A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

A deployable assembly comprises a supporting structure, a set of panels, each being linked to the adjacent panel by a hinge defining an intermediate axis of rotation, capable of switching from a stowed configuration in which the panels are folded one on top of the other to a deployed configuration, by rotation of the panels about the respective intermediate axes of rotation, wherein the panels are arranged substantially in the same plane, an articulation device defining a main axis of rotation of the set of panels relative to the supporting structure. The set of panels is rotationally mobile about the intermediate axes of rotation and the main axis of rotation to switch from the stowed configuration to the deployed configuration and the set of panels is only rotationally mobile about the main axis of rotation in deployed configuration to orient the set of panels relative to the supporting structure.

A photovoltaic generator deployable for a satellite stabilized on three axes. The photovoltaic generator includes an assembly of planar panels articulated with respect to each other, and an attachment arm to the structure of the body of the satellite. In a first or launch position of the photovoltaic generator, the planar panels are folded one over the other. In a second or deployed position of the photovoltaic generator, the planar panels are fully deployed with at least a part of the planar panels being photovoltaic panels. At least one planar panel consists of a thermal radiator, with the radiative face thereof being orientated to be opposite the face of the photovoltaic panels carrying the photovoltaic sensors when the photovoltaic generator is in the deployed position. This radiative face is termed the shade face, and the face opposite the panel shaped radiator is termed the sun face.

A spacecraft includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls, disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors. At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array. The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector is disposed, undeployed, forward of the respective feed array, proximate to and outboard of one of the plurality of sidewalls. In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.

A material collection system includes a planar structure, at least one actuator, and a plurality of pull cables. The planar structure includes a plurality of interconnected geometric panels having a plurality of holes therethrough, and each interconnection between two geometric panels defines a foldable coupling. The plurality of pull cables pass through the holes such that a first end of each pull cable is coupled with at least one geometric panel and a second end of each pull cable is coupled with the at least one actuator. The planar structure is operable between a first stable geometric state and a second stable geometric state. An actuation to pull each of the plurality of pull cables transitions the planar structure between the first stable geometric state and the second stable geometric state.

Spacecraft Heat Shield A deployable spacecraft atmospheric-entry heat shield (30, 40, 50, 60) is configured in a flasher pattern with a transformable polyhedral-surface. The transformable polyhedral-surface has a plurality of sectors (2, see FIG. 1a), each sector (2) having a plurality of mountain fold lines (4, 5), a plurality of valley fold lines (6, 7), a plurality of facets (8) lying between the fold lines (4, 5, 6, 7) and an outside edge (12). The heat shield (30, 40, 50, 60) is configured to unfold from a stowed configuration to a deployed configuration.

A self-folding machine comprises a laminate including a flexible layer with a first side and a second side; a first rigid layer including at least one gap laminated to the first side of the flexible layer; a second rigid layer including at least one gap laminated to the second side of the flexible layer, wherein the rigid layers are more rigid than the flexible layer; a first contractible layer laminated to the first rigid layer and extending across at least one gap in the first rigid layer; and a second contractible layer laminated to the second rigid layer and extending across at least one gap in the second rigid layer, wherein the first and second contractible layers retract to respectively create folds in the machine across gaps in the first and second rigid layers when activated.

A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom is provided. Each solar power station includes a plurality of satellite modules. The plurality of satellite modules each include a plurality of modular power generation tiles including a photovoltaic solar radiation collector, a power transmitter and associated control electronics. The power transmitters can be coordinated as a phased array and the power generated by the phased array is transmitted to one or more power receivers to achieve remote wireless power generation and delivery. Each satellite module may be formed of a compactable structure capable of reducing the payload area required to deliver the satellite module to an orbital formation within the space-based solar power station.

A system for compact stowage and deployment of a flexible solar array includes a deployer unit and a blanket container for containing the flexible solar array. The deployer unit includes a frame, a closed-section collapsible mast for deploying and supporting the solar array, a mast stowage reel for supporting the mast in a collapsed stowed state, and an actuator to drive the mast from the stowed state to a deployed state. The frame has a first section extending along a vertical plane and a second section extending along a horizontal plane. The blanket container is pivotably coupled to the frame of the deployer unit. In a stowed state, the blanket container is oriented facing the second section of the frame. In a deployed state, the blanket container is oriented parallel to the vertical plane, and perpendicular to a longitudinal axis of the mast.

This description relates to an extensible space-based infrastructure platform having modules that can be launched in a stowed configuration, placed in orbit, and then deployed to extend the modules away from each other for an integrated infrastructure platform configuration. This infrastructure platform provides power, timing, communications, data management, attitude control, and other vital and non-vital services to docked payloads. Multiple payloads can be launched into orbit, maneuvered into position, and docked with the space-based services platform. Each docked payload utilizes the infrastructure of the space-based services platform and its interconnected network of docked payloads. Multiple space-based platforms can be docked together to provide a larger space-based infrastructure platform with a broader array of services available to all docked payloads and users.