Modular mother satellite bus for subsidiary payloads

• US 5,271,582 A
• Filed: 05/01/1992
• Issued: 12/21/1993
• Est. Priority Date: 06/29/1990
• Status: Expired due to Fees

• Current Assignee: Frederick W. Perkins
• Original Assignee: Standard Space Platforms Corporation
• Inventors: Perkins, Frederick W., Kananen, Phil
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): BIDWELL, ANNE
• Application Number:
  US07/877,145
• Time in Patent Office: 599 Days
• Field of Search: 244/158 R, 244/159
• US Class Current: 244/173.1
• CPC Class Codes: B64G 1/22 Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• CPC Class Codes: B64G 1/223 Modular spacecraft systems
• CPC Class Codes: B64G 1/64 Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• CPC Class Codes: B64G 1/641 Interstage or payload connectors docking systems B64G1/646

Abstract

Multiple subsidiary small payloads are connected to standard mechanical and electrical interfaces provided by an expendable or recoverable modular mother satellite bus (MMSB) and launched into space as an assembly acting as a common carrier providing low unit launch costs for the attached subsidiary payloads and also providing a variety of electrical, pointing, and thermal control services for these payloads after reaching orbit. These services include but are not necessarily limited to controlled separation of free-flying satellites or re-entry vehicles, regulated electric power at a variety of voltages, telemetry, computer control, payload control via time delayed pre-programmed instructions, optional real-time payload control via direct radio communication or transmission through geostationary or other communication satellite links, time-driven or event-driven control logic, mass data memory, encryption and decryption of data and commands, payload pointing, augmented heat rejection, and interconnection between subsidiary attached payloads through the data bus.

Claims

1. A self-contained, unmanned spacecraft adapted to be launched into space by a launch vehicle and subsequently separated therefrom, the spacecraft adapted to carry one or more subsidiary attached payloads and to provide bus services to each of said one or more payloads upon separation of the spacecraft from the launch vehicle, the spacecraft comprising:

a main structural body;

one or more standardized mechanical and electronic interface means for mechanically and electronically attaching each of said one or more subsidiary attached payloads to said main structural body of the spacecraft;

means operative through said interface means for controlling the function of each of said one or more subsidiary payloads;

means operative through said interface means for providing spacecraft electric power and computer/controller and data bus resources to each of said one or more subsidiary attached payloads;

means operative through said interface means for retrieving data from said one or more subsidiary attached payloads; and

means for permitting communication between the spacecraft and external source.

2. A spacecraft according to claim 1 and including industry-standard open architecture digital subsystem configurations to implement said means for controlling the function of said one or more subsidiary attached payloads.

3. A spacecraft according to claim 1 and including industry-standard open architecture digital subsystem configurations to provide access for said one or more subsidiary attached payloads to said computer/controller and data bus resources means.

4. A spacecraft according to claim 1 and including industry-standard open architecture digital subsystem configurations to provide payload access to said means for retrieving data from said one or more subsidiary attached payloads.

5. A spacecraft according to claim 1 and including industry-standard open architecture digital subsystem configurations.

6. A spacecraft according to claim 5 wherein said interface means comprises one or more preconfigured mechanical, electrical, and electronic interfaces is defined independently of payload specification such that the said one or more subsidiary attached payloads may be built substantially in conformity with the said one or more preconfigured interfaces.

7. A spacecraft according to claim 6 and wherein said means for mechanically and electronically attaching each of said one or more attached payloads to said main structural body comprises industry-standard electrical connectors.

8. A spacecraft according to claim 6 and wherein said means for mechanically and electronically attaching each of said one or more attached payloads to said main structural body comprises industry-standard mechanical connectors.

9. A spacecraft according to claim 1 and also comprising means for metering bus services provided to said one or more subsidiary attached payloads.

10. A spacecraft according to claim 1 wherein said interface means comprises one or more preconfigured mechanical, electrical, and electronic interfaces defined independently of payload specification such that the said one or more subsidiary attached payloads may be built substantially in conformity with the said one or more preconfigured interfaces.

11. A spacecraft according to claim 10 and wherein said means for mechanically and electronically attaching each of said one or more attached payloads to said main structural body comprises industry-standard electrical connectors.

12. A spacecraft according to claim 10 and wherein said means for mechanically and electronically attaching each of said one or more attached payloads to said main structural body comprises industry-standard mechanical connectors.

13. A spacecraft according to claim 1 wherein said means for providing spacecraft electric power and computer/controller and data bus resources comprises one or more distributed controllers.

14. A spacecraft according to claim 13 including a standard modular interface control unit for each of said one or more attached subsidiary payloads.

15. A spacecraft according to claim 14 wherein said interface control units are each accessible from the exterior of said spacecraft and may be reconfigured for individual payloads.

16. A spacecraft according to claim 15 wherein integral connectors are provided such that connections with said spacecraft electric power and computer/controller and data bus resources for any one of said attached subsidiary payloads is established by mechanically attaching one or more associated interface control unit subassemblies to said main spacecraft and broken by mechanically removing said one or more associated interface control unit subassemblies.

17. A spacecraft according to claim 15 and which includes means for adaptation of said interface control units to accommodate one or more particular payload characteristics.

18. A spacecraft according to claim 1 and wherein said means for mechanically and electronically attaching each of said one or more attached payloads to said main structural body comprises industry-standard electrical connectors.

19. A spacecraft according to claim 1 and wherein said means for mechanically and electronically attaching each of said one or more attached payloads to said main structural body comprises industry-standard mechanical connectors.

20. A spacecraft according to claim 1 adapted to carry two or more attached subsidiary payloads.

21. A spacecraft according to claim 20 and including

means for separating one or more of said attached subsidiary payloads from the spacecraft main structural body after a predetermined period of attachment following launch;

and

means for continuing to provide said bus services to remaining attached subsidiary payloads following separation of said one or more payloads.

22. A spacecraft according to claim 21 and wherein said means for mechanically and electronically attaching each of said one or more attached subsidiary payloads to said main structural body comprises industry-standard mechanical connectors.

23. A spacecraft according to claim 20 and including industry-standard open architecture digital subsystem configurations to provide means for providing electronic data produced by said one or more attached subsidiary attached payloads to one or more other of said attached subsidiary payloads.

24. A spacecraft according to claim 23 and providing means for controlling the function of said one or more attached subsidiary payloads dependent on one or more of electronic data retrieved from said one or more other attached subsidiary payloads.

25. A spacecraft according to claim 20 and providing means for modifying the operation of one or more of said attached subsidiary payloads dependent on one or more of electronic data retrieved from said one or more other attached subsidiary payloads.

26. A spacecraft according to claim 20 and providing means for metering bus services.

27. A spacecraft according to claim 20 and which provides said bus services by means of one or more distributed controllers.

28. A spacecraft according to claim 27 wherein said interface means comprises a standard modular interface control unit for each of said one or more attached subsidiary payloads.

29. A spacecraft according to claim 28 wherein said interface control units are accessible from the exterior of said spacecraft and may be reconfigured for said one or more individual payloads by removal and substitution of one or more appropriate components or subassemblies, thereby allowing integration into and interconnection of diverse payload types onto said spacecraft without reconfiguring internal electronics of said spacecraft.

30. A spacecraft according to claim 27 wherein said interface means further comprises integral connectors such that connections with said spacecraft electrical power and data/command services for any one of said attached subsidiary payloads is established by mechanically attaching one or more said associated interface control unit subassemblies to said main spacecraft body and broken by mechanically removing said associated interface control unit subassemblies.

31. A spacecraft according to claim 20 and which also provides means for functional coupling and integration of two or more discrete payload subelements such that the functionally integrated aggregate payload may be comprised of dispersed payload subelements, each of which subelements is itself an attached subsidiary payload.

32. A spacecraft according to claim 20 and which also provides means for functionally integrating said attached subsidiary payload through one or more spacecraft buses.

33. A spacecraft according to claim 20 and which also provides means for functionally integrating two or more combined payload elements through one or more direct connections between the discrete payload elements, each of which is itself one of said attached subsidiary payload.