Integrated spacecraft control system and method

• US 6,298,289 B1
• Filed: 04/24/1999
• Issued: 10/02/2001
• Est. Priority Date: 04/24/1999
• Status: Expired due to Term

• Current Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Original Assignee: The Boeing Co.
• Inventors: Botzong, Bret M., Lloyd, David W.
• Primary Examiner(s): Zanelli, Michael J.
• Assistant Examiner(s): Gibson, Eric M.
• Application Number:
  US09/298,542
• Time in Patent Office: 892 Days
• Field of Search: 701/13, 244/158.R, 244/164, 244/165, 244/166, 244/167, 244/168, 244/169, 244/170, 244/171, 244/172, 244/173, 342/352, 342/355, 342/357.06, 342/357.11, 342/357.12, 714/25, 714/30, 714/48, 714/31
• US Class Current: 701/13
• CPC Class Codes: B64G 1/10 Artificial satellites; Systems of such satellites; Interplanetary vehicles space shuttles B64G1/14
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/285 using momentum wheels
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/361 using star sensors
• CPC Class Codes: B64G 1/366 using magnetometers
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for

Abstract

A spacecraft control electronics system provides multi-functionality to a spacecraft in a single electronics box. The system is subdivided into a plurality of modular electronic subunits. Each of the modular subunits plugs into a backplane in the electronics box and is positioned side-by-side. A serial data bus in the backplane of the box interconnects the modular subunits to each other. The data bus provides fully redundant, standard interfacing for the modular subunits. The plurality of electronic subunits provides spacecraft attitude determination, control, telemetry and command and data processing functions to the spacecraft as one unit. The electronics box connects to the spacecraft harness via external connectors. The spacecraft has a minimum number of harness connections as a result of the integrated functions in the spacecraft control electronics system. The control system applies selective internal redundancy in its subunits. The CPU subunit has triple mode redundancy through three microprocessors that are voted together to detect and correct errors due to single event upsets. The T&C/GPS subunit has an embedded GPS receiver that performs attitude determination as well as orbital positioning. The modular subunits have a built in self-test that verifies minute circuitry interconnections and detects faults automatically. The subunits are tested as stand-alone subunits, as a part of the spacecraft control electronics system, and/or as part of the spacecraft level integration using this automated built-in self test capability. Faults in the subunits or the system are detected in seconds. The built in self-test feature also provides an end-to-end spacecraft harness verification automatically in minutes. Defective modular subunits are removed and replaced with substitute modular subunits during spacecraft level integration.

Claims

1. A multi-functional electronic control system for spacecraft comprising:

a housing;

a backplane interconnected to the housing, the backplane comprising a serial data bus and external connections to the spacecraft; and

a plurality of electronic subunits, each of said subunits fitting into the housing and electrically interconnecting to the backplane data bus, wherein one of said subunits includes a central processing subunit for processing data among the plurality of subunits,

wherein said plurality of electronic subunits provides spacecraft attitude determination, control, telemetry and command and data processing functions to the spacecraft in the single housing.

2. The multi-functional electronic control system of claim 1, further comprising a global positioning system receiver in one of the plurality of subunits, wherein the receiver is in direct communication with the system data processing function and spacecraft antennas for providing spacecraft attitude determination.

3. The multi-functional electronic control system of claim 1, further comprising reaction wheel drivers in one of the plurality of subunits, wherein the reaction wheel drivers are in direct communication with spacecraft reaction wheels for providing spacecraft attitude control.

4. The multi-functional electronic control system of claim 1, further comprising a star camera interface in one of the plurality of subunits, wherein the star camera interface receives and processes spacecraft star camera data in cooperation with the data processing function for providing spacecraft attitude determination.

5. The multi-functional electronic control system of claim 1, further comprising a built-in self test for fault detection in and verification of connectivity of the backplane and of interfaces to the spacecraft that are external to the system.

6.The multi-functional electronic control system of claim 5, wherein said subunits are stand-alone, plug-in modules that are removable and replaceable during spacecraft level integration.

6. The multi-functional electronic control system of claim 1, wherein the backplane data bus comprises a fully redundant serial backplane data bus and at least one of the plurality of subunits comprises internal selective redundancy to the backplane data bus.

7. The multi-functional electronic control system of claim 1, wherein the plurality of subunits each comprises at least one printed wiring board mounted on a rigid frame and plug-in connectors for interconnection to the backplane.

8. The multi-functional electronic control system of claim 1, wherein each of the plurality of subunits comprises a built-in self test to verify the electrical and functional integrity of and detect faults in the subunit.

9. A multi-functional electronic control system for a spacecraft comprising:

a housing;

a backplane interconnected to the housing, the backplane comprising a serial data bus and external connections to the spacecraft;

a plurality of electronic subunits, each of said subunits fitting into the housing and electrically interconnecting to the backplane data bus, wherein said plurality of electronic subunits provides spacecraft attitude determination, control, telemetry and command and data processing function to the spacecraft in the single housing; and

a built-in self test for fault detection in and verification of connectivity of the backplane and of interfaces to the spacecraft that are external to the system,

the built-in self test verifies end-to-end connectivity of connections between the system and the spacecraft.

10. A multi-functional electronic control system for a spacecraft comprising:

a housing;

a backplane interconnected to the housing the backplane comprising a serial data bus and external connections to the spacecraft; and

a plurality of electronic subunits, each of said subunits fitting into the housing and electrically interconnecting to the backplane data bus, wherein said plurality of electronic subunits provides spacecraft attitude determination, control, telemetry and command and data processing functions to the spacecraft in the single housing,

wherein the plurality of subunits each comprises at least one printed wiring board mounted on a rigid frame and plug-in connectors for interconnection to be backplane; and

wherein the plurality of subunits each comprises two printed wiring boards mounted back-to-back on an aluminum web frame to provide a 2-for-1 internal redundancy to the system.

11. An integrated spacecraft control electronics system having attitude determination, control, telemetry and command and data processing functions in a single unit for a spacecraft comprising:

a housing having a backplane;

a fully redundant serial data bus on the backplane;

a plurality of subunits that fit into the housing and plug into the backplane data bus, wherein the plurality of subunits are in communication with each other via the backplane data bus, the plurality of subunits comprising;

a telemetry and command subunit for communicating with spacecraft transponders and antennas;

a wheel drive subunit for communicating with spacecraft reaction wheels;

an actuator subunit that communicates with spacecraft motors, thrusters and deployment mechanisms; and

a central processing subunit for processing data among the subunits and the spacecraft,

wherein the system electrically interconnects to the spacecraft via an external connector on the backplane of the housing.

12. The integrated spacecraft control electronics system of claim 12, further comprising an automatic built in self-test feature to test connectivity and detect faults between the system and the spacecraft.

13. The integrated spacecraft control electronics system of claim 12, wherein the telemetry and command subunit comprises:

a telemetry and command application specific integrated circuit;

a global positioning system receiver, wherein each of the integrated circuit and the receiver is independently connected to the backplane data bus;

a built-in internal redundancy; and

a built-in self test feature that automatically tests subunit and circuit connectivity and detects faults.

14. The integrated spacecraft control electronics system of claim 12, wherein the wheel drive subunit comprises a plurality of wheel drivers, each having a separate power supply, wherein each of the plurality of wheel drivers are independently connected to the backplane data bus, and a built-in self test feature that automatically tests subunit connectivity and detects faults.

16. The integrated spacecraft control electronics system of claim 12, wherein the actuator subunit comprises an interface application specific integrated circuit, drivers and a built-in self test feature that automatically tests subunit and circuit connectivity and detects faults, wherein the interface integrated circuit is in direct communication with the backplane data bus and the drivers.

18. The integrated spacecraft control electronics system of claim 12, wherein the central processing subunit comprises a processor, memory, and a built-in self test feature that automatically tests subunit and circuit connectivity and detects faults, wherein the subunit is connected to the backplane data bus and is in communication with the spacecraft through the processor.

15. The integrated spacecraft control electronics system of claim 15, wherein the wheel drive subunit has four wheel drivers in communication with three spacecraft wheels to provide a 4 for 3 wheel driver redundancy to the spacecraft.

17. The integrated spacecraft control electronics system of claim 17, wherein the actuator subunit further comprises a redundant interface application specific integrated circuit to provide redundancy to the backplane data bus and the drivers.

19. The integrated spacecraft control electronics system of claim 19, wherein the processor comprises a plurality of microprocessors voted together and a processor support application specific integrated circuit connected to the plurality of microprocessors, wherein the processor support integrated circuit has direct interfaces to the backplane data bus and the spacecraft.

20. A spacecraft having a spacecraft harness with a minimum number of spacecraft harness connections comprising:

a bus section;

a payload section; and

a multi-functional spacecraft control electronics unit on the bus section that communicates with the payload section, the control electronics unit comprising;

a housing having a backplane; and

a plurality of control electronics subunits that fit in the housing and interconnect to the backplane, wherein the subunits provide spacecraft attitude determination, control, telemetry and command and data processing functions to the spacecraft, wherein one of said subunits includes a central processing subunit for processing data among the plurality of subunits; and

interfaces external to the electronics unit,

wherein the spacecraft harness is connected to the external interfaces of electronics unit to obtain the functions with a minimum number of harness connections.

21. The spacecraft of claim 21, wherein the control electronics unit further comprises a fully redundant serial backplane data bus that electrically interconnects the subunits in the housing for communication between subunits.

22. The spacecraft of claim 21, wherein each of the plurality of the subunits is modular and comprises circuitry for supporting one or more of the functions, wherein the circuitry is supported by a printed wiring board, a rigid frame for mounting the printed wiring board, and connectors that plug into the housing.

23. The spacecraft of claim 21, wherein the spacecraft control electronics unit further comprises built in self-test functions for independently verifying electrical connectivity of the circuitry, the subunits and external interfaces and for detecting faults.

24. A method of spacecraft integration and test with a minimum number of spacecraft harness connections comprising the steps of:

testing electronic components used in the spacecraft at the component level;

assembling the tested electronic components into electronic subunits, the electronic subunits being modular and providing a plurality of spacecraft control functions;

testing the modular subunits, wherein each of the subunits has an automatic built-in self test capability to test the components, internal circuitry and external interfaces;

electrically interconnecting the subunits to a housing to form a electronic control system, the housing having a backplane, the backplane having a serial data bus for interconnecting the subunits to each other, the electronic control system providing a spacecraft attitude determination, control, telemetry and command and data processing functions to the spacecraft;

testing the electronic control system, wherein the system has an automatic built-in self test capability to further test backplane connectivity;

integrating the electronic control system with the spacecraft through external connectors on the backplane of the housing to provide the spacecraft functions; and

testing the integrated spacecraft, wherein the integrated spacecraft has an automatic built-in self test capability to further test backplane external interfaces and harness connections to the spacecraft.

25. The method of claim 25, wherein the step of electrically interconnecting comprises the steps of:

providing mating pairs of connectors in the control system, wherein one mate of the mating pair is positioned on an internal face of the backplane in alignment with the other mate of the mating pair that is positioned on an external face of the subunits; and

mating the connectors together as the subunit is inserted into the housing.

26. The method of claim 25, wherein the steps of testing the electronic control system and the integrated spacecraft comprise the steps of;

commanding the subunits into a test mode using a remotely located computer that is interfaced with a high speed serial connection in the electronic control system; and

viewing test results from the automatic built-in self test capability at the computer.