ANTENNAS FOR SMALL SATELLITES

• US 20150162656A1
• Filed: 06/11/2013
• Published: 06/11/2015
• Est. Priority Date: 06/11/2012
• Status: Active Grant

• Current Assignee: University of Florida Research Foundation, Incorporated (State University System of Florida)
• Original Assignee: University of Florida Research Foundation, Incorporated (State University System of Florida)
• Inventors: Fitz-Coy, Norman G., Shirvante, Vivek, Johnson, Shawn, Cason, Kathryn
• Granted Patent: US 9,966,658 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64G 1/105 Space science
• CPC Class Codes: B64G 1/222 for deploying structures between a stowed and deployed state
• CPC Class Codes: B64G 1/2222 Folding
• CPC Class Codes: B64G 1/443 Photovoltaic cell arrays
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: H01Q 1/288 Satellite antennas
• CPC Class Codes: H01Q 19/106 using two or more intersecting plane surfaces, e.g. corner reflector antennas
• CPC Class Codes: H01Q 9/30 with feed to end of elongated active element, e.g. unipole H01Q9/44 takes precedence

Abstract

Various embodiments of the present invention include assemblies and methods for utilizing antennas with high gain in small satellites. In one embodiment, a satellite comprising a payload configured for transmitting data is provided. The payload may include various components of the satellite, such as the attitude control system, electrical power system, and/or communication system. The satellite may be configured to communicate with one or more ground stations. The satellite includes a support structure comprising at least one deployable panel, wherein the support structure houses the payload. The satellite also includes at least one antenna coupled to the support structure, wherein the deployable panel is configured to cover the antenna in a non-deployed state and to expose the antenna in a deployed state.

Claims

1. A satellite comprising a payload configured for transmitting data, the satellite comprising:

a support structure comprising at least one deployable panel, the support structure configured to house the payload; and

at least one antenna coupled to the support structure, wherein the deployable panel is configured to cover the antenna in a non-deployed state and to expose the antenna in a deployed state.

2. The satellite according to claim 1, wherein the satellite is a pico-or nano-satellite.

3. The satellite according to claim 1, wherein the support structure is a 1U Cubesat.

4. The satellite according to claim 1, wherein the support structure is a 3U Cubesat.

5. The satellite according to claim 1, wherein the at least one antenna is an S-band antenna.

6. The satellite according to claim 1, wherein the at least one antenna comprises a radiation monopole.

7. The satellite according to claim 6, wherein the monopole is disposed on an outer surface of the support structure.

8. The satellite according to claim 1, wherein the at least one antenna comprises a parabolic-shaped reflector.

9. The satellite according to claim 8, wherein the parabolic-shaped reflector is defined within the support structure, and wherein the at least one deployable panel is configured to cover the parabolic-shaped reflector in the non-deployed state.

10. The satellite according to claim 1, wherein the at least one antenna comprises at least one patch antenna.

11. The satellite according to claim 1, wherein the at least one antenna comprises at least one annular ring patch antenna.

12. The satellite according to claim 1, wherein the at least one antenna comprises an array of patch antennas.

13. The satellite according to claim 12, further comprising a diversity switch configured to switch between each of the patch antennas.

14. The satellite according to claim 1, wherein the support structure comprises a plurality of deployable panels.

15. The satellite according to claim 1, wherein the plurality of deployable panels are disposed at an angle between 0-90 degrees with respect to a ground plane of the support structure.

16. The satellite according to claim 1, wherein the antenna is configure to provide a gain of at least 7 dBi and a bandwidth of at least 10 MHz.

17. The satellite according to claim 1, wherein the antenna is configured to provide a gain of at least 7 dBi and a bandwidth of at least 40 MHz.

18. The satellite according to claim 1, wherein the antenna is configured to provide a beam width of about 50-60 degrees.

19. The satellite according to claim 1, wherein the antenna is configured to provide a beam width between 0 and 90 degrees.

20. The satellite according to claim 1, wherein the support structure is an elongated cube shape.

21. The satellite according to claim 1, wherein the deployable panel is disposed substantially parallel to a ground plane of the support structure in the non-deployed state.

22. The satellite according to claim 21, wherein the deployable panel is disposed substantially perpendicular to the ground plane of the support structure in the deployed state.

23. The satellite according to claim 1, wherein the support structure comprises a plurality of sides, and wherein the at least one antenna is located at about the center of one of the sides.

24. The satellite according to claim 1, wherein the deployable panel is disposed substantially parallel to a ground plane of the support structure in the non-deployed state.

25. The satellite according to claim 1, wherein at least one deployable panel comprises a solar panel.

26. The satellite according to claim 1, wherein at least one deployable panel comprises a conductive material.

27. The satellite according to claim 1, wherein the antenna comprises an elastic material.