Abstract: A spacecraft includes 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. The at least one equipment panel and the at least one exterior 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. 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.

Abstract: 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.

Abstract: A lattice structure includes a plurality of strut elements, each strut element formed by coupling one or more lengths of uncured graphite fiber reinforced polymer (GFRP) tow or yarn with posts so as to form a lattice, then curing the lattice. The lattice may include a plurality of open tetrahedral-like truss arrangements, each open tetrahedral-like truss arrangement including six strut elements and four posts.

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 lattice structure includes a plurality of strut elements, each strut element formed by coupling one or more lengths of uncured graphite fiber reinforced polymer (GFRP) tow or yarn with posts so as to form a lattice, then curing the lattice. The lattice may include a plurality of open tetrahedral-like truss arrangements, each open tetrahedral-like truss arrangement including six strut elements and four posts.

Abstract: Design of a 3-D truss structure, including a plurality of coupling nodes and a plurality of struts, is optimized by performing a quantitative optimization of an objective function corresponding to a figure of merit of the design. The quantitative optimization includes: generating a finite element analysis model, the analysis model a 3-D lattice mesh of strut-like finite elements; computing, with the finite element analysis model, a value for the objective function; and optimizing the objective function by executing at least two cycles of an optimization loop. The optimization loop includes a) computing a respective parameter of each strut-like finite element; b) deleting, from the finite element analysis model, selected finite elements for which a resulting mechanical property is less than a threshold; (c) computing an updated value for the objective function; and repeating the optimization loop until the objective function is within a desired tolerance of the specified value.

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: Design of a 3-D truss structure, including a plurality of coupling nodes and a plurality of struts, is optimized by performing a quantitative optimization of an objective function corresponding to a figure of merit of the design. The quantitative optimization includes: generating a finite element analysis model, the analysis model a 3-D lattice mesh of strut-like finite elements; computing, with the finite element analysis model, a value for the objective function; and optimizing the objective function by executing at least two cycles of an optimization loop. The optimization loop includes a) computing a respective parameter of each strut-like finite element; b) deleting, from the finite element analysis model, selected finite elements for which a resulting mechanical property is less than a threshold; (c) computing an updated value for the objective function; and repeating the optimization loop until the objective function is within a desired tolerance of the specified value.