Spacecraft exoskeleton truss structure

1. A spacecraft comprising:

a structural interface adapter for mating to a launch vehicle;

at least one radiator panel;

at least one equipment panel;

a first 3-D truss structure proximal to and mechanically coupled with the structural interface adapter; and

a second 3-D truss structure distal from the structural interface adapter and coupled mechanically with the structural interface adapter by way of the first 3-D truss structure; wherein the at least one equipment panel and the at least one radiator panel is coupled mechanically by one or both of the first 3-D truss structure and the second 3-D truss structure with the structural interface adapter; and

each 3-D truss structure includes at least four coupling nodes and at least six strut elements, attached together by a respective plurality of joints, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes.

2. The spacecraft of claim 1 , further comprising ring clamps, wherein the first 3-D truss structure and the second 3-D truss structure are detachably joined together by the ring clamps.

3. The spacecraft of claim 1 , wherein the at least one equipment panel is thermally coupled with the at least one radiator panel by heat pipes.

4. The spacecraft of claim 1 , further comprising:

a propulsion module that includes the first truss structure; and

an antenna module that includes the second truss structure; wherein

the propulsion module includes at least one propellant tank mechanically coupled with the first truss structure; and

the antenna module includes at least one antenna reflector mechanically coupled with the second truss structure.

5. The spacecraft of claim 4 , further comprising a repeater module including electrical payload equipment thermally coupled with the at least one radiator panel and disposed on the at least one equipment panel or on the at least one radiator panel.

6. The spacecraft of claim 4 , further comprising an avionics module including a third 3-D truss structure, wherein the avionics module includes avionics equipment mechanically coupled with the third 3-D truss structure.

7. The spacecraft of claim 6 , further comprising a plurality of ring clamps, wherein:

the first truss structure and the third truss structure are detachably joined together by a first portion of the plurality of ring clamps; and

the second truss structure and the third truss structure are detachably joined together by a second portion of the plurality of ring clamps.

8. The spacecraft of claim 7 , wherein the avionics module is disposed between the propulsion module and the antenna module.

9. The spacecraft of claim 7 , wherein the second 3-D truss structure is coupled mechanically with the structural interface adapter by way of the first 3-D truss structure and the third 3-D truss structure.

10. The spacecraft of claim 7 , wherein the first 3-D truss structure is structurally coupled with the second 3-D truss structure only by way of the third 3-D truss structure.

11. The spacecraft of claim 7 , further comprising a repeater module including electrical payload equipment.

12. The spacecraft of claim 11 , wherein a proximal portion of the repeater module is proximate to a distal portion of the avionics module and a distal portion of the repeater module is proximate to a proximal portion of the antenna module.

13. The spacecraft of claim 12 , wherein, the distal portion of the repeater module is located at a first distance from the structural interface adapter, the proximal portion of the antenna module is located at a second distance from the structural interface adapter, and the first distance is greater than the second distance.

14. The spacecraft of claim 1 , wherein each 3-D truss structure is configured to be fabricated by:

forming a dry fit assembly of a plurality of coupling nodes and a plurality of strut elements, the dry fit assembly being self-supporting;

aligning the dry fit assembly; and

rigidizing each joint.

15. The spacecraft of claim 14 , 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.

16. The spacecraft of claim 14 , wherein rigidizing each joint includes affixing each joint with an adhesive.