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 compliant hinge for deployable membrane-like structures and other applications is provided. The compliant hinge generally includes a flexible intermediate portion having one or more enclosed contours connected by inner longitudinal segments along a longitudinal axis of symmetry. The enclosed contours are resiliently deformable in response to an in-plane load, including tension and shear forces. The compliant hinge allows for rotation, bending, and extension, and can interconnect rigid panels in tensioned precision structures and other applications.

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 sparse-isogrid columnar lattice structure including rigid ring frames connected by a mirrored symmetric double helix pattern comprised of first shell hinge elements in a first helical pattern and second shell hinge elements in a second helical pattern oriented in an opposite direction to the first helical pattern and congruent thereto. The helical axes of the first and second helical patterns intersect the respective centers of the ring frames. The first and second shell hinge elements are configured to stow in a stored energy state when the ring frames are collapsed toward one another along the helical axis, and the first and second shell hinge elements are configured to release the stored energy to deploy to a restored state and extend the ring frames apart from each other along the helical axis when deployed to form a stable rigid axial column in a restored state.

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 compliant hinge for deployable membrane-like structures and other applications is provided. The compliant hinge generally includes a flexible intermediate portion having one or more enclosed contours connected by inner longitudinal segments along a longitudinal axis of symmetry. The enclosed contours are resiliently deformable in response to an in-plane load, including tension and shear forces. The compliant hinge allows for rotation, bending, and extension, and can interconnect rigid panels in tensioned precision structures and other applications.