An extensible mast according to the present disclosure includes a first fiber layer made of a fiber-reinforced plastic, a second fiber layer that is arranged in contact with the first fiber layer and made of a fiber-reinforced plastic having a thermal expansion coefficient in a longitudinal direction larger than a thermal expansion coefficient in the longitudinal direction of the fiber-reinforced plastic applied to the first fiber layer, and an electric heating wire arranged on the second fiber layer. The number of times of overlapping of the electric heating wire in different layers when the first fiber layer, the second fiber layer, and the electric heating wire are wound and retracted in a roll shape is minimized. Thus, the elastic restoring force of the extensible mast can be maintained while an increase in weight and volume is suppressed.

A deployable device includes a supporting structure, a mandrel able to move in rotation with respect to the supporting structure about a first axis Z, a membrane able to pass from a rolled-up configuration rolled up around the mandrel about the first axis Z to a deployed configuration deployed along a second axis X substantially perpendicular to the first axis Z. The device comprises two fittings secured to the mandrel at their centre, arranged one on either side of the membrane and comprising first stubs on their periphery, a casing extending between the two fittings, the casing comprising second stubs of a shape complementing the shape of the first stubs, the casing being able to pass from a rolled-up configuration at least partially enveloping the membrane in the rolled-up configuration to a deployed configuration at least partially superposed on the membrane in the deployed configuration.

An extensible boom is extended in an extension direction from a state of being rolled in a cylindrical form, the extension direction being one of short directions of the cylindrical form. Protruding portions and recessed portions are alternately formed at each of one end and another end in a long direction of the cylindrical form. The protruding portions at the one end are located opposite the recessed portions at the other end. The recessed portions at the one end are located opposite the protruding portions at the other end. When the extensible boom is extended along the extension direction, the protruding portions at the one end engage with the recessed portions at the other end, and the recessed portions at the one end engage with the protruding portions at the other end, such that a cylindrical shape is formed along the extension direction.

An atmosphere reentry and landing device for a safe reentry of a rocket stage into the atmosphere and for a safe splashdown thereof. The device includes a ballute which is folded in a first state and unfolded in a second state, a shrouding mechanism which carries out a shrouding of the rocket stage with the ballute, a filling mechanism, and a control unit which controls the shrouding mechanism and the filling mechanism. The ballute is disposed on the rocket stage so that an aerodynamics thereof is not compromised in the first state. The ballute substantially shrouds the rocket stage in the second state. During reentry into the atmosphere, the filling mechanism fills the ballute in the second state with air or a gas from a boundary layer which is created between a plasma formed in front of a surface of the device and the surface of the device.

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.

An expandable antenna includes: a plurality of ribs arranged with a regulated angular pitch at an outer circumferential portion of a hub; and a metal mesh installed between the plurality of adjacent ribs, wherein each of the plurality of ribs is formed in a horizontally elongated thin flat plate shape with elasticity, and a segment to which the metal mesh is attached is formed in a parabolic shape. A flat plane of each of the plurality of ribs is arranged so as to be substantially parallel to a central axis of the hub. The object of the present invention is to provide the expandable antenna which can be easily expanded in outer space with a simple structure and can realize a desired shape after expansion.

The disclosed technology includes systems, methods, and mechanism configurations related to satellite solar panels, including stowing arrangements, deployment sequences, special purpose hinges, hold down and release mechanisms, and associated components for controlled deployment of the satellite solar panels.

The disclosed technology includes systems, methods, and mechanism configurations related to satellite solar panels, including stowing arrangements, deployment sequences, special purpose hinges, hold down and release mechanisms, and associated components for controlled deployment of the satellite solar panels.

A reflective antenna comprising a flexible reflective sheet extending between a central hub and a perimeter edge, and a reflective sheet support mechanism comprising one or more spiral ribs articulated to the reflector sheet at least at several locations along the perimeter edge of the reflective sheet; wherein at a collapsed, stowed position of the reflective antenna the one or more spiral ribs are coiled about a common center and the reflective sheet is folded at a compact configuration, and at an expanded, deployed position the one or more spiral ribs are radially expanded and the reflective sheet is stretched over the expanded one or more spiral ribs, imparting the reflective sheet a parabolic shape.

A spacecraft with a linear extension boom, an antenna feed, and a rigid antenna reflector is provided. The rigid antenna reflector may be connected with one end of the linear extension boom, and the other end of the linear extension boom may be connected with the spacecraft main body. In a launch configuration of the spacecraft, the linear extension boom may be retracted into a stowed configuration, and in an on-orbit configuration of the spacecraft, the linear extension boom may be extended into a deployed configuration, thereby moving the rigid antenna reflector away from the yaw axis of the spacecraft and positioning the rigid antenna reflector such that the focal point of the rigid antenna reflector may be oriented to align on, and be collocated with, the antenna feed. The rigid antenna reflector may be connected with the linear extension boom by a positioning mechanism that provides for adjustment in the angular orientation of the rigid antenna reflector relative to the linear extension boom.