| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244172700 | With solar panel | 17 |
| 20080272240 | Active vibration damping (AVD) system for precision pointing spacecraft - An active vibration damping (AVD) control system for spacecraft provides a simple-to-implement and robust formulation that provides a novel damping control method for reducing spacecraft structural vibrations and improving antenna and instrument pointing. The AVD control system comprises an excitation signal generator configured to generate excitation input signals, and a damping model identification unit configured to receive system identification data and configured to produce control model parameters, the system identification data comprising the excitation input signals and information associated with motion of the spacecraft. The AVD control system further comprises an AVD control unit configured to receive the control model parameters, the AVD control unit configured to produce AVD control signals to control one or more actuators of the spacecraft. | 11-06-2008 |
| 20090101758 | FORMATION FLIGHT DEVICE INTENDED FOR A SOLAR CORONAGRAPHY MISSION - The present invention relates to a device making it possible to study the solar corona on a space mission requiring the formation flight of two satellites: an occulting satellite (OCC), the role of which is to create an artificial eclipse of the sun from the point of view of a coronagraph ( | 04-23-2009 |
| 20090230250 | SOLAR ARRAY MOMENTUM CONTROL - One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The spacecraft also comprises a solar array selection controller configured to selectively deactivate a portion of the array of solar cell sections to generate a torque on the spacecraft based on a difference in at least one of solar and thermal radiation pressure between an activated portion of the array of solar cell sections and the deactivated portion of the array of solar cell sections. | 09-17-2009 |
| 20090250555 | Solar Powered Excess Electron Emission Device - The chassis of a spacecraft has one side exposed to ultraviolet photons and another side shielded from the ultraviolet photons. An electrically conductive surface is disposed on the exposed side of the chassis and is electrically isolated from the chassis. A field-emission array device has a gate, an emitter array, a first terminal electrically connected to the gate, and a second terminal electrically connected to the emitter array. The first terminal electrically couples the gate to the electrically conductive surface on the exposed side of the chassis, and the second terminal electrically couples the emitter array to a surface on the shielded side of the chassis. The emitter array discharges electrons from the surface on the shielded side when a voltage difference in excess of a threshold voltage develops between the gate and the emitter array because of differential charging of the exposed and shielded sides of the chassis. | 10-08-2009 |
| 20100116942 | HIGH-EFFICIENCY SOLAR CELL STRUCTURES - Solar cells include a substrate consisting essentially of silicon, a first junction disposed over the substrate, the first junction comprising at least one III-V material and having a threading dislocation density of less than approximately 10 | 05-13-2010 |
| 20110011983 | MULTIJUNCTION PHOTOVOLTAIC CELL GROWN ON HIGH-MISCUT-ANGLE SUBSTRATE - The present invention provides a photovoltaic cell comprising a GaInP subcell comprising a disordered group-III sublattice, a Ga(In)As subcell disposed below the GaInP subcell, and a Ge substrate disposed below the Ga(In)As subcell comprising a surface misoriented from a (100) plane by an angle from about 8 degrees to about 40 degrees toward a nearest (111) plane. | 01-20-2011 |
| 20110309200 | Apparatus, Satellite and Method for Trapping High-Speed Particles - An apparatus for trapping high-speed particles, such as space debris, is provided. The apparatus includes a first front tapping surface and at least one rear trapping surface. The front and rear trapping surfaces are arranged substantially parallel to each other and are spaced apart from each other in the normal direction. | 12-22-2011 |
| 20130299642 | Multifunctional Controller for a Satellite - A multifunctional controller includes an onboard computer (OBC) and a power supply unit (PCDU) of a satellite. The controller includes reconfiguration functions for monitoring the correct functioning of components of an onboard computer of the satellite and for switching over between redundant components and/or turning off electrical loads of the satellite in the event of a malfunction. The controller also includes control functions for controlling and distributing energy to satellite components, which is designed for turning on and off the power supply to satellite components together with the reconfiguration unit. | 11-14-2013 |
| 20140326833 | Directionally Controlled Elastically Deployable Roll-Out Array - A directionally-controlled roll-out elastically deployable solar array structure is disclosed. The structure includes one or more longitudinal elastic roll out booms that may be closed section or open section to allow for efficient rolled packaging onto a lateral mandrel. A flexible photovoltaic blanket is attached to a tip structure and to a lateral base support structure, but remains uncoupled from the longitudinal booms. The solar array system may be stowed simultaneously into a rolled package comprised of the roll out booms and the flexible planar blanket together, or onto independent rolls. Alternatively, the system may be stowed by rolling the booms, and accordion Z-folding the hinged flexible photovoltaic blanket into a flat stack. Structural deployment is motivated by the elastic strain energy of the roll out booms, and several methods of deployment direction control are provided to ensure a known, controlled, and unidirectional deployment path of the elastically unrolling booms. | 11-06-2014 |
| 20160114910 | DEPLOYABLE SOLAR ARRAY FOR SMALL SPACECRAFT - The present disclosure provides, among other things, a deployable solar array comprising: an array of electromagnetic transducer devices such as photovoltaic devices; and a flexible, elongated, rectangular sheet for supporting the array of electromagnetic transducer devices composed of a composite laminate having a predetermined pattern of graphite fiber plies which impart a predefined tension in the planar surface of the sheet so that it curls into a planar sheet with a uniform radius of curvature along its major axis. | 04-28-2016 |
| 20160176547 | ANTI-TWIST JOINT, ORIENTING SYSTEM AND METHOD | 06-23-2016 |
| 244172800 | Having solar concentrator | 6 |
| 20100276547 | SYSTEMS FOR SOLAR POWER BEAMING FROM SPACE - 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. | 11-04-2010 |
| 20110006163 | SEGMENTED PARABOLIC CONCENTRATOR FOR SPACE ELECTRIC POWER - A segmented parabolic concentrator includes a concave surface which extends from a central support, the concave surface defines a multitude of flat segments. | 01-13-2011 |
| 20110017875 | PHOTOVOLTAIC ARRAY - 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. | 01-27-2011 |
| 20120261514 | System and Method of Solar Flux Concentration for Orbital Debris Remediation - 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 f | 10-18-2012 |
| 20120325975 | Hybrid Assembly Equipped with At Least One Solar Panel - 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. | 12-27-2012 |
| 20150028159 | SIDE-BY-SIDE DUAL-LAUNCH ARRANGEMENT WITH IMPROVED PAYLOAD COMPATIBILITY - 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. | 01-29-2015 |
