An example system for extraterrestrial deployment of a flexible membrane surface includes a flexible membrane having a periphery and an interior. The flexible membrane is rolled about a roll axis into a cylindrical geometric shape in an undeployed state. A payload base has extendable radial booms, wherein the distal end of each extendable radial boom is attached to the periphery of the flexible membrane and the interior of the flexible membrane is free of attachment to the extendable radial booms. The payload base and the extendable radial booms are positioned to one side of the flexible membrane along the roll axis. The extendable radial booms are configured to extend orthogonally to the roll axis from the payload base to unroll the flexible membrane about the roll axis to form the flexible membrane surface in a deployed state, wherein the roll axis is substantially orthogonal to the flexible membrane surface.

A satellite includes a first radiator panel with first heat-generating components attached to its surface and a second radiator panel with second heat-generating components attached to its surface. One or more actuators are configured to deploy the first and second radiator panels from a compact configuration in which the first and second radiator panels are overlapping to a deployed configuration in which the first and second radiator panels are non-overlapping.

A telecommunication satellite with geostationary orbit comprises an upper module, a lower module, and a lateral module, disposed in a storage configuration between the upper module and the lower module, and deployed to an operational configuration of the satellite in the orbit by a rotation in relation to an axis Z oriented towards the earth in the operational configuration. The lateral module comprises two substantially plane and mutually parallel main surfaces, termed dissipative surfaces, able to dissipate by radiation a quantity of heat generated by facilities of the satellite; the dissipative surfaces being, in the operational configuration, held in a manner substantially parallel to the plane of the orbit, making it possible to limit the solar flux received by the dissipative surfaces and to optimize the quantity of heat dissipated by the lateral module.

A deployable truss with modified primary orthogonal joints. The construction of these joints causes the center-hinged primary chords on opposite sides of a truss bay to fold inward in a plane orthogonal to the folding planes of the side diagonals while the two secondary chords fold in planes orthogonal to the plane of the in-folding primary chords. This provides for stiffness and stability during deploy and retract. The unique joint configuration permits the truss to deploy one bay at a time in a stable manner while having lateral bending stiffness, and the truss thus can extend and retract in a sequential manner. It can deploy integral flat panels nested between the secondary folding chords, or use cross bracing in lieu of panels. The truss can be triangular, square or rectangular in cross-section. A powered support frame may be used in conjunction with the truss.

A method and apparatus for deploying a group of panels. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft.

A method and apparatus for deploying a group of panels. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft.

A method of deploying a space based occulter is provided. The occulter comprises a base portion and a blanket section extending radially from the base portion. A plurality of starlight blocking petals are attached to the base portion and attached to the blanket section, the petals extending radially from the base portion, each of the petals being hingedly connected to an adjacent petal.

A modular, lightweight, high-survivable, photovoltaic flexible blanket assembly for a space solar array is disclosed. The modular blanket is an accordion foldable or rollable flexible photovoltaic solar panel blanket assembly comprising a plurality of common photovoltaic modules spaced in an orthogonal pattern. Each module is mechanically attached with multiple low profile fasteners on their backside to an open weave mesh tensioned backplane structure. The backplane forms a tensioned dimensionally stable planar surface in the deployed configuration onto which the modules are suspended. Each module is common and comprised of a rectangular substrate that includes solar cell assemblies, circuitry, exposed electrical contacts for integration of blanket-level harnessing, and frontside and rearside shielding and coatings as required for the mission application. The blanket assembly may be dispersed with an open pattern of compliant and formable material on the backside to provide insulation against the vigorous vibration of the launch environment.

An elastic roll out boom includes a thin wall, tubular, elongate structure having a plurality of interlocking elements disposed in spaced-apart relation along the surface thereof. The elastic roll out boom is configured to be flattened and rolled tightly to form a roll in a stowed configuration. The plurality of interlocking elements are positioned such that a first interlocking element engages a second interlocking element when the elastic roll out boom is in the stowed configuration. This prevents shear displacement between layers of the roll out boom.

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.