Spacecraft exoskeleton truss structure
View Patent ↗A spacecraft includes a structural interface adapter for mating to a launch vehicle, at least one radiator panel, at least one interior equipment panel and a 3-D truss structure. The 3-D truss structure is mechanically coupled with the structural interface adapter, the at least one radiator panel, and the at least one interior equipment panel, and at least a portion of the 3-D truss structure is disposed between the radiator panel and the interior panel.
1. A spacecraft comprising:
a structural interface adapter for mating to a launch vehicle;
at least one radiator panel;
at least one interior equipment panel; and
a 3-D truss structure including at least four coupling nodes and at least six strut elements, attached together by a plurality of joints, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes; wherein:
the at least one interior equipment panel and the at least one exterior radiator panel is coupled mechanically by the 3-D truss structure with the structural interface adapter.
2. The spacecraft of claim 1 , wherein a first plurality of heat dissipating units is disposed on a first side of the at least one interior equipment panel and a second plurality of heat dissipating units is on a second side, opposite to the first side, of the at least one interior equipment panel.
3. The spacecraft of claim 1 , wherein the at least one interior equipment panel is thermally coupled with the at least one radiator panel by heat pipes.
4. The spacecraft of claim 1 , wherein at least a portion of the 3-D truss structure is disposed between the radiator panel and the interior panel.
5. The spacecraft of claim 1 , wherein each respective pair of the plurality of coupling nodes includes a first respective coupling node mechanically coupled with a second respective coupling node by way of a respective one of the at least six strut elements, the respective one of the at least six strut elements being attached at a first end with a first leg of the first respective coupling node and attached at a second end with a second leg of the second respective coupling node, the first leg being substantially longer than the second leg.
6. The spacecraft of claim 1 , wherein the at least one radiator panel is substantially parallel to the at least one interior equipment panel.
7. The spacecraft of claim 6 , wherein, in a launch configuration, the radiator panel is parallel with a velocity vector of the launch vehicle.
8. The spacecraft of claim 6 , wherein the radiator panel is orthogonal to a pitch axis of the spacecraft.
9. The spacecraft of claim 8 , wherein, the radiator panel is substantially longer than the interior equipment panel in a direction parallel to the yaw axis.
10. The spacecraft of claim 1 , wherein the truss structure is configured to be fabricated by:
forming a dry fit assembly of the plurality of coupling nodes and the plurality of strut elements, the dry fit assembly being self-supporting;
aligning the dry fit assembly; and
rigidizing each joint.
11. The spacecraft of claim 10 , wherein the dry fit assembly includes one or more dry fitted joints configured to resist gravitational forces and incidental contact, and to yield to a persistently applied force in the range of about 5-30 pounds.
12. The spacecraft of claim 10 , wherein rigidizing each joint includes affixing each joint with an adhesive.
13. A spacecraft comprising:
a structural interface adapter for mating to a launch vehicle;
at least one radiator panel;
at least one interior equipment panel; and
a 3-D truss structure; wherein:
the at least one interior equipment panel and the at least one exterior radiator panel is coupled mechanically by the 3-D truss structure with the structural interface adapter; and
at least a portion of the 3-D truss structure is disposed between the radiator panel and the interior equipment panel.
14. The spacecraft of claim 13 , wherein a first plurality of heat dissipating units is disposed on a first side of the at least one interior equipment panel and a second plurality of heat dissipating units is on a second side, opposite to the first side, of the at least one interior equipment panel.
15. The spacecraft of claim 13 , wherein the 3-D truss structure includes at least four coupling nodes and at least six strut elements, attached together by a plurality of joints, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes.
16. The spacecraft of claim 15 , wherein each respective pair of the plurality of coupling nodes includes a first respective coupling node mechanically coupled with a second respective coupling node by way of a respective one of the at least six strut elements, the respective one of the at least six strut elements being attached at a first end with a first leg of the first respective coupling node and attached at a second end with a second leg of the second respective coupling node, the first leg being substantially longer than the second leg.
17. The spacecraft of claim 16 , wherein the truss structure is configured to be fabricated by:
forming a dry fit assembly of the plurality of coupling nodes and the plurality of strut elements, the dry fit assembly being self-supporting;
aligning the dry fit assembly; and
rigidizing each joint.
18. The spacecraft of claim 17 , wherein the dry fit assembly includes one or more dry fitted joints configured to resist gravitational forces and incidental contact, and to yield to a persistently applied force in the range of about 5-30 pounds.
19. The spacecraft of claim 13 , wherein the radiator panel is orthogonal to a pitch axis of the spacecraft.
20. The spacecraft of claim 19 , wherein, the radiator panel is substantially longer than the interior equipment panel in a direction parallel to the yaw axis.