Abstract: In the present invention, a diaphragm for pressurizing and heating an encapsulating material is pre-heated to a predetermined temperature before laminating a lamination unit comprising a photovoltaic module and the encapsulating material. As a result, one surface of the lamination unit is heated by a heater provided on a table and the other surface is heated by the diaphragm, so it is possible to prevent appearance of a temperature difference between the surfaces.

Abstract: A tractor and trailer combination, the trailer having a cover for covering a load support surface thereof and a frame assembly is provided which includes a roller and a plurality of solar cell lengths for extending along the cover, the solar cell lengths being movably connected to one another for rolling up of the solar cell lengths about the roller and the roller being removably rotatably mounted relative to the frame assembly. The tractor and trailer combination is a type of vehicle having a planar surface for protectively covering a load carrying surface of the vehicle and collectively flexible solar cell lengths disposable as the outwardly facing side of the planar surface which may additionally include a gas motor fueled by cryogenic fuel, a climate control arrangement supplied with the cryogenic fuel, and a solar thermal energy system for cooling operations.

Abstract: A photovoltaic device and a method for its manufacture. The device essentially comprises a thin film cell layer 14, a contact transfer release sheet 54, and a foil strip interconnect clip 80. The contact transfer release sheet 54 is bonded to the thin film cell layer 14 in vacuum deposition chambers 12 to produce a roll 62 of photovoltaic material. The photovoltaic material is then cut into segments that are referred to as thin film cell stickers 64. The thin film cell stickers have a barrier layer which is removable to expose a ready-to-apply sticker. The stickers 64 are then adhered to a substrate, like glass, and arranged, side by side, in a row 66. Row 66 of stickers 64 is formed into a series or parallel circuit using a conductive foil strip interconnect clip 80. The interconnect clip is used to complete the circuit between adjacent thin film stickers, preferably by crimping the interconnect to adjacent bus bar segments 87 & 91, of adjacent stickers 64.

Abstract: A flexible solar power assembly (2) includes a flexible photovoltaic device (16) attached to a flexible thermal solar collector (4). The solar power assembly can be rolled up for transport and then unrolled for installation on a surface, such as the roof (20, 25) or side wall of a building or other structure, by use of adhesive and/or other types of fasteners (23).

Abstract: A solar panel is operably connected to a power capacitor and associated circuitry which includes at least one diode for ensuring correct current flow direction. The power capacitor is inside a cartridge which is has exterior electrical contacts and overall dimensions enabling it to fit into the space intended for and replace at least one conventional battery. The exterior contacts, in conjunction with the power capacitor and associated electrical circuitry, enable provision of direct current (DC) electrical power of appropriate voltage and amperage to various electronic devices: cellular telephones, personal digital assistants (PDAs), compact disc (CD) and digital video disc (DVD) players, infrared and radio remote controllers, and other low power consumption devices including radios, alarms and calculators, etc.

Abstract: A roll-out solar generator has a roll-out solar cell structure and a roll-out array structure which has a first cross member and is connected with a stowage housing for the solar cell structure. The array structure can be rolled out independently of the solar cell structure and has guiding devices for rolling out the solar cell structure after the array structure has rolled out.

Abstract: An apparatus adapted for use with a solar cell, such as a camera, includes a body and a cover member to which the solar cell is attached, where the cover member is movable between an open position and a closed position with respect to the body of the apparatus. The apparatus further includes an air layer providing member which provides an air layer between the cover member and the body of the apparatus when the cover member is in the closed position, thereby reducing transmittance of heat from the solar cell to the body of the apparatus.

Abstract: A solar module (10) for mounting on motor vehicles, which is provided with a top cover layer (12) and a bottom cover layer (14), between which a solar generator (18) is embedded which has a plurality of electrically interconnected solar cells (20), and with two electrical connections (28, 30) on a connection side for tapping of the solar current generated by the solar generator. There are connections (28, 30) on a connection socket (26) which is located on one side of the solar module (10), and of which the side (32) facing away from the connection side is embedded in a sealed manner between the two cover layers (12, 24).

Abstract: A transparent solar cell and method of manufacture. The method includes steps of providing a transparent substrate. The method also includes forming a first conductive layer overlying the substrate. The method also includes forming a first amorphous silicon layer of a first dopant type overlying the first conductive layer. A step of annealing the first amorphous silicon layer is included. The method also forms a second amorphous silicon layer of a second dopant type, and also anneals the second amorphous silicon layer. A second conductive layer is formed overlying the second amorphous silicon layer. A combination of these steps forms a transparent solar cell structure.

Abstract: The electrically conducting backsides of solar blankets forming arrays are electrically interconnected by electrically conducting hinges. Tubular hinge elements are connected in an electrically conducting manner to edges of the blankets and an electrically conducting hinge pin extends through the tubular hinge elements.

Abstract: A new, large-area, thin-film, flexible photovoltaic structure is disclosed, as well as a general fabrication procedure, including a preferably roll-to-roll-type, process-chamber-segregated, “continuous-motion”, method for producing such a structure. A special multi-material vapor-deposition environment is disclosed to implement an important co-evaporation, layer-deposition procedure performed in and as part of the fabrication procedure. A structural system adapted to create a vapor environment generally like that just referred to is disclosed, as is an organization of method steps involved in the generation of such a vapor environment. Also, a unique, vapor-creating, materials-distributing system, which includes specially designed heated crucibles with carefully arranged, spatially distributed, localized and generally point-like, heated-nozzle sources of different metallic vapors, and a special multi-fingered, comb-like, vapor-delivering manifold structure is shown.

Abstract: A solar cell module comprises a front surface member disposed on a front surface side of a photovoltaic element having at least a semiconductor photoactive layer on a flexible substrate, a back surface member disposed on a back surface side of the photovoltaic element, and a sealing material interposed therebetween. The flexible substrate of the photovoltaic element has a plurality of substantially parallel surface grooves on a surface thereof at the semiconductor photoactive layer side of the flexible substrate. At least one portion of the solar cell module is processed to deform in such a direction that strain generated in a substantially parallel direction to the surface grooves is applied to the photovoltaic element. In this way, a solar cell module can be subjected to deformation-processing that prevents, to the extent possible, cracks in the semiconductor photoactive layer of the photovoltaic elements; in other words, deformation-processing can be achieved without influencing electrical characteristics.

Abstract: The invention provides a process for producing a semiconductor layer by introducing a raw gas into a discharge chamber and supplying high-frequency power to the chamber to decompose the raw gas by discharge, thereby forming a semiconductor layer on a substrate within the discharge chamber, the process comprising the steps of supplying high-frequency power of at least very high frequency (VHF) as the high-frequency power; supplying bias power of direct current power and/or high-frequency power of radio-frequency (RF) together with the high-frequency power of VHF to the discharge chamber; and controlling a direct current component of an electric current flowing into an electrode, to which the bias power is supplied, so as to fall within a range of from 0.1 A/m2 to 10 A/m2 in terms of a current density based on the area of an inner wall of the discharge chamber. A good-quality semiconductor layer can be deposited over a large area at a high speed.

Abstract: A solar generator especially for a spacecraft or space flight body has a plurality of first collector panels hinged to each other in a column extending in a first direction (D1) when the first collector panels are unfolded and a plurality of second panels coupled to the first panels so that the second panels can be unfolded in a second direction (D2) only after the first panels have been unfolded. The second panels are coupled to the first panels by journal struts or by hinges so that at least one first panel forms with at least one second panel, preferably with two or more second panels, a panel packet. The hinges (40) that articulate the first panels to each other permit unfolding the panel packets in said first direction (D1), whereupon the second panels in the individual packets can be unfolded in the second direction (D2).

Abstract: A power sphere preferably used as part of a nanosatellite is formed using a plurality of flat panels solar arrays interconnected together by rotating hinges to approximate a spherical shape for use as an enclosure of a payload. The solar array panels are supported by an extending internal strut. The spherical shape provides attitude insensitive solar energy collection and heat radiation.

Abstract: An apparatus and method for recharging a handheld computing device using solar power is provided. A recharger housing includes a first slot for receiving a handheld computing device. A solar panel support member is slidably attached to the recharger housing. A solar panel is connected to the solar panel support member for recharging the handheld computing device when the solar panel support member is in an extended position.

Abstract: This invention comprises deposition of thin film photovoltaic junctions on metal substrates which can be heat treated following deposition in a continuous fashion without deterioration of the metal support structure. In a separate operation, an interconnection substrate structure is produced in a continuous roll-to-roll fashion. In this way the interconnection substrate structure can be uniquely formulated from polymer-based materials since it does not have to endure high temperature exposure. Cells comprising the metal foil supported photovoltaic junctions are then laminated to the interconnection substrate structure. Conductive interconnections are deposited to complete the array. The conductive interconnections can be accomplished with a separately prepared interconnection component.

Abstract: A novel energy producing flexible material is provided particularly suited for high altitude and stratospheric applications. The flexible energy producing covering includes a flexible solar cell layer, a flexible substrate which preferably matches the shape and size of the airship gore as well and an electrically conductive conduit disposed in a flexible electrically non-conductive adhesive connecting the flexible solar cell substrate to the airship substrate. Preferably two electrically conductive conduits are provided between the substrate layer and the flexible solar cell layer with the electrically conductive conduits being insulated from one another by the non-conductive adhesive. The novel process provided by the invention for joining the airship substrate to the flexible solar cell substrate includes heat, pressure and the selection of substrate materials and in certain applications the use of a vacuum.

Abstract: A satellite solar array performance optimizing system that isolates a subsection of a solar array to provide power during transfer orbit operation, then connects the subsection in series with an adjacent section to maintain maximum power output at the satellite operating bus voltage. The isolated subsection is provided on an outer panel populated with solar cells in series calculated according to the parameters of the satellite mission to provide maximum power output matching the operating bus voltage. The outer panel subsection of solar cells is connected directly to the operation bus by a passive diode or a mechanical switch such as a latching relay. An adjacent or intermediate panel has a section of solar cells that are connected in series with the subsection of the outer panel and connected through a blocking diode to the operating bus.

Abstract: A portable solar module cart is provided which comprises a platform, a pair of wheels attached to opposite sides of the platform, a pair of support struts attached to opposite sides of the platform and movable relative to the platform between a first retracted position in which they lie substantially parallel to the platform and a second erected position in which they extend at a selected angle to the platform so that a DC power source can be disposed on and supported by the platform, a solar panel pivotally mounted to the struts, the solar panel being movable on its pivot when the struts are in their erected position so as to be in a perpendicular relationship with an imaginary line connecting the sun and the solar panel, whereby to maximize the solar energy collected by the panel, and means for locking the solar panel in any selected position on its pivot.

Abstract: One embodiment of the present invention is a solar cell array intended for use in space. The solar cell array includes a lightweight, compressible concentrator which can be efficiently deployed. The solar cell array includes a first column of solar cells and a second column of solar cells. A reflective concentrator may be positioned between the first column of solar cells and the second column of solar cells. The reflective concentrator may include a thin film material, where the reflective concentrator is compressible to a first height when in the stowed position. A spring may be coupled to the concentrator, wherein the spring urges the reflective concentrator to a second height when the reflective concentrator is deployed.

Abstract: A transparent solar cell and method of manufacture. The method includes steps of providing a transparent substrate. The method also includes forming a first conductive layer overlying the substrate. The method also includes forming a first amorphous silicon layer of a first dopant type overlying the first conductive layer. A step of annealing the first amorphous silicon layer is included. The method also forms a second amorphous silicon layer of a second dopant type, and also anneals the second amorphous silicon layer. A second conductive layer is formed overlying the second amorphous silicon layer. A combination of these steps forms a transparent solar cell structure.

Abstract: An improved solar panel for a spacecraft. The solar panel has a rigid base, at least one row of solar cells, and at least one elongated, collapsible, self-deploying reflector. Preferably, a plurality of rows and the reflectors are mounted on the face of the base and are generally parallel to each other in an alternating fashion. The deployed reflector forms a triangular shape having a first and second reflecting side that reflects radiation onto adjacent rows of solar cells. The collapsible reflector has a reflector sheet and an erector that deploys the sheet to form the triangular shape. The sheet is mounted to the base along its two lengthwise edges. The erector is mounted to the base beneath the sheet and adjacent to one of the sheet's lengthwise edges. The erector has a rigid erector arm that tilts upwardly to engage the underside of the sheet and to deploy the sheet into the triangular shape.

Abstract: A shape memory alloy hinge assembly for deploying at least a first object in a controllable, substantially shockless manner is disclosed. Generally, the hinge assembly includes at least a first flexure member capable of moving from a first, folded configuration to a second, straightened configuration, and a controller for controlling the movement of at least the first flexure member as the first flexure member moves or reconfigures from the folded configuration to the straightened configuration.

Abstract: The power to weight ratio obtained with a spacecraft's solar array (3) is enhanced by a factor of at least two to five through use of support structure for individual solar panels or solar arrays (31a-17a) containing a curved outwardly bowed surface as deployed that packs essentially flat for storage. Defining a D-shaped wing (15a) in cross-section as deployed, the support structure (4 & 6) for a string of solar cells (10, FIG. 3) provides greater inertia and thereby greater rigidity than prior designs. One member (4) to the support structure is relatively flexible. One-hundred and eighty degree strain energy hinges (19) carried by the other support member (6) outwardly bows that flexible to define a curved sector when the support structure is released from the stowed condition in which the support structure is held relatively thin and flat.

Abstract: Flexible, lightweight reflective sheets are positioned to concentrate solar radiation upon spacecraft solar panels. The sheets are positioned with inner and outer spring members which urge each sheet towards a planar configuration and further urge the sheet in a rotation away from a solar panel face. Restraint members in the form of tethers limit this rotation to place the sheet in a deployed position in which it defines an angle with the panel to reflect solar radiation onto the panel face. The increased incident radiation permits a reduction of the number of solar cells with consequent savings in spacecraft cost and weight. The spring members are configured to permit rotation to a stowed position behind the solar panel. In this position, the tethers are received into guides which are configured to initiate automatic deployment of the spring members and their reflective sheets.

Abstract: A lightweight photovoltaic concentrator is disclosed. The concentrator comprises at least two sections each comprising a cell panel, a radiator panel and a reflector panel. In one embodiment, the concentrator system of the present invention comprises at least two hinged sections each comprising a solar cell panel, a flat radiator panel, and a curved reflective concentrator panel. The solar cell panel comprises at least one photovoltaic cell for generating electrical power in response to radiation. The solar cell panel is aligned with the radiator panel at an angle less than 180 degrees but not less than 90 degrees facing the reflective concentrator panel. In another embodiment, the cell panels on adjoining sections are angled in opposite directions with respect to the radiator panels and wherein the reflective concentrator panels are located on opposite sides of the radiator panels. A heat pipe or loop heat pipe is located in the radiator panel to dissipate heat from the solar cells.

Abstract: A novel, high-efficiency, extremely light-weight, inflatable refractive solar concentrator for space power is described. It consists of a flexible Fresnel lens, flexible sides, and a back surface, together enclosing a volume of space which can be filled with low pressure gas to deploy the concentrator on orbit. The back surface supports the energy receiver/converter located in the focal region of the Fresnel lens. The back surface can also serve as the waste heat radiator. Prior to deployment, the deflated flexible lens and sides are folded against the back surface to form a flat, low-volume package for efficient launch into space. The inflatable concentrator can be configured to provide either a line focus or a point focus of sunlight. The new inflatable concentrator approach will provide significant advantages over the prior art in two different space power areas: photovoltaic concentrator arrays and high-temperature solar thermal conversion systems.

Abstract: An apparatus comprising a solar battery, or a device adapted to be used with the apparatus, includes a first arrangement for driving the apparatus into a redetermined state so as to prevent the apparatus from being adversely affected by heat from illumination light impinging on the solar battery, and a second arrangement for driving the apparatus into a state different from the predetermined state by using a driving force of the first arrangement.

Abstract: For facilitating work and improving durability of a grounding conductor without a need for preparation of a separate grounding conductor for grounding a solar cell array, a solar cell array is provided comprising a plurality of solar cell modules each comprising a solar cell element and an electroconductive outer portion, the plurality of solar cell modules being electrically connected by an electric wire, wherein the electric wire has a plurality of cores, at least one of the cores being connected to an electric connection portion for leading a power of the solar cell elements out and at least one of the cores being connected to a grounding portion.

Abstract: An apparatus adapted to use a solar battery or an apparatus applied to such an apparatus comprises a first cover which is provided on the apparatus adapted to use the solar battery, a second cover which is provided on the apparatus adapted to use the solar battery and which is capable of moving independently of the first cover, and an opening device for opening both of the first and second covers when a temperature rise occurs.

Abstract: Solar panel assembly comprising a number of rectangular panels each carrying solar cells on one of the two main surfaces, said panels being interconnected by mutually parallel hinges such that the assembly from a first state, in which the panels are folded zigzag wise into a package, can be brought into a second state in which the package is unfolded and the panels are situated alongside each other in one plane. In the unfolded state each panel is curved in a direction parallel to the panel edges to which said hinges are attached.

Abstract: The device for tensioning sheet material applies a tensioning force around he outer edge of a sheet material to prevent the sheet material from wrinkling. These devices are attached to a supporting member forming the outer frame of a structure upon which the sheet material is to be attached and consist of tape strips or wires attached to or free sliding along the support member, sheet material of a differing material wrapped around the support member and attached to the main sheet material, with or without holes or slots, and extensions of the main sheet material around the support member, with or without heat created depressions along the border to relieve tearing stresses. Another tensioning member is a corner brace between perpendicular segments of the supporting member to remove wrinkles caused by manufacturing irregularities.

Abstract: A reflector system for a solar wing is provided in which adjacent reflector panels are inhibited from relative movement by coupling tethers. Each reflector panel rotates to be in a stored position adjacent a backface of a respective solar panel. From this stored position, each reflector panel then rotates to be in a deployed position in which it forms a reflection angle with a solar cell face of the respective solar panel. Because of the inhibition of the tethers, the reflector panels deploy together so that one of them does not move past another of them and damage its reflection surface. Upon deployment of a solar wing, a set of spring-biased reflector sheets are automatically urged to cover respective apertures which facilitate installation of restraint structures that maintain the solar wing in its stored configuration.

Abstract: In a solar cell including a photoelectric conversion layer 14 disposed on a flexible substrate 11 and constituted by a laminated layer of non-single crystalline silicon thin films, the flexible substrate 11 has a coefficient of linear thermal expansion of is 2.0 ppm to 10.0 ppm. By this, the coefficient of linear thermal expansion of the flexible substrate 11 and that of the photoelectric conversion layer 14 become close to each other, so that warp and deformation during manufacturing steps and after the steps are decreased. Further, since stress applied to the photoelectric conversion layer 14 is also lessened, the photoelectric conversion efficiency can be increased.

Abstract: A panel assembly includes a number of rectangular panels each carrying solar cells or a cooling radiator on one of the two main surfaces, where the panels are interconnected mutually by hinges such that the assembly from a first state, in which the panels are folded into a package, can be brought into a second state in which the package is unfolded and the panels are situated alongside each other. A torsion element substantially extends across the other main surface of each panel from a first position on the hinge axis between the panel and the adjoining panel at one side, to a second position on the hinge axis between the panel and the adjoining panel at the other side, whereby the torsion element at or near the first and second positions is attached to the respective adjoining panel.

Abstract: Flexible, lightweight reflective sheets are positioned to concentrate solar radiation upon spacecraft solar panels. The sheets are held with inner and outer spring members which urge each sheet from a gathered edge-stowed configuration towards a deployed, planar configuration. The outer spring members further urge each fully extended sheet to rotate about an axis along the panel's edge in a direction away from the solar panel's face. Restraint members in the form of tethers limit this rotation to place the sheet in a stable deployed position and orientation chosen by design to reflect solar radiation onto the panel face. The increased incident radiation permits a reduction of the number of solar cells needed to satisfy a power requirement, and allows consequent savings in spacecraft cost and weight.

Abstract: A series of solar panels are assembled into an array for use as a source of solar power for a satellite. The panels are designed with diminishing thickness from the yoke to the tip to obtain a constant stress distribution.

Abstract: A transmission for folding out the solar cell panels (3 through 7) folded in an accordion-like manner on a spacecraft (1) has cable pulleys (22 through 27) at the hinges (9 through 14), around pairs of which pulleys endless cables (29 through 33) are wound. To adapt its change in length during temperature changes to the change in the length of the panels (3 through 7) and to increase its rigidity to elongation, the cable (29 through 33) is provided with a plastic sheathing (47, 48) firmly connected to same outside the area of the cable pulleys (22 through 27).

Abstract: This invention concerns a solar roof consisting of unmodified mass-produced roofing elements (1), for example of fiber cement, upon which solar cells (2) which have also been mass produced have been made fast using adhesive or clamps. Each solar cell (2) has a border element (3) on its upper edge upon which a connecting terminal (4) is placed. This connecting terminal (4) has at least one receptacle (5) into which can be inserted an asymmetrically formed plug (6) at the end of a cable (7). All of the named elements (1 to 7) rest on the roofing elements (1) so that no ducts of any kind need to be provided through the roofing elements (1), for example, a longer cable (17) leads from the final roofing element (1) of a row under the next higher overlaying roofing element and under the roof to a converter or direct consumer. The switch type (series or parallel) of the individual solar cells (2) is established by the wiring in the connecting terminal (4).

Abstract: A solar power system for orbiting spacecraft includes a collector surface and attached mirror which is retained in a coiled position around the outer surface of the spacecraft in its launch mode. The system is deployed from the orbiting spacecraft by releasing restraining straps and permitting the mirror and attached collector surface to automatically uncoil as a result of the resilient spring characteristics of the mirror. During orbit, the deployed system extends from one side or both sides of the spacecraft such that the mirrored surface faces the sun. Heating pipes are pivotably disposed between the mirror and the collector surface to also function as spacing struts. The collector surface covered with photovoltaic solar cells made of silicon or Gallium Arsenide-Phosphide (GaAsP) in a first embodiment of the invention, can be replaced by a flat heat pipe for conducting heat energy to the input of an external heat engine electric generator in a second embodiment of the invention.

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: In order to control the deployment of secondary deployment structures in a deployment system that includes both a primary and a secondary deployment, an improved deployment sequencer utilizes the rotational motion of primary deployment structures. In particular, the rotational motion serves to control the retention and release of the secondary deployment structures during the primary deployment. Still more specifically, the deployment sequencer restrains the deployment of the secondary deployment structures until the primary deployment structures have deployed or rotated far enough so that collisions between the secondary deployment structures are avoided.

Abstract: A solar concentrator having flexible retractable reflector panels of a thin lastic film coated with aluminum or silver configured as a trough along the long edges of the solar panel and tilted so as to direct the reflected sunlight onto the solar panel in such a manner that the ray from the extreme outer edge of a reflector panel will fall on the edge of the opposite side of the solar panel, resulting in an even distribution of reflected sunlight on the solar panel for optimum performance. The flexible reflector panels are stowed during launch by rolling them around the booms or around themselves. For launch, the booms with the reflector panel rolled thereon, are stowed against the long edges of the solar panel. After launch, the booms are extended to a an angular position respective to the solar panel, by a system of pulleys and wires that keep tension on the reflector panels as the reflector panels are deployed as the plurality of sections of the solar panel are extended to a flat position.

Abstract: A concentrating solar array consisting of a roll of reflective film which is stretched between tension wires strung between a pair of wire stays. There is a roll of film and a take up roll such that the film can be unrolled from the storage roll and pulled toward the take-up roll to replace degraded film. A pair of extension arms holds a solar cell at a fixed position relative to the solar concentrator film surface to receive concentrated sunlight. The roll of reflective film ensures the life requirements of the solar concentrator can be met in space, by replacing exposed concentrator film as it degrades.

Abstract: A battery charger is provided with a battery charger unit which connects to, and charges a battery Solar cells are used as the source of power for charging the battery, and connecting parts electrically connect the solar cells and the battery charger unit. The battery charger unit is provided with a solar cell compartment for stowing the solar cells batteries when not in use charging a battery.

Abstract: A constrained solar array (24) for a satellite (20) and method for making the same are disclosed. The solar array (24) includes a superstructure (30) with solar cells (80) mounted thereon to provide power to a main satellite body (22) and instruments mounted thereon. A flexible tensile member (40) extends relative to the superstructure (30) and is placed under tension to place the solar array (24) in a constrained condition which reduces thermal transients in and increases the bending frequency of the solar array (24). Preferably, a pair of support arms (34,36) are cantilevered from the superstructure (30). The flexible tensile member (40) pulls upon the support arms (34,36) to apply bending moments to the superstructure (30) to maintain the solar array (24) in a distorted shape.

Abstract: An integrated restraint/release/deployment initiation device 40 suitable for use with mechanisms such as solar panel arrays 22 on a space-based support structure such as a satellite 20 is disclosed. The device 40 comprises a releasable restraining mechanism 70, 90, 92 for applying restraining force to a stowed solar panel array to substantially prevent lateral movement of the solar panels 26a-26d relative to each other and to substantially prevent movement of the solar panel array relative to the support structure. The restraining mechanism provides an adjustable pre-load and tilt adjustment for the solar panel array. A non-explosive actuated releasing mechanism 42, 46 is provided to rapidly release the restraining force applied to the stowed solar panel array.

Abstract: An equipment adapted to use a solar cell, or a device adapted to this equipment, includes a first unit for setting the equipment in a first state in which the equipment is in use, and in a second state in which the equipment is not in use, and a second unit for setting the equipment in a third state for heat insulation, which is different from the first and second states, under a condition in which the solar cell generates electricity.

Abstract: A spacecraft includes a plurality of solar panels interconnected with a power coupler and an electrically operated device to provide power to the device when the solar cells are insolated. The solar panels are subject to bending distortion when entering or leaving eclipse. Spacecraft attitude disturbances are reduced by mounting each of the solar panels to an elongated boom made from a material with a low coefficient of thermal expansion, so that the bending of one panel is not communicated to the next. The boom may be insulated to reduce its bending during changes in insolation. A particularly advantageous embodiment mounts each panel to the boom with a single mounting, which may be a hinge. The single mounting prevents transfer of bending moments from the panel to the boom.