1、DOD-s-D57TB 38 7777733 0338b2 5 W- distribution unlimited. . THIS DOCUMENT CONTAINS 1% PAGES. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-1578B LB 9 77777LL 0033863 7 - DOD-STD-1578B (USAF) O1 JUN 1987 DEPARTMENT OF THE AIR.FORCE Washingt
2、on, D.C. 20330 Nickel-Cadmium Battery Usage Practices for Space Vehicles DOD-STD-1578B (USAF) 1. This Military Standard is approved for use by the Department of the Air Force, and is available for use by all Departments and Agencies of the Department of Defense. 2. Beneficial comments (recommendatio
3、ns, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: USAF Space Division, SD/ALM P. O. Box 92960 Worldway Postal Center Los Angeles, CA 90009-2960 by using the self-addressed Standardization Document Improvement Proposal (DD Form 142
4、6) appearing at the end of this document or by letter. ii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. 8 DOD-STD-1578B (USAF) O1 JUN 1987 CONTENTS Page 1.0 SCOPE 1 1.1 Purpose 1 1.2 Application 1 . . . 2.0 REFERENCED DOC.NTS 2 3.0 DEFINITIONS 3
5、. 3.1 3.2 3.3 3.4 3.5 3.6 3.7 3.8 3.9 3.10 3.11 3.12 3.13 3.14 3.15 3.16 3.17 3.18 Battery . Battery Capacity (C) Battery Cell Battery Conditioning Module . Battery Set . Cell Activation . C/n Charge or Discharge Current . Cold Storage Depth of Discharge High Rate Charge Inert Storage . Quiescent Pe
6、riods . Recharge Ratio Reconditioning Shorting Plug . State of Charge . Trickle Charge Destructive Physical Analysis . 4.0 GENERAL REQUIRE3ENTS 4.1 Battery Storage and Handling 4.1.1 4.1.2 4.1.3 4.1.4 4.1.5 4.1.6 4.1.7 4.1.8 Storage . Battery Discharge and Shorting Battery Conditioning Module . Shor
7、ting Plugs Handling Fixture Terminal Cover Connector Saver . Shipment to Space Vehicle Fabrication and Assembly Site . 3 3 3 3 4 4 4 4 4 4 4 5 5 5 5 5 6 6 7 7 9 iii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-1578B (USAE) OX JN 1987 CONTE
8、NTS (Continued) Page Conditioning Prior to Installation on Space . .Vehicle . 9 4.1.9 4.1.10 Acceptance Testing of Space Vehicle . 9 4.1.11 Transportation to Launch Site . 9 4.1.14 Cumulative Open Circuit Time . 10 4.1.15 Reconditioning 10 4.1.17 Not for Flight Marking 11 4.1.12 Quiescent Periods .
9、10 4.1.13 Installed Battery Discharge and Shorting 10 4.1.16 Records . 11 4.2 On-Orbit Operations . 11 4.2.1 4.2.2 4.2.3 4.2.4 4.2.5 4.2.6 4.2.7 4.2.8 4.2.9 4.2.10 4.2.11 Charge control 11 Amount of Recharge 11 Charge Current 11 Trickle Charging 12 Reconditioning 12 Quiescent Periods . 12 Depth of D
10、ischarge and Cycle Limits . 12 Temperature . 12 Overtemperature Backup Protection . 12 Battery Monitoring 12 Battery Isolation . 12 4.3 Development Testing . 13 4.3.1 Charge Control Development 13 4.3.2 Life Tests 13 4.3.3 Vehicle Thermal Vacuum Testing 14 . J iv a Provided by IHSNot for ResaleNo re
11、production or networking permitted without license from IHS-,-,-DOD-STD-3578B 38 m 7779933 0033866 2 m DOD-STD-1578B (USAF) O1 JUN 1987 SECTION 1 SCOPE 1.1 PURPOSE This standard establishes requirements for the storage, handling, and usage of nickel-cadmium batteries for space vehicle applications.
12、Compliance with this standard is intended to assure proper performance of nickel-cadmium batteries and to provide protection against preflight degradation and premature degradation during operational use on space vehicles. 1.2 APPLICATION This standard is intended for reference in applicable space v
13、ehicle specifications or other documents to incorporate common requirements and practices necessary to assure successful nickel-cadmium battery operation during space missions. 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-1578B (USAI?) O
14、1 JUN 1987 SECTION 2 REFERENCED DOCUMENTS (Not applicable) 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-3578B 38 m 3779733 0033868 b , DOD-STD-1578B (USAI?) O1 JUN 1987 SECTION 3 DEFINITIONS 3.1 BATTERY A battery for use on space vehicle
15、s is an assembly of battery cells electrically connected in series to provide the desired voltage. Generally, the cells are physically integrated into either a single assembly or into several separate assemblies connected in series. The battery may also include one or more attachments such as electr
16、ical bypass devices, heaters, strain gauges, temperature sensors, or thermal switches. 3.2 BATTERY CAPACITY (C) The “nameplate“ or “rated“ nickel-cadmium battery capacity is denoted by C. It is the minimum number of ampere-hours that a battery, that has been charged at C/10 amperes for 16 f. 2 hours
17、, is required to provide when discharged at C/2 amperes to an average cell voltage of 1.0 volts, at beginning of life (initial battery acceptance test). Both the C/10 charge and the C/2 discharge are with the battery at a stabilized ambient O temperature of 22 3 degrees C. 3.3 BATTERY CELL A battery
18、 cell is a single unit device that transforms chemical energy into electrical energy at a characteristic voltage when discharged. Battery cells covered by this standard are hermetically sealed, contain nickel and cadmium electrodes, and have passed formal acceptancs test requirements. 3.4 BATTERY CO
19、NDITIONING MODULE A battery conditioning module is a ground support apparatus that performs the function of discharging a battery, through the battery main power connectors, or discharging individual battery cells, through a wiring harness connected to each of the battery cell terminals, at specifie
20、d controlled discharge currents. A number of battery conditioning modules currently in use have the battery discharging as well as the charging function packaged in a single unit. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-1578B (USAF)
21、 O1 JUN 1987 3.5 BATTERY SET A battery set is the complete complement of two or more nickel-cadmium batteries installed in the same space vehicle. 3.6 CELL ACTIVATION The addition of potassium hydroxide (KOH) electrolyte to the nickel cadmium cell during final assembly and test constitutes cell acti
22、vation. 3.7 C/n CHARGE OR DISCHARGE CURRENT The charge or discharge current for a battery is defined as C/n amperes where C is the rated battery capacity in ampere-hours and n is any value for elapsed time measured in hours. For example, a discharge current of C/2 for a 16 ampere-hour rated battery
23、is a discharge current of 8 amperes. 3.8 COLD STORAGE Cold storage for nickel-cadmium batteries that are not in use is long term storage where the temperature environment is controlled between -10 degrees C and +5 degrees C. 3.9 DEPTH OF DISCHARGE The depth of discharge for a battery that has been c
24、harged at least to its rated capacity (C) is the ratio of capacity removed 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 a systematic, logical, detailed examination of the cell, incl
25、uding examination and measurement during various stages of physical disassembly, and subsequent chemical, electrochemical, and metallurgical analysis. 3.11 HIGH RATE CHARGE A high rate charge current is the current sequence used to recharge a battery to its rated capacity. 4 Provided by IHSNot for R
26、esaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-157B 18 = 7777711 0031870 LI M DOD-STD-1578B (USAF) O1 J“ 1987 3.12 INERT STORAGE Inert storage is he maintenance of i-ems, such as electrodes or unactivated cells, in a sealed chamber containing an inert atmosphere su
27、ch as dry nitrogen. Usually an inert gas pressurizing system is used to maintain a positive pressure of approximately +125 millimeters vertical water column above ambient conditions. If an adequate purge is not provided, the seal integrity may be the most important feature, since the partial pressur
28、e of water vapor, or other contaminants, across the seal is independent of the internal pressure of the inert gas. 3.13 QUIESCENT PERIODS Quiescent periods are the periods of time during either ground or on-orbit operations that a charged battery is not in active use, that is, it is not being discha
29、rged or recharged except for possible trickle charge. 3.14 RECHARGE RATIO The recharge ratio for a battery is the number of ampere-hours returned to the battery by high rate charging, exclusive of trickle charge, divided by the number of ampere-hours removed from the battery during the preceding dis
30、charge. 3.15 RECONDITIONING Reconditioning of a nickel-cadmium battery is a discharge-charge sequence intended to minimize degradation of the battery electrical performance. The process involves the discharge of the battery at a C/100 rate or less, to an average cell voltage of 1.0 volts or less. Th
31、e subsequent charging process should be sufficient to restore the rated, or actual measured capacity, whichever is greater, and to conpensate for charge inefficiency. 3.16 SHORTING PLUG A shorting plug is a device that provides a current path across the terminals of each individual cell of a fully d
32、ischarged nickel-cadmium battery in order to finally discharge all .battery cells and maintain a shorted condition at the cell level. Shorting plugs are generally connected to an intermediate mating connector mounted on the battery case, or on the space vehicle structure, where the intermediate conn
33、ector leads form a wiring harness that is in turn connected to each of the battery cell terminals. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-1578B (USAF) O1 JUN 1987 3.17 STATE OF CHARGE The state of charge of a battery that has been
34、charged at least to its rated capacity, is the ratio of the rated battery capacity (C) minus capacity removed, to the rated battery capacity (C), expressed as a percentage. Thus, the state of charge is 100 percent minus the depth of discharge. 3.18 TRICKLE CHARGE A trickle charge current is a low ra
35、te charging current usually used following a significantly higher charge current to offset open circuit stand losses that would occur in the absence of the lower rate trickle charge current. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-3
36、578B 38 m 7777733 0033872 8 m DOD-STD-1578B (USAI?) O1 JUN 1987 SECTION 4 GENERAL REQUIREMENTS 4.1 BATTERY STORAGE AND HANDLING The requirements set forth in this section and subsequent subsections, apply to the storage, handling, and operation of nickel-cadmium batteries during ground activities pr
37、eceding launch. The organization of requirements generally follows the chronological order of events normally expected to occur from battery fabrication through launch. Where practicable, inert storage for electrodes and unactivated cells shall be utilized prior to battery assembly, to minimize degr
38、adation. Following completion of assembly, batteries for operational use on a space vehicle shall successfully complete acceptance testing and then either be prepared for installation on the space vehicle or placed in a cold storage facility. Storage, handling, and conditioning shall be in accordanc
39、e with practices that minimize preflight degradation. use shall be placed in cold storage, whenever practicable, in a fully discharged state and shorted at the battery cell level with shorting plugs. Cold storage temperatures shall be maintained between -10 degrees C and +5 degrees C. In no instance
40、 shall a battery that is not in use remain outside of cold storage for a period exceeding 45 days. 4.1.1 Storaue. Nickel-cadmium batteries that are not in Batteries not in use and not in cold storage, shall be stored inside a building under a controlled temperature environment between -10 degrees C
41、and +25 degrees C, and whenever practicable, maintained in a fully discharged state and shorted at the battery cell level with shorting plugs. Even if properly stored, batteries shall not be used for flight if the time between battery cell activation and launch exceeds three years (1095 days). nicke
42、l-cadmium batteries to accommodate periods of nonuse, shall be accomplished with a battery conditioning module at the rate of C/10 amperes, or less, until 1.0 volt is achieved by any one cell, and then each cell discharged to a state of charge low enough to prevent cell voltage recovery from occurri
43、ng prior to 4.1.2 Batterv Discharue and Shortinq. The discharge of a 7 I- # Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DOD-STD-1578B (USAF) O1 JN 1987 the installation of shorting plugs. Shorting plugs shall then be used for the purpose of maint
44、aining a shorted condition across the terminals of each battery cell. The battery shall be maintained at 22 f 3 degrees C during the discharge and shorting process. 4.1.3 Battery Conditionina Module. A battery conditioning module shall be used as specified herein to discharge a battery or individual
45、 battery cells at specified control rates. As a safety feature, devices shall be incorporated in the design of battery conditioning modules to accommodate the discharge of any battery charge, up to rated capacity, without causing any damage to the battery or space vehicle, including the prevention o
46、f any battery cell voltage reversals. 4.1.4 Shortina Pluas. Shorting plugs shall be used as specified herein to maintain a shorted condition across the terminals of each individual nickel-cadmium battery cell. As a safety feature, shorting plugs shall be designed to accommodate an inadvertent connec
47、tion to a charged battery, up to its rated capacity, without causing any damage to any component of the battery or to the space vehicle. Shorting plugs shall also be designed to prevent any battery cell voltage reversals. To implement these safety features, shorting plugs shall incorporate heat diss
48、ipating resistors, fuses, circuit breakers, resistors, fuseable links, combinations of these, or other components. The design shall provide a means for verifying that any fuses or fuseable links have not opened, and that circuit breakers are in their correct positions. 4.1.5 Handlinq Fixture. A hand
49、ling plate shall be used after the battery is assembled and prior to installation of the battery on the space vehicle. The handling plate shall protect from damage the battery bottom and any other structural or thermal interface of the battery with the space vehicle. The handling plate shall be removed when the battery is installed on the space vehicle.
