Abstract: A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.

Abstract: Exemplary embodiments described herein may include lightweight, low stow volume solar concentrator.

Abstract: Systems and methods described herein include collapsible and deployable antenna structures including shape memory composite components. An example antenna structure includes a base structure comprising a shape memory component; a conductive component; and a support structure creating an inflatable sleeve. The support structure may be configured to support the conductive material and the base structure. The support structure and base structure may work together to deploy the deployable antenna from the collapsed configuration to the deployed configuration. An exemplary method of deploying an antenna structure may include storing the antenna structure in a stored configuration; inflating an inflatable sleeve with an inflation gas to transition the antenna structure from the stored configuration to a deployed configuration defining an antenna shape; and retaining the deployed configuration defining the antenna shape with the shape memory component.

Abstract: Systems and methods described herein include collapsible and deployable antenna structures. The antenna structures may include any combination of shape memory composites, inflatable envelopes, and/or degradable materials.

Abstract: Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.

Abstract: Exemplary embodiments provided herein include connection systems in which a gripper is actuated through introduction of a material to an interior cavity. Embodiments may include more than one cavity such that deployment and actuation may be separately controlled. Additional cavities may also be used and/or selection of valves between cavities such that actuation and/or deployment may further be controlled.

Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

Abstract: Exemplary embodiments provided herein include an attachment and deployment system and method. Exemplary embodiments may use features together or separately as desired. The attachment feature may be used to periodically couple a solar sail.

Abstract: Exemplary embodiments are described herein for compactable antennas and methods of making such an antenna. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.

Abstract: Systems and methods described herein include collapsible and deployable antenna structures. The antenna structures may include any combination of shape memory composites, inflatable envelopes, and/or degradable materials.

Abstract: A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.

Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

Abstract: Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.

Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

Abstract: Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.

Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

Abstract: A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.

Abstract: Exemplary embodiments are described herein for compactable antennas and methods of making such an antenna. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.

Abstract: Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.

Abstract: Systems and methods are described herein that may be used to form a heliostat. Various reflective surfaces and support structures are described that permit lightweight construction of configurable heliostats.