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.

Systems and methods for the in situ extraction of materials, for example lunar regolith, from a celestial body. The systems and methods described herein can be used in outer space or on Earth. A high pressure gas is delivered to loosen up the material and form a borehole. A deployable mast deploys from a stowed, coiled configuration to a linear, deployed configuration into the borehole. A deployable tube may deploy to assist with delivering the gas and/or collecting the loosened material. One or more jets emit the gas. The jets may be supported at a free end of the tube or mast. The jets may direct loosened material through the tube and/or mast toward a collection reservoir. A flow separator may filter the loosened material from the gasses.

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.

A deformable hybrid inflatable boom includes an inflatable tube of a first material having an inflatable tube surface and an inflatable tube longitudinal boom direction in a hybrid inflatable boom inflated state. Each longeron of a plurality of longerons is disposed on the inflatable tube surface and spaced apart from each other and held in place by the inflatable tube, and in the hybrid inflatable boom inflated state the each longeron is extended in a direction of the inflatable tube longitudinal boom direction. A method for deploying a deformable hybrid inflatable boom is also described.

A stereostructure spacecraft of the present invention comprises multiple deployable beam members, multiple tension members, and a spacecraft for storing the deployable beam members and the tension members. The stereostructure spacecraft is formed by deploying the deployable beam members and the tension members around the spacecraft. The deployable beam members stored in the spacecraft are deployed and arranged equidistantly in directions of multiple rotational symmetry axes, the rotational symmetry axes being rotational symmetry axes of a virtual polyhedron that is formed to have a substantial center of the spacecraft as an origin. The tension members support two end portions of two adjacent deployable beam members with tension. The respective end portions of the deployable beam members are simultaneously supported by three or more of the tension members.