Ultra-low cost high performance satellite aperture
An antenna system of a satellite may consist of an antenna receiver that is coupled to a plurality of flexible couplings. The couplings may each be affixed to one or more antenna elements. The couplings may be deployed in space in an uncontrolled manner. Additionally, the spacing between the couplings, and in turn the antenna elements, may be spaced in an uncontrolled manner. The antenna elements may have no pointing requirements. The antenna system may receive training signals and associate an antenna element to a time of arrival based on the training signal. Upon receiving a data signal, the antenna system may apply coefficients determined from the association of the antenna element to the time of arrival to the data signal to discover wanted signal coherence among the antenna elements.
1. An antenna system of a satellite, comprising:
an antenna receiver;
a plurality of antenna elements coupled to the antenna receiver via a plurality of respective couplings, wherein the antenna system is packaged for deployment in a compact arrangement of the plurality of respective couplings, and wherein during deployment of the antenna system in space the plurality of antenna elements are spread over an aperture area of the antenna system while respective deployed positions of the plurality of antenna elements within the aperture area are not predetermined;
a training processor configured to:
receive one or more first signals from the antenna receiver associated with one or more training signals from a first transmitter, and
associate each of the plurality of antenna elements with a first respective time of arrival based at least in part on the one or more training signals; and
a beam weight processor configured to combine one or more second signals associated with a data signal from a second transmitter received via the antenna receiver according to a plurality of coefficients determined based at least in part on associations between the plurality of antenna elements and the first respective time of arrivals.
2. The antenna system of claim 1 , wherein the plurality of antenna elements are each directly attached to a respective coupling.
3. The antenna system of claim 1 , wherein the plurality of antenna elements are each attached to a respective coupling via a coupler.
4. The antenna system of claim 1 , wherein each of the plurality of couplings is constructed of a semi-rigid material.
5. The antenna system of claim 1 , wherein the deployed positions of the plurality of antenna elements form a volumetric shape.
6. The antenna system of claim 1 , wherein the plurality of couplings between the antenna receiver and the plurality of antenna elements are each comprised of a plurality of segments including a first segment type and a second segment type, wherein a segment of the first segment type is coupled to one or more segments of the second segment type.
7. The antenna system of claim 6 , wherein each segment of the plurality of segments of the second segment type is coupled to one or more respective antenna elements of the plurality of antenna elements.
8. The antenna system of claim 6 , wherein each segment of the plurality of segments of the second segment type is separated from one another by a minimum distance.
9. The antenna system of claim 8 , wherein the minimum distance is maintained utilizing one or more mechanical devices.
10. The antenna system of claim 6 , wherein each segment of the plurality of segments of the second segment type is coupled to a same quantity of antenna elements.
11. The antenna system of claim 1 , wherein during the deployment of the antenna system in space positions of the plurality of antenna elements are not controlled.
12. A method for receiving radio waves at an antenna system of a satellite, comprising:
receiving one or more first signals using a plurality of antenna elements, the one or more first signals corresponding to a training signal transmitted by a first transmitter, wherein the plurality of antenna elements are coupled to an antenna receiver via a plurality of respective couplings, wherein the antenna system is packaged for deployment in a compact arrangement of the plurality of respective couplings, and wherein during deployment of the antenna system in space the plurality of antenna elements are spread over an aperture area of the antenna system while respective deployed positions of the plurality of antenna elements within the aperture area are not predetermined;
associating each of the plurality of antenna elements with a first respective time of arrival based at least in part on the one or more first signals;
receiving one or more second signals using the plurality of antenna elements, the one or more second signals corresponding to a data signal transmitted by a second transmitter; and
combining the one or more second signals according to a plurality of coefficients determined based at least in part on associations between the plurality of antenna elements and the first respective time of arrivals.
13. The method of claim 12 , wherein the plurality of antenna elements are each directly attached to a respective coupling.
14. The method of claim 12 , wherein the plurality of antenna elements are each attached to a respective coupling via a coupler.
15. The method of claim 12 , wherein each of the plurality of couplings is constructed of a semi-rigid material.
16. The method of claim 12 , wherein the deployed positions of the plurality of antenna elements form a volumetric shape.
17. The method of claim 12 , wherein the plurality of couplings between the antenna receiver and the plurality of antenna elements are each comprised of a plurality of segments including a first segment type and a second segment type, wherein a segment of the first segment type is coupled to one or more segments of the second segment type.
18. The method of claim 17 , wherein each segment of the plurality of segments of the second segment type is coupled to one or more respective antenna elements of the plurality of antenna elements.
19. The method of claim 17 , wherein each segment of the plurality of segments of the second segment type is separated from one another by a minimum distance.
20. The method of claim 19 , wherein the minimum distance is maintained utilizing one or more mechanical devices.
21. The method of claim 17 , wherein each segment of the plurality of segments of the second segment type is coupled to a same quantity of antenna elements.
22. The method of claim 12 , wherein during the deployment of the antenna system in space positions of the plurality of antenna elements are not controlled.
23. The antenna system of claim 9 , wherein the one or more mechanical devices comprise one or more of: a semi-rigid member, an inflatable structure, an ejectable weighted object, a flexible coupling, a ratchet, a pawl, a chemically hardened member, a thermally-expandable member, a reaction jet, a pyrotechnic device, or an ion thruster.
24. The method of claim 20 , wherein during the one or more mechanical devices comprise one or more of: a semi-rigid member, an inflatable structure, an ejectable weighted object, a flexible coupling, a ratchet, a pawl, a chemically hardened member, a thermally-expanded member, a reaction jet, a pyrotechnic device, or an ion thruster.