Abstract: An apparatus for collecting solar energy and converting it to electrical energy utilizing solar panels pivotally mounted to a base such that the panels may be pivoted to a storage position inside said base. Additional solar panels may be pivotally mounted on retractable frame trays which stow inside the base when the panels are pivoted to a horizontal position.

Abstract: A photovoltaic solar module having at least one solar cell embedded in synthetic resin and resting on a flexible supporting element and which further includes a sheet-like rigid element reinforcing the solar cell.

Abstract: A solar power satellite (30) includes a truss structure (32) having a plurality of independently controlled solar power modules (34) mounted to one face of the truss structure. The solar power satellite is constructed in orbit by first forming and then assemblying component beam members (50, 52) to the truss structure. The solar power modules (34) are constructed on a fabrication and assembly station (36) movably attached to the truss structure and are then attached to the truss structure. The solar power modules (34) include a primary reflector (200) having a substantially parabolic curvature in cross section. A collector-radiator (202) is mounted on the primary axis of the primary reflector. The cross-sectional configuration of the collector-radiator (202) approximates a flattened inverted S-shape whereon the radius of curvature decreases as the curve approaches both its center and its end furthermost from the primary reflector (200).

Abstract: A carrier membrane supports area covering solar cells and, preferably, is used for energy supply on a spacecraft. The membrane is stretched in a frame between two opposite sides and consists of plastic sheeting covered by a fiber-reinforced plastic fabric. To save weight, prevent insulation problems and thereby increase service reliability, the fabric is made of plastic reinforced with aromatic polyamide fibers in the form of woven crossing bands. The bands extend in the direction in which the membrane is stretched and transversely of the stretched direction.

Abstract: A panel comprising an aluminum honeycomb core and outer face skins of Kevlar, a bi-directional epoxy-reinforced polyparabenzamide fabric which is a thermal and electrical insulator adhering to the core and forming the opposite flat surfaces of the panel. Solar cells are glued directly to one face skin while a set of epoxy-reinforced carbon fiber stiffeners are glued to the other face skin. The composite structure has a coefficient of thermal expansion closely matching that of the solar cells providing a very lightweight and stiff structure.

Abstract: A deployable panel structure for spacecraft solar cell arrays and other collapsible panel structures. The panel structure consists of a number of panel sections mounted edge to edge along parallel hinge lines by hinges which allow the panels to be collapsed accordian fashion toward a support. The panels are attached to and deployed by an extendable boom which is extended from and retractable to the support. In the deployed configuration, the panels are extended to form a planar surface in which the boom is essentially coplanar. The panel sections are formed from a plurality of layers of thin film insulative substrate which is stiffened with ribs formed into the substrate during the manufacturing process. The hinges are formed of the same material as the substrate and bonded to the edges of the panel. The bonding is accomplished while the panels are in the folded, face-to-face position such that maximum stored energy and out-of-plane stiffness is available in the deployed configuration.

Abstract: The present invention relates to a novel system for folding and stabilizing flexible and continuous solar panels including fold lines. The folding system comprises a V-shaped element having arms whose free ends are fixed on both sides of the corresponding fold line of the panel, while the tip of the V is connected to the fold line itself by means of a pull sheet. The arms of the V-shaped element have a camber when the panel is unfolded, so as to exert a pulling force on the fold line, said folding systems being optionally associated with suitable stabilizing systems. The invention is useful in the folding and stabilizing of solar panels.

Abstract: A spacecraft associated deployable support structure which incorporates a ssive mechanism for extending an elongated arm, having a supporting surface, from a position adjacent to the spacecraft into a position extensive in relation to the spacecraft, whereby solar cells or instrumentation mounted on the supporting surface can be employed for their intended use.

Abstract: A solar power supply for a spacecraft comprises an array of semiconductor devices for photovoltaic conversion of sunlight into electrical energy. Each semiconductor device is secured by a substantially stress-free electrically conductive joint to a flexible dielectric substrate that can be folded into a compact stowage configuration or opened into an elongate operational configuration. The stress-free joint is formed by securing an electrical terminal of the semiconductor device to a stress-relieving electrical conductor that is affixed to the substrate. Preferably, the stress-relieving conductor is a metallic wire mesh, a peripheral portion of which is adhesively bonded to the substrate circumjacent an aperture in the substrate. A pattern of metallic traces formed on the substrate provides a circuit for connecting the wire mesh to connectors for coupling electrical power generated by the array of semiconductor devices to an electrical load on the spacecraft.

Abstract: A plurality of lightweight sheets or panels are assembled to form a solar generator, especially for space craft. The panels or sheets which carry the solar cells, are made of fiber compound materials and are secured to a frame structure made of lightweight tubular members. Tensioning elements are operatively interposed between the frame structure and the panel sheets. The corners of the frame structures are provided with connecting elements so that several frames may be interconnected to form still larger assemblies. These assemblies may be folded and unfolded as desired.

Abstract: A lightweight solar cell array for space vehicles powered by solar electric propulsion. The array incorporates a plurality of hinged solar cell units which can be folded for stowage and thereafter extended into a planar configuration. Light is directed onto the solar cell array by a flexible reflector assembly which is carried below the array. The reflector assembly preferably comprises sheets of flexible material stowed on rolls whereby the sheets can be pulled from the rolls into extended positions. The solar cell array and the reflector are carried between two frames, one of which can be moved away from the other to deploy the array and the reflector assembly.

Abstract: The position and attitude of a spacecraft is modified by selectively adjusting the positions of panels and vanes extending from the spacecraft body, relative to the direction of the ambient solar radiation.