Modular platform architecture for satellites

• US 20070029446A1
• Filed: 05/02/2006
• Published: 02/08/2007
• Est. Priority Date: 05/02/2005
• Status: Abandoned Application

• Current Assignee: Utah State University
• Original Assignee: Utah State University
• Inventors: Mosher, Todd, Young, Quinn
• Application Number:
  US11/417,003
• Publication Number:
  US 20070029446A1
• Time in Patent Office: Days
• US Class Current: 244/158.100
• CPC Class Codes: B64G 1/10 Artificial satellites; Systems of such satellites; Interplanetary vehicles space shuttles B64G1/14
• CPC Class Codes: B64G 1/223 Modular spacecraft systems

Abstract

A method for implementing a modular platform for the construction of satellites and other spacecraft based on modular platform architecture, the method comprising: (a) identifying a plurality of functional elements and their associated functional routines that may be operable within at least one satellite; (b) associating the functional routines with one another in a strategic manner; (c) dividing the functional routines to define a plurality of subsystems; and (d) deriving a plurality of modules from the plurality of subsystems, each of the modules being configured to operably interface with at least one other module to construct a working satellite capable of carrying out a pre-determined number of the functional routines.

Claims

1. (canceled)

2. A method for implementing a modular platform for the construction of satellites and other spacecraft based on modular platform architecture, said method comprising:

identifying a plurality of functional elements and their associated functional routines that may be operable within at least one satellite;

associating said functional routines with one another in a strategic manner;

defining a plurality of subsystems from said functional elements, and any divisions thereof; and

deriving a plurality of modules from said plurality of subsystems, each of said modules being configured to operably interface with at least one other module to construct said satellite capable of carrying out at least one of said functional routines, said satellite being constructed substantially from said plurality of modules.

3. The method of claim 2, wherein a set of said plurality of said modules may be selected to construct a variant of said satellite.

4. The method of claim 2, wherein said modules, or a component thereof, may be selectively interchanged to construct a plurality of variants of said satellite intended for different mission types.

5. The method of claim 2, further comprising reconfiguring said modules to meet different mission types.

6. The method of claim 2, further comprising standardizing one or more interfaces between said modules to enable an increased degree of commonality between different variants of said satellite.

7. The method of claim 2, further comprising optimizing said modular platform for at least one of flexibility, standardization, and manufacturability.

8. The method of claim 2, wherein said functional elements are selected from the group consisting of power management, spacecraft processor, communications, separation system, payload interface, attitude control, attitude determination, and propulsion functional elements.

9. A method for constructing a satellite from a modular platform based on modular platform architecture, said method comprising:

obtaining a plurality of modules, each of said modules facilitating execution of at least one function of a functional routine of said satellite, and each being derived from at least one subsystem defined by at least one functional element;

selecting a set of said plurality of modules to be used to construct said satellite configured to conduct an intended mission, said satellite being constructed substantially from said set of said modules; and

operably interfacing each of said modules within said set with at least one other module in said set to construct said satellite capable of performing all required and optional functional routines, said satellite being constructed substantially from said set of said modules.

10. The method of claim 9, further comprising interchanging at least one of said modules within said set with at least one other module to construct a variant of said satellite.

11. The method of claim 9, wherein said interfacing is selected from the group consisting of mechanical, electrical, fluid, data, and any combination of these.

12. The method of claim 9, wherein said interfacing comprises directly interfacing said modules with one another.

13. The method of claim 9, wherein said interfacing comprises interfacing said modules with one another via an electrical backbone.

14. A modular platform for use in constructing a satellite and variants thereof, said modular platform being based on modular platform architecture, and comprising:

a plurality of modules, each being derived from at least one subsystem, and each being configured to operably interface with at least one other module to construct a working satellite capable of carrying out said functional routines,

said modules being derived from a plurality of subsystems corresponding to and defined by a plurality of functional elements and functional routines,

said subsystems being defined by a plurality of functional elements and their associated functional routines that identify and control various operations and functions of said satellite, said functional elements being strategically divided to form said functional routines, said functional routines being strategically associated with one another.

15. The modular platform of claim 14, wherein said plurality of subsystems is selected from the group consisting of a payload subsystem, an attitude control subsystem, a command and data handling subsystem, a propulsion subsystem, a power subsystem, and a structure subsystem, each being based on a corresponding, like functional element.

16. The modular platform of claim 14, wherein said modules further comprise components configured to perform a pre-determined function and to facilitate execution of a functional routine of said satellite.

17. A satellite configured for use in performing a mission, said satellite comprising:

a plurality of independent modules selected and assembled from a modular platform based on modular platform architecture, each of said plurality of modules being derived from a plurality of subsystems, and configured to perform a pre-determined functional routine; and

means for interfacing each of said plurality of modules with at least one other module in an operable manner to construct said satellite and to facilitate the performance of all functional routines capable of being performed by said satellite.

18. The satellite of claim 17, wherein said means for interfacing comprises a mechanical interface configured to physically interconnect said modules.

19. The satellite of claim 17, wherein said means for interfacing comprises an electrical interface configured to electrically couple said modules.

20. The satellite of claim 17, wherein said means for interfacing comprises a software interface configured to control the functions of said modules.

21. The satellite of claim 17, wherein said means for interfacing comprises a data interface.

22. The satellite of claim 17, wherein said means for interfacing comprises a fluid interface configured to permit the transfer of fluid between modules.

23. The satellite of claim 17, wherein said plurality of modules is selected from the group consisting of a data handling structural module, an attitude control structural module, a propulsion module, a launch interface deck module, a payload interface deck module, a spacecraft processor panel module, a communications panel module, a power management panel module, a power management panel module, an attitude control shelf module, an attitude control panel module, a solar array gimbal panel module, and a solar array assembly module, each of these being based on corresponding subsystems.

24. The satellite of claim 17, wherein a set of said plurality of modules may be selected and varied to form specific variants of said satellite.

25. The satellite of claim 17, wherein at least some of said plurality of modules further comprise various other components supported thereon that are configured to perform a pre-determined function.

26. The satellite of claim 17, further comprising a connector that physically couples said modules together.

27. The satellite of claim 17, wherein at least one of said modules is generic, and capable of being utilized across a number of different satellite variants.

28. The satellite of claim 17, wherein at least one of said modules is variant-specific.