Imaging array fed reflector
View Patent ↗An imaging array fed reflector for a spacecraft is included in a spacecraft payload subsystem. The payload subsystem includes a multi-beam antenna including a reflector, a plurality of amplifiers, and a plurality of radiating feed elements, the feed elements configured as a phased array, illuminating the reflector, operable at a frequency having a characteristic wavelength (λ), and configured to produce, in a far field at the reflector, a set of contiguous abutting beams. The amplifiers are disposed proximate to the plurality of radiating feed elements. Each radiating feed element has a respective coupling with at least one respective amplifier of the plurality of amplifiers. Each radiating feed element, together with the at least one respective amplifier, is disposed in a closely packed triangular lattice such that separation between adjacent radiating feed elements is not greater than 1.5λ.
1. A multi-beam antenna (MBA) system for a spacecraft, the MBA system comprising:
a reflector; and
a plurality of radiating feed elements, configured as a phased array, illuminating the reflector, operable at a frequency having a characteristic wavelength (λ), and configured to produce, in a far field at the reflector, a set of contiguous abutting beams; wherein: the frequency is at least 20 GHz, and λ is no greater than 15 mm and no smaller than 7.5 mm;
each radiating feed element is coupled with and proximate to a respective amplifier module and is associated with a respective beamlet;
the radiating feed elements and amplifier modules are disposed in a closely packed triangular lattice such that separation between adjacent radiating feed elements is not greater than 2λ;
each respective beamlet has a beamlet width, the beamlet being a function of λ and a beamlet spacing in the far field; and
the beamlet width is approximately 0.1 degree when λ is 15 mm and the beamlet spacing is less than the beamlet width.
2. The MBA system of claim 1 , wherein each of the radiating feed elements is associated with only one of the contiguous abutting beams.
3. The MBA system of claim 1 , wherein each beam is formed from a plurality of associated beamlets and each radiating feed element is associated with a single one of the plurality of associated beamlets.
4. The MBA system of claim 1 , wherein the respective coupling is a coaxial connection.
5. The MBA system of claim 1 , wherein the at least one respective amplifier includes a first amplifier and a second amplifier, each amplifier corresponding to orthogonal polarizations.
6. The MBA system of claim 1 , wherein the reflector is approximately 9 meters in diameter, and the beamlet width is approximately 0.1 degrees in a 20 GHz band.
7. The MBA system of claim 1 , wherein the beamlet spacing is approximately 0.07 degrees.
8. The MBA system of claim 1 , wherein, for each beam in the set of contiguous abutting beams, a single carrier is operated.
9. The MBA system of claim 1 , wherein for each beam in the set of contiguous abutting beams, a set of amplifiers is configured to provide soft redundancy.
10. The MBA system of claim 1 , wherein each radiating feed element includes an end-fired element.
11. The MBA system of claim 10 , wherein the end-fired element is configured as a helical, Yagi, crossed Yagi, log periodic, or a stacked patch antenna element.
12. The MBA system of claim 1 , wherein the at least one respective amplifier includes at least one main amplifier and at least one auxiliary amplifier.
13. The MBA system of claim 12 , wherein the at least one main amplifier and at least one auxiliary amplifier are arranged in a Doherty configuration.
14. A spacecraft comprising a communications payload subsystem, the payload subsystem including:
a reflector; and
a plurality of radiating feed elements, configured as a phased array, illuminating the reflector, operable at a frequency having a characteristic wavelength (λ), and configured to produce, in a far field at the reflector, a set of contiguous abutting beams; and
wherein:
the frequency is at least 20 GHz, and λ is no greater than 15 mm and no smaller than 7.5 mm:
the radiating feed element is coupled with and proximate to a respective amplifier module and is associated with a respective beamlet;
the radiating feed elements and amplifier modules are disposed in a closely packed triangular lattice such that separation between adjacent radiating feed elements is not greater than 2λ;
each respective beamlet has a beamlet width, the beamlet being a function of λ and a beamlet spacing in the far field; and
the beamlet width is approximately 0.1 degree when λ is 15 mm and the beamlet spacing is less than the beamlet width.
15. The spacecraft of claim 14 , wherein each of the radiating feed elements is associated with only one of the contiguous abutting beams.
16. The spacecraft of claim 14 , wherein each beam is formed from a plurality of associated beamlets and each radiating feed element is associated with a single one of the plurality of associated beamlets.
17. The spacecraft of claim 14 , wherein the at least one respective amplifier includes a first amplifier and a second amplifier, each amplifier corresponding to orthogonal polarizations.
18. The spacecraft system of claim 14 , wherein the at least one respective amplifier includes at least one main amplifier and at least one auxiliary amplifier.