Active spacecraft thermal control system and method

• US 5,954,298 A
• Filed: 04/28/1997
• Issued: 09/21/1999
• Est. Priority Date: 04/28/1997
• Status: Expired due to Term

• Current Assignee: CDC Propriete Intellectuelle
• Original Assignee: Motorola, Inc. (Motorola Solutions, Inc.)
• Inventors: Basuthakur, Sibnath, Allen, Robert David, Miller, Daniel David
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US08/842,106
• Time in Patent Office: 876 Days
• Field of Search: 244/158 R, 244/163, 244/172, 165/41, 165/104.12, 165/104.14, 165/104.21, 165/104.23, 165/104.31, 165/904
• US Class Current: 244/171.8
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 1/50 for temperature control
• CPC Class Codes: B64G 1/503 Radiator panels
• CPC Class Codes: B64G 1/506 Heat pipes

Abstract

A spacecraft (10) has combined propulsion and active thermal control systems. A propellant storage tank (20) couples to a pressurant storage tank (18). A working fluid (52) resides in the pressurant storage tank (18) and propels propellant when needed while concurrently acting as a thermal working fluid. The working fluid (52) is expanded then routed to selected cooled components (64). After passing by the cooled components (64), the working fluid (52) is compressed and passed by selected heated components (82). A controller (36) monitors temperature sensors (88) and controls valve assemblies (60, 78) to determine the components (64, 82) to which the working fluid (52) is routed.

Claims

1. A spacecraft having a combined propulsion and active thermal control system, said spacecraft comprising:

a first component which includes a propellant valve;

a second component which includes a battery, wherein said second component is active and temperature sensitive;

a storage tank which contains a propulsion system fluid;

a pump;

a thruster;

a power amplifier; and

a conduit system coupled to said tank, said pump, said first component, said second component, said thruster, and said power amplifier, said conduit system including said propulsion system fluid transferring heat between said first component and said second component, and so that heat generated by said battery and said power amplifier is transferred to said propellant valve.

2. A spacecraft as claimed in claim 1 wherein said propulsion system fluid is a propulsion system pressurant.

3. A spacecraft as claimed in claim 1 wherein:

said spacecraft additionally comprises a body having an external surface;

said second component comprises a battery; and

said battery is distally located within said body from said external surface.

4. A spacecraft as claimed in claim 1 wherein:

said spacecraft additionally comprises a body having an external surface;

said second component comprises a power amplifier; and

said power amplifier is distally located within said body from said external surface.

5. A spacecraft having a combined propulsion system and active thermal control system, said spacecraft comprising:

a plurality of active and temperature sensitive components, including a battery and a power amplifier;

a storage tank that contains a pressurizing fluid;

a storage tank that contains a propellant fluid, said storage tank being coupled to a propellant valve;

a pump;

a plurality of regulator valve assemblies;

an expansion valve;

a controller electrically coupled to said plurality of regulator valve assemblies; and

a conduit system coupled to said pressurizing and propellant fluid storage tanks, said propellant valve, said pump, said plurality of regulating valve assemblies, said expansion valve, and said plurality of active and temperature sensitive components including said battery and said power amplifier, said conduit system including said pressurizing fluid transferring heat generated by said battery and said power amplifier is transferred to said propellant valve and between said plurality of active and temperature sensitive components in accordance with a configuration of said regulating valve assemblies defined by said controller.

6. A spacecraft as claimed in claim 5 wherein said pump comprises a compressor assembly.

7. A spacecraft as claimed in claim 6 wherein said compressor assembly comprises first and second redundant compressors.

8. A spacecraft as claimed in claim 7 wherein:

said expansion valve is a first expansion valve; and

said spacecraft additionally comprises a second expansion valve, said first and second expansion valves being coupled in parallel for redundancy.

9. A spacecraft as claimed in claim 5 wherein at least a portion of said regulator valve assemblies each comprises first and second redundant regulator valves.

10. A spacecraft as claimed in claim 5 wherein:

said spacecraft additionally comprises a body having an external surface;

said plurality of active and temperature sensitive components include a battery; and

said battery is distally located within said body from said external surface.

11. A spacecraft as claimed in claim 5 wherein:

said spacecraft additionally comprises a body having an external surface;

said plurality of active and temperature sensitive components include a power amplifier; and

said power amplifier is distally located within said body from said external surface.

12. A spacecraft as claimed in claim 5 additionally comprising a plurality of temperature sensors located proximate said plurality of active and temperature sensitive components, said temperature sensors being electrically coupled to said controller.

13. A spacecraft having a combined propulsion system and active thermal control system, said spacecraft comprising:

a thermal radiator panel;

a plurality of active and temperature sensitive components including a battery and a power amplifier;

a storage tank that contains a pressurizing fluid;

a storage tank that contains a propellant fluid, coupled to a propellant valve;

a pump;

a plurality of regulator valve assemblies;

an expansion valve;

a controller electrically coupled to said plurality of regulator valve assemblies; and

a conduit system coupled to said pressurizing and propellant fluid storage tanks, said propellant valve, said pump, said plurality of regulating valve assemblies, said plurality of active and temperature sensitive components including said battery and said power amplifier, and said thermal radiator panel such that said controller configures said conduit system so that said pressurizing fluid conveyed by said conduit transfers heat generated by said battery and said power amplifier is transferred to said propellant valve and transfers heat generated from said plurality of active and temperature sensitive components to said thermal radiator panel.

14. A spacecraft as claimed in claim 13 wherein:

said spacecraft additionally comprises a body having an external surface;

said plurality of active and temperature sensitive components include a battery; and

said battery is distally located within said body from said external surface.

15. A spacecraft as claimed in claim 14 wherein:

said plurality of active and temperature sensitive components additionally include a power amplifier; and

said power amplifier is distally located within said body from said external surface.