High capacity communication satellite
View Patent ↗A spacecraft includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls, disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors. At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array. The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector is disposed, undeployed, forward of the respective feed array, proximate to and outboard of one of the plurality of sidewalls. In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.
1. A spacecraft, comprising:
a structural interface adapter for mating to a launch vehicle;
an aft surface disposed proximate to the structural interface adapter;
a forward surface disposed opposite to the aft surface;
a main body structure disposed between the aft surface and the forward surface, the main body structure including a plurality of sidewalls disposed between the aft surface and the forward surface; and
a plurality of unfurlable antenna reflectors, at least one unfurlable antenna reflector configured to be illuminated, in an on-orbit configuration, by a respective feed array, wherein:
the spacecraft is reconfigurable from a launch configuration to the on-orbit configuration;
in the launch configuration, the at least one unfurlable antenna reflector is disposed, undeployed, forward of the respective feed array, proximate to and outboard of one of the plurality of sidewalls; and,
in the on-orbit configuration, the spacecraft is disposed with the forward surface being earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.
2. The spacecraft of claim 1 , wherein, in the launch configuration, a portion of the at least one unfurlable antenna reflector is disposed aft of the forward surface.
3. The spacecraft of claim 1 , wherein, in the on-orbit configuration, the at least one unfurlable antenna reflector is illuminated by the respective feed array.
4. The spacecraft of claim 1 , wherein the respective feed array is an active phased array of radiating elements.
5. The spacecraft of claim 1 , wherein the respective feed array is disposed proximate to the aft surface.
6. The spacecraft of claim 1 , wherein each unfurlable antenna reflector is articulably linked with the main body structure by way of a respective deployment boom.
7. The spacecraft of claim 1 , further comprising a rigid antenna reflector and a solar array, wherein:
the spacecraft is configured to operate in an orbital plane, such that the spacecraft has a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin;
the plurality of sidewalls includes, orthogonal to the roll axis, an east sidewall and a west sidewall, and, orthogonal to the pitch axis, a north sidewall and a south sidewall; and
each of the solar array and the rigid antenna reflector is disposed, in the on-orbit configuration, proximate to one of the north sidewall and the south sidewall, the rigid reflector being forward of the solar array.
8. The spacecraft of claim 7 , wherein the rigid reflector is disposed, in the launch configuration, such that an aperture plane of the rigid reflector is approximately orthogonal to the forward surface.
9. A spacecraft, comprising:
a structural interface adapter for mating to a launch vehicle;
an aft surface disposed proximate to the structural interface adapter;
a forward surface disposed opposite to the aft surface;
a main body structure disposed between the aft surface and the forward surface, the main body structure including a plurality of sidewalls disposed between the aft surface and the forward surface; and
at least three antenna subsystems, each antenna subsystem including an unfurlable antenna reflector, wherein:
the spacecraft is reconfigurable from a launch configuration to an on-orbit configuration;
each antenna system is disposed, undeployed, such that, in the launch configuration, the unfurlable antenna reflector is forward of a respective feed array, proximate to and outboard of one of the plurality of sidewalls; and, in the on-orbit configuration, the unfurlable antenna reflector configured to be illuminated by the, respective feed array; and
in the on-orbit configuration, the spacecraft is disposed with the forward surface being earth-facing and each unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the aft surface.
10. The spacecraft of claim 9 , wherein, in the launch configuration, a portion of each unfurlable reflector is disposed aft of the forward surface.
11. The spacecraft of claim 9 , wherein each feed array is an active phased array of radiating elements.
12. The spacecraft of claim 9 , wherein each feed array is disposed proximate to the aft surface.
13. The spacecraft of claim 9 , wherein each antenna reflector is articulably linked with the main body structure by way of a respective deployment boom.
14. The spacecraft of claim 9 , further comprising a rigid antenna reflector and a solar array, wherein:
the spacecraft is configured to operate in an orbital plane, such that the spacecraft has a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin;
the plurality of sidewalls includes, orthogonal to the roll axis, an east sidewall and a west sidewall, and, orthogonal to the pitch axis, a north sidewall and a south sidewall; and
each of the solar array and the rigid antenna reflector is disposed, in the on-orbit configuration, proximate to one of the north sidewall and the south sidewall, the rigid reflector being forward of the solar array.
15. The spacecraft of claim 14 , wherein the rigid reflector is disposed, in the launch configuration, such that an aperture plane of the rigid reflector is approximately orthogonal to the forward surface.
16. A method comprising:
reconfiguring a spacecraft from a launch configuration to an on-orbit configuration; wherein:
the spacecraft includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate to the structural interface adapter, a forward surface disposed opposite to the aft surface, a main body structure disposed between the aft surface and the forward surface, the main body structure including a plurality of sidewalls disposed between the aft surface and the forward surface, an unfurlable antenna reflector and an associated feed array;
in the on-orbit configuration, the spacecraft is disposed with the forward surface being earth-facing; and reconfiguring includes:
repositioning the unfurlable antenna reflector from an undeployed position to a deployed position, the undeployed position being forward of the respective feed array, proximate to and outboard of one of the plurality of sidewalls and the deployed position being earth-facing from a position aft of the associated feed array; and
illuminating the unfurlable antenna reflector with the associated feed array.
17. The method of claim 16 , wherein, in the launch configuration, a portion of the unfurlable antenna reflector is disposed aft of the forward surface.
18. The method of claim 16 , wherein, in the on-orbit configuration, the unfurlable antenna reflector is illuminated by the associated feed array.
19. The method of claim 16 , wherein the associated feed array is an active phased array of radiating elements.
20. The method of claim 16 , wherein the associated feed array is disposed proximate to the aft surface.