Abstract: A substrate structure for lightweight, flexible solar cell arrays, in which a plastic substrate is provided with a structure for discharging accumulations of electrons on its rear face and has appropriate heat emmissivity properties. In one embodiment, a Kapton substrate layer is coated with a grounded aluminum layer, which is suitably painted for emissivity. In another embodiment, a poorly conductive Kapton substrate layer, impregnated with carbon, is used to dissipate the charge, and to provide the appropriate emissivity. In a third embodiment, a grounded VDA layer is sandwiched between two Kapton layers.

Abstract: A solar energy electric generating system for space vehicles is provided which directly generates alternating current from ambient light without the use of inefficient power conversion. Light incident to photocell arrays is mechanically or electrically gated to produce fluctuating DC. A number of transforming devices are provided to convert the fluctuating direct current to alternating current. By varying the frequency and duty cycle of the pulsing output voltage, frequency and phase relative to some reference may be controlled. Additionally, direct current may also be produced efficiently from the same photocell arrays. A closed-loop system is provided for regulation. The rotational torque produced by a rotating shutter version may also be used, under inertial navigation control, to provide a rotational torque for vehicle positioning.

Abstract: A solar energy collector arrangement is comprised of a plurality of parallely arranged strip-like mirrors, preferably made of aluminum with a silver layer on a concavely curved surface and solar cells being arranged on the rear convexly curved surface, upon which the mirror next to the first mentioned one concentrates solar radiation. These mirror strips are suspended by means of cable inbetween two bars so as to change the orientation of them vis-a-vis the sun; the bars, in turn, are preferably pivotably connected to a telescopic mast, there being additionally guide cable for gathering the individual mirrors. The entire arrangement can be pulled together by pulling all mirrors in juxtaposed position and pivoting the transverse bars against the telescopic mast.

Abstract: A novel solar panel is disclosed which has a supporting substrate which is comprised of one or more plies of resin reinforced novoloid fabric.

Abstract: A deployable space panel structure for use in connection with space vehicles such as satellites and the like. The deployable space panel structure includes a first series of interconnected substantially flat panel members and a second series of interconnected substantially flat members. Pivotal connectors that allow substantially free rotational movement interconnect the edges of certain of the flat panel members of the first and second series of interconnected panel members and a deployment mechanism is provided that permit the first series of interconnected panel members to be in a separate plane from the second series of interconnected panel members. This permits the first and second series of interconnected panel members to have greater strength and rigidity than if they were both located in the same plane.

Abstract: A space-based solar operated power module is configured for storage aboard a shuttle and then automatic deployment in the assigned orbit. It includes an articulated base support which is coupled to the ship's frame during deployment, and a chassis module, which also serves as a housing for electrical components of the power supply, and which is connected to the base support. A pair of oppositely extended foldable arms are movably mounted on the chassis sides and each carries an assembly of collapsible solar panels for converting incident radiant energy to electrical energy. The chassis also supports radiator panels which extend from the top of the chassis in the craft's vertical plane. At the start of deployment the shuttle's remote controlled cargo arm is used for lifting the chassis and its appendages from the hold of the ship.

Abstract: A large cylindrically-shaped balloon-like structure having hemispherical ends with fins utilized in conjunction with airflow thereacross based upon Bernoulli's principle for maneuvering and maintaining stability. The balloon is compartmentalized, contains a uniquely designed structural support system, and contains pumps for evacuating the air therein. The structure may be used for any lifting application. In particular solar-energy is collected through a transparent portion of the structure and reflected from shaped surfaces that direct solar energy on energy converting panels. The electrical energy generated is utilized to operate an evacuation system, while the remainder of the electrical energy is beamed by microwaves to a receiving station on earth.

Abstract: A laminar plastics material sheet including a transparent, electrically conductive layer used to cover the front and/or rear surfaces of a spacecraft solar array to alleviate electrostatic charge build-up thereon due to electron bombardment.

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: Electrical power at microwave frequencies produced by solar cells or similar devices on satellite stations in space is phase modulated prior to its being beamed to earth. At the receiving station on earth, the power in the beamed signal is recovered at the modulation frequency. In the first embodiment, the microwave signal from the power originating device drives a circularly polarized antenna; the modulation is achieved by reversing the phase of the drive signals so that the polarization of the propagated wave alternates between right hand and left hand polarization at a 360 Hertz rate. On earth, the detected outputs of the receiving antennas are combined in such a manner to produce a 60 Hertz three phase power signal. In the second embodiment, the microwave signal drives two orthogonal, linearly polarized antennas; the modulation is achieved by gradually changing the phase of the microwave drive signals so that the polarization of the propagated wave rotates at a 60 Hertz rate.

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 solar energy reflector useful in space-oriented apparatus for reflecting the rays of the sun to a panel carrying solar cells. The solar cells generate direct current power for conversion into microwave energy for transmission to the earth or other spacecraft. The reflector comprises a rotating mirror and a fixed mirror arranged to reflect the solar energy rays to the solar cell panel continuously.

Abstract: The present invention relates to the arrangement of an artificial satellite provided with foldable solar generators and antennas. According to the invention, extensions are provided on the articulated flaps and the proximal panels, in order to be able optimally to adjust the distance of the solar generators with respect to the satellite, so that the articulation between the proximal panel and the flap is located above the folded antennas of which the ends are housed between said extensions. The invention results in elimination of the shadow cast by a satellite on its solar generators and the thermal influence of said satellite on the cells of said generators.

Abstract: Disclosed is apparatus for collecting solar energy with means of producing electricity by concentrating solar energy on sets of photovoltaic cells to be either positioned at high altitudes and which may be fitted to balloons or to structures floating on water.

Abstract: A system for compensating the disturbance torques applied to a satellite, which eliminates the requirement for a thruster control loop. The disturbance torque itself is used as the compensating torque in order to super-impose to the incidental misalignment of the solar panel arrays an artificial misalignment that can cause the momentum vector to be adjusted to the desired direction in order to restore the correct attitude of the satellite. The direction of the momentum vector is controlled in orbit only by solar sailing, that is by organizing at prescribed times suitable manoeuvres of one of the solar panels in order to adjust the solar panel array configuration when the roll angle of the satellite exceeds a determined threshold value.

Abstract: A highly efficient battery charging system in which the ampere-hour discharge of the battery is sensed for controlling the battery charging rate. The battery is charged at a relatively high charge rate during a first time period proportional to the extent of battery discharge and at a second lower rate thereafter.

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 system for beaming solar energy from space to an earth location and putting it to useful work either as heat or light energy, or by converting it into some other form of energy such as steam or electrical power. In the system illustrated, a receiver satellite is in polar orbit and a relay satellite is in equatorial orbit, rotating with the earth and therefore stationary with respect to earth location. Solar energy is collected by the receiver satellite through an array of parabolic collectors and focused by a series of mirrors onto a coherent radiation energy generator, preferably a laser beam generator. The laser beam is directed by a mirror to another mirror on the relay satellite which redirects it to a selected earth location. Alternatively, the relay satellite may convert the laser beam to a maser beam to better penetrate clouds, smoke and haze at the earth location.

Abstract: An arrangement or array of solar cells comprises a plurality of cells each having contacting connectors which establish an electrically conducting connection between the individual solar cells. Each solar cell has a connector which projects slightly from the edge thereof and is of a selected profile or shape such that the contacting connectors of adjacent cells may be overlapped and connected to each other for electrical connection in an arrangement in which they do not come in contact with each other adjacent the solar cells.

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 laminar panel assembly which is particularly useful in space vehicles for contact with solar cells includes a first and a second cover layer, a supporting core structure interposed between the cover layers and at least one force infeed element disposed within the core structure between the cover layers. The force infeed element includes at least one solid central piece for punctiform load infeed, and shear webs extending from the central piece radially outwardly in a branched formation such that the number of shear webs increases with increasing radial distance from the central piece.