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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 a

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.

대표청구항 ▼

1. A satellite comprising a payload configured for transmitting data, the satellite comprising: a satellite body comprising a support structure configured to house the payload, the satellite body and the support structure are made at least in part of a conductive material;at least one deployable pan

1. A satellite comprising a payload configured for transmitting data, the satellite comprising: a satellite body comprising a support structure configured to house the payload, the satellite body and the support structure are made at least in part of a conductive material;at least one deployable panel, the deployable panel secured to the support structure and at least a portion of the panel comprising a solar panel; andat least one reflector antenna coupled to the support structure, the reflector antenna comprising an antenna and a reflector, the reflector being embedded, at least in part, within a surface of 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,the at least one deployable panel is configured to reflect a signal emitted by the antenna, anda ground plane of the at least one deployable panel is a ground plane for the at least one reflector antenna. 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 antenna comprises a radiation monopole. 7. The satellite according to claim 6, wherein the monopole is disposed on an outer surface of the satellite body. 8. The satellite according to claim 1, wherein the reflector comprises a parabolic reflector. 9. The satellite according to claim 8, wherein the parabolic reflector is defined within the support structure, and wherein the at least one deployable panel is configured to cover the parabolic reflector in the non-deployed state. 10. The satellite according to claim 1, wherein the support structure comprises a plurality of deployable panels. 11. 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 conductive surface of the satellite body. 12. 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 10 MHz. 13. 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. 14. The satellite according to claim 1, wherein the antenna is configured to provide a beam width of about 50-60 degrees. 15. The satellite according to claim 1, wherein the antenna is configured to provide a beam width between 0 and 90 degrees. 16. The satellite according to claim 1, wherein the support structure is an elongated cube shape. 17. 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. 18. The satellite according to claim 17, wherein the deployable panel is disposed substantially perpendicular to the ground plane of the support structure in the deployed state. 19. 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. 20. 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. 21. The satellite according to claim 1, wherein at least one deployable panel comprises a solar panel. 22. The satellite according to claim 1, wherein the antenna comprises an elastic material. 23. A satellite comprising a payload configured for transmitting data, the satellite comprising: a satellite body comprising a support structure configured to house the payload, at least a portion of the satellite body and the support structure are made of a conductive material;at least one deployable panel, the deployable panel secured to the support structure and at least part of the at least one deployable panel comprises a solar panel; andat least one patch antenna coupled to the support structure such that a surface of the support structure is an extension of a ground plane of the at least one patch antenna,wherein:the deployable panel is configured to cover the patch antenna in a non-deployed state and to expose the patch antenna in a deployed state, andthe at least one deployable panel is configured to reflect a signal emitted by the patch antenna. 24. The satellite according to claim 23, wherein the at least one antenna comprises at least one annular ring patch antenna. 25. The satellite according to claim 23, wherein the at least one antenna comprises an array of patch antennas, wherein at least one antenna of the array of patch antennas is disposed on the at least one deployable panel. 26. The satellite according to claim 25, further comprising a diversity switch configured to switch between each of the patch antennas.