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| Number | Title | Issue Date |
| 8056862 | Thermal protection systems for air and space vehicles having hidden fastener attachments A thermal protection system for use upon an air or space vehicle includes a plurality of thermal protection panels formed of a suitable ceramic matrix composition or other thermally protective material each panel having a continuous outer surface free of penetration... | 11/15/2011 |
| 7837154 | Deployable heat shield and deceleration structure for spacecraft An apparatus for heat shielding and deceleration of a spacecraft comprises an unfoldable shield of individual panels made of a high temperature resistant fiber reinforced ceramic and pivotally mounted on the outer structure of the spacecraft. An unfolding ring slide... | 11/23/2010 |
| 7721997 | Method and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy A system for reducing plasma induced communication disruption utilizes an electrophilic gas injectant, bent reentry vehicle nose shaping and a number of flaps configured to provide 3-axis steering capability. Injecting electrophilic gas injectant into plasma accompl... | 05/25/2010 |
| 7546982 | Shuttle thermal integrity detection system A detection-grid is disclosed that is part of a vehicle's thermal protection layer, such as that of a space shuttle. A hybrid digital/analog system detects electrical changes in the detection grid caused by mechanical trauma to a vehicle's external surface. The syst... | 06/16/2009 |
| 7407131 | Method for creating an aeronautic sound shield having gas distributors arranged on the engines, wings, and nose of an aircraft The present invention blocks and/or attenuates the upstream travel of acoustic disturbances or sound waves from a flight vehicle or components of a flight vehicle traveling at subsonic speed using a local injection of a high molecular weight gas. Additional benefit ... | 08/05/2008 |
| 7392964 | Method and apparatus for utilizing a lifeboat for a space station in earth orbit to serve as a lunar spacecraft Methods and an apparatus for a lifeboat of a space station in orbit to be docked with and used in combination with a separately launched logistics module having an upper stage propulsion capability as a space craft for human pilots and passengers to be flown to orbi... | 07/01/2008 |
| 7381459 | Toughened uni-piece, fibrous, reinforced, oxidization-resistant composite A composite thermal protection structure, for applications such as atmospheric re-entry vehicles, that can withstand temperatures as high as 3600° F. The structure includes an exposed surface cap having a specially formulated coating, an insulator base adjacent to ... | 06/03/2008 |
| 7377469 | Heat shield The invention discloses systems for mounting heat shields onto a spacecraft. It shows a number of ways to attach heat shield tiles in a way that allows for and accommodates the thermal expansion and contraction of the tiles without overstressing them and without loo... | 05/27/2008 |
| 7354020 | System for use of external secondary payloads An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next g... | 04/08/2008 |
| 7281688 | Materials for self-transpiring hot skins for hypersonic vehicles or reusable space vehicles A self-transpiring hot skin for a hypersonic or reusable space vehicle that can provide protection to the vehicle during short periods of abnormally high heat flux (either planned in the flight profile or an off-nominal event). The hot skin includes a ceramic compos... | 10/16/2007 |
| 7275720 | Actively cooled ceramic thermal protection system An apparatus and method for thermal protection is provided. A thermal protection apparatus includes a porous layer attached to an inner structural member requiring thermal protection. The porous layer serves as both a cooling air plenum and a transpiring medium. The... | 10/02/2007 |
| 7267303 | Method and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy A system for reducing plasma induced communication disruption is disclosed. The system utilizes an electrophilic gas injectant, bent reentry vehicle nose shaping and a number of flaps configured to provide 3-axis steering capability. Injecting electrophilic gas inje... | 09/11/2007 |
| 7237752 | System and method for reducing plasma induced communication disruption utilizing electrophilic injectant and sharp reentry vehicle nose shaping The present invention discloses a system and a method for reducing plasma induced communication disruption utilizing electrophilic injectant and sharp reentry vehicle nose shaping. Injecting electrophilic gas into plasma accomplishes reduction of plasma induced comm... | 07/03/2007 |
| 7229048 | Aerodynamic control of a hypersonic entry vehicle A hypersonic vehicle having in one or more embodiments a control surface that is movable to a deployed position. The control surface is movable in a pivotal manner that establishes a gap between the leading edge of the control surface and the outer surface of the ve... | 06/12/2007 |
| 7226017 | Aerodynamically stable, high-lift, vertical takeoff aircraft In a preferred embodiment, a vertical takeoff aircraft body having an inverted hemispherical upper portion, a generally cylindrical lower portion with a diameter of its upper end slightly greater than a diameter of its lower end but less than a diameter of the lower... | 06/05/2007 |
| 7219859 | Multipurpose modular spacecraft A reentry vehicle includes a nose section, a modular section comprised of two or more connected modules, a flared section. The nose section is connected to a first end of the modular section, and the flared section is positioned proximate a second end of the modular... | 05/22/2007 |
| 7198231 | Method of applying ablative insulation coatings and articles obtained therefrom A method of forming ablative insulation coatings on aerospace structures and articles produced thereby. The method includes forming a mold having a cavity configured to complementarily receive at least a portion of the structure and directly molding the ablative coa... | 04/03/2007 |
| 7195207 | Winged spacecraft A rocket-powered spacecraft having a wing which has hinged aft portions which can be elevated about a hinge line. Tail booms extend rearwardly from the outer ends of the aft wing portions, and rudders are mounted at the aft ends of the booms. Each tail boom supports... | 03/27/2007 |
| 7106215 | Device for monitoring the integrity of spacecraft thermal protection tiles An electrical circuit, attached to the tiles of the space shuttle, provides an indication of tile integrity in real time. Each tile has a resistor attached thereto between parallel conductors, and a series of tiles forms a protected grid series tile section. A compu... | 09/12/2006 |
| 7083147 | Modularized insulation, systems, apparatus, and methods Modularized insulation blanket for thermal and/or acoustical insulation. The modularized insulation blanket has a cover formed of a distal layer and proximal layer in sealed mated relationship. The distal and proximal layers are sealed along longitudinal and latitud... | 08/01/2006 |
| 6241184 | Vehicle having a ceramic radome joined thereto by an actively brazed compliant metallic transition element A missile has a body with a substantially circular nose opening therein, and a ceramic radome sized to cover the nose opening. A compliant metallic circular transition element is disposed structurally between the radome and the body. The transition elemen... | 06/05/2001 |
| 4833030 | Polymer impregnated and carbonized carbon/carbon composite Metal complexes are obtained by reacting furfurylamine with a metal carbonyl selected from the group consisting of tungsten carbonyl, molybdenum carbonyl and chromium carbonyl. Multi-cycle reimpregnation polymers are obtained by reacting one of these meta... | 05/23/1989 |
| 4804571 | Reusable thermal protection member for an object subject to great heating The present invention relates to a reusable thermal protection member for an object subject to great heating, e.g. an aircraft or spacecraft. The member comprises in per se known manner a refractory shield and an insulating layer between the refractory shield ... | 02/14/1989 |
| 4797325 | Spacecraft materials A method of manufacturing a dielectric material for use in spacecraft, comprising the operation of coating a dielectric substrate with a layer comprising a metal oxide dispersed in a solution of a polymer material of a thickness such that when the polymer... | 01/10/1989 |
| 4767656 | Composite material structure with integral fire protection A load-bearing composite material structure (2, 2') has a plurality of layers of composite material. Each layer includes a matrix material (4) that maintains its structural integrity at 1200° F. for at least five minutes. Preferred matrix materials are p... | 08/30/1988 |
| 4713275 | Ceramic/ceramic shell tile thermal protection system and method thereof The present invention discloses a ceramic reusable externally applied thermal protection system (TPS). The system functions by using the composite device created by combining an upper shell, thermal insulation and lower tile components shown in FIG. 2. Th... | 12/15/1987 |
| 4704732 | Method of suspending a platform for communications and observation kept at high altitude by atmospheric molecular momentum transfer The instant invention comprises a method for freely suspending without any solid material support, a platform in an atmosphere by atmospheric-particle-momentum transfer having opposite surface portions which are structured to have different atmospher... | 11/03/1987 |
| 4702439 | Support for thermally expanding conical heatshield The front end of a conical forward carbon-carbon heatshield is attached to arbon-carbon nose tip by a threaded connection. The nose tip provides rigid structural support for the small end of the heatshield at all conditions of thermal expansion. The joint ... | 10/27/1987 |
| 4671348 | Transverse flow edge heat pipe An edge situated in high speed flow of medium is cooled by a tubular heat pipe having a longitudinal axis situated parallel to the edge. The exterior surface of the evaporator section of the heat pipe forms the edge. The heat pipe contains a working fluid... | 06/09/1987 |
| 4663234 | Coating capables of resisting to high thermal stress and particularly to coatings for satellites and spatial vessels and to methods for producing those coatings A composite coating for objects subjected to high thermal stresses. This composite coating comprises a first layer made of a material suitable for ensuring heat control, an intermediate layer made of a transparent, amorphous inorganic substance insensitive to ... | 05/05/1987 |
| 4624888 | Acetylene (ethynyl) terminated polyimide siloxane and process for preparation thereof Siloxane-containing addition polyimides having improved physical property characteristics of flexibility, drape, tack and toughness and the process for preparing and utilizing same are disclosed.... | 11/25/1986 |
| 4557444 | Aerospace vehicle A dual structure aerospace vehicle 10 having an aeroshell structure 11 and an internally disposed separable and reusable integral tank/thrust structure 13 is disclosed. Tank/thrust structure 13 is insulated for cryogenic fuels and the cavity 24 within aer... | 12/10/1985 |
| 4522883 | Circumferentially wrapped carbon-carbon structure A carbon-carbon structure useful for fabricating a nosetip for a reentry vehicle, which consists essentially of a central core, a plurality of layers of woven carbon fabric circumferentially wrapped around the core, and a carbon binder, wherein the core c... | 06/11/1985 |
| 4520601 | Mechanical fastener A device for fastening a temporary replacement heat shield tile to the strain isolation pad of a space vehicle is disclosed. An internally threaded, flanged cylinder 20 is rotatably connected to a threaded brass plug 18 through a flanged aluminum sleeve 1... | 06/04/1985 |
| 4519290 | Braided preform for refractory articles and method of making A braided preform fabrication for annular refractory articles such as an integral monolithic throat section and exit cone of a rocket motor nozzle is formed on a mandrel and includes closely spaced radially oriented carbon rods that extend to a uniform le... | 05/28/1985 |
| 4515847 | Erosion-resistant nosetip construction A pierced fabric carbon-carbon structure is selectively loaded with a particulate material to provide resistance to erosion.... | 05/07/1985 |
| 4456208 | Shell tile thermal protection system A reusable, externally applied thermal protection system is disclosed and functions by utilizing shell tile structure 10 which effectively separates its primary functions as an insulator and load absorber. Tile 10 consists of structurally strong upper and... | 06/26/1984 |
| 4439968 | Pre-stressed thermal protection systems A hexagonal protective and high temperature resistant system for the Space Shuttle Orbiter consists of a multiplicity of pockets formed by hexagonally oriented spacer bars 11 secured ot the vehicle substructure 12, a packing of low density insulating batt... | 04/03/1984 |
| 4421806 | Low density resin systems for improved filament-wound composites useful as rocket motor cases Filament-wound composite bodies are disclosed. These bodies contain filament-wound fibers and resin. The resin, when cured, has a density of less than 1.05 g/cc and exhibits a water pick up of less than 1% by weight. When uncured, the resin contains an ar... | 12/20/1983 |
| 4400421 | Four-directional structure for reinforcement The structure comprises four groups of elongated rectilinear elements, with the elements of each group parallel to one another. The elements of three of the groups are mutually orthogonal and the elements of the other group are disposed diagonally to the ... | 08/23/1983 |
