nickel-cadmium battery usage practices for space …

DOD-STD-1578B (USAF)01 JUN 1987

SUPERSEDINGDOD-STD-1 578A (USAF)31 MAY 1984

MILITARY STANDARD

NICKEL-CADMIUM BATTERY USAGE

PRACTICES FOR SPACE VEHICLES

NO DELIVERABLE DATA REQUIREDBY THIS DOCUMENT

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DEPARTMENT OF THE AIR FORCEWashington, D.C. 20330

Nickel-Cadmium Battery Usage Practices for Space Vehicles

DOD-STD-1578B (USAF)

1. This Military Standard is approved for use by theDepartment of the Air Force, and is available for use by allDepartments and Agencies of the Department of Defense.

2. Beneficial comments (recommendations, additions,deletions) and any pertinent data which may be of use inimproving this document should be addressed to:

USAF Space Division, SD/ALMP. O. BOX 92960Worldway Postal CenterLos Angeles, CA 90009-2960

by using the self-addressed Standardization Document ImprovementProposal (DD Form 1426) appearing at the end of this document orby letter.

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DOD-STD-1578B (USAF)01 JuN 1987

CONTENTS

1.0

1.11.2

2.0

3.0

3.13.23.33.43.53.63.73.83.93.103.113.123.133.143.153.163.173.18

4.0

4.1

4 .1.14.1.24.1.34.1.44.1.54.1.64.1.74.1.8

SCOPE .*.*..*.-*.,...**.......................● .....

Purpose ● .***.**.*● *..*****..*.*,,*..*...........Application.......................................

REFERENCED DOCUMENTS................................

DEFINITIONS ● ..● .● ● ...0.....*● *.............● *● ......

Battery...0...0.*..*.*,,..0.,.............00..0● .*Battery Capacity (C)...● ..● .● ...● *......● ● *......●

Battery Cell,0....0.....,***● .,****,,.,00..,,0,,0.Battery Conditioning Module.......................Battery Set...*.*.....0....● 0....0.....00.....0...Cell Activation....................,,00● ......0● ,*C/n Charge or Discharge Current...................Cold Storage.0....00.,..*.**.,...,.......*........Depth of Discharge................................Destructive Physical Analysis.....................High Rate Charge,.● .● .....**● ● *...● .....● .● .● ***● ●

Inert Storage..● *.....,...● O..,● ● .*● ..● .● ,,● ● ,..● .Quiescent Periods.................................Recharge Ratio.....00....*..*.. ..000.. . . . . ...0 ● ,..

Reconditioning..,.,● ● .,● .● ● ● ● .● .● O● ,..● ● ● .● ● .● ....Shorting Plug ● ● ...● ● ● ● .● ..● ..,..● *● ● ● . ● ● . ● . ● . . . . . ●

State of Charge .0 ,0.0.0 .. 0.,,., ,,, ...,, . ...0,.. ● ,*

Trickle Charge.....0..................00..........

GENERAL REQUIREMENTS..........● ........● ....● ● ● .....

Battery Storage and Handling......................

Storage.....o...................................Battery Discharge and Shorting..................Battery Conditioning Module.....................Shorting Plugs..................................Handling Fixture................................Terminal Cover..................................Connector Saver.....*....0..,.,● *.....*......,*.Shipment to Space Vehicle Fabrication andAssembly Site...0....● ,..*.**,0..,0.,● ,..*,*,,..

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11

2

3

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7788888

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CONTENTS (Continued)

Page

4.1.9

4.1.104.1.114.1.124.1.134,1.144.1.154.1.164.1.17

Conditioning Prior to Installation on Space.....Vehicle ......................................... 9Acceptance Testing of Space Vehicle........*.**c 9Transportation to Launch Site.........e”*.***.e” 9Quiescent Periods............................... 10Installed Battery Discharge and Shorting........ 10Cumulative Open Circuit Time.......*..***...... 10Reconditioning ● *● ..● *● ● *● ● ● ● ● ● ● ● *.*● ● ● *● ● *● *● ● *●

10Records......................................... 11Not for Flight Marking ● .● , ● . ● . . . ● ● .*. . . . ● . ● . . ● * ●

11

4.2 On-Orbit Operations............................... 11

4.2.14.2.24.2.34.2.44.2.54.2.64.2.74.2.84.2.94.2.104.2.11

Charge Control.00,..,.. ...00.. . . ...*** .0 .,.... . . 11Amount of Recharge.● .*● ..● ..● ● ● o.● ● .,.● ● .● ● ● .... 11Charge Current.....● .● ● *● ● ● ● .● .● ● o● ● ● .● ● .● ● ● ● ● *●

11.Trickle Charging................................ 12.

Reconditioning,..● ● ● ..● ● ,● .● ● . .** . ● . ● ● . ● , ● . . ● ● ● ●12

Quiescent Periods.***....● ,..000. . ..*.**. .00...0 12Depth of Discharge and Cycle Limits....o..o..... 12Temperature..................................... 12Overtemperature Backup Protection............... 12,Battery Monitoring.............................. 12Battery Isolation..........*....● ..**..● ● ..● *● ● *●

12

4.3 Development Testing..,.● ....● .*....*.s.● .● ....● ...● ●13

4.3.1 Charge Control Development...................... 134.3.2 Life Tests.,● *● .*.● ..● ***● *.● ● ● ,*● **.● *9*.● ● ● ● ● ●

134.3.3 Vehicle Thermal Vacuum Testing.................. 14

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DoD-sTD-1578B (USAF)01 J7JN1987

SECTION 1

SCOPE

1.1 PURPOSE

This standard establishes requirements for the storage,handling, and usage of nickel-cadmium batteries for spacevehicle applications. Compliance with this standard is intendedto assure proper performance of nickel-cadmium batteries and toprovide protection against preflight degradation and prematuredegradation during operational use on space vehicles.

1.2 APPLICATION

This standard is intended for reference in applicable spacevehicle specifications or other documents to incorporate commonrequirements and practices necessary to assure successfulnickel-cadmium battery operation during space missions.

1


DOD-STD-1578B (USAF)01 J(JN1987

SECTION 2

REFERENCED DOCUMENTS

(Not applicable)



SECTION 3

DEFINITIONS

3.1 BATTERY

A battery for use on space vehicles is an assembly ofbattery cells electrically connected in series to provide thedesired voltage. Generally, the cells are physically integratedinto either a single assembly or into several separateassemblies connected in series. The battery may also includeone or more attachments such as electrical bypass devices,heaters, strain gauges, temperature sensors, or thermal switches.

3“2 ~

The “nameplate” or “rated” nickel-cadmium battery capacityis denoted by C. It is the minimum number of ampere-hours thata battery, that has been charged at C/10 amperes for 16 A 2hours, is required to provide when discharged at C/2 amperes toan average cell voltage of 1.0 volts, at beginning of life(initial battery acceptance test), Both the C/10 charge and theC/2 discharge are with the battery at a stabilized ambienttemperature of 22 ~ 3 degrees C.

3.3 J3ATTERYCELL

A battery cell is a single unit device that transformschemical energy into electrical energy at a characteristicvoltage when discharged. Battery cells covered by this standardare hermetically sealed, contain nickel and cadmium electrodes,and have passed formal acceptance test requirements.

3.4 BATTERY CONDITIONING MODULE

A battery conditioning module is a ground support apparatusthat performs the function of discharging a battery, through thebattery main power connectors, or discharging individual batterycells, through a wiring harness connected to each of the batterycell terminals, at specified controlled discharge currents. Anumber of battery conditioning modules currently in use have thebattery discharging as well as the charging function packaged ina single unit.



3.5 BATTERY SET

A battery set is the complete complement of two or morenickel-cadmium batteries installed in the same space vehicle.

3.6 CELL ACTIVATION

The addition of potassium hydroxide (KOH) electrolyte to thenickel cadmium cell during final assembly and test constitutescell activation.

The charge or discharge current for a battery is defined asC/n amperes where C is the rated battery capacity inampere-hours and n is any value for elapsed time measured inhours. For example, a discharge current of C/2 for a 16ampere-hour rated battery is a discharge current of 8 amperes.

3.8 COLD STORAGE

Cold storage for nickel-cadmium batteries that are not inuse is long term storage where the temperature environment iscontrolled between -10 degrees C and +5 degrees C.

3.9 DEPTH OF DISCHlil@Z

The depth of discharge for a battery that has been chargedat least to its rated capacity (C) is the ratio of capacityremoved during discharge to the rated battery capacity (C)expressed as a percentage.

3.10 DESTRUCTIVE PHYSICAL ANALYSIS

Destructive physical analysis of a battery cell is asystematic, logical, detailed examination of the cell, includingexamination and measurement during various stages of physicaldisassembly, and subsequent chemical, electrochemical, andmetallurgical analysis.

3.11 JIIGHRATE CHAR~

A high rate charge current is the current sequence used torecharge a battery to its rated capacity.

4



3.12 JNERT STORAGE

Inert storage is the maintenance of items, such aselectrodes or inactivated cells, in a sealed chamber containingan inert atmosphere such as dry nitrogen. Usually an inert gaspressurizing system is used to maintain a positive pressure ofapproximately +125 millimeters vertical water column aboveambient conditions. If an adequate purge is not provided, theseal integrity may be the most important feature, since thepartial pressure of water vapor, or other contaminants, acrossthe seal is independent of the internal pressure of the inertgas.

3.13 CENT PJ?RIOD~

Quiescent periods are the periods of time during eitherground or on-orbit operations that a charged battery is not inactive use, that is, it is not being discharged or rechargedexcept for possible trickle charge.

3.14 RECHARGE

The recharge ratio for a battery is the number ofampere-hours returned to the battery by high rate charging,exclusive of trickle charge, divided by the number ofampere-hours removed from the battery during the precedingdischarge.

3.15 RECONDITIONI~

Reconditioning of a nickel-cadmium battery is adischarge-charge sequence intended to minimize degradation ofthe battery electrical performance. The process involves thedischarge of the battery at a C/100 rate or less, to an averagecell voltage of 1.0 volts or less. The subsequent chargingprocess should be sufficient to restore the rated, or actualmeasured capacity, whichever is greater, and to compensate forcharge inefficiency.

3.16 iWORTING PLUG

A shorting plug is a device that provides a current pathacross the terminals of each individual cell of a fullydischarged nickel-cadmium battery in order to finally dischargeall battery cells and maintain a shorted condition at the celllevel. Shorting plugs are generally connected to anintermediate mating connector mounted on the battery case, or onthe space vehicle structure, where the intermediate connectorleads form a wiring harness that is in turn connected to each ofthe battery cell terminals.

5



3.17 STATE OF CHARGE

The state of charge of a battery that has been charged atleast to its rated capacity, is the ratio of the rated batterycapacity (C) minus capacity removed~ to the rated batterycapacity (C), expressed as a percentage. Thus, the state ofcharge is 100 percent minus the depth of discharge.

3.18 TRICKLE CHARGE

A trickle charge current is a low rate charging currentusually used following a significantly higher charge current tooffset open circuit stand losses that would occur in the absenceof the lower rate trickle charge current.

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SECTION 4

GENERAL REQUIREMENTS

4.1 BATTERY STORAGE AND HANDLING

The requirements set forth in this section and subsequentsubsections, apply to the storage, handling, and operation ofnickel-cadmium batteries during ground activities precedinglaunch. The organization of requirements generally follows thechronological order of events normally expected to occur frombattery fabrication through launch.

Where practicable, inert storage for electrodes andinactivated cells shall be utilized prior to battery assembly,to minimize degradation, Following completion of assembly,batteries for operational use on a space vehicle shallsuccessfully complete acceptance testing and then either beprepared for installation on the space vehicle or placed in acold storage facility. Storage, handling, and conditioningshall be in accordance with practices that minimize preflightdegradation.

4.1.1 Storaa~ Nickel-cadmium batteries that are not inuse shall be place~ in cold storage, whenever practicable, in afully discharged state and shorted at the battery cell levelwith shorting plugs. Cold storage temperatures shall bemaintained between -10 degrees C and +5 degrees C. In noinstance shall a battery that is not in use remain outside ofcold storage for a period exceeding 45 days.

Batteries not in use and not in cold storage, shall bestored inside a building under a controlled temperatureenvironment between -10 degrees C and +25 degrees C, andwhenever practicable, maintained in a fully discharged state andshorted at the battery cell level with shorting plugs.

Even if properly stored, batteries shall not be used forflight if the time between battery cell activation and launchexceeds three years (1095 days).

4.1.2 Battery Dzscharue. and Shortinq. The discharge ofnickel-cadmium batteries to accommodate periods of nonuse, shallbe accomplished with a battery conditioning module at the rateof C/10 amperes, or less, until 1.0 volt is achieved by any onecell, and then each cell discharged to a state of charge lowenough to prevent cell voltage recovery from occurring prior to

7


DOD-STD-1578B (USAF)01 JuN 1987

the installation of shortingbe used for the purpose ofacross the terminals of eachmaintained at 22 ~ 3 degreesprocess.

plugs, Shorting plugs shall thenmaintaining a shorted conditionbattery cell. The battery shall beC during the discharge and shorting

4.1.3 Batterv Conditioning Modul& A batteryconditioning module shall be used as sp~cified herein todischarge-a battery or individual battery cells at specifiedcontrol rates. As a safety feature, devices shall beincorporated in the design of battery conditioning modules toaccommodate the discharge of any battery charge, up to ratedcapacity, without causing any damage to the battery or spacevehicle, including the prevention of any battery cell voltagereversals.

4.1.4 .ortxna Pw . Shorting plugs shall be used asspecified herein to maintain a shorted condition across theterminals of each individual nickel-cadmium battery cell. As asafety feature, shorting plugs shall be designed to accommodatean inadvertent connection to a charged battery, up to its ratedcapacity, without causing any damage to any component of thebattery or to the space vehicle. Shorting plugs shall also bedesigned to prevent any battery cell voltage reversals. Toimplement these safety features, shorting plugs shallincorporate heat dissipating resistors fusesf circuit breakers~resistors, fuseable links, combinations of these, or othercomponents. The design shall provide a means for verifying thatany fuses or fuseable links have not opened, and that circuitbreakers are in their correct positions.

4.1.5 Fixture.nu A handling plate shall be usedafter the battery is assembl~d and prior to installation of thebattery on the space vehicle. The handling plate shall protectfrom damage the battery bottom and any other structural orthermal interface of the battery with the space vehicle. Thehandling plate shall be removed when the battery is installed onthe space vehicle.

4.1.6 Terminal Cover An easily attachable and removableplastic cover shall prote& the battery’s terminal side afterits assembly until just prior to its installation on the spacevehicle. Optionally, the cover may remain in place for some orall of the space vehicle launch preparation, but shall beremoved prior to launch.

4.1.7during allvehicle to

Co nectorn Sa ver. A connector saver shall be usedtesting prior to battery installation on the spaceavoid repeated connecting and disconnecting of the

8


DoD-sTD-1578B (USAF)01 JUN 1987

flight connector. The connector saver shall interface betweenthe battery flight connectors and any mating test or groundsupport equipment cables. The connector saver shall be removedjust before storage or space vehicle installation.

4.1.8 Shi~ment to Space Vehicle Fabrication and AssemblyS&2. Nickel-cadmium batteries shall be transported from thebattery manufacturers factory location to the space vehiclefabrication and assembly site in a fully discharged state andshorted at the battery cell level with shorting plugs.Batteries shall be maintained between -10 degrees C and +25degrees C during handling and transportation.

4.1.9 Condltlo. . ninu Prior to Installation On Space Vehicle.A battery conditioning module shall be used to initiallycondition a nickel-cadmium battery after removal from coldstorage. The battery shall be charged at the rate of C/20amperes for 40 k 4 hours, and then discharged at the rate of C/2amperes, or less, until 1.0 volt is achieved by any one batterycell. Each battery cell shall then be fully discharged until aspecified low level cell voltage is attained (usually a valuebetween 10 and 100 millivolts per cell). The batterytemperature shall be maintained at 22 A 3 degrees C during theinitial conditioning process.

Before the installation of a nickel-cadmium battery on aspace vehicle is allowed to proceed, the battery must undergoone or more operational charge-discharge cycles to verify thecapability of meeting battery specification operating andcapacity requirements. With the use of a battery conditioningmodule, the battery shall be charged at the rate of C/10amperes, and then discharged at the rate of C/2 amperes, until aspecified cell voltage is achieved (generally about 1.0 volt percell). The battery temperature shall be maintained at 22 ~ 3degrees C during operational charge-discharge cycling.

4.1.10 Acceptance Testlna. of *Qace Vehicle To maximizeon-orbit performance, the actual batteries to be ~sed for flightshall not be installed or used for space vehicle levelintegration or acceptance tests at the space vehicle fabricationand assembly site, except as may be necessary for nonoperationaltests such as spin balance. Test batteries that are equivalentin configuration to the flight batteries, and that have passedbattery flight level acceptance tests, shall be used for spacevehicle level integration and acceptance testing.

4.1.11 Transnortation to Launch Site. Flight batteriesmay be installed in the space vehicle before it is shipped tothe launch site or they may be shipped separately and installed

9



at the launch site. In either case, the batteries shall beshipped in a fully discharged state and shorted at the celllevel with shorting plugs. Vibration and shock loads duringhandling, transportation and installation shall not exceed thelevels specified in the detailed battery specification.Batteries shall be maintained between -10 degrees C and +25degrees C, if it is practicable to do so, during handling,transportation and installation. In no case shall the uppertemperature limit for a battery exceed +30 degrees C duringhandling, transportation and installation, The batterytemperature environment shall be continually monitored andrecorded during transportation.

4.1.12 Quiescent Perio~ During ground operationquiescent periods, a nickel-cad~ium battery installed on a spacevehicle shall be maintained in the trickle charged or the fullydischarged and shorted at the cell level condition wheneverpracticable. The quiescent time period when a charged batteryis open circuited shall be minimized in number and duration. Inno case shall quiescent periods exceed 96 hours for a chargedbattery without initiating trickle charging or discharging thebattery and shorting each individual cell. Battery temperaturesshall be maintained between -10 degrees C and +25 degrees Cduring quiescent periods.

4.1.13 tailed Battery Dlscharae &. Short=. Thedischarge of nickel-cadmium batteries installed on a“ spacevehicle to accommodate quiescent periods during groundoperations, shall “be accomplished with a battery conditioningmodule at a specified rate not to exceed C/2 amperes, until anyone battery cell reaches 1.0 volt, and then each battery celldischarged to a state of charge low enough to prevent cellvoltage recovery from occurring prior to the installation ofshorting plugs. Shorting plugs shall then be used for thepurpose of maintaining a shorted condition across the terminalsof each battery cell. The battery shall be maintained at 22 A 3degrees C during the discharge and shorting process.

4.1.14 ●~e. The number andduration of periods when a nickel-cadmium battery is opencircuited shall be minimized when the battery is not in use orquiescent, The total open circuit time accumulated on a flightbattery during nonuse and quiescent periods shall not exceed 20days during ground operations.

4.1.15 Reconditioning. Flight batteries that are not instorage shall be reconditioned every 45 A 3 days. For spacevehicles launched by an expendable launch vehicle, the flightbatteries shall be reconditioned within the 30 day period

10


_ _


immediately preceding the launch. For space vehicles launchedby the Space Transportation System, the flight batteries shallbe reconditioned within the 30 day period immediately precedingspace vehicle placement into the cargo bay.

4.1.16 RecordS. Records documenting the flightaccreditation status of batteries shall be maintained. Theserecords shall provide traceability from production of thebattery, through final installation in the space vehicle, and onthrough to launch. The records shall indicate changes inbattery location, status, use, or any conditions that couldaffect reliability or performance. Time-correlated recordsshall be maintained indicating battery charge or dischargecurrent, battery voltage, and temperature to a sufficientaccuracy to allow an assessment of potential degradation.

4.1.17 Not for Flzaht. Marking Batteries, the cells ofwhich have been activated over thr~e years (1095 days), orwhich by intent, by usage, or by material disposition are notsuitable for use in flight, and which could be accidentallysubstituted for flight or flight spare hardware, shall be redtagged or striped with red paint, or both, to prevent suchsubstitution. The red tag shall be conspicuous and marked “NOTFOR FLIGHT.” The red paint shall be material compatible and thestripes unmistakable.

4.2. ON-ORBIT OPERATIO~

4.2.1 ~. Normal battery charging andcontrol procedures, and contingency procedures, shall beprepared based upon test data obtained during vehicle andbattery development testing (see 4.3) and the requirementsstated herein. These documented procedures shall be the basisfor battery operations and controls while on orbit.

4.2.2 ~. High rate battery chargingshall be controlled so as to return the amount of capacity whichhas been discharged plus an additional amount to compensate forcharge inefficiency. Provisions shall exist for increasing andfor decreasing the recharge ratio automatically, by groundcommand, or both.

4.2.3 ~. Charge current shall be regulatedconsistent with battery operating temperature, battery chargevoltage limits, time available for recharging, and chargingsource capability, Overcharging at a high rate shall beminimized.

11



4.2.4 ~ raing. When the amount of rechargerequirements have been satisfied, battery charging is consideredcomplete and the battery shall be maintained in trickle chargeuntil its next discharge, orbit permitting. The trickle chargecurrent shall be at a rate sufficient to maintain the capacityachieved by the high rate charging.

4.2.5 Reconditioning. Reconditioning shall be performedperiodically, orbit permitting, from the onset of the mission.For space vehicles in geosynchronous orbits, reconditioningshall be performed prior to every eclipse season, once the spacevehicle is on station. For space vehicles in other orbits,reconditioning shall be performed on a regular basis, dependingupon orbit.

4.2.6 g~S . . During on-orbit quiescentperiods, the battery shall be trickle charged, orbitpermitting. The trickle charge current shall be at a ratesufficient to maintain the existing battery capacity.

4.2.7 ~. .i . Battery depth

of discharge and number of cycles during the mission shall be nogreater than warranted by available data germane to the batterydesign and the mission. The number of cycles is defined as thenumber of charge-discharge sequences predicted for eclipse andother operations during the complete orbital lifetime.

4.2.8 YemDerature. Battery temperatures throughout theorbital lifetime shall be maintained in the range O degrees C to+10 degrees C, with excursions beyond these limits minimized.

4.2.9 gvertemu~ ture Backup Protectlo~. Backupprotection against battery overheating shall be “providedin theform of switching that reduces or terminatescharging. Chargecurrent to a battery shall be automatically reduced orterminated if the temperature of that battery reaches +32degrees C.

4.2.10 Batterv Monitoring Battery voltage, includingindividual cell voltage, curre~t, and temperature shall bemonitored periodically during flight, including during batteryreconditioning and eclipse operations. These data, togetherwith depth of discharge performance shall be summarized andevaluated to provide performance predictions for on-orbitoperations.

4.2.11 Batterv Isolation. If on-orbit conditionswarrant, either the battery charge circuits, or the spacevehicle load circuits, or both, shall be switched by command toprovide electrical isolation from the battery.

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DoD-sTD-1578B (USAF)01 JUN 1987

4.3. Pm LOPMENT TESTING

Development testing shall be conducted on new batterydesigns for each application. Development testing shall also beconducted on existing battery designs for each new supplier, foreach new application, and when changes are incorporated. Thedevelopment tests specified herein are not inclusive of alltests that should be conducted during battery and space vehicledevelopment, but the tests that are included in this standardhave a close relationship to battery usage practices. Thefollowing development tests shall be conducted to evaluate thebatteries under the operating conditions that will exist whenredundant batteries in the battery set have failed and beenremoved from the circuit, as well as in the no failure case.

4.3.1 ntrol Development. Testing of the batteryshall be performed to determine the minimum recharge ratio thatwill provide a full charge under the conditions of intendedoperational use in the space vehicle. Control parameters to beused, such as battery voltage and battery temperature, shall becharacterized for a flight-type battery sufficiently to permit acharge control design that will meet the requirements forvehicle operations including contingencies. Third electrodecells, coulomb meter cells, or a single temperature set pointshall not be used as the basis for primary charge control.

4.3.2 Life Testi. Life testing is intended to developand demonstrate the required charge control procedures to ensurenecessary battery orbital lifetime. Real time life tests shallbe performed on a sufficient number of battery cells to permitannual removal of at least one cell from the life test group fordestructive physical analysis over the duration of the real timelife test. The number of cells in the life test group shall besufficiently large so that all of the cells are not sacrificedto destructive physical analysis during the test period. Thedestructive physical analysis data shall be used to evaluatebattery cell degradation with time and usage and to predict celldegradation as a function of mission duration. Life tests shallalso be performed on previously acceptance tested, flight-typebatteries operating under the electrical and environmentalconditions expected during operational use in the spacevehicle. Battery temperatures shall be measured at intervalsadequate to characterize the battery thermal profile for themission. These tests shall demonstrate that flight batteriescan meet their on-orbit performance requirements for therequired mission life. These tests shall accurately simulatecharge and discharge periods and reconditioning shall beincluded as planned for the mission.

13



4.3.3 Vehicle Therms1 Vacuu Testznq. . Flight typebatteries shall be installed and o~erated during space vehiclethermal vacuum testing. Temperatures on and around thebatteries shall be monitored during the thermal cycling of thevehicle such that analytical simulations of battery heattransfer can be validated. These tests may be conducted as partof the vehicle thermal balance testing or vehicle qualificationtesting.

Custodian:Air Force - 19

Preparing Activity:Air Force - 19

(Project No. 1820-F017)(Dec. 1429b, Arch. 1212b)

14


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