Abstract: The Structural Origami ARray (SOAR) concept is an extremely high performance, deployable solar array system that delivers high power output and exceeds state-of-the-art packaging efficiencies. Unlike existing Z-folding panels or rolled architectures, this approach utilizes an origami-inspired two-dimensional packaging scheme of a flexible blanket/substrate that is coupled with a simple and compact deployable supporting structure that stabilizes the array by external tension or internal support. This enables large deployed areas populated with high efficiency photovoltaic (PV) cells or antenna elements, which compactly stows in a square form factor with thin stack height that minimizes impingement on spacecraft bus internal volume.

Abstract: The Structural Origami ARray (SOAR) concept is an extremely high performance, deployable solar array system that delivers high power output and exceeds state-of-the-art packaging efficiencies. Unlike existing Z-folding panels or rolled architectures, this approach utilizes an origami-inspired two-dimensional packaging scheme of a flexible blanket/substrate that is coupled with a simple and compact deployable supporting structure that stabilizes the array by external tension or internal support. This enables large deployed areas populated with high efficiency photovoltaic (PV) cells or antenna elements, which compactly stows in a square form factor with thin stack height that minimizes impingement on spacecraft bus internal volume.

Abstract: A foldable segmented structure includes a substantially center portion and a plurality of strut assemblies radially disposed around the center portion. Each strut assembly includes an inner and outer strut. The inner strut includes a first end portion rotatably coupled at the center portion and a second end portion rotatably coupled to the outer strut at an intermediate portion of the strut assembly. The intermediate portion is spaced apart from the center portion. At least one shell segment is disposed on at least one of the inner and outer strut. Each inner strut is configured to rotatably articulate about the first end portion in a first angular direction. Each outer strut is configured to rotatably articulate about the second end portion in a second angular direction opposite to the first angular direction to form an axially extending structure from the center portion to the intermediate portion in a stowed configuration.

Abstract: The Structural Origami ARray (SOAR) concept is an extremely high performance, deployable solar array system that delivers high power output and exceeds state-of-the-art packaging efficiencies. Unlike existing Z-folding panels or rolled architectures, this approach utilizes an origami-inspired two-dimensional packaging scheme of a flexible blanket/substrate that is coupled with a simple and compact deployable supporting structure that stabilizes the array by external tension or internal support. This enables large deployed areas populated with high efficiency photovoltaic (PV) cells or antenna elements, which compactly stows in a square form factor with thin stack height that minimizes impingement on spacecraft bus internal volume.

Abstract: The Structural Origami ARray (SOAR) concept is an extremely high performance, deployable solar array system that delivers high power output and exceeds state-of-the-art packaging efficiencies. Unlike existing Z-folding panels or rolled architectures, this approach utilizes an origami-inspired two-dimensional packaging scheme of a flexible blanket/substrate that is coupled with a simple and compact deployable supporting structure that stabilizes the array by external tension or internal support. This enables large deployed areas populated with high efficiency photovoltaic (PV) cells or antenna elements, which compactly stows in a square form factor with thin stack height that minimizes impingement on spacecraft bus internal volume.

Abstract: Multi-axis compliant hinges used in conjunction with strut elements to form a collapsible structure. The hinges behaves similar to a pin-clevis hinges but have increased compliance during the deployment sequence allowing connected struts to translate and rotate finite amounts relative to each other. Once deployed, the hinges lock out to form strong and stiff joints. The hinge uses two opposing resilient tape spring surfaces for each axis. The opposing tape spring surfaces of each axis are joined together by rigid inserts at their ends opposite the common connection point and to which structural members or struts are connected.

Abstract: A non-planar surface support structure that is compatible with deployable thin shell reflector segments. The structure is composed of multiple four strut closed loops connected to compliant hinges at the nodes to create an effective surface. The deployed surface shape is determined by the strut lengths (L) and the node locations and the packaged compatibility constraint in which L1+L3?L2?L4 approximately equals zero. Each of the compliant hinges have degrees of freedom such that the compact configuration of the support structure is obtained by the translation of two opposite nodes of each loop upwards and the remaining two nodes downwards in a continuous process until all struts are approximately parallel and tightly bundled and the hinges lock out all degrees of freedom in the deployed configuration.