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| Number | Title | Issue Date |
| 8104264 | Low minimum impulse bit propellant gas thruster A gas thruster is configured to supply thrust over a relatively wide range, from a relatively low value to a relatively high thrust value, and exhibits relatively fine minimum impulse bit (MIB) performance. The gas thruster includes a thrust nozzle, a main stage, a ... | 01/31/2012 |
| 8051640 | Propulsion system, opposing grains rocket engine, and method for controlling the burn rate of solid propellant grains A solid propellant thrust control system, method, and apparatus for controlling combustion of solid propellants in an opposing grains solid propellant rocket engine (OGRE) is provided. In particular, an opposing grains rocket engine and propulsion system is provided... | 11/08/2011 |
| 7647763 | Polyoxymethylene as structural support member and propellant A vehicle includes at least one polyoxymethylene structural support member. The polyoxymethylene structural support member includes a polyoxymethylene component that is a propellant that provides thrust to the vehicle upon pyrolysis or combustion of the polyoxymethy... | 01/19/2010 |
| 7565797 | Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles The thrust of a rocket motor can be varied while maintaining efficiency over a range of pressure ratios using a design that allows for changing the relative position of a plug and a combustion chamber exit. The plug or the chamber exit may be attached to an adaptive... | 07/28/2009 |
| 7358314 | Polybenzoxazole-filled nitrile butadiene rubber compositions An insulation composition that comprises at least one nitrile butadiene rubber (“NBR”) having an acrylonitrile content that ranges from approximately 26% by weight to approximately 35% by weight and polybenzoxazole (“PBO”) fibers. The NBR may be a copolymer ... | 04/15/2008 |
| 7331292 | Venting system for explosive warheads An ordnance venting system has one or more adapters that separate the warhead section from other sections of a rocket, or submunition compartments within the warhead itself. The adapters structurally fail at given temperatures and pressures to reduce the danger of e... | 02/19/2008 |
| 7313910 | Jet vane thrust vector control system Disclosed is a jet vane thrust vector control (JV-TVC) system. A general system has many problems in design techniques considering actual operation environments, and does not have reliability in component assembly design. The JV-TVC system improves thrust vector con... | 01/01/2008 |
| 7281367 | Steerable, intermittently operable rocket propulsion system A propulsion system including an extinguishable rocket motor and an incorporated maneuver control system. The rocket motor may be of the solid fuel type. One or more proportional axial thrust valves in communication with a pressure vessel or motor case containing a ... | 10/16/2007 |
| 7269951 | Throat retention apparatus for hot gas applications A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein. The flow path has a throat section. The insert is made of material cap... | 09/18/2007 |
| 7254936 | Simple solid propellant rocket engine and super-staged rocket A solid propellant rocket engine includes: a propellant formed into a predetermined shape having a combustion cavity and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand the hot, high-pressure gas in... | 08/14/2007 |
| 7210282 | Case burning rocket A case-burning rocket booster includes a combustible case containing a solid rocket fuel, a combustion chamber adjustably coupled to the case for burning the case and the solid rocket fuel, a nozzle connected to the combustion chamber for expelling the burned case a... | 05/01/2007 |
| 7194852 | Propulsion from combustion of solid propellant pellet-projectiles Propulsion from combustion of solid propellant pellet-projectiles for providing a useful propulsion that has the advantages of both solid and liquid propulsion engines, and also can make use of either solid chemical propellants or fissionable nuclear material as the... | 03/27/2007 |
| 7191558 | Dynamic process for enhancing the wear resistance of ferrous articles A dynamic process for increasing the wear life of ferrous articles subjected to a high-temperature environment created by combustion of a propellant or fuel comprises selecting the propellant or fuel so that its combustion products include relatively large amounts o... | 03/20/2007 |
| 7117797 | Pyrotechnic charge structure A pyrotechnic charge structure, in particular for use as propellant in a rocket motor, is disclosed. The charge structure has a predetermined longitudinal extension and cross sectional area adapted to the intended purpose. The pyrotechnic charge structure (1; 2; ... | 10/10/2006 |
| 7070705 | Fiber-reinforced rocket motor insulation Insulation for a rocket motor is provided, as is a method for insulating a rocket motor. The insulation includes a cured elastomer and vapor-grown carbon fibers dispersed in the cured elastomer. The cured elastomer is preferably formed from a precursor composition c... | 07/04/2006 |
| 7051511 | Method and arrangement for preventing encased explosives being caused to explode by an external fire This disclosure relates to a method and an arrangement for preventing explosives such as rocket engines from exploding while subjected to an external fire in an ammunition bunker. The basic principle underlying the invention is that the casing surrounding the explos... | 05/30/2006 |
| 7012107 | Elastomeric rocket motor insulation A rocket motor insulation including an elastomer-based polymer is improved in its processability by the addition of silica particles treated with a hydrophobic coating. The insulation also preferably includes a metallic coagent cross-linker, which when used in combi... | 03/14/2006 |
| 7003942 | System and method of controlling pressure oscillations of hydrodynamic origin for a solid propellant thruster The invention provides a system for passively controlling pressure oscillations of hydrodynamic origin in a solid propellant thruster comprising a body containing a charge of solid propellant, the system comprising at least one insert disposed in the thruster body t... | 02/28/2006 |
| 7000377 | Super-staged and continuously staged rocket A super-staged rocket includes at least approximately 50 rocket engines, where the engines are distributed according to at least one of: at least five multi-engine stages connected in series, each stage including at least ten engines connected in parallel; and at le... | 02/21/2006 |
| 6968676 | Propulsion from combustion of solid propellant pellet-projectiles Propulsion from combustion of solid propellant pellet-projectiles for providing a useful propulsion that has the advantages of both solid and liquid propulsion engines, and also can make use of either solid chemical propellants or fissionable nuclear material as the... | 11/29/2005 |
| 6964154 | Axisymmetric, throttleable non-gimballed rocket engine A rocket engine assembly is provided for a vertically launched rocket vehicle. A rocket engine housing of the assembly includes two or more combustion chambers each including an outlet end defining a sonic throat area. A propellant supply for the combustion chambers... | 11/15/2005 |
| 6935242 | Methods and apparatus for increasing aerodynamic performance of projectiles A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after la... | 08/30/2005 |
| 6902759 | Technique for coating or marking glass strands A method for providing a metallic coating on glass strands or organically precoated glass strands comprising the steps of coating the glass strand (or organically precoated glass strand) with a metallorganic material, heating the metallorganically coated glass stran... | 06/07/2005 |
| 6901740 | Engine with a central spike for a space launcher The pointed end of a central spike, used in an engine of a space launcher, may have a deformable structure that can adopt either a folded position or a deployed position. ... | 06/07/2005 |
| 6902809 | Rhenium tantalum metal alloy The present invention provides a method for preparing a rhenium-tantalum alloy with improved strength and ductility characteristics. The method includes mixing powders of rhenium and tantalum with a weight ration of approximately 97% rhenium to approximately 3% tant... | 06/07/2005 |
| 6873945 | Rocket motor propellant temperature simulator The present invention comprises a device which is inert and “thermally-equivalent” to actual ordnance. The device can travel with live ordnance and track the propellant temperatures in order to get a more precise propellant temperature for the ordnance. The devi... | 03/29/2005 |
| 6782693 | Case burning rocket with drive system for combustion chamber and nozzle A case-burning rocket booster includes a combustible case containing a solid rocket fuel, a combustion chamber adjustably coupled to the case for burning the case and the solid rocket fuel, a nozzle connected to the combustion chamber for expelling the burned case a... | 08/31/2004 |
| 6769241 | Description of methods to increase propellant throughput in a micro pulsed plasma thruster Propellant modules for Micro Pulsed Plasma Thrusters, and techniques for bundling propellant modules and for using a two-stage discharge process to increase MicroPPT propellant throughput, and decrease the output voltage required from the power-processing unit are p... | 08/03/2004 |
| 6739121 | Flame holder for a hybrid rocket motor A flame holder is provided at a head end of a combustion chamber of a hybrid rocket motor. The flame holder includes a high-temperature casing defining a cavity, and a solid propellant within cavity around or near the injector. The propellant may be provided in an a... | 05/25/2004 |
| 6736912 | Combustible compositions for air-augmented rocket engines A solid combustible composition for use in solid fuel air-augmented rocket engines which very substantially increases the temperature efficiency of afterburner fuel combustion with ram air, thereby greatly increasing engine performance. The improvement comprises dis... | 05/18/2004 |
| 6711890 | Pressure-actuated joint system A pressure vessel is provided that includes first and second case segments mated with one another. First and second annular rubber layers are disposed inboard of the first and second case segments, respectively. The second annular rubber layer has a slot extending f... | 03/30/2004 |
| 6705075 | Digital solid rocket motor and gas generator A method and device for producing a controlled combustion by placing a combustion chamber in communication with a feed chamber that contains a solid propellant/body, introducing at least a portion of the body into the combustion chamber, isolating the combustion cha... | 03/16/2004 |
| 6691505 | Fiber-reinforced rocket motor insulation Insulation for a rocket motor is provided, as is a method for insulating a rocket motor. The insulation includes a cured elastomer and vapor-grown carbon fibers dispersed in the cured elastomer. The cured elastomer is preferably formed from a precursor co... | 02/17/2004 |
| 6619029 | Rocket motors with insensitive munitions systems An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive ... | 09/16/2003 |
| 6606852 | Rocket motor insulation containing hydrophobic particles A rocket motor insulation including an elastomer base polymer is improved in its processability by the addition of silica particles treated with a hydrophobic coating. The insulation also preferably includes a metallic coagent cross-linker, which when use... | 08/19/2003 |
| 6554936 | Method of constructing insulated metal dome structure for a rocket motor An elastomerized phenolic resin ablative insulation particularly suitable for use in connection with the thermal insulation of selected components of rocket motors. A composition for making the elastomerized ablative insulation is disclosed. Furthermore, ... | 04/29/2003 |
| 6499289 | Pyrolytic graphite gauge for measuring heat flux A gauge for measuring heat flux, especially heat flux encountered in a high temperature environment, is provided. The gauge includes at least one thermocouple and an anisotropic pyrolytic graphite body that covers at least part of, and optionally encases ... | 12/31/2002 |
| 6494035 | Towing rocket motor assembly A towing rocket motor assembly has a tubular solid propellant grain defined by exterior surface area and interior surface area. The exterior surface area is inhibited from ignition within a tubular region of a housing. The housing includes a first end and... | 12/17/2002 |
| 6421999 | Modular solid-fuel rocket charges with rigid support casings A modular solid-fuel rocket propellent charge has a combustion-chamber wall, a plurality of separate elements including frozen fuel or oxidizer, and respective rigid casings completely surrounding and enclosing the elements. Respective formations on the c... | 07/23/2002 |
| 6405526 | Solid fuel propulsion system for a ram jet rocket A solid fuel propulsion system for a ran jet rocket having a combustion chamber (B) surrounded by a tubular casing (2) and a gas generator (G) disposed upstream from the combustion chamber (B) and surrounded by a tubular casing (1) for generation of a com... | 06/18/2002 |
