Spacecraft power system

• US 6,049,190 A
• Filed: 04/13/1998
• Issued: 04/11/2000
• Est. Priority Date: 04/13/1998
• Status: Expired due to Fees

• Current Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Original Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Inventors: Canter, Stanley, Hall, John C
• Primary Examiner(s): Riley, Shawn
• Application Number:
  US09/059,224
• Time in Patent Office: 729 Days
• Field of Search: 323/906, 320/101, 320/102, 320/162, 320/163, 320/164
• US Class Current: 320/101
• CPC Class Codes: H02J 7/0024 Parallel/serial switching of connection of batteries to charge or load circuit
• CPC Class Codes: H02J 7/35 with light sensitive cells
• CPC Class Codes: H02J 9/061 for DC powered loads
• CPC Class Codes: Y02E 10/56 Power conversion systems, e.g. maximum power point trackers
• CPC Class Codes: Y10S 323/906 Solar cell systems

Abstract

A spacecraft power system having an increased number of battery cells that is charged to the battery'"'"'s full capacity, which exceeds a predetermined maximum voltage allowed by a bus. The battery can be disconnected from the bus during charging. The battery is then partially discharged to accommodate the bus before being reconnected. This provides a reduced voltage range experienced by the bus, as the minimum battery voltage is increased by the increased number of cells. A tap is provided to supply the bus with power when the battery is disconnected from the bus, and when a solar array powering the bus fails to supply current to the bus.

Claims

1. A spacecraft power system comprising:

a power bus having a first node coupled to a set of batteries supplying power to said power bus, and having a second node coupled to a solar array alternatively supplying power to said power bus;

switching means for disconnecting the set of batteries from said power bus allowing said set of batteries to be charged to a fully charged voltage that exceeds a maximum voltage value allowed by said power bus; and

means for reducing said fully charged voltage to a voltage acceptable by said power bus before reconnecting said set of batteries to said power source.

2. A spacecraft power system as set forth in claim 1, wherein said means for reducing said fully charged voltage bus comprises at least ore resistor switchably connected across said set of batteries.

3. A spacecraft power system as set forth in claim 1, wherein said switching means comprises at least one relay connected in series between said set of batteries and said power bus.

4. A spacecraft power system as set forth in claim 3, wherein said switching means further comprises at least one diode connected in series with said relay.

5. A method for charging a spacecraft power system to a voltage level above a predetermined maximum voltage allowed by a power bus comprising the steps of:

determining at least one condition for disconnecting the power bus from a battery;

disconnecting the battery from the power bus;

charging the battery to a full capacity having a voltage that exceeds the predetermined maximum voltage allowed by the power bus;

partially discharging -he battery thereby reducing the battery voltage to a level allowed by the power bus;

determining at least one condition for reconnecting the battery to the power bus; and

reconnecting the battery to the power bus.

6. A spacecraft power system comprising:

a power bus having a first node coupled to a set of batteries supplying power to said power bus, and having a second node coupled to a solar array alternatively supplying power to said power bus;

switching means for coupling and decoupling said set of batteries to said power bus; and

an emergency power supply, said emergency power supply comprising;

a tap coupled to said set of batteries in such a way that said tap'"'"'s voltage stays within a predetermined range utilizing part of the power derived from said set of batteries supplying power to said power bus when needed; and

a diode which only allows current to pass through said tap to said bus when said solar array power is less than required by said bus.

7. A spacecraft power system as set forth in claim 6, wherein said set of batteries can be charged to a voltage value exceeding a predetermined maximum voltage allowed by the power bus, and wherein said tap is positioned so as not to exceed the predetermined maximum voltage.

8. A spacecraft power system as set forth in claim 7, wherein said emergency power supply supplies said power bus with power when the solar array is not able to supply said power bus with power.

9. A spacecraft power system comprising a power bus having a predetermined maximum bus voltage value X, said power bus having a first node coupled to a battery with a predetermined number n of series connected cells, having a maximum voltage value Y, where Y>

X, and a second node coupled to a solar array, said power system comprising;

a battery tap located at n-m cells and having a voltage V_n-m, where V_n-m ≦

X; and

at least one diode for selectively coupling and decoupling said tap from said bus.

10. A spacecraft power system as set forth in claim 9, wherein said tap supplies said power bus with power when said set of batteries is disconnected from said power bus and when said solar array is not able to supply said power bus with sufficient power.

11. A spacecraft power system comprising a power bus with a first node coupled to a set of batteries supplying power to said power bus, and a second node coupled to a solar array alternatively supplying power to said power bus, wherein there is a predetermined power bus voltage X, a value Y denotes a maximum voltage of said set of batteries supplying power to said power bus, where Y>

X, a variable V_B denotes the voltage value of said set of batteries supplying power to said power bus, where V_B ≦

Y, said power system further comprising switching means for disconnecting said set of batteries from said power bus allowing said set of batteries to be charged to Y, and reconnecting said set of batteries to said power bus when V_B ≦

X;

means for reducing V_B from X<

V_B ≦

Y to V_B ≦

X; and

control means for coordinating said switching means and said means for reducing V_B.

12. A spacecraft power system as set forth in claim 11, wherein said switching means is comprised of at least one relay.

13. A spacecraft power system as set forth in claim 12, wherein said switching means is comprised of at least one diode connected in series with said relay.

14. A spacecraft power system as set forth in claim 11, wherein said control means is comprised of an on-board computer.

15. A spacecraft power system as set forth in claim 11, wherein said means for reducing V_B is comprised of at least one resistor switchably (connected across said batteries by said control means.

16. A method for charging a spacecraft power system to a voltage level above a predetermined maximum voltage allowed by a power bus, comprising the steps of:

in response to determining at least one condition for disconnecting the power bus from a battery, disconnecting the power bus from the battery;

charging the battery to a full capacity having a voltage that exceeds the predetermined maximum voltage allowed by the power bus;

partially discharging the battery thereby reducing the battery voltage to a level allowed by the power bus;

determining at least one condition for reconnecting the battery to the power bus; and

reconnecting the battery to the power bus.

17. A method for applying emergency power to a spacecraft power bus, comprising steps of:

providing a tap coupled to a set of batteries in such a way that a voltage of said tap stays within a predetermined voltage range; and

in response to a condition wherein the set of batteries is disconnected from said power bus and wherein an electric current supplying said power bus is below a predetermined level, supplying emergency power to the poser bus through the tap.