A lightweight, low stow volume solar concentrator/collector may include one or more reflective surfaces comprising a shape memory material. The solar concentrator/collector may include.
Systems and methods are provided herein for making a high precision three-dimensional surface by cutting panels having curved outer edges, aligning the edges of adjacent panels on a mandrel having a curved surface, illuminating the mandrel to show space between the panels, adjusting the panels to bring into precision alignment, using a magnifier and micrometer to readjust the position of the panels relative to each other for a more precise alignment, and adhering the panels together in a precise orientation for creating the high precision three dimensional surface.
A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.
Systems and methods described herein include collapsible and deployable antenna structures. The antenna structures may include any combination of shape memory composites, inflatable envelopes, and/or degradable materials.
Exemplary embodiments include systems and method for making a membrane surface having an axis of revolution using first and second mandrel having precise and accurate working surfaces. The systems and methods may also use gore material that are cut and positioned using the first and second mandrels and seamed together to create the membrane surface.
Systems and methods described herein include collapsible and deployable structures that may be used as antenna, collectors, reflectors, or other large structures. The systems and methods may use modular designs so that larger structures may be obtained for space applications.
Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.
A heating system and method is provided herein that provides a compact storage configuration that can deploy to a deployed configuration to heat an environment, structure, component, etc. The heating system may include a heating source, frame, and deployment device, and power cords, The deployment device may be configured to deploy the system from the stowed configuration to the deployed configuration while reducing stresses on the cords and other system components.
Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.
B64G 1/40 - Arrangements or adaptations of propulsion systems
B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
B65H 75/42 - Cores, formers, supports, or holders for coiled, wound, or folded material, e.g. reels, spindles, bobbins, cop tubes, cans specially adapted or mounted for storing and repeatedly paying-out and re-storing lengths of material provided for particular purposes, e.g. anchored hoses, power cables involving the use of a core or former internal to, and supporting, a stored package of material mobile or transportable attached to, or forming part of, mobile tools or machines
10.
Light Weight, Low Stowed Volume, Space Deployable Batten-less Truss
Systems and methods are provided herein for making a high precision three dimensional surface by cutting panels having curved outer edges, aligning the edges of adjacent panels on a mandrel having a curved surface, illuminating the mandrel to show space between the panels, adjusting the panels to bring into precision alignment, using a magnifier and micrometer to readjust the position of the panels relative to each other for a more precise alignment, and adhering the panels together in a precise orientation for creating the high precision three dimensional surface.
Exemplary embodiments described herein may include lightweight, low stow volume solar concentrator. A solar concentrator may include a support frame; a support structure coupled to the support frame; and a reflective surface coupled to the support structure. A method of concentrating solar rays may include providing a solar collector having a reflector; and positioning the solar collector so that sun's rays hit the reflector.
F24S 23/71 - Arrangements for concentrating solar rays for solar heat collectors with reflectors with parabolic reflective surfaces
F24S 23/72 - Arrangements for concentrating solar rays for solar heat collectors with reflectors with hemispherical reflective surfaces
F24S 20/25 - Solar heat collectors for receiving concentrated solar energy, e.g. receivers for solar power plants using direct solar radiation in combination with concentrated radiation
Exemplary embodiments include systems and method for making a membrane surface having an axis of revolution using first and second mandrel having precise and accurate working surfaces. The systems and methods may also use gore material that are cut and positioned using the first and second mandrels and seamed together to create the membrane surface.
Exemplary embodiments provided herein include an attachment and deployment system and method. Exemplary embodiments may use features together or separately as desired. The attachment feature may be used to periodically couple a solar sail.
Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.
E04H 12/18 - TowersMasts or polesChimney stacksWater-towersMethods of erecting such structures movable or with movable sections, e.g. rotatable or telescopic
Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.
B64G 1/40 - Arrangements or adaptations of propulsion systems
B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
B65H 75/42 - Cores, formers, supports, or holders for coiled, wound, or folded material, e.g. reels, spindles, bobbins, cop tubes, cans specially adapted or mounted for storing and repeatedly paying-out and re-storing lengths of material provided for particular purposes, e.g. anchored hoses, power cables involving the use of a core or former internal to, and supporting, a stored package of material mobile or transportable attached to, or forming part of, mobile tools or machines
A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.
Systems and methods described herein include collapsible and deployable antenna structures. The antenna structures may include any combination of shape memory composites, inflatable envelopes, and/or degradable materials.
Systems and methods described herein include collapsible and deployable antenna structures. The antenna structures may include any combination of shape memory composites, inflatable envelopes, and/or degradable materials.
Exemplary embodiments provided herein include connection systems in which a gripper is actuated through introduction of a material to an interior cavity. Embodiments may include more than one cavity such that deployment and actuation may be separately controlled. Additional cavities may also be used and/or selection of valves between cavities such that actuation and/or deployment may further be controlled.
Exemplary embodiments are described herein for compactable antennas and methods of making such an antenna. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.
B64G 1/40 - Arrangements or adaptations of propulsion systems
B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
B65H 75/42 - Cores, formers, supports, or holders for coiled, wound, or folded material, e.g. reels, spindles, bobbins, cop tubes, cans specially adapted or mounted for storing and repeatedly paying-out and re-storing lengths of material provided for particular purposes, e.g. anchored hoses, power cables involving the use of a core or former internal to, and supporting, a stored package of material mobile or transportable attached to, or forming part of, mobile tools or machines
Exemplary embodiments provided herein include an attachment and deployment system and method. Exemplary embodiments may use features together or separately as desired. The attachment feature may be used to periodically couple a solar sail.
Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.
Exemplary embodiments are described herein for compactable antennas and methods of making such an antenna. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.
Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.
B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
B65H 75/34 - Cores, formers, supports, or holders for coiled, wound, or folded material, e.g. reels, spindles, bobbins, cop tubes, cans specially adapted or mounted for storing and repeatedly paying-out and re-storing lengths of material provided for particular purposes, e.g. anchored hoses, power cables
A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.
Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.
Systems and methods are described herein that may be used to form a heliostat. Various reflective surfaces and support structures are described that permit lightweight construction of configurable heliostats.
G02B 7/183 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy
F24S 23/70 - Arrangements for concentrating solar rays for solar heat collectors with reflectors
F24S 23/77 - Arrangements for concentrating solar rays for solar heat collectors with reflectors with flat reflective plates
F24S 25/00 - Arrangement of stationary mountings or supports for solar heat collector modules
F24S 25/65 - Fixation means, e.g. fasteners, specially adapted for supporting solar heat collector modules for coupling adjacent supporting elements, e.g. for connecting profiles together
A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.
Exemplary embodiments are described herein for compactable antennas. Exemplary compactable antennas include a support structure and a reflector surface. The support structure may directly or indirectly define the reflector shape. Exemplary embodiments comprise deployable support structures to permit the compactable antenna to have a smaller volume stowed configuration and a larger volume deployed configuration.
A truss is disclosed in which rigid longitudinal members define a frame and flexible connecting members permit the truss to collapse into a stowed configuration or expand into a deployed configuration.
E04H 12/18 - TowersMasts or polesChimney stacksWater-towersMethods of erecting such structures movable or with movable sections, e.g. rotatable or telescopic
A truss is disclosed in which rigid longitudinal members define a frame and flexible connecting members permit the truss to collapse into a stowed configuration or expand into a deployed configuration.
E04H 12/00 - TowersMasts or polesChimney stacksWater-towersMethods of erecting such structures
E04C 3/28 - JoistsGirders, trusses, or truss-like structures, e.g. prefabricatedLintelsTransoms of materials not covered by groups
E04C 3/00 - Structural elongated elements designed for load-supporting
E04H 12/18 - TowersMasts or polesChimney stacksWater-towersMethods of erecting such structures movable or with movable sections, e.g. rotatable or telescopic
E04C 3/04 - JoistsGirders, trusses, or truss-like structures, e.g. prefabricatedLintelsTransoms of metal
37.
LIGHTWEIGHT, LOW-COST HELIOSTAT MIRROR FOR CONCENTRATING SOLAR POWER
Systems and methods are described herein that may be used to form a heliostat. Various reflective surfaces and support structures are described that permit lightweight construction of configurable heliostats.
Systems and methods are described herein that may be used to form a heliostat. Various reflective surfaces and support structures are described that permit lightweight construction of configurable heliostats.
G02B 7/183 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy
F24J 2/10 - having reflectors as concentrating elements
A unidirectional elastomeric composite comprises a plurality of fibers generally aligned in a first direction with an elastomer filling the space between fibers. The plurality of fibers may comprise an intermediate modulus carbon fiber. Preferably, the plurality of fibers have an ultimate elongation at failure or tensile failure strain of 1 % or greater, a tensile modulus between 200-400 GPa and tensile strength greater than 4 GPa. The resin or matrix may be a passive elastomer that will maintain its mechanical and chemical properties at a specific operational temperature range. Elastomers are polymers with viscoelasticity, generally having low Young's modulus and high failure strain. Methods of manufacturing the unidirectional elastomeric composite include apply the resin to fibers maintained in tension to maintain the fiber alignment.
patents
