Class / Patent application number | Description | Number of patent applications / Date published |
244171700 | With shield or other protective means (e.g., meteorite shield, insulation, radiation/plasma shield) | 52 |
20090032647 | PROTECTIVE SHIELD ASSEMBLY FOR SPACE OPTICS AND ASSOCIATED METHODS - A protective shield assembly capable of being deployed from a launch vehicle is provided, and methods for assembling and deploying the protective shield assembly are also provided. The protective shield assembly includes a shroud, and a flexible sheet of material within the shroud. The flexible sheet of material is capable of substantially conforming to a contour of at least a portion of the launch vehicle to provide a protective barrier. | 02-05-2009 |
20090065647 | SOLAR PROTECTION DEVICE FOR SPACE INSTRUMENT - The present invention relates to a solar protection device for space instrument. This invention is particularly suited to electromagnetic measuring instruments pointing in a direction close to that of the sun. To ensure the continuous availability, the performance and the non-degradation of collecting instruments directed towards the sun, the invention proposes the use of solar baffling ( | 03-12-2009 |
20090084902 | THERMAL PROTECTION SYSTEM WITH STAGGERED JOINTS - The thermal protection system disclosed herein is suitable for use with a spacecraft such as a reentry module or vehicle, where the spacecraft has a convex surface to be protected. An embodiment of the thermal protection system includes a plurality of heat resistant panels, each having an outer surface configured for exposure to atmosphere, an inner surface opposite the outer surface and configured for attachment to the convex surface of the spacecraft, and a joint edge defined between the outer surface and the inner surface. The joint edges of adjacent ones of the heat resistant panels are configured to mate with each other to form staggered joints that run between the peak of the convex surface and the base section of the convex surface. | 04-02-2009 |
20090084903 | Spacecraft Having A Magnetic Space Radiation Shield - There is provided a radiation shield device for providing radiation protection to an area, such as a spacecraft including, for example, a manned vehicle. The radiation shield device comprises a magnetic field generator, such as a solenoid, of superconductive material that provides a magnetic field around the area to shield the area from radiation. The solenoid preferably defines an axial length that is substantially smaller than a diameter of the solenoid. A thermal control system, comprising a limited amount of coolant or a refrigeration cycle, is included to control a temperature of the superconductive material during operation of the magnetic field generator. A magnetic shield device is also provided between the magnetic field generator and the area to be shielded from radiation to substantially shield the area from the magnetic field generated by the magnetic field generator. | 04-02-2009 |
20100187364 | CRYOGENIC PROPELLANT DEPOT AND INTEGRAL SUNSHIELD - A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot. | 07-29-2010 |
20100187365 | CRYOGENIC PROPELLANT DEPOT AND DEPLOYABLE SUNSHIELD - A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot. | 07-29-2010 |
20110049303 | SPACECRAFT SHIELD - A spacecraft is described which uses a magnetic field source to generate a shield magnetic field to protect the spacecraft from energetic charged particles. The field may be perturbed to increase the effectiveness of the protection. Injection of material into the shield cavity to enhance the local plasma density may also be used. | 03-03-2011 |
20110198446 | Device for Eliminating Space Debris in Orbit - A device for eliminating space debris in orbit, the device including a covering that when struck by an object of space debris breaks this up into multiple pieces of predetermined size, and captures and binds at least many of the pieces. The covering includes at least one layer of deformable fabric that encloses a spatial volume of the device, wherein a foam material is disposed inside the at least one layer for the purpose of retaining shape, the initial volume of the foam material being able to be changed into a final volume that is larger relative to the initial volume, wherein the device has its specified shape and function once the foam material attains its final volume. | 08-18-2011 |
20110260007 | SPACE PROBING APPARATUS - A space probing apparatus is provided that can further enhance its thermal protective function for electronic apparatuses and batteries that are apparatuses each having a narrow range of permissible temperature. | 10-27-2011 |
20120001027 | TRANSPARENT CERAMIC COMPOSITE - A ceramic composite and method of making are provided. The ceramic composite may be transparent and may serve as transparent armor. The ceramic portion of the composite may be spinel. The composite may provide adequate protection from projectiles while exhibiting large surface areas and relatively low areal densities. | 01-05-2012 |
20120043427 | ABSORBENT DOME FOR A RADIATING COLLECTOR TUBE - The device for thermal monitoring for a piece of equipment, whereby said piece of equipment is integrated on a craft placed in a forced vacuum environment, an outside part ( | 02-23-2012 |
20120068018 | ORBITAL DEBRIS MITIGATION SYSTEM AND METHOD - 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. | 03-22-2012 |
20120080562 | LANDING DEVICE FOR A SPACE PROBE, AND LANDING METHOD FOR A PROBE PROVIDED WITH SUCH A DEVICE - A space probe including a descent module with a mobile exploration vehicle, wherein the descent module is a landing module inside which the mobile exploration vehicle is fastened, the landing module being provided with landing legs which can be deployed under the lower level of the mobile exploration vehicle. | 04-05-2012 |
20120091280 | CRYOGENIC PROPELLANT DEPOT AND INTEGRAL SUNSHIELD - A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot. | 04-19-2012 |
20120091281 | CRYOGENIC PROPELLANT DEPOT AND DEPLOYABLE SUNSHIELD - A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot. | 04-19-2012 |
20120097799 | ORBIT DEBRIS REMOVAL AND ASSET PROTECTION ASSEMBLY - An orbital debris removal assembly is provided. The orbital debris removal and asset protection assembly includes a plurality of spaced layers of netting. Each netting layer includes a plurality of sub-layers of meshed composite fibers that are configured and arranged to break up debris that comes in contact with the assembly. | 04-26-2012 |
20120160966 | CNT-TAILORED COMPOSITE SPACE-BASED STRUCTURES - An apparatus having a composite space-based structure with a first carbon nanotube infused material and a second carbon nanotube infused material. The first and second carbon nanotube infused materials each having a range of carbon nanotube loading selected to provide different functionalities. | 06-28-2012 |
20120175467 | MICROMETEOROID AND ORBITAL DEBRIS (MMOD) AND INTEGRATED MULTI-LAYER INSULATION (IMLI) STRUCTURE - A micrometeoroid and orbital debris-integrated multi-layer insulation (MMOD/IMLI) structure including at least one ballistic layer, which may be flexible, and at least one insulation layer, which may also be flexible is described. The ballistic layer or layers and the insulation layer or layers may be separated by a plurality of spacers. In one example, the spacers include a leg extending obliquely between the ballistic layer and the insulation layer. The spacer may include three deformable legs defining a tri-pod configuration with the tri-pod configuration including a ring supporting the legs. | 07-12-2012 |
20120267482 | Device for Protecting an Optical Instrument of a Satellite - A device for protecting an optical instrument of a satellite comprises a body on which the optical instrument is mounted, said protection device having a folded-down position and a deployed position, and further comprising a plurality of rigid panels in the deployed position, the device forming a tube, the section of which is a polygon, arranged so as to protect the optical instrument, the longitudinal axis of the tube being substantially parallel with the focal axis of the optical instrument, the faces of the tube of polygonal section being formed by panels, in the folded-down position, said panels being held against the body of the satellite. | 10-25-2012 |
20120273622 | MULTIFUNCTIONAL CHAMBERED RADIATION SHIELDS AND SYSTEMS AND RELATED METHODS - Radiation shields include an outer composite wall, an inner composite wall, and an enclosed fuel chamber disposed between the inner and outer composite walls. A fuel may be contained within the enclosed fuel chamber. Spacecraft include one or more such radiation shields, and may further include a fuel cell and a conduit providing fluid communication between the fuel chamber of the radiation shield and the fuel cell. Methods of forming a radiation shield system include forming an enclosed fuel chamber between an outer composite wall and an inner composite wall of a radiation shield, and providing fuel within the enclosed fuel chamber. | 11-01-2012 |
20120318928 | Spacecraft magnetic shield - A spacecraft magnetic shield apparatus is disclosed. One embodiment has an armature attached at one end of a spacecraft and an electromagnet attached to the other end. A computer determines the position of the armature and electromagnet in relation to the spacecraft, and a power source powers the electromagnet. In operation, the positioning of the electromagnet is generally in line with incoming charged particles or ion radiation and powering of the electromagnet creates a magnetic field that deflects a percentage of the incoming charged particles or ion radiation from directly impacting the spacecraft. | 12-20-2012 |
20130037656 | UTILIZATION OF AN ENHANCED ARTIFICIAL MAGNETOSPHERE FOR SHIELDING AGAINST SPACE ENVIRONMENTAL HAZARDS - This invention relates to technology used for creating an enhanced artificial magnetosphere or electromagnetic shield for use in both manned and unmanned spacecraft. The invention includes an Interference Generating Pattern (IGP) which is tuned to the high-frequency radiation of X-rays and gamma rays and a conformal magnetic field. This technology will reduce the exposure of astronauts or other space travelers, as well as radiation-sensitive equipment, to the environmental hazards present therein. The net result will be reduced radiation intensity in order to create a space radiation-free environment as to render space travel safe. | 02-14-2013 |
20130062472 | Apparatus for Spacecraft - The invention relates to the protection of spacecraft from debris and to de-orbiting devices of the atmospheric drag type, and to debris sweeping apparatus for the removal of debris from the space environment. The debris shielding apparatus for a spacecraft has a shield unit including a shielding surface for impeding incident debris. The shield unit is attached to the spacecraft body and has a drive mechanism for positioning the shield unit in relation to the spacecraft body. The drive mechanism is capable of moving the shield unit between a stowed first position and a deployed second position. In the deployed second position the plane of the shielding surface is at an angle to the spacecraft body. | 03-14-2013 |
20130181094 | ORBIT DEBRIS REMOVAL AND ASSET PROTECTION ASSEMBLY - An orbital debris removal assembly is provided. The orbital debris removal and asset protection assembly includes a plurality of spaced layers of netting. Each netting layer includes a plurality of sub-layers of meshed composite fibers that are configured and arranged to break up debris that comes in contact with the assembly. | 07-18-2013 |
20140239124 | SPACECRAFT WITH OPEN SIDES - A spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft. | 08-28-2014 |
20150291292 | VEHICLE ABLATOR SYSTEM - A vehicle ablator system (“VAS”) is described that includes a reinforcing core and ablative material that has been packed and cured into the reinforcing core. In general, the VAS includes the reinforcing core that is attached to a vehicle structure such as, for example, a reentry vehicle or hypersonic vehicle prior to the ablative material being packed into the reinforcing core. | 10-15-2015 |
20150314894 | HEAT SHIELD FOR A SPACECRAFT - Various material compositions of a heat shield for a spacecraft are described. The heat shield can be formed by multi-dimensional weaver or three-dimensional (3-D) printer. Furthermore, the heat shield can be configured with a superconducting coil. | 11-05-2015 |
20150353210 | Thermal Seal with Thermally Induced Shape Change - A thermal seal may include a flexible insulation layer, and an element made of shape memory alloy attached to the insulation layer, the element being treated to bend in response to heating, whereby an increase in the temperature of the element causes the insulation layer to transform from a first configuration to a second configuration. | 12-10-2015 |
20160016678 | SOLAR REJECTION SYSTEM WITH MOVABLE SUNSHADE - A solar rejection system includes an enclosure for housing a sensor, and a movable sunshade. The housing has an opening or aperture for admitting light to the sensor, and the sunshade is moved as needed to prevent harmful solar illumination of the sensor. The sunshade may be a flat panel. The sunshade panel is mounted to a hinge that is located on one side of a large diameter bearing that allows the shade to be rotated around the aperture of the sensor to always prevent the sun from illuminating the aperture. The hinge allows the shade to be tilted to either allow the sensor to see further off axis without obscuration or to block the sun when it moves in front of the sensor. Full closure of the sunshade on its hinge allows it to also function as an aperture door, blocking the opening or aperture. | 01-21-2016 |
20160107770 | SHIELD ASSEMBLY FOR PROTECTING SPACECRAFT - A shield assembly for protection of vehicles traveling in space consisting of at least five layers that would replace the thin metal impact shield in Whipple shields fabricated using the current art that employs only a single metal. All of the layers in the present invention are metallic. At least three different metals must be used in this invention. | 04-21-2016 |
20160152355 | Apparatus For Spacecraft | 06-02-2016 |
20160167811 | Multi-Layered Self-Healing Material System Towards Impact Mitigation | 06-16-2016 |
20160200460 | SPACECRAFT AND SPACECRAFT PROTECTIVE BLANKETS | 07-14-2016 |
20160376039 | HEAT SHIELD FOR A SPACECRAFT - Various material compositions of a heat shield for a spacecraft are described. The heat shield can be formed by multi-dimensional weaver or three-dimensional (3-D) printer. Furthermore, the heat shield can be configured with a superconducting coil. | 12-29-2016 |
20180022439 | LEADING EDGE SYSTEMS AND METHODS FOR AEROSPACE VEHICLES | 01-25-2018 |
244171800 | Active thermal control | 17 |
20080217483 | THERMAL CONTROL DEVICE ON BOARD A SPACECRAFT - The invention relates to a thermal control device intended to dissipate the heat generated by a payload on a spacecraft, comprising a number of surfaces and including means for circulating a refrigerant. An evaporation zone (Z | 09-11-2008 |
20080277532 | Spacecraft battery thermal management system - A spacecraft battery thermal management system is provided that includes a battery, a first radiator panel and a second radiator panel. A first face of the first radiator panel is arranged to face a first direction and a first face of the second radiator panel is arranged to face a second direction opposite the first direction. A first heat pipe thermally couples the battery and the first radiator panel and is configured to control the transfer of heat between the battery and the first radiator panel. A second heat pipe thermally couples the battery and the second radiator panel and is configured to control the transfer of heat between the battery and the second radiator panel. Solar cells are optionally arranged on the faces of the first and/or second radiator panels. | 11-13-2008 |
20100019093 | Payload modules - A plurality of sufficient closely-packed functional units which are interconnected to form a non-planar payload module assembly | 01-28-2010 |
20100243817 | SPACECRAFT HEAT DISSIPATION SYSTEM - A spacecraft is provided. The spacecraft comprises a plurality of heat generating electrical components. A first thermal radiator panel and a second thermal radiator panel are provided on the spacecraft, each panel being thermally coupled to the heat generating electrical components. Heat pipes are also provided. At least one first heat pipe is externally attached to the first thermal radiator panel and at least one second heat pipe is externally attached to the second thermal radiator panel. The at least one first heat pipe is thermally coupled to the at least one second heat pipe. | 09-30-2010 |
20110001013 | SPACECRAFT MODULAR THERMAL PLATFORM - Thermal module ( | 01-06-2011 |
20110036953 | METHODS AND APPARATUS FOR AN INTEGRATED INSTRUMENTATION MODULE FOR A THERMAL PROTECTION SYSTEM - An integrated instrumentation system includes a body comprising a thermal protection system (TPS) material (e.g., an ablatable material), one or more sensors embedded within the body, and a processor (e.g., an FPGA or the like) communicatively coupled to the plurality of sensors. The processor is configured to acquire sensor signals from the plurality of sensors and produce digital sensor data associated therewith. The sensors may include, for example, recession sensors, pressure transducers, thermocouples, and accelerometers. | 02-17-2011 |
20120205492 | Satellite Having Multiple Aspect Ratios - A high capacity satellite having multiple aspect ratios is configured to have at least two modules. Each module includes a first panel and a third panel facing, in an on-orbit configuration, respectively, toward north and south and having a width in an east-west direction (EW width); and a second and a fourth panel oriented, in the on-orbit configuration, respectively, east and west and having a width in the north-south direction (NS width). Each module has a respective aspect ratio of EW width to NS width, a first module is configured with a first aspect ratio, a second module is configured with a second aspect ratio; and the second aspect ratio is substantially larger than the first aspect ratio. At least one antenna reflector is disposed, during launch, proximate to at least one of the first and third panel of the second module. | 08-16-2012 |
20130068891 | Structural Panel for a Satellite, with Integrated Heat Exchangers - A structural panel for a satellite comprises an outer skin intended to be outside the satellite, a core comprising at least one integrated heat pipe mounted in fixed contact with said outer skin, and an inner skin intended to be inside the satellite, said structural panel being equipped with generic heat exchangers which are adapted to be associated with a heat control circuit using the circulation of a liquid coolant, said circuit being situated outside the panel. | 03-21-2013 |
20130200220 | NON-INTERFERING DEPLOYABLE RADIATOR ARRANGEMENT FOR GEO SPACECRAFT - A deployable radiator arrangement for cooling a geostationary earth orbit spacecraft is provided. In some aspects, the geostationary earth orbit spacecraft may comprise first and second deployable radiators mounted on an east or west surface of the spacecraft when stowed. The first and second deployable radiators are configured to rotate into a north and south facing position, respectively, when deployed. The geostationary earth orbit spacecraft may further comprise first and second fixed radiators disposed on a north and south surface of the spacecraft, respectively. The first and second deployable radiators are thermally coupled to the first and second fixed radiators, respectively. | 08-08-2013 |
20130200221 | DEPLOYABLE RADIATOR HAVING AN INCREASED VIEW FACTOR - A geostationary earth orbit (GEO) spacecraft is disclosed that includes a body with north, east, south, and west sides and a north-south axis. The spacecraft has at least one deployable radiator rotatably coupled to the body. The deployable radiator has a stowed position proximate to one of the east and west sides and a deployed position that is greater than 90 degrees from the north-south axis in a direction away from the respective one of the east and west sides. | 08-08-2013 |
20140110531 | Spacecraft with Anti Nadir Battery Radiator - According to an embodiment, a satellite is disclosed comprising an anti-nadir panel having a first side and a second side. In one or more embodiments, the first side of the anti-nadir panel is mounted to an anti-nadir side of the main body of the satellite. The satellite further comprises at least one battery pack mounted to the second side of the anti-nadir panel, where at least one battery pack comprises at least one battery cell. | 04-24-2014 |
20140246544 | THERMAL MANAGEMENT SYSTEM AND METHOD FOR SPACE AND AIR-BORNE SENSORS - According to one embodiment, an apparatus includes a sensor having one or more thermally sensitive components. The sensor is gimbal mounted on a space or air-borne vehicle and includes a component. The component is configured to at least partially adjust a center-of-gravity of the sensor and to at least partially receive and store thermal energy from the one or more thermally sensitive components. The Apparatus also includes a radiator configured to dissipate thermal energy to the ambient environment. The component is thermally coupled between the radiator and the one or more other thermally sensitive components. The radiator is configured to receive thermal energy from the component. | 09-04-2014 |
20140284428 | Method and apparatus for the thermal protection of a space vehicle. - The essence of the invention is a method and apparatus for thermally protecting the external surface of the structure of a space vehicle during atmospheric reentry. The method, in detail, uses a recently discovered fundamental electrodynamic combustion mechanism for alkali metals to burn the metal onto the surface of the outer wall of the vehicle. In this mechanism, a static electric field that is always inherent to the burning alkali metal surface interacts electrodynamically with the ionized particles streaming behind the atmospheric front shock wave that propagates in front of the vehicle such that the electrodynamic Lorentz force deflects the particles perpendicularly away from the original direction of the ionized atmospheric flow. Thus, convective heat flux into the vehicle's structure is prevented. | 09-25-2014 |
20140299714 | HEAT GENERATING TRANSFER ORBIT SHIELD - A system and apparatus are provided for preventing heat loss in a spacecraft during the upper stage launch phase and transfer orbit. A thermal control panel can be provided that can be positioned adjacent to exposed areas of radiator panels on the spacecraft in a collapsed configuration. The outer surface of the panel can have a high absorptivity, and the inner surface can have a high emissivity. During upper stage launch phase and transfer orbit, the panel can tend to emit heat toward the radiator panels on an inboard side of the spacecraft, thus reducing heat loss from the radiator panels to reduce the need for onboard electronic heaters and thereby preserve battery power for other onboard systems. | 10-09-2014 |
20150069187 | HOSTED INSTRUMENT RADIATOR SYSTEM - An instrument mounting system for a geosynchronous host satellite provides independent heat rejection capability for a hosted instrument. The system may include an instrument mounting structure that is thermally coupled to a radiator component via heat pipes that may include one or both of rigid and flexible elements. In some embodiments, the system is mounted on the hosting satellite so as to provide satellite components and the hosted instrument with a clear field of view while rejecting heat in one or both of the north and south directions. The system may also provide structural support for components of one or both of the hosted instrument or the hosting satellite. | 03-12-2015 |
20150144739 | CRYOGENICALLY COOLED RADIATION SHIELD DEVICE AND ASSOCIATED METHOD - A cryogenically cooled radiation shield device and method are provided to shield an area, such as the capsule of a space vehicle, from radiation. A cryogenically cooled radiation shield device may include at least one first coil comprised of a superconducting material extending about an area to be shielded from radiation. The cryogenically cooled radiation shield device also includes a first conduit extending about the area to be shielded from radiation. The at least one first coil is disposed within the first conduit. The cryogenically cooled radiation shield device also includes a second conduit extending about the area to be shielded from radiation. The first conduit is disposed within the second conduit. The cryogenically cooled radiation shield device also includes a first cryogen liquid disposed within the first conduit and a second cryogen liquid, different than the first cryogen liquid, disposed within the second conduit exterior of the first conduit. | 05-28-2015 |
20160200459 | SPACECRAFT AND SPACECRAFT RADIATOR PANELS WITH COMPOSITE FACE-SHEETS | 07-14-2016 |