AstroSAT 500
Contents
1. ER 9 2 2 Reference GOCUIMOEMNS eee re te ro rer ae re Ea Ra Ee eng etae ora ee Ru MR E x ERR Rua eaa a ee ran 9 3 FUNCTIONAL AND PERFORMANCE REQUIREMENTS nennen senes 10 3 1 Functional Requirements Xn Desa e ep Ma aive yx ae 10 Bled Battery Ay OUT e225 sa ds Rm 10 3 1 2 Battery ern ar ER onse ex Rare X uua 10 3 2 Performance Requirements 2 222 10 3 2 1 Power and energy amp 10 3 2 2 Battery charge eene entren nnne nns 10 9 2 9 POLO CUOINS a iiit teer 11 3 2 4 Battery voltage range aaea sente sen asisten estet nnns 11 4 UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS seen 12 4 1 Mechanical Design and Interface Requirements sse enne 12 LMECEE 12 4 1 2 Cemre of Gravity EMI anaa A kaa aaraa EEE 12 AAS ENVGIO DC eee e EA A E EE EE 12 4 2 Thermal Design and Interface Requirements ssssssssssssseeseeee ener 12 4 2 4 Heat DISSIPATION nere 12 4 2 2 Unit Thermal Properties eret reden nr2. _86 4 3 2 2 14 _87 4 3 2 2 14 _88 4 3 2 2 14 _90 4 3 2 3 15 _91 4 3 2 3 15 _93 4 3 15 _99 4 41 2 16 _100 4 41 2 16 _103 4 4 2 1 16 _105 4 4 2 2 16 _114 4 4 2 3 16 _116 4 4 2 3 16 _118 4 4 2 4 17 _119 _120 _121 _122 _123 _125 _126 _127 4 4 2 5 17 _128 4 4 2 5 17 _129 4 4 2 5 17 _130 4 4 2 5 17 _133 4 4 2 6 18 _135 18 _136 E E 18 _138 4 4 4 18 Ref LXO SP 00005 DT ASTR AStroSAT 500 Issue 2 Rev 01 Date 12 07 2010 Page 25 of 27 DOCUMENT CHANGE DETAILS ISSUE CHANGE AUTHORITY CLASS RELEVANT INFORMATION INSTRUCTIONS 01 Initial release 07 05 09 02 Consistency with AS500 specification 1502 impedance change 02 01 Connector pins update EADS Astriu
3. BAT 73 4055 T The applicable unit temperature limits are Operating Temperature Limits 0 C to 30 C Extended Operating Temperature Limits 10 C to 40 C Note 1 Qualification Temperature Limits 20 TFQ min to 50 C TFQ max Note 2 Non operating Temperature Limits 30 C TNF min to 55 C TNF max Average Temperature life time lt 20 C This shall be verified by thermal testing as specified in AD 02 Note 1 The cumulative time for these extended range shall not exceed 1000 TBC Charge discharge cycles as per 3025 Any performance which cannot be met shall be identified and justified Note 2 This is the Qualification range to be applied during the Thermal Vacuum tests Full performance is not required between 10 to 0 and 30 C to 50 4 2 4 Thermal control 75 4060 The battery shall be equipped with thermal heaters and thermal sensors that will make possible its temperature control by the On Board Computer The battery shall be fitted with a redundant thermal heater and three thermal sensors used for regulation 1 nominal 1 redundant and 1 for monitoring BAT 76 4066 R The thermal heaters locations are under the subcontractor responsibility R 40 ohms in the extended operating temperature range ESCC4009 002 Double layer heater recommended Remark The power switching frequency shall be 1 8 Hz maximum 4 3 Electrical Design and Interface Requirements 4 3 1 Power C
4. charge at this voltage until the end of the sunlight phase 3 2 Performance Requirements 3 2 1 Power and energy requirements BAT 44 3025 R The battery shall withstand the following cycle definition along its complete life time Average discharge power 418 W during 33 5 min Average available charge current 10 A during 67 8 min BAT 45 3030 T R The battery shall provide 1 215 Wh under an average power consumption of 250 W during the spacecraft launch and until charge is started BAT 46 3035 R The battery shall always keep a minimum of 555 Wh reserve energy under an average power consumption of 265 W along its complete life time with the exception of the launch phase for spacecraft safe mode acquisition BAT 47 3040 R The battery shall provide a peak power capability of 750 W in discharge over a duration of 6 seconds 3 2 2 Battery charge management 49 3045 T R The battery shall be current limited in charge at 37 5 A The limitation shall not be done at battery level but at System level BAT 50 3050 T R The battery shall be voltage limited at 33 6 V 0 0 4 V The limitation shall not be done at battery level but at System level The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 11 o
5. 12 4 2 3 Temperature Hequlrerients cutie 13 4 2 4 Thermal CORO hereto end en Rant t nega n pk pag Neu E Ra Rex EE RR XR aa Rv RV a IRAE 13 4 3 Electrical Design and Interface Requirements 0 cccccceeceeceeeeeeeeeeeeeeeeceeeeeeaaeeeeaaeseeeesaeeesaaeeseaeeeenees 13 4 3 1 Power P 13 4 3 2 Electrical Interface 13 4 3 3 Electrical ERN Mon ia 15 4 4 Operational ntn internes 15 4 4 1 Mission profile aded n ano Rada da 15 4 4 2 Reliability and availability 4 n nnne enne 16 44S SATAY Mm 18 4 4 4 Identification and nnne nennen sn nenne nsen nes 18 5 GENERAL DESIGN AND INTERFACE REQUIREMENTS sss 20 6 VERIFICATION REQUIREMENTS 21 7 PRODUCT ASSURANCE REQUIREMENTS sse eee nnne nnns innen en 22 revealed to ind panies wa phar EAD Astrium Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 AstroSAT 500
6. 27 AstroSAT 500 6 VERIFICATION REQUIREMENTS Refer to AD 02 and AD 03 for generic verification requirements The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 22 of 27 AstroSAT 500 7T PRODUCT ASSURANCE REQUIREMENTS Refer to AD 01 The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 EADS AstroSAT 500 Date 12 07 2010 Page 23 of 27 CHANGE LOG Note This log is autogenerated from Doors Special symbols may not be rendered correctly and hence the main body of the document shall always take precedence for requirements Thus it should only be used as a guide to the modifications in the document and not as a substitute Modified Objects In the following table modifications to the Object Text attribute are shown using red line markup For other attributes the new value and the old value are shown in separate columns The codes used in the object type OT column are Rq Requirement Inf Information Hd Heading Ah Applicability Matrix Heading Ar Applicability
7. 4 Identification and marking BAT 138 R The unit hardware shall be marked by a nameplate in order to achieve configuration traceability The identification shall be made by a label containing the following information eProject Name AstroSAT 500 eUnit Name Model BAT EM PFM FM2 ePT Item Code TBD eSerial Number TBD by supplier eDrawing Number TBD by supplier revealed pares pior EADS Astrium Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 19 of 27 AstroSAT 500 Individual unit shall be marked with a serial number For standard parts and where the physical size of an item precludes identification of the hardware itself a bag and label technique shall be used up to final integration as appropriate The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 20 of 27 AstroSAT 500 5 GENERAL DESIGN AND INTERFACE REQUIREMENTS Refer to AD 02 The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 21 of
8. 4125 R Each battery module shall provide 3 temperature monitoring signals in addition to these required in section 4 2 4 BAT 712 4130 T R The characteristics of the temperature monitoring interface for the battery shall be as defined in AD 02 requirements 4370 and 4380 Betatherm 15KOhm 25 4 3 3 Electrical insulation 93 4140 impedance between any cell of the battery and its chassis shall be greater than 100 MQ under 250 V to avoid any cell voltage drift 4 4 Operational requirements 4 4 1 Mission profile 4 4 1 1 Lifetime Refer to ADO2 The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 16 of 27 AstroSAT 500 4 4 1 2 Duty cycle 99 4150 T A The battery shall be designed to withstand 100 charge discharge see conditions cycles over the ground storage period and 28000 charge discharge over the 5 years mission lifetime nominal operations in orbit BAT 100 4151 T A The battery design shall be such that EOL performances meet requirement 4150 and cumulative effects of e3 years of storage under the conditions as per the User Manual e2 years of AIT with an average SOC of 50 in tapering at 20 e3 capacity measurements 100 DoD at 20 4 4 2 Re
9. Matrix Requirement 86 Object Text The battery power interface shall consist of 810 AWG12 wires 45 section positive lines 45 negative lines The wiring of both polarities lines 4 3 2 2 shall be done to minimise as far as possible magnetic momentum section 4 3 2 2 section 4 3 2 2 BAT 734 Object Text The pins which are not used in Table 4 3 2 shall be double insulated section ins Deleted 4 3 2 2 BAT 734 Intended section Verification 4 3 2 2 Method Inserted Objects Identifier Object Type Text BAT 791 Information For power interface J01 which includes more than 5 pins all the pins shall section be externally connected to positive power lines 4 3 2 2 section 8 1 section 8 1 Deleted Objects 9 differences found The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing C EADS Astri um Ref LXO SP 00005 DT ASTR AStroSAT 500 Issue 2 Rev 01 Date 12 07 2010 Page 24 of 27 Requirement Section Cross Reference Page numbers are the pages where the sections start 708 4 8 2 4 15 709 4 3 2 4 15 _711 4 8 2 5 s 15 BAT 712 4 3 2 5 15 _732 4 3 2 2 14 _734 4 3 2 2 14
10. Page 4 of 27 TABLES Table 4 3 1 Connector LISL utei een ae Ra EAN NIRE EP 14 Table 4 3 2 pin function available at power 4 enne nennen nnne nen 14 The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 5 of 27 AstroSAT 500 INTENTIONALLY BLANK The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 AstroSAT 500 Page 6 of 27 SUMMARY The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 7 of 27 AstroSAT 500 1 INTRODUCTION AND SCOPE 1 1 Introduction AstroSAT 500 refers to a family of satellite of the 500 kg class It is designed to operate five years in Low Earth polar orbit at an altitude of about 700 km The battery specified in this document is of the Li lon techno
11. T R The battery internal impedance AC on the power interface shall be eLower than 20 m2 for frequencies lt 1 kHz and eLower than 60 m2 for frequencies at 10 kHz This applies for 10096 SOC at Tamb 22 43 C And Lbatt 110 nH for frequencies lt 10 kHz Tamb gt 0 C and at 100 SOC The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 15 of 27 AstroSAT 500 BAT 88 4086 T A R The battery internal impedance DC on the power interface shall be lower than BOL 40 for frequencies lt 1 kHz T0 100 SOC EOL 120 m2 for frequencies lt 1 kHz 0 SOC Min Vcell 3 0 V 4 3 2 3 Heater interface 90 4090 The battery heater supply interface shall consists 2 pairs of AWG20 wires BAT 91 4095 R The battery heater shall be supplied with a non regulated 22 to 35 V power bus protected by current limiters 4 3 2 4 Battery voltage monitoring BAT 708 4115 R Each battery module shall provide two battery voltage monitoring signals BAT 709 4120 R The characteristics of the battery voltage monitoring interface shall be as follows e Voltage range battery voltage e Protection by resistance located in the battery 12 1 0 0296 1 4 W 4 3 2 5 Temperature monitoring BAT 711
12. EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astrium EADS di AstroSAT 500 Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 27 of 27 Astrium Product Policy Distribution SCHWAB Armin Astrium AstroTerra Distribution ECE Seosat Project Distribution BORGES ALEJO Andr s X Astrium CSO Project Distribution SANZ CUESTA Juan Andr s X CORREGE Alain PERAN Francisco X GARCES Sylvain CORTES David JACOMOND Alain LOPEZ Amador LOCHE Didier BOURGEAL Silvia LUZURIER J r me GIL Miguel Angel MONTEIL Denis LIZONDO Jose Luis SIBILLA Christian DE MIGUEL Elena Diana TOURNIER Thierry PALACIOS Cristina VILLEFRANCHE Patrice SEOSAT Documentation CSO Documentation SEOSAT Configuration GALLAND Philippe LOCHE Didier The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astrium
13. Ref LXO SP 00005 DT ASTR AstroSAT 500 Issue 2 Rev 01 Date 12 07 2010 Page 1 of 27 CI CODE DRL Refs Val rie COSCULLUELA v Prepared by AS250 Power Architect A 2 03 2010 Checked by Brigitte FOURNE gt AS250 Avionics Electrical Architect Serge CAZALS 5250 Avionics Product Assurance Manager Didier LOCHE Power MPC amp Battery product focal point Authorised by e Christophe LEMERCIER Head of Astrium EOS Satellite product definition amp implementation AET6 Application Authorised by EADS ASTRIUM CONFIDENTIAL Document Autogenerated from DOORS Module DIVAS AS250 Level 4 4 6 Battery RS Li lon BATTERY 500 AstroTerra Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 2 of 27 AstroSAT 500 INTENTIONALLY BLANK The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 AstroSAT 500 Page 3 of 27 CONTENTS T INTRODUCTION AND SCOPE a a ee 7 psiceium EL 7 12 es 7 LS 7 LES uris ene 7 1 5 abbreviations and acronyms rns n nnns sn 8 2 DOGUMENTS iesp 9 PA Applicable
14. TR Issue 2 Rev 01 Date 12 07 2010 Page 9 of 27 EADS AstroSAT 500 rm 2 DOCUMENTS 2 1 Applicable documents The following documents are applicable documents to this specification Only those parts of them are applicable for the contractors product design test and manufacturing which are distinctly made transparent by references within this specification AD 01 LXO SP 0009 MMS T Product Assurance Requirements AD 02 LXO SP 0005 MMS T Unit Requirement Document AD 03 LXO SOW 00002 DT ASTR Statement Of Work for delivery of Li ion Battery for AstroSAT 500 Bus 2 2 Reference documents The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 10 of 27 AstroSAT 500 3 FUNCTIONAL AND PERFORMANCE REQUIREMENTS 3 4 Functional Requirements 3 1 1 Battery layout BAT 38 3005 R The battery shall be made of one module such as to comply with all the performance requirements 3 1 2 Battery management BAT 40 3015 R The battery functional management shall be performed at battery level BAT 41 3020 T R Battery charge shall be ensured in two steps Charge at maximum available current limited to a fixed value until a voltage limit is reached Once the battery voltage limit is reached
15. above are not requirements and will not be verified or tracked 1 4 Summary Description Battery is mainly needed during the launch phase to support the solar array when its power capability is lower than the consumption and in case of contingency The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 AstroSAT 500 Date 12 07 2010 Page 8 of 27 The battery consists in the following items eOne structure for mechanical support and thermal dissipation eCells e Temperature sensor for temperature telemetries eHeaters if applicable eConnectors for electrical interface Except otherwise specified all requirements of the specification apply at battery level 1 5 abbreviations and acronyms AIT Assembly Integration amp Test BOL Beginning Of Life COG Centre Of Gravity DOD Depth Of Discharge EOL End Of Life FDIR Failure Detection Isolation and Recovery ICD Interface Control Document MLI Multi Layer Insulator SOC State Of Charge SEU Single Event Upset TBC To Be Confirmed TBD To Be Defined The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be EADS Astrium reproduced or revealed to third parties without prior permission of that company in writing Ref LXO SP 00005 DT AS
16. ardwired automatism if the time for avoiding propagation is less than 10 s TBC eControl through On Board Software if the time for avoiding propagation is compliant with the time to react of the On Board Software i e higher than 10 s These failures shall be detectable through battery data transmitted to the on Board Software and the adequate resources needed to switch the battery in a safe state i e no failure propagation shall not be affected by the failure BAT 120 4190 A The battery elements shall be tolerant to SEU no physical damage BAT 121 4195 A The battery elements shall not be latch up sensitive BAT 122 4200 A The battery shall achieve all its nominal EOL performances despite the in orbit cumulated radiations dose as specified in AD 02 BAT 123 4205 A The battery shall respect all design rules specified in AD 02 regarding interface connections cross strapping links and FDIR features 4 4 2 5 Single Point Failure SPF BAT 125 4210 A No single failure within the battery shall lead to open circuit on more than one battery string The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 18 of 27 AstroSAT 500 BAT 126 4215 A No single failure within the battery shall lead to a short cir
17. cuit within the battery or within any of the strings BAT 127 4220 A No single failure within the battery shall lead to the loss of the battery management BAT 128 4225 A No single failure within the battery shall lead to failure propagation outside the battery voltage BAT 129 4226 A No single failure within the battery shall lead to battery voltage below 23 V including transients BAT 130 4230 A No single failure within the battery shall lead to permanent thermal dissipation 10 above maximum specified dissipated power specified in requirement 4030 4 4 2 6 Feared events This section addresses some specific events identified in the system risk analysis and specifies the related requirements BAT 133 4250 A The battery shall be able to withstand a 19V minimum for 500 ms TBC without damage b 24 V to 20 V minimum voltage during 20 min with average power of 265 W 0 min c 20V minimum voltage with no current for indefinite time 4 4 3 Safety BAT 135 4300 A The battery shall be designed in order to avoid any hazard once the battery is packaged BAT 136 4302 A The battery shall be designed in order to include an on ground protection on the top side of the battery to avoid any electrical hazard once the battery is packaged The design of this protection shall be submitted to prime for approval with Mechanical ICD The protection is for on ground operation only and will not be submitted to Thermal vacuum and vibration 4 4
18. f 27 AstroSAT 500 51 3052 T R The battery shall be able to withstand an abnormal charge current of 37 5 A during 100 ms fifty times in life time whatever the battery SOC is 3 2 3 Protections 53 3055 Double insulation shall be implemented order to avoid any short circuit including connectors case of single failure 3 2 4 Battery voltage range 55 3060 T R The battery voltage range shall be between 24 V and 34 V when used according to sections 3 2 1 to 3 2 3 The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 12 of 27 AstroSAT 500 4 UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS 4 1 Mechanical Design and Interface Requirements 4 1 1 Mass 59 4015 The overall battery mass flight configuration shall be lt 20 8 kg without interconnecting harness This shall be verified by mass measurement on the fully assembled unit 4 1 2 Centre of Gravity BAT 61 4020 T A The Centre of Gravity w r t the unit reference hole shall be provided This shall be derived from a CoG measurement on the fully assembled unit 4 1 3 Envelope BAT 63 4025 T The battery including mounting feet and connectors shall not exceed the following dimens
19. ic levels are specified Severity scale BAT 116 4175 A The failure modes and effects analysis of the battery shall consider the following severity scale The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 17 of 27 AstroSAT 500 1 Failure propagation outside the battery power bus 2 Degradation of the battery functions a n a b n a c n a d Availability target not respected outages on occurrence of transient phenomenon e Degradation of the battery performances sensors 3 Effect leading to minor impact on the mission latent failure on protection devices 4 Effect without any operational impacts telemetry not used for operate the battery 4 4 2 4 Design rules BAT 118 4180 The battery strings shall be physically separated no string failure shall propagate to another string through thermal means BAT 119 4185 A The failures which are likely to propagate see definition shall be controlled which means either the failure is eliminated through redundancy or the unit is placed into a safe state in which the propagation is no longer active eControl through internal redundancy if the time for avoiding failure propagation is immediate eControl through h
20. ions Width x Depth x Height 295 mm x 355 mm x 180 mm This shall be verified by dimension measurement 4 2 Thermal Design and Interface Requirements 4 2 1 Heat Dissipation 66 4030 T R According to the energy and power cycle requirements of section 3 2 1 the battery dissipation shall not exceed the following range 10 0 C 15 lt lt 40 Max Dissipation averaged over one orbit 14W 9W 5 5W Max Dissipation averaged over the discharge 26 W 22W 16W Above figures shall be verified in frame of unit functional testing with an accuracy of the measured value of better than 596 4 2 2 Unit Thermal Properties BAT 68 4035 R The battery shall not be allowed to exchange heat by radiation The battery shall be covered by Multi Layer Insulator MLI BAT 69 4040 R The battery heat exchange shall be done only by conduction through its base plate BAT 70 4045 R The battery base plate to satellite structure thermal conductivity will be better than 400 W C m TBC BAT 71 4050 R The battery thermal design shall assume a maximum temperature gradient of the base plate of 2 The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 Date 12 07 2010 Page 13 of 27 AstroSAT 500 4 2 3 Temperature Requirements
21. liability and availability 4 4 2 1 Reliability BAT 103 4155 A The probability of success full achievement of the battery functions and the related performances of the battery over 5 years shall be better than 0 99 considering the specified in orbit duty cycle and considering the nominal environment of the battery 4 4 2 2 Availability BAT 105 4160 T A The probability of occurrence of SEU whose effects lead to an outage of the main battery functions shall be less than 2 10 day the estimation shall take into account a minimum of 2 Solar flares during the 5 years in orbit 4 4 2 3 Failure modes analysis The objectives and the assumptions of the FMECA are described in the PA generic requirements section RAMS Failure propagation definition A failure occurring on a function Fa propagates on the function Fg when the failure on function F4 leads eTo stress the function Fg permanently with a level higher than the derating level eTo stress the function Fg temporarily with a level higher than the manufacturer rating physically damage the function pollution destruction The term permanently means that no action is initiated in order to control eliminate the failure The failure remains active at each switching on of the function BAT 114 4170 A For the electrical and thermal interfaces the levels to be respected in case of failure shall be the nominal levels specified in the technical specification unless specif
22. logy 1 2 Scope The document in hand comprises the contractually relevant requirements and constraints for the AstroSAT 500 battery This includes ethe performance as well as design and interface requirements of subject hardware ethe product assurance requirements ethe testing and verification requirements ethe verification method Verif method as one of the following R review of design l inspection A analysis T test S similarity D definition not be tracked 1 3 Guidelines Requirements within this document are shown in italic font Each requirement is preceded by a summary line that contains the following fields delimited by eDoors requirement number eRequirement number in the AstroSat 500 battery specification elntended Verification method 11 TR The Doors Requirement Number has the form BAT xxx yyy a b where xxx is a unique number assigned consecutively yyy is the requirement number in the AstroSat 500 specification and a b are the intended verification methods The Intended Verification Method codes are as follows eR Review eA Analysis el Inspection eT Test eS Similarity The requirement text follows the summary line If tables are considered as part of requirement they are referenced clearly in the text and inserted after and separated from the requirement and are managed as free text attached to the identifier requirement All document elements not presented in the format explained
23. m Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 AstroSAT 500 Date 12 07 2010 EADS di Page 26 of 27 DISTRIBUTION LIST Corporate use Project Limited Controlled Configured Document internal X X Classification Em AS250 Avionics Distribution AS250 Avionics Distribution BARADAT Pierre LEBREDONCHEL Jerome BILLIEN Jean Luc MARCILLE Herve X BONNEAU Celine MARTINEZ Alain CAZALS Serge X CHUPIN Stephane COSCULLUELA Valerie PALOUS Jean Claude DEFENDINI Ange POQUET GOURDON FOURNE Brigitte X PREVOT Sylvain GALLAND Philippe TABOUELLE Alain GENTY Patrick TEOFILI Fabrice GILLOT Bernard THIBAUD Pierre GUIONNET Pascal PENALVA Sonia X FAVREAU Michel AS250 Documentation LEBLOND Philippe AS250 Configuration manager X Astrium Product Policy Distribution Astrium AstroTerra Distribution BARABOTTI Laurent X ALARY S bastien X LEMERCIER Christophe X BELLEAU Patrick PITZ Wolfgang BORDE Jacques BOUSQUET Christophe Astrium MPC DAREL Anthony X ALCINDOR Peter X HAMEURY Olivier BALDWIN Robert PONCIN Thierry BARRIERE Jacques SIGUIER Michel BERTHELIER David VIVIER Jean Maurice CAMILLERI Stephane ASTROTERRA X DEBUS Volker ASTROTERRA Configuration JANVIER Michel OESTERLE Eduard The copyright in this document is the property of
24. onsumption BAT 79 4070 R The battery shall not require any primary power supply 4 3 2 Electrical Interface Description 4 3 2 1 Connectors 82 4075 The battery shall be equipped with connectors accordance with the following connector list The copyright in this document is the property of EADS ASTRIUM SAS and the contents may not be reproduced or revealed to third parties without prior permission of that company in writing EADS Astri um Ref LXO SP 00005 DT ASTR Issue 2 Rev 01 AstroSAT 500 Date 12 07 2010 Page 14 of 27 Connector number Connector type Connector function J01 Power Positive lines ESCC3401 001 J04 Power Negative lines ESCC3401 001 J02 D M 9P Heater supply ESCC3401 001 or 002 D M 25S Telemetries ESCC3401 001 or 002 Table 4 3 1 Connector List 4 3 2 2 Power interface BAT 86 4080 R The battery power interface shall consist of 10 AWG12 wires 5 positive lines 5 negative lines The wiring of both polarities lines shall be done to minimise as far as possible magnetic momentum For power interface J01 which includes more than 5 pins all the pins shall be externally connected to positive power lines BAT 732 4135 R The pin allocation shall be as in Table 4 3 2 Power Interface J01 Pins 1 2 3 4 5 6 7 8 Power Interface J04 Pins 1 2 3 4 5 Table 4 3 2 pin function available at power interface 734 4145 Deleted 87 4085
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