A method and apparatus provides cube-shaped satellite primary structures, each comprised of six identical, or nearly identical, rectangular truss panels and internal struts. The struts, all adjustable in length, connect, and are directed between all cube opposite corners and all cube opposite panel centers. All struts meet at the cube center where they attach rigidly to either a block called the “nucleus fitting” or to a hollow sphere. Each strut attaches to either a ball-socket corner fitting located at the interior corner of the cube, or to a ball-socket panel center fitting located at the panel center interior to the cube.

A magnetically damped mounting and isolation system with pointing capability. A payload is mounted to an isolator plate, a base plate is mounted to a satellite or other space vehicle, and the isolation system provides damping of all six degrees of freedom of isolator plate motion relative to the base plate. Three bidirectional magnetic dampers are connected between the isolator plate and the base plate and arranged to provide the required amount of temperature-independent damping. The bidirectional magnetic dampers can be connected to the base plate and the isolator plate in different configurations based on desired mass and natural frequency characteristics. Flexures which statically position the isolator plate are also designed to optimize normal modes of vibration. The isolation system may include a motion amplification feature to increase magnetic damping effectiveness, and the isolation system may also include active positioning of the payload relative to the satellite.

A magnetically damped mounting and isolation system with pointing capability. A payload is mounted to an isolator plate, a base plate is mounted to a satellite or other space vehicle, and the isolation system provides damping of all six degrees of freedom of isolator plate motion relative to the base plate. Three bidirectional magnetic dampers are connected between the isolator plate and the base plate and arranged to provide the required amount of temperature-independent damping. The bidirectional magnetic dampers can be connected to the base plate and the isolator plate in different configurations based on desired mass and natural frequency characteristics. Flexures which statically position the isolator plate are also designed to optimize normal modes of vibration. The isolation system may include a motion amplification feature to increase magnetic damping effectiveness, and the isolation system may also include active positioning of the payload relative to the satellite.

A debris management system for use in space and a method of controlling space debris is disclosed. In one embodiment, the system includes: (1) a frame, (2) a plurality of material sections, coupled to the frame, that cooperate to form a material structure when deployed from the frame and (3) a plurality of microvehicles, coupled to the plurality of material sections, each one of the plurality including propulsion units configured to eject the each one relative to the frame and pull the plurality of material sections to deploy the plurality of material sections to form the material structure.

A joint for unfolding and locking a solar generator or a reflector, or other aerospace components that can be unfolded, includes two half joints, a joint axis, and a drive. A drive spring of the drive has a progressive characteristic curve over the unfolding angle of the two half joints, which increases over the unfolding, to compensate for a frictional torque that varies over the unfolding angle.

Provided herein are various enhancements for panel inserts which can provide for mounting of threaded fasteners or other mounting members into various panels. In one example, a panel insert carrier comprises a barrel having flanged ends. The barrel comprising an axial bore therein having a threaded surface configured to removably accept a threaded insert. At least one of the flanged ends comprises an aperture for injection of potting around an exterior of the barrel when inserted into a bore hole of a panel.

A device including a first member for supporting a user; and a second member 14, attached to the first member, including a counterbalance portion. The first member and the second member are each moveable, and operable to slide with respect to each other in opposite directions, between a first position and a second position. The device can be operable such that between the first and second positions, the combined center of mass of the device 10 and its user remains substantially fixed. This serves to reduce the extent of forces and vibrations generated by use of the device on the object to which the device is located.

A device including a first member for supporting a user; and a second member 14, attached to the first member, including a counterbalance portion. The first member and the second member are each moveable, and operable to slide with respect to each other in opposite directions, between a first position and a second position. The device can be operable such that between the first and second positions, the combined center of mass of the device 10 and its user remains substantially fixed. This serves to reduce the extent of forces and vibrations generated by use of the device on the object to which the device is located.

A device is provided for unfurling and refurling comprising at least one tape spring having an axis of unfurling and of refurling parallel to an axis X and a rotor capable of rotating about an axis Y perpendicular to the axis X, the tape spring being able, autonomously, to pass from a state in which it is wound around the rotor to an unwound state. The tape spring is mounted bent in two in the shape of a U and comprises a first end fixed rigidly to a first anchor point that may be secured to a stator or to the rotor and a second end wound around the rotor.

A deployable structure comprises a first and second flexible tension members respectively defining a first and second contours of a ring. A first plurality of rigid compression members extends between the first and second contours. Only one end of each first plurality compression member is mounted on the first contour. A second plurality of rigid compression members extends between the first and second contours. Only one end of each second plurality compression member is mounted on the second contour. The first and second plurality of compression members are arranged with a repetitive crossing pattern around the ring. A first plurality of flexible tension members link each end of a compression member mounted on one of said contours to an end of another non-mounted compression member and a second plurality of flexible tension members link each end of a non-mounted compression member to an end of another non-mounted compression member.