High capacity broadband satellite
View Patent ↗A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.
1. A spacecraft, comprising:
a structural interface adapter for mating to a launch vehicle;
an aft surface disposed, in a launch configuration within a fairing of the launch vehicle, proximate to the structural interface adapter;
a forward surface disposed, in the launch configuration opposite to and above said aft surface;
a main body structure disposed between said aft surface and said forward surface;
at least one antenna reflector, wherein, the spacecraft is reconfigurable from the launch configuration to an on-orbit configuration:
in the launch configuration, the antenna reflector is disposed, undeployed, such that no part of the antenna reflector is aft of said forward surface; and,
in the on-orbit configuration the spacecraft is disposed with the aft surface substantially Earth facing and the forward surface substantially facing in an anti-Earth direction and the antenna reflector is disposed, deployed, so as to be Earth facing from a position substantially forward and outboard of the forward surface.
2. The spacecraft of claim 1 , wherein the at least one antenna reflector comprises at least four antenna reflectors.
3. The spacecraft of claim 1 , wherein the at least one antenna reflector is unfurlable.
4. The spacecraft of claim 3 , wherein the at least one antenna reflector has a diameter, when deployed, of at least three meters, and is disposed, when furled, in a relatively compact, approximately cylindrical, volume.
5. The spacecraft of claim 1 , wherein the at least one antenna reflector has a diameter, when deployed, that exceeds three meters and a focal length that exceeds six meters.
6. The spacecraft of claim 5 , wherein an antenna feed illuminating the at least one antenna reflector is located approximately equidistant from the aft surface and the forward surface.
7. The spacecraft of claim 6 , wherein an average length of a plurality of waveguides serving the antenna feed is minimized.
8. The spacecraft of claim 6 , wherein the average length of the plurality of waveguides serving the antenna feed is approximately three meters.
9. The spacecraft of claim 6 , wherein the average line loss associated with the plurality of waveguides is no greater than 3 dB.
10. The spacecraft of claim 6 ,wherein the average line loss associated with the plurality of waveguides is approximately 1.5 dB.
11. The spacecraft of claim 1 , wherein torques resulting from thruster plume impingement on an antenna reflector are substantially eliminated.
12. The spacecraft of claim 1 , wherein an antenna pointing error is less than 0.028 degrees.
13. The spacecraft of claim 1 , wherein an antenna pointing error is less than 0.023 degrees.
14. The spacecraft of claim 1 , wherein the spacecraft is compatible with a plurality of conventional launch vehicles.
15. The spacecraft of claim 14 , wherein the plurality of conventional launch vehicles comprises at least two of: Ariane V, Atlas XEPF, Proton, and Sea Launch.
16. A spacecraft, comprising:
a payload providing a data capacity of at least 200 Gbps and at least 100 user beams;
a structural interface adapter for mating to a launch vehicle;
an aft surface disposed, in a launch configuration within a fairing of the launch vehicle, proximate to the structural interface adapter; and,
a forward surface disposed, in the launch configuration opposite to and above said aft surface;
a main body structure disposed between said aft surface and said forward surface, wherein
the payload comprises at least one antenna reflector; wherein:
the spacecraft is reconfigurable from the launch configuration to an on-orbit configuration;
in the launch configuration, each antenna reflector is disposed, undeployed, such that no part of the antenna reflectors is aft of the forward surface; and
in the on-orbit configuration, the spacecraft is disposed with the aft surface substantially Earth facing, the forward surface substantially facing in an anti-Earth direction, and, each antenna reflector is deployed so as to be Earth facing from a respective position substantially forward of and outboard of said forward surface.
17. The spacecraft of claim 16 , wherein the payload provides a data capacity of at least 400 Gbps distributed across approximately 300 user beams.
18. The spacecraft of claim 16 , wherein the payload is operable at frequencies in the Ka or V-bands.
19. The spacecraft of claim 16 , the at least one antenna reflector comprises at least four antenna reflectors.
20. The spacecraft of claim 16 , wherein the at least one antenna reflector is unfurlable.
21. The spacecraft of claim 20 , wherein the at least one antenna reflector has a diameter, when deployed of at least three meters, and is disposed, when furled, in a relatively compact, approximately cylindrical, volume.
22. The spacecraft of claim 16 , wherein at least one antenna reflector has a diameter, when deployed, that exceeds three meters and a focal length that exceeds six meters.
23. The spacecraft of claim 22 , wherein an antenna feed illuminating at least one antenna reflector is located approximately equidistant from the aft surface and the forward surface.
24. The spacecraft of claim 23 , wherein an average length of a plurality of waveguides serving the antenna feed is minimized.
25. The spacecraft of claim 23 , wherein the average length of the plurality of waveguides serving the antenna feed is approximately three meters.
26. The spacecraft of claim 23 , wherein the average line loss associated with the plurality of waveguides is no greater than 3 dB.
27. The spacecraft of claim 23 , wherein the average line loss associated with the plurality of waveguides is approximately 1.5 dB.
28. The spacecraft of claim 16 , wherein torques resulting from thruster plume impingement on an antenna reflector are substantially eliminated.
29. The spacecraft of claim 16 , wherein an antenna pointing error is less than 0.028 degrees.
30. The spacecraft of claim 16 , wherein an antenna pointing error is less than 0.023 degrees.
31. The spacecraft of claim 16 , wherein the spacecraft is compatible with a plurality of conventional launch vehicles.
32. A method of reconfiguring a spacecraft from a launch configuration to an on-orbit configuration, the spacecraft comprising a structural interface adapter for mating to a launch vehicle, an aft surface disposed, in the launch configuration within a fairing of the launch vehicle, proximate to the structural interface adapter, a forward surface disposed, in the launch configuration opposite to and above said aft surface, a main body structure disposed between said aft surface and said forward surface, and at least one antenna reflector, the method comprising:
deploying the antenna reflector from a first position wherein no part of the antenna reflector is aft of said forward surface to a second position wherein the antenna reflector is Earth facing from a position substantially forward of and outboard of said forward surface, wherein, in the on-orbit configuration, the spacecraft is disposed with the aft surface substantially Earth facing, the forward surface substantially facing in an anti-Earth direction.