Abstract: A spacecraft includes a main body structure and a plurality of deployable modular reflector elements, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the modular reflector elements are disposed in a storage system that includes an arrangement for supporting the modular reflector elements with respect to dynamic launch loads. In the on-orbit configuration, in some implementations, an assembly of the plurality of modular reflector elements forms a large-aperture, offset fed, reflector, the reflector being coupled with a boom or yoke with the main body structure by way of a two or three axis positioning mechanism configured to steer the reflector with respect to the main body structure. In some implementations, in the on-orbit configuration, the plurality of modular reflector elements are assembled to form a large aperture reflective surface that is self-supporting.

Abstract: A spacecraft includes a 3-D closed truss structure including at least four coupling nodes and at least six strut elements, attached together by a plurality of joints, each coupling node including at least two legs, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes. Each coupling node is attached, at respective ones of the plurality of joints, with at least two strut elements. Each strut element is attached at a first end with a first leg of a first coupling node and is attached at a second end with a second leg of a second coupling node, the first leg being substantially longer than the second leg.

Abstract: A spacecraft includes a 3-D closed truss structure including at least four coupling nodes and at least six strut elements, attached together by a plurality of joints, each coupling node including at least two legs, each strut element disposed between and attached with a respective pair of the plurality of coupling nodes. Each coupling node is attached, at respective ones of the plurality of joints, with at least two strut elements. Each strut element is attached at a first end with a first leg of a first coupling node and is attached at a second end with a second leg of a second coupling node, the first leg being substantially longer than the second leg.