A deployable root stiffness mechanism and method increases the bending and torsional stiffness and strength of a tubular slit boom while allowing the slit boom to be flattened and rolled to a compact stowage volume. The slit booms may be flattened and rolled into a compact cylindrical stowage volume and once released, elastically and immediately deploy from the rolled stowed configuration to the final structural tube shape. An embodiment of the disclosed apparatus comprises a base member which is engaging contact with a bottom surface of the tubular slit boom and a reaction member which translates along the base member as the tubular slit boom transitions between the storage configuration to the deployed configuration and between the deployed configuration to the storage configuration. The reaction member provides an opposing reactive force to a load conveyed through the thin-wall construction of the boom. The method provides a means for increasing the bending and torsional stiffness and strength of a tubular slit boom by reacting external loads through the boom walls into a structure which generally conforms to the shape of the boom as it is deployed.

The invention provides an extendible member which is configurable between a coiled form and an extended form. The extendible member comprises: a primary member comprising a sheet of material resiliently biased in a slit tube form, wherein the slit tube can be opened out at the slit to assume an open form in which it has a flattened cross section; at least one resilient secondary member having first and second connections to the primary member at respective different circumferential positions on the primary member, wherein in the extended form, the primary member is in its slit tube form and the resiliency of the secondary member causes at least part of the secondary member to displace towards the slit in the primary member to provide torsional and axial stiffness to the primary member, and wherein in the coiled form, the primary member is in its open form and the secondary member conforms to the flattened cross section of the primary member so that primary and secondary member can be co-coiled. Corresponding methods are also provided.

Gossamer apparatus and systems for use with spacecraft may include a deployable gossamer apparatus. The deployable gossamer apparatus may include a plurality rib members and gossamer material extending therebetween and may be configured in a stowed configuration and a deployed configuration. The rib members of the deployable gossamer apparatus store potential energy used for deployment of the deployable gossamer apparatus.

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, and/or compactible structures and deployment mechanisms used to form and deploy such satellite modules and power generation tiles associated therewith are provided. Each satellite module and/or power generation tile may be formed of a compactable structure and deployment mechanism capable of reducing the payload area required to deliver the satellite module to an orbital formation within the space-based solar power station and reliably deploy it once in orbit.

Disclosed is a system for a satellite, the system including a carrier panel and a tensioning device, the tensioning device being switchable from a holding state, in which it holds the carrier panel in a transportation pose, to a release state, in which it permits movement of the carrier panel from the transportation pose into a working pose, wherein the system is configured such that the carrier panel is elastically deformed in the transportation pose and, after switching the tensioning device into the release state, a restoring force based on the elastic deformation of the carrier panel contributes to the movement of the carrier panel from the transportation pose into the working pose. Furthermore, a corresponding carrier plate and a satellite are disclosed.

An extensible boom is made of a fiber-reinforced composite material. When the extended extensible boom is deployed, in a first area, directions of fiber are a first low-angle direction forming a negative angle to a clockwise direction with respect to an extending direction (A) and a second low-angle direction forming a positive angle to the clockwise direction with respect to the extending direction (A). In a second area, directions of fiber are a first high-angle direction forming a negative angle to a clockwise direction with respect to the extending direction (A) and a second high-angle direction forming a positive angle to the clockwise direction with respect to the extending direction (A). The first low-angle direction is closer to the extending direction (A) than the first high-angle direction, and the second low-angle direction is closer to the extending direction (A) than the second high-angle direction.

A deformable support apparatus includes a deformable body configured to transition between at least an extended state and a contracted state where a stiffness of the deformable body in the extended state is greater than a corresponding stiffness of the deformable body in the contracted state. The deformable body includes a first member and a second member coupled to and in opposition to the first member, and arranged about a longitudinal axis. In the extended state, the first member has at least a first curved portion and the second member has at least a second curved portion. The at least a first curved portion is a positive curved portion with respect to the longitudinal axis and the at least a second curved portion is a negative curved portion with respect to the longitudinal axis.

A deployer for storing and deploying a boom from a satellite, with antennas and sensors attached to the boom. The deployer includes a motor disposed within a drum and a motor shaft coupled to the drum for rotating the drum. The drum has a circular cross section and the boom, stowed in a stowed cross-sectional configuration, is wrapped around the drum with a first end of the boom attached to the drum. As the drum rotates, the boom is deployed. A tensioning mechanism applies radially inward directed forces on the folded and wrapped boom while the motor rotates the drum for deploying the boom. A microprocessor responsive to a plurality of sensors controls boom deployment.

Deployable structures are described, in particular linearly-deployable structures, such as masts or booms. The masts may be stowed for transport and then deployed at their destination in space or on earth. A deployment system includes a storage reel storing a stowed elongate band. A drive mechanism biases and guides the band helically out of the storage reel to form an elongated mast. Adjacent edges of the deployed band may secure together using openings and corresponding protrusions, such as rivets. A welding system may use a rotating welder to weld adjacent edges of the band as it deploys. The band may be formed of multiple band segments attached together by connectors such as doublers. Protrusions such as rivets or other fasteners may attach the connectors to opposing sides of the band segments. A cylindrical space habitat or other macrostructure may be formed using multiple deployable masts that connect large rings.

Deployable structures are described, in particular linearly-deployable structures, such as masts or booms. The masts may be stowed for transport and then deployed at their destination in space or on earth. A deployment system includes a storage reel storing a stowed elongate band. A drive mechanism biases and guides the band helically out of the storage reel to form an elongated mast. Adjacent edges of the deployed band may secure together using openings and corresponding protrusions, such as rivets. A welding system may use a rotating welder to weld adjacent edges of the band as it deploys. The band may be formed of multiple band segments attached together by connectors such as doublers. Protrusions such as rivets or other fasteners may attach the connectors to opposing sides of the band segments. A cylindrical space habitat or other macrostructure may be formed using multiple deployable masts that connect large rings.