Educational Satellite system and a method of use thereof

• US 20060058023A1
• Filed: 09/14/2004
• Published: 03/16/2006
• Est. Priority Date: 09/14/2004
• Status: Abandoned Application

• Current Assignee: Colorado Satellite Services, LLC
• Original Assignee: Colorado Satellite Services, LLC
• Inventors: Barnhart, David J., Sellers, Jerry Jon, White, Timothy L., Clark, John B., White, James J., Enloe, Carl Lon
• Application Number:
  US10/940,899
• Publication Number:
  US 20060058023A1
• Time in Patent Office: Days
• US Class Current: 455/427
• CPC Class Codes: B64G 7/00 Simulating cosmonautic conditions, e.g. for conditioning crews

Abstract

In one embodiment, an educational non-flight capable satellite is described comprising a plurality of modular subsystems that are adapted to be coupled together via standardized bus connectors and standard mechanical connectors. The educational satellite is fully functional and can be utilized for teaching satellite engineering and operation at high school through college level courses.

Claims

1. An educational satellite system comprising:

a central data handling subsystem module adapted to receive and send data and command signals, the central data handling subsystem module having a first bus connector;

a communications subsystem module adapted to receive commands and transmit telemetry, the communications subsystem module having a second bus connector;

an attitude control subsystem module adapted to determine the orientation of educational satellite system, the attitude control subsystem module having a third bus connector; and

a power subsystem module adapted to supply power to educational satellite system, the power subsystem module have a fourth bus connector;

wherein the first, second, third, and fourth bus connectors share a common configuration and are situated on the central data handling subsystem module, the communications subsystem module, the attitude control subsystem module, and the power subsystem module respectively to facilitate the operative coupling of the modules.

2. The educational satellite of claim 1, wherein at least one of the central data handling subsystem module, the communications subsystem module, the attitude control subsystem module, and the power subsystem module is non-flight capable.

3. The educational satellite system of claim 1, wherein each of the central data handling subsystem module, the communications subsystem module, the attitude control subsystem module, and the power subsystem module comprises at least one circuit board distinct from the circuit boards of the other modules.

4. The educational satellite system of claim 1, wherein each of the central data handling subsystem module, the communications subsystem module, the attitude control subsystem module, and the power subsystem module further comprises at least one mechanical connector, the mechanical connectors being adapted to couple to each other.

5. The educational satellite system of claim 4, wherein the mechanical connectors comprise snap-together connectors.

6. The educational satellite of claim 1, further comprising a housing, the housing being adapted to at least partially contain and support the central data handling, communications subsystem, attitude control subsystem, and power subsystem modules therein.

7. The educational satellite of claim 6, wherein the housing is translucent.

8. The educational satellite of claim 1, wherein the communications module includes a wireless transceiver.

9. The educational satellite of claim 1, wherein the attitude control subsystem module is further adapted to control the attitude positioning of the educational satellite about at least one axis.

10. The educational satellite of claim 9, wherein the attitude control subsystem module further comprises one or more torque rods.

11. The educational satellite of claim 9, wherein the attitude control subsystem module further comprises at least one reaction wheel.

12. The educational satellite of claim 3, wherein the power subsystem module further comprises a battery pack located on a second circuit board.

13. The educational satellite of claim 1, wherein the bus connectors comprise a PC/104 bus configuration.

14. The educational satellite of claim 1, wherein the power subsystem module further comprises one or more solar panels.

15. The educational satellite of claim 1, wherein the attitude control subsystem module further comprises at least one of the group including attitude sensors and sun sensors.

16. The educational satellite of claim 1, further comprising a hanger, the hanger being located on the top of the satellite coincident with a pivotal axis of the satellite.

17. The educational satellite of claim 1, wherein the communications subsystem module is adapted for wireless communication with a personal computer equipped with a wireless modem.

18. An educational satellite comprising two or more functional subsystems, at least one of the two or more functional subsystems being physically separable from the at least one other functional subsystem of the two or more functional subsystems, the separate functional subsystems being adapted to couple to each other by way of a standard bus through compatible bus connectors on each separate functional subsystem, at least one separate subsystem being non-flight capable.

19. The educational satellite of claim 18, wherein the two or more functional subsystems include at least two of the group comprising:

(a) a power subsystem;

(b) a central data handling subsystem;

(c) a communications subsystem; and

(d) an attitude control subsystem.

20. The educational satellite of claim 18, wherein the separate functional subsystems are further adapted to be coupled using compatible mechanical connectors.

21. The educational satellite of claim 18, wherein each separate functional subsystem is capable of operation independent of the other separate functional subsystems when a suitable power source is provided.

22. The educational satellite of claim 19, wherein the power subsystem, the central data handling subsystem module, and the attitude control subsystem each have a data interface connector for directly coupling with a personal computer through a suitable cable.

23. The educational satellite of claim 18, wherein each circuit board of each separate functional subsystem module is the substantially same size and configuration as each other circuit board of each other separate functional subsystem module.

24. The educational satellite of claim 18, wherein the standard bus includes both a power and a data bus.

25. A method comprising:

providing one or more non-flight capable satellites, each satellite comprising two or more functional subsystems, at least one of the two or more functional subsystems being physically separable from the at least one other functional subsystem of the two or more functional subsystems, the separate functional subsystems being adapted to couple to each other by way of a standard bus; and

using the satellite in conjunction with instruction to one or more students concerning at least one of the group of (i) satellite design, (ii) satellite engineering, (iii) satellite operation, (iv) satellite fabrication, and (v) satellite testing.

26. The method of claim 25, wherein the two or more functional subsystems include at least two of the group comprising:

(a) a power subsystem;

(b) a central data handling subsystem;

(c) a communications subsystem; and

(d) an attitude control subsystem.

27. The method of claim 25, wherein the separate functional subsystems are adapted to be coupled using compatible mechanical connectors.

28. The method of claim 25, wherein said using the satellite in conjunction with instruction further comprises:

(1) performing functionality testing on each separate functional subsystem prior to integration with the other functional subsystems; and

(2) performing functionality testing on the satellite when the two or more functional systems are integrated together.

29. A method of building a satellite comprising:

providing a modular satellite kit, the satellite kit including a plurality of prefabricated modules, each module utilizing a common bus standard and including (i) standard bus connectors compatible with bus connectors of each other module, (ii) standard mechanical connectors adapted to couple the module with each other module;

testing each module to verify the functionality of the module prior to integration of the module with the other modules of the plurality of modules;

coupling each module with the other modules of the plurality of modules by way of the standard mechanical connectors and the standard bus connectors; and

testing the integrated satellite kit to verify functionality thereof.

30. The method of claim 29, wherein said testing each module to verify functionality of the module further comprises calibrating one or more parameters of at least one module.

31. The method of claim 29, wherein said testing each module to verify functionality of the module further comprising reading telemetry directly from the module by coupling the module with a personal computer

32. The method of claim 29, wherein said testing the integrated satellite kit to verify functionality further comprises sending commands and receiving telemetry to and from the integrated satellite wirelessly using a personal computer having a wireless transceiver.

33. The method of claim 29, further comprising installing the integrated satellite kit in a structural housing.

34. The method of claim 29, further comprising designing and fabricating a new module using the common bus standard and including the standard bus and mechanical connectors.