10 77 Power SCOE Spec Date 24 06 2013 Issue1 Revo Application Process Identifier Avionic Model Battery Conditioning Equipment Battery Simulator Central Checkout System Cryostat Control Unit Check Out Terminal Equipment Control and Data Management Unit Electrical Ground Support HouseKeeping Integration and Test Integrated System Checks Integrated System Tests Local Area Network Launch
69. the on board units 7 10 On line Activities VA I O The On line software will be automatically started after the Power SCOE power On it shall be designed and used in order to perform the test activities on the Service Module and on Spacecraft 7 10 1 Test Session start up Auxiliary information input VA EQ T At the Test Session start up the user shall be asked to input several auxiliary information useful to define the test configuration and SCOE initial set up 7 10 2 Test Session start up time VA EQ T The On Line software shall be ready to be used by the operator for Test activities in less than 5 minutes after the start up 7 10 3 Simulation ON OFF VA EQ T The POWER simulation of the SCOE shall be started and stopped upon user commands sent either locally or remotely from CCS Note for Battery Conditioning Equipment BCE only this requirement is not applicable for BCE for what concerns the reception of remote commands from the CCS Page 62 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 7 10 4 On line mode Test execution VA EQ T The Power SCOE shall provide at least the following functions available during a Test execution session Simulate Thermistors and Switches as defined in the simulation configuration files Comm
70. the verification documentation and give approval to the test procedures in advance respect to the tests run The Contractor shall witness the Final System Acceptance tests Test results shall be provided within The Test Reports that shall include also the test description and the configuration status of the item under test Page 73 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use 11 5 Verification methods VA N A For qualification of a generic item against a requirement dealing with either Hardware or Software or the union of the two the following methods are allowed Test T Analysis A Es x B d Similarity S Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC Assessment E including both Review of Design and Inspection The convention used inside this document to indicate the Verification Method is here below explained The Verification Method statement syntax foresee to have VQ lt Code level gt lt Method Code gt Note for Qualification VA lt Code level gt lt Method Code gt Note for Acceptance where Level Code SY System PF Platform IT Instrument SS Subsystem EQ Equipment Method Code T Test A Analysis Review of Design E Assessment Inspection S Similarity Note IO Information Only N R Not Required N A
71. tion and identification of failed items without dismounting or disconnecting other equipment 2 Calibration 3 Integration 4 Maintenance 6 4 5 Grounding concept VA EQ T Refer to Annex 1 6 5 Power and Signal ground separation VA EQ T Signal and power returns of the Power SCOE shall be separated It shall be possible to ground the Power Supply return There will be DC isolation between the Power Supply and the remaining part of the Power SCOE 6 6 External powering VA EQ T Page 48 77 Power SCOE Spec uropean Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europe ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC An independent Power Distribution Unit Insulation Transformer shall be used in order to power the Power SCOE 6 7 Power SCOE to CCS Interfaces VA EQ T The Power SCOE shall be able to interface with the CCS node via a 100 Mb s Ethernet Local Area Network using the standard TCP IP protocol Refer to Annex 3 6 7 1 Communication Control for Power SCOE VA EQ T The communication links between CCS and the POWER SCOE shall be managed following a Client Server philosophy where the CCS acts as a Client and the SCOE is the Servers accepting connection and service requests 6 7 2 Communication Link start up VA EQ T The Power SCOE shall automatically accept a connection request coming from the CCS in order t
72. ttery Simulator shall have the capability to sense the battery temperature lines 5 2 17 Battery Simulator BS Over voltage protection VA EQ T The Battery Simulator BS shall provide an over voltage protection mechanism at the user interface with adjustable level for the outputs lines Default value triggering the over voltage protection shall be 28 volts protection intervention time shall be 50 micro seconds without exceeding the over voltage protection threshold Page 20 77 Power SCOE Spec uropean Space Agency Date 24 06 2013 Issue1 Revo Ag spatiale europe ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC Isolation of the fault shall not result in the spacecraft interface being shorted to ground it is preferred that the BS be isolated via an output switch 5 2 18 Battery Simulator BS Over current protection VA EQ T The Battery Simulator BS shall provide an over current protection mechanism at the user interface for the outputs lines Default value triggering the over current protection shall be 2 of the maximum current protection intervention time shall be lt 50 micro seconds without exceeding the over voltage protection threshold Isolation of the fault shall not result in the spacecraft interface being shorted to ground it is preferred that the BS be isolated via an output switch 5 2 19 Battery Simulator BS
73. unicate with the CCS for data transfer and mode control Execute Test and pre programmed sequences of commands Parameters acquisition monitoring display and archiving ON eee ba Other 7 10 5 On Line software Further capabilities VA EQ T The On Line software shall provide to the user at least the capabilities summarised here below Acquire and monitor of Power SCOE peculiar data and parameters Display of SCOE status and test data in dedicated presentation windows see below Send commands directly entered at local keyboard QV e DE Other 7 10 6 On Line software Acquisition and Monitoring VA EQ T When the On line software is running the Power SCOE shall perform as an always running background task a cyclic acquisition of all the parameters relevant to the particular running function The list of parameters to be cyclically acquired and monitored shall be contained inside a configuration file table The acquisition cycle for SCOE parameters only shall be not lower than 10 seconds The monitored SCOE parameters shall be transmitted to the CCS in the correct packet format Note for Battery Conditioning Equipment BCE It is not required to transmit data to the CCS 7 10 6 1 Logbook window VA EQ T Page 63 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract N
74. unted on the launcher it will be connected to the facility patch panel with 15 m cables In any case the LPS shall be carefully designed in order to fulfil performance requirements over long cables distance and taking into account the cabling characteristics of the Launch facility infrastructure i e i Cables type Twisted shielded 2 Cable total TBD Page 40 77 Power SCOE Spec Date 24 06 2013 Issue 1 Revo Agence sp p enn ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 6 2 4 Cables naming VA EQ E All cables shall be identified with unambiguous names and properly labelled Moreover cables shall be labelled on both side indicating at least besides the cable identification SCOE or Satellite side and relevant connector it has to be connected to 6 3 Power SCOE Connectors and pins function VA I O The connectors mounted on POWER SCOE harness and interfacing the Spacecraft shall be capable of mating the Spacecraft connectors as specified in the next paragraphs Related Spacecraft Connectors type and relevant pins function are detailed in Annex 2 All Power SCOE connectors shall be identified with unambiguous names and properly labelled 6 3 1 Deleted 6 3 2 Deleted 6 3 3 Deleted Page 41 77 Power SCOE Spec European Spa Date 24 06 2013 Issue1 Revo spe ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL
75. us voltages currents or short circuits that could damage the on board equipment 11 3 Power SCOE Acceptance VA N A The Acceptance tests of each EGSE item shall be run to verify all hardware and software requirements stated inside the relevant Specification documents Preliminary acceptance tests shall be run at Contractors premises and shall foresee a hierarchical test approach i e from module to fully integrated SCOE level in all possible configuration and operational mode Further Acceptance tests are foreseen at Customer premises with the POWER SCOE included in the overall EGSE configuration Page 71 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 11 3 1 Power SCOE Acceptance Performance tests VA N A The Power SCOE Contractors shall demonstrate that the provided product fully conforms to the Performance requirements planning and executing a complete performance test under worst case load conditions Page 72 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europeenne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC 11 4 Final Power SCOE Acceptance documentation approval and witnessing VA N A The Customer shall review
76. us regulation in the S C PCDU The use of a mechanical relay is required at the power feeding outputs in order to galvanically isolate the Power SCOE from the Satellite 5 4 3 Launch Power Supply LPS Umbilical connection VA EQ T The Launch Power Supply LPS shall provide and shall be able to manage the interface between the SCOE and the S C Umbilical connectors such that 1 2 3 No single failure within the SCOE shall result an overload of the PCDU interface current gt 3 0A Voltage 31V Over voltage OR over current protection shall be effective within 5ous without exceeding item 1 above No single failure shall result in the loss of both prime and redundant support systems The SCOE shall provide back EMF protection during separation simulation to prevent arks at the end of the SCOE cable Charge array disable link 5 4 4 Launch Power Supply LPS Umbilical parameters acquisition VA EQ T The Launch Power Supply LPS shall receive the spacecraft s precision Main Bus voltage sense lines see paragraph 6 1 1 and accurately buffer them for distribution to the following functions Remote main bus voltage control for distribution to bus voltage monitor via prime umbilical connector Prime bus voltage monitor Prime battery voltage monitor Page 27 77 Power SCOE Spec European Space Date 24 06 2013 Issue1 Revo ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC
77. voltage Battery overall current Temperature readout from thermistors Acquisition date and time Half string voltage The monitored values shall be acquired each second and with an accuracy of 0 01 V for voltages and 0 01 A for charge discharge current 55 8 Battery Conditioning Equipment BCE Automated operation VA EQ T The Battery Conditioning Equipment BCE shall provide the capability to perform charge and discharge cycles under the supervision of dedicated software installed inside the BCE controller At least the following functions shall be provided to the local operator Definition and storage of different charge and discharge profiles Definition of levels limits that if exceeded cause the charge discharge process to be interrupted Archiving voltage current and temperature values as monitored during battery conditioning Calculation of battery capacity Archived data retrieval post processing and presentation 5 5 8 1 Charge discharge configuration set up VA EQ T The Battery Conditioning Equipment BCE shall provide for example the possibility to define that 1 The charge shall be performed according to the selected constant current until the following limits are reached Battery Voltage from 25 2 V to 25 5 V 2 The discharge shall be performed at the selected constant current until the following limits are exceeded Battery Under Voltage from 20 V to 16 V Page 33 77 Power SCOE Spec European
78. will be used to provide power to the Spacecraft during the final count down Refer to figures 3 2 1 and 3 2 2 for possible EGSE configurations in which the Power SCOE is foreseen to be used The Power SCOE shall be able to provide the required electrical power simulating the batteries and the Solar Array The control of the Power SCOE shall be possible for the operator either if the SCOE is locally commanded or when it is remotely controlled by the CCS via the SCOE DFE LAN Page 11 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue 1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use esa Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC I Il Il Il Il VIS Stimuli On board 1553 RT Battery Umbilical Optical Stimuli amp TT amp C memories Simulator inan es Simulator I F Stimuli Feedback SCOE 11 Load amp p Trapping 11 Dump i i wv Solar Array SCOE SCOE Simulation Controller ARE Controller Controller TM TC NISP SCOE DFE Stimuli Controller POWER SCOE A SCOE DFE LAN IS LAN Central Check out System Station m NDIU Lite and or Traditional Experiment Y EGSE Page 12 77 Power SCOE Spec European Space Agency Date 24 06 2013 Issue1 Revo Agence spatiale europ enne ESA UNCLASSIFIED For Official Use Appendix 2 to ESA AO 1 7612 13 NL GLC Appendix 3 to ESA Contract No 4000xxxxxx 13 NL GLC Figure 3 2 1 Euclid AVM FM and EG

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