Abstract: A solar panel for a spacecraft has a base with a face, and at least one row of solar cells and at least one elongated reflector are mounted on the face of the base. The reflectors and the rows are mounted generally parallel to each other in an alternating fashion. The reflector has first and second reflecting sides when the reflector is in a deployed position. The reflector is mounted so that the first side of the reflector is adjacent to a row of solar cells and reflects radiation incident on the first side onto the adjacent row of solar cells when the reflector is in a deployed position. Preferably, a plurality of rows and a plurality of reflectors are mounted on the face of the base, with at least one of the reflectors being disposed between two adjacent rows of solar cells.

Abstract: A lightweight structure for space application is deployable from a compact bundle of interconnected struts into a plurality of tiled substantially rectangular bays. Each bay preferably comprises four or six hinged strut members having substantially rectangular cross sections, such that a solar or other suitable blanket may be compactly nested within the bundled struts. In one aspect of the invention, the blanket is attached to two opposed strut members of a six-member strut bundle, such that the blanket is unfolded during deployment of the strut bundle into a substantially rectangular bay. In another aspect of the invention, the blanket is attached to, and held against, a single strut in a strut bundle. After the strut bundle is deployed into a substantially rectangular bay, the blanket is spread across the bay via a cable mechanism or other deployment mechanism.

Abstract: A solar panel for a spacecraft has a base with a face, and at least one row of solar cells and at least one elongated reflector are mounted on the face of said base. The reflectors and the rows are mounted generally parallel to each other in an alternating fashion. The reflector has a first and a second reflecting side when the reflector is in a deployed position. The reflector is mounted so that the first side of the reflector is adjacent to a row of solar cells and reflects radiation incident on the first side onto the adjacent row of solar cells when said reflector is in a deployed position. Preferably, a plurality of rows and a plurality of reflectors are mounted on the face of the base, with at least one of the reflectors being disposed between two adjacent rows of solar cells.

Abstract: A braking apparatus for imparting constant mechanical torque to effect a braking action is capable of operating in a constant, smooth, and adjustable manner, yet operates essentially independent of friction and temperature, as well as independent of rotational speed. The braking apparatus includes a hub assembly having a hub, a collar, a plurality of torsional springs, a spring cap, a spring bushing, and damping means, and a sprocket assembly having a sprocket, a hub bearing, a retaining ring, and a plurality of roller assemblies each of which has a roller. The sprocket assembly is rotatably connected to the hub assembly by a hub assembly spring, a sprocket assembly spring, an adjustment cap, and an adjustment means. The apparatus provides braking by releasably contacting at least one of each of the rollers with at least one of each of the torsional springs so as to deflect and then release the torsional spring as the sprocket assembly rotates about the hub assembly.

Abstract: A solar array according to this invention includes a solar blanket which is folded into adjacent panels that are hinged together in an accordion-folded mode at parallel hinges. A pair of foldable spines is fixed to the panels and runs the length of the array. The hinges are included in the spine. The spines are mounted at one end to a base plate, and also at the other end to a tip plate. The base plate is intended to be attached to the spacecraft structure with a yoke which will provide required standoff for rotational clearance during sun-tracking. A pantograph deployment structure extends between the two plates. It can be retracted for storage and extended to deploy the blanket. A conductive harness is attached to the blanket to collect current from the panels.

Abstract: A solar array with a blanket having solar cells incorporated in modules that can readily be removed, replaced, and accordion-folded to a stowed condition. A scissors array having tracks in which scissors linkages are slidingly fitted enables the array to be stowed or deployed from a container in which the module are interleaved with soft, compressed leaves that protect the blanket from inertial forces during handling and launching.

Abstract: A compressible and deployable antenna includes a top and a bottom plate. A deployable structure is fitted between the plates which can forcibly separate the plates, and place in tension a plurality of foldable unstretchable cords to provide a rigid antenna structure. An antenna conductor is connected to the plates and is coiled around the structure in a helical shape so its convolutions can be brought closer to one another for stowage, and spaced farther apart in deployment.

Abstract: A stowable and deployable concentrator for solar cells. A substrate mounts a row of solar cells. A row of Fresnel lens elements is mounted to the substrate so as to be deflectable toward the substrate in a stowed configuration and biased away from it in the deployed configuration. The Fresnel lens is linear and flexibly mounted in a shaper which shapes it to a proper curvature in the deployed configuration. A pair of these concentrators can be hinged together to form a conveniently stowed and readily deployed combination.

Abstract: A stowable and self-deployable parallelogram-type panel array for solar cells. The array includes two sets of rigid panels, the panels of each set being hinged together, and the sets extending side-by-side along a central axis. The sets are foldable, and are pivoted together at their central points so as to form parallelogram-type structures. A respective yoke is hinged to each set to coordinate the movement of the sets. The yokes are hinged to a base on the opposite side of the axis from their respective set to provide greater structural stability and a higher first node resonant frequency. Deployment force is exerted by self-powered hinges, and are the only source of deployment force. The yokes are joined by gears to coordinate their rotation and thereby the stowing and deploying of the array.

Abstract: A module for forming part of an articulated mast which can be retracted to be stowed and elongated to be deployed, the mast when deployed having a central axis of elongation and a plurality of these modules. Each module has at least three rigid non-folding station rods joined to form a rigid station, and an equal number of non-folding longerons, each hingedly connected to a corner of the station. Four diagonal segments are formed as part of two flexible inelastic cables, which are brought together at a control which always holds one of the cables, and passes the other. The control includes a releasable catch to hold the other cable when its segments are at lengths respective to a deployed module.

Abstract: A powered hinge powered by a hot wax linear actuator, which can provide for bi-directional rotation of the hinge as the consequence of sequential and intermittent energizing and deenergizing sequence of the actuator.

Abstract: A mast forming and deployment system comprising a storage reel for storing a strip of sheet metal wound on the reel, and a tube forming a deployment apparatus. The strip is fed to ploy guides that form the sheet metal into a tube with overlapping edges. A drive system feeds the strip of sheet metal to and through the tube forming apparatus and drives staples which hold together the overlapping edges.

Abstract: A mast which is retractable to a lesser height and volume, and deployable to a greater height, and which when deployed can survive a very high temperature event. All structural elements which are required for structural integrity while the mast is deployed are rigid members made of high temperature resistant material. Where the ends of structural diagonals must move toward one another during retraction, that diagonal is provided as a rigid body of two relatively sliding parts which can be latched in an extended condition when the mast is deployed. A lanyard is provided for unlatching and retraction purposes, which may be sacrificed to a high temperature event.

Abstract: A deployable and retractable mast which can be rotated while deployed, using only one drive means for all three functions. Flexible longerons carry followers which pass through guides in a storage cannister for transition between a coiled retracted condition and an extended deployed condition. The followers pass through a gate opening, past a gate, and when the mast is rotated, the gates enable or prevent followers from taking the longerons into the retracted condition, and entitles rotation of the mast when retraction is disabled.

Abstract: A bearing system providing redundancy of bearing function. An inner race and an outer race are concentric and axially spaced apart from one another. A bearing set includes a pin of individually rotatable bearing wheels. The wheels are mounted by an intermediate retainer. A selector is provided to restrain either of the races from rotation relative to its respective wheel, thereby providing for selection of which race is to be active in providing relative rotation of the races.

Abstract: An adjustment system for a suspension system having the property of providing a zero spring rate response to limited vertical excursions from a reference level, the suspension system including a load suspension spring supported from a load spring anchor. The adjustment system includes a rigid reference element below the suspension spring, bi-directional drive means between the load spring and the load spring anchor, and a probe insertable into an aperture in the reference element. Circuit means are responsive to the location of the probe relative to the reference element, to adjust the elevation of the load spring relative to the reference level and thereby to tend to restore the reference element to the reference level.