Abstract: A system for harvesting solar energy on a spacecraft includes a stiff substrate layer and a working layer disposed on the substrate layer to provide at least one of a photovoltaic or a reflective function. In a first operational state, the substrate layer is arranged as a tape spring to store potential energy which causes the substrate layer to uncoil and provide, in a second operational state, a photovoltaic module and/or a solar concentrator.

Abstract: The present disclosure provides various apparatuses, systems, software, and methods for three-dimensional (3D) printing. The disclosure delineates various optical components of the 3D printing system, their usage, and their optional calibration. The disclosure delineates calibration of one or more components of the 3D printer (e.g., the energy beam).

Abstract: A technique which can reduce a cost of a space machine installed with a solar cell. The space machine is composed of a light collecting unit and the solar cell. The light collecting unit is arranged on a surface of the body of the space machine to collect incident sun light inside the body. The solar cell is installed inside the body to receive the sun light collected by the light collecting unit.

Abstract: A side-by-side dual-launch spacecraft arrangement is provided. The arrangement may include a dual-launch adaptor, a first spacecraft, and a second spacecraft. The first spacecraft and the second spacecraft may be mounted on the dual-launch adaptor and may be arranged side by side on the dual-launch adaptor. An aspect ratio of each of the first and second spacecraft may be within a range of 0.55 and 0.8.

Abstract: A spacecraft comprises a hybrid assembly equipped with at least one solar panel characterized in that said assembly comprises at least one solar cell provided with luminous energy concentration means and said assembly also comprises at least one solar cell with no luminous energy concentration means.

Abstract: A method for producing a heated fluid for use within an engine for propulsion of a vehicle is described. The method includes receiving cooled fluid from a fluid source, directing the cooled fluid between a first window configured to operate as a structural member of the engine and a second window configured to separate the cooled fluid from a heated fluid, passing an electromagnetic beam through the first window and the second window, absorbing the passed electromagnetic beam with a heat exchanger within the engine, and directing the cooled fluid through the heat exchanger to become heated fluid.

Abstract: A system for concentrating solar radiation onto a space debris object to vaporize includes a focusing system, an object tracking system and a positioning system. The focusing system has a total focal length fT, and includes a first focusing device and a second focusing device. The first focusing devices change from a compact state to a deployed state, and the compact surface area is less than the deployed surface area. The object tracking system determines the location of the object. The positioning system orients the focusing system such that solar radiation focuses on the space debris object.

Abstract: A rollable and accordion foldable refractive lens concentrator flexible solar array blanket structure assembly for a spacecraft/satellite application consisting of at least one or more rows of electrically interconnected solar cells and at least one or more rows of deployable elongated refractive lenses elevated and aligned from the top surface of the solar cells. The entire blanket assembly, inclusive of lenses and solar cell substrates, kinematically deploys by unrolling or unfolding the assembly for its stowed package configuration, and the final tensioning of the blanket assembly produces an aligned assembly where the solar cell substrate subassembly and the lens subassembly are coplanar. Deployment of the integrated blanket assembly (with refractive lenses) is directly coupled through the unrolling or the accordion unfolding deployment kinematics of the concentrator blanket assembly.

Abstract: A spacecraft comprises a hybrid assembly equipped with at least one solar panel characterized in that said assembly comprises at least one solar cell provided with luminous energy concentration means and said assembly also comprises at least one solar cell with no luminous energy concentration means.

Abstract: A system for concentrating solar radiation onto a space debris object to vaporize includes a focusing system, an object tracking system and a positioning system. The focusing system has a total focal length fT, and includes a first focusing device and a second focusing device. The first focusing devices change from a compact state to a deployed state, and the compact surface area is less than the deployed surface area. The object tracking system determines the location of the object. The positioning system orients the focusing system such that solar radiation focuses on the space debris object.

Abstract: A solar concentrator includes a plurality of separate panels positioned between opposed support rods. Tension elements extend between the support rods and mount the plurality of panels.

Abstract: Fiber-based debris interceptors are used to intercept and/or contain space debris. The debris interceptors may be made up of fibers that are formed in space from a material supply on a space vehicle. The fibers for the debris interceptors may be formed by extrusion, with a heat source, such as a mirror to focus sunlight, used to heat the material of the material supply that is carried on the space vehicle. The debris interceptor may be separated from the space vehicle, and used to remove debris from an orbit, or otherwise prevent debris entering an orbit from damaging a satellite or other spacecraft that travels in that orbit. The debris interceptor may be deployed prior to later launch of a valuable spacecraft, in order to “cleanse” the intended orbit of debris. Debris objects may pass through the debris interceptor, but in so doing may lose energy so as to de-orbit.

Abstract: A geosynchronous Solar Power Satellite System is created by an artificial gravity, closed ecology, multiple use structure in low earth orbit that manufactures modular solar power panels and transmitter arrays. This facility takes empty fuel tanks and expended rocket boosters from launch vehicles that are sent into low earth orbit, and re-manufactures them into structural components. These components are mated to solar cells that are launched from earth. The modular solar panels are transported to geosynchronous orbit by vehicles with ion engines, where the panels are mated to other solar panels to collect power. Structural components are also mated to transmitter elements launched from earth. These are likewise transported to geosynchronous orbit. They are mated to the solar power collecting panels and they beam the collected power back to earth.

Abstract: A reflective concentrated photovoltaic (CPV) array includes a plurality of Fresnel reflectors connected to and extending outward from a support structure, which direct light onto a CPV panel. The CPV panel is at least thermally connected to the center structure via a heat pipe radiator.

Abstract: A segmented parabolic concentrator includes a concave surface which extends from a central support, the concave surface defines a multitude of flat segments.

Abstract: A low earth orbit system for beaming energy to earth includes a solar reflector that collects and focuses solar light onto a solar panel, transforming it into electricity to drive a diode pumped laser, which then produces a high-power laser beam that is directed to a receiver on the surface of the Earth via a diffractive lens. A steering system of optics and automated hardware controls the beam direction.

Abstract: A solar powered aerial vehicle includes an elongated airframe incorporating lifting and control surfaces, a mechanism for propelling the airframe through the air such that lift developed by the lifting surface is equal to or greater than the weight of the aerial vehicle, a planar solar sail coupled to the airframe and having at least one surface adapted to collect solar energy during the day and to power the propelling mechanism with a first portion of the energy collected, and an apparatus such as a fuel cell/electrolyzer for storing a second portion of the solar energy collected by the solar sail during the day and for powering the propelling mechanism with the second portion of energy during the night. The vehicle is capable of continuous operation at northern latitudes and during the winter months for extended periods without landing or refueling.

Abstract: A flexible inflatable hinge includes curable resin for rigidly positioning panels of solar cells about the hinge in which wrap around contacts and flex circuits are disposed for routing power from the solar cells to the power bus further used for grounding the hinge. An indium tin oxide and magnesium fluoride coating is used to prevent static discharge while being transparent to ultraviolet light that cures the embedded resin after deployment for rigidizing the inflatable hinge.

Abstract: Apparatus, satellite, and method for illumination of at least one solar cell. Apparatus includes at least one solar cell and at least one optical device structured and arranged for an indirect frequency-selective illumination of the at least one solar cell. The at least one optical device reflects spectral components relevant for energy conversion onto the solar cells and guides the spectral components not relevant for energy conversion away from the solar cells.

Abstract: An integrated power and attitude control system and method for a vehicle efficiently supplies electrical power to both low voltage and high voltage loads, and does not rely on relatively heavy batteries to supply power during the vehicle initialization process. The system includes an energy storage flywheel, and a solar array that is movable between a stowed position and a deployed position. The energy storage flywheel is spun up, using electrical power supplied from a low voltage power source, to a rotational speed sufficient to provide attitude control. Then, after the solar array is moved to its deployed position, the energy storage flywheel is spun up, using electrical power supplied from a second power source, to a rotational speed sufficient to provide both attitude control and energy storage.

Abstract: A device is disclosed for reducing the risk of primary and secondary electrostatic discharges occurring in particular in the solar generators of spacecraft. A solar energy concentrator device for spacecraft includes a reflector for reflecting solar radiation onto a photovoltaic cell for converting solar energy into electrical energy and a heat transfer arrangement for transporting to a cold area heat energy stored by the cell following reception of solar radiation. One particular application of the device is to solar panels for satellites.

Abstract: There is an increasingly intense need to harness solar energy due to an ever growing shortage of conventional energy sources, The instant invention is concerned with method and apparatus for solar concentrator micro-mirrors on solar power satellites and the moon to focus and reflect large quantities of solar energy. Method and apparatus are taught for directly reflecting solar energy to the Earth; reflecting solar energy to a microwave converter in space which transmits microwave energy to the Earth; and reflecting solar energy to a laser radiation converter which beams laser radiation to the Earth. The concentrated energy received at the Earth may be converted directly to electricity or indirectly by thermo-mechanical means. The advantages and disadvantages of the different means of sending such concentrated energy to the Earth are discussed. A particularly important objective of this invention is the focussing of sunlight for solar power conversion and production.