Satellite battery reconditioning system and method

• US 3,997,830 A
• Filed: 11/27/1974
• Issued: 12/14/1976
• Est. Priority Date: 11/27/1974
• Status: Expired due to Term

• Current Assignee: RCA Corporation
• Original Assignee: RCA Corporation
• Inventors: Bacher, Joel Herman, Newell, Richard Abbott, Callen, Patrick Joseph, Bilsky, Herbert Walter
• Primary Examiner(s): Miller. J D
• Assistant Examiner(s): Hickey, Robert J.
• Application Number:
  US05/527,835
• Time in Patent Office: 748 Days
• Field of Search: 320/2-5, 320/13, 320/31, 320/14, 320/15, 320/9, 320/35, 320/20, 320/39, 320/40, 320/48, 320/22, 244/173
• US Class Current: 320/102
• CPC Class Codes: B64G 1/425 Power storage
• CPC Class Codes: B64G 1/428 Power distribution and management
• CPC Class Codes: B64G 1/443 Photovoltaic cell arrays
• CPC Class Codes: H01M 10/44 Methods for charging or discharging circuits for charging H02J7/00
• CPC Class Codes: H02J 7/35 with light sensitive cells
• CPC Class Codes: Y02E 60/10 Energy storage using batteries
• CPC Class Codes: Y10S 320/16 Removal of memory effect in batteries

Abstract

Reduction of battery effectiveness due to memory effect and unequal cell voltages is minimized by a spacecraft power control system which reconditions the battery preferably just prior to eclipse seasons of a geo-stationary orbit by discharging each battery cell through a network of shunting resistors. Recharging is accomplished by a low power dissipation charging sequence. The load of the system, except for during the eclipse season, is receiving power continuously from the solar cells and during peak load requirements receives supplementary power from the battery cells. During the eclipse seasons, the system power is supplied solely by the battery cells.

Claims

1. A system for reconditioning a secondary battery in a space vehicle, said vehicle having a solar array source of charging current comprising:

a secondary battery having a plurality of cells, a plurality of resistance networks each of said networks comprising a pair of substantially equal resistors wherein each of said networks is associated with a respective one of each of said cells,

relay switch means for connecting one of said networks in shunt across its associated cell of said battery,

temperature sensitive means for detecting the voltage of said battery and providing a control signal manifesting said battery voltage as a function of the temperature of said battery,

means for regulating the flow of charging current from said solar array to said battery at a low charging rate,

signalling means for receiving and transmitting signals between said space vehicle and a ground command station,

means responsive to a signal from said signalling means manifesting a ground command for changing said regulating means to regulate the flow of charging current to a high charging rate, and

means responsive to said control signal from said temperature sensitive means for changing said regulating means to regulate automatically the flow of charging current to said said low charging rate as the voltage of said battery exceeds a critical value for a given temperature.

2. A system according to claim 1 wherein said temperature sensitive means includes a network of two resistors in series connected across said battery, and a thermistor connected across one of said resistors.

3. A system according to claim 1 wherein said relay switch means includes a pair of relay switches connected in series relation between each of said cells and its associated pair of shunting resistors.

4. A system according to claim 3 wherein said relay switch means includes two relay coils, each of said coils arranged to operate a respective one of said pair of relay switches.

5. A system according to claim 1 wherein said regulating means includes a differential amplifier responsive to a reference voltage and said ground command signals for generating a bias signal for controlling said flow rate at either of said low and high rates in response to said ground command signals.

6. A system according to claim 5 wherein said regulating means includes a transistor connected to conduct said charging current from said solar source to said battery, said transistor being biased by said differential amplifier.

7. A method for reconditioning any one of a plurality of secondary batteries in a space vehicle, each of said batteries having a plurality of cells and said vehicle having a solar array source of charging current arranged to provide normally a low charge rate to each of said batteries, comprising the steps of:

disconnecting a selected one of said secondary batteries from said solar array source,

discharging the cells of said battery through a pair of resistors connected to said cells by relay switch contacts at a fixed discharge rate,

generating a signal representing the voltage of said battery and transmitting said signal to a ground station,

transmitting a control signal from said ground station to reconnect said selected battery to said solar source and to charge said battery from said source at a low charge rate,

changing the low charge rate to a high rate by ground command when said battery voltage reaches a first selected voltage,

sensing the voltage and temperature of said battery and automatically changing the high charge rate to said low rate when said battery voltage reaches a second selected value, greater than said first voltage.

8. A method according to claim 7 including the step of starting said discharging step of a selected battery at least 20 hours before an eclipse season of said space vehicle.