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.

A deployable multi-section boom comprising a first hinge assembly including a base section adapted to be attached to a structure, a movable section that is pivotably attached to the base section and a first boom attached to the movable section. The first hinge assembly is configured to allow the first boom to pivot in a first direction to a first predetermined maximum angle with respect to the base section. A first constant torque assembly constantly urges the first boom to pivot in the first direction and includes a component attached to the base section of the first hinge assembly. The multi-section boom includes a second hinge assembly that includes a first section attached to the first boom and a second section that is pivotably attached to the first section. A second boom is attached to the second section of the second hinge assembly wherein the second hinge assembly allows the second boom to pivot in a second direction to a second predetermined maximum angle with respect to the first boom. A second constant torque assembly constantly urges the second boom to pivot in the second direction and includes a component that is attached to the first section of the second hinge assembly. The first constant torque assembly and second constant torque assembly cooperate to configure the multi-section boom in a fully deployed state wherein the constant torque applied to the first boom causes the entire multi-section boom to pivot in the first direction while the constant torque applied to the second boom causes the second boom to simultaneously pivot in the second direction with respect to the first boom while the entire multi-section boom continues to pivot in the first direction. The multi-section boom is fully deployed when the first boom pivots to the first predetermined maximum angle and the second boom pivots to the second predetermined angle.

An imaging system includes a metering structure and a plurality of foldable members disposed around a periphery of the metering structure. Each foldable member in the plurality of foldable members includes an arm comprising a strain deployable composite and a reflector disposed on the arm. The arm in a respective foldable member in the plurality of foldable members is configured to hold the respective foldable member toward the metering structure in a first state and to hold the respective foldable member away from the metering structure in a second state such that the reflector of the respective foldable member forms part of a sparse aperture in the second state.

A roll-out solar array includes a first mandrel having first and second ends and a second mandrel having first and second ends. A hinge extends between the first and second mandrels, such that the roll-out solar array can transition between a stowed position where the mandrels are in a substantially parallel configuration and a deployed position where the mandrels are in a series configuration. A latch may be provided to lock the roll-out solar array in the stowed configuration.

Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.

A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

An artificial-satellite antenna mounted in an artificial-satellite including a satellite body, the artificial-satellite antenna includes solar cell panels, radiators, and conductors that are mechanically and electrically connected to the solar cell panels, in which the solar cell panels and conductors are used as reflectors.