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| Number | Title | Issue Date |
| 7296396 | Method for using variable supersonic Mach number air heater utilizing supersonic combustion A supersonic combustion apparatus and method for using the same including a fixed geometric nozzle having a converging area, throat, and a diverging area, at least one fuel injection means and at least one flame stabilization means located in the divergent area, and... | 11/20/2007 |
| 7246483 | Energetic detonation propulsion A propulsion system for creating a propulsive force has a combustion chamber, a pair of electrodes within the combustion chamber and a power supply attached to the electrodes to create a high voltage field within an initiation zone of the combustion chamber, and an ... | 07/24/2007 |
| 7168603 | Hydrogen powered fastener driving tool with onboard generator of hydrogen A hydrogen operated fastener driving tool assembly including a hydrogen generator that is an integral part of the driving tool assembly. The hydrogen generator can use chemicals to generate hydrogen or electrolysis. Additionally, the generator may be disposable. Wha... | 01/30/2007 |
| 7128624 | Rechargeable open cycle underwater propulsion system In an underwater vehicle, hydrogen and oxygen are fed into a combustion chamber of a combustor of the underwater vehicle to initiate a combustion reaction, which generates high-pressure steam. The high-pressure steam can be cooled with the injection of seawater, and... | 10/31/2006 |
| 7124574 | Method and apparatus for a substantially coaxial injector element A system to provide a two piece robust fluid injector. According to various embodiments, the fluid injector is a fuel injector for a combustion engine. The injector includes two coaxially formed annuluses. One annulus is formed in a face plate and the second annulus... | 10/24/2006 |
| 7082750 | Pressurizer for a rocket engine A pressurizer for pressurizing a fluid includes: at least two storage tanks, where, for each storage tank, the pressurizer further includes: a propellant entrance valve, a propellant exit valve, a pressurant entrance valve, and a pressurant exit valve, where each of... | 08/01/2006 |
| 7080504 | Laser augmented turbojet propulsion system The invention is a turbojet propulsion system which includes a compressor section, a turbine section coupled by a shaft to the compressor section, a combustion section mounted between the compressor section and the turbine section, and an exhaust duct coupled to the... | 07/25/2006 |
| 7063247 | Power driven equipment utilizing hydrogen from the electrolysis of water Applicant's novel invention relates to a novel hydrogen generator for supplying hydrogen to drive a hydrogen operated engine. The regulator can supply hydrogen to drive an engine for operating the cutter assembly of a lawnmower as well as supply the output of a hydr... | 06/20/2006 |
| 6983587 | Method and apparatus for thrust augmentation for rocket nozzles A method and apparatus for augmenting thrust in a rocket traveling through atmospheric gas. Rocket motor designs are provided where a throat(s) from one or more rocket motors eject high-speed primary exhaust gas in a configuration which peripherally surrounds an out... | 01/10/2006 |
| 6918243 | Bi-propellant injector with flame-holding zone igniter A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-ho... | 07/19/2005 |
| 6832471 | Expander cycle rocket engine with staged combustion and heat exchange In a supersonic nozzle incorporating injectors and a combustion chamber as part of an expander cycle rocket engine, the oxidizer is injected in two streams. One of the streams, preferably a small fraction of the total, is injected into an upstream or preburner secti... | 12/21/2004 |
| 6807805 | Hypergolic fuel system A hypergolic fuel system comprises hydrogen peroxide, silane and a liquid fuel. The hypergolic fuel system is employed in a method for producing thrust, for example in a rocket, by contacting hydrogen peroxide with silane to obtain initial ignition and thereafter fe... | 10/26/2004 |
| 6695938 | Reduced toxicity hypergolic bipropellant fuels The reduced toxicity hypergolic bipropellant fuels of the present invention contain a hypergolic fuel and rocket grade hydrogen peroxide oxidizer, preferably HTP. The hypergolic fuel may be a reactive fuel or a catalytic fuel. The rocket grade hydrogen pe... | 02/24/2004 |
| 6620004 | Marine propulsion system A marine propulsion system is disclosed that includes at least one nozzle having a combustion chamber therein. The nozzle has an exit end that is shaped so as to flare outwardly. A fuel reformer separates gasoline or other liquid hydrocarbon fuel into hyd... | 09/16/2003 |
| 6593525 | Direct burial outdoor membrane pressurization system A system configured to deliver dry pressurized air, derived from ambient air, to underground or outdoor cables, conduit, waveguides, plenums or other air spaces for the purpose of preventing the ingress of moisture or contamination. The system includes a ... | 07/15/2003 |
| 6546714 | Reduced toxicity fuel satellite propulsion system including plasmatron A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the... | 04/15/2003 |
| 6499288 | Pressurizer for a rocket engine The present invention provides for a pressurizer for pressurizing a fluid, comprising a pressurant entrance for the introduction of a pressurant, a fluid entrance for the fluid, a fluid exit for the fluid, and a transfer chamber movable in a cycle with re... | 12/31/2002 |
| 6484491 | Hydrogen motor for water craft A system for propelling a watercraft using hydrogen. The system comprises a combustion chamber, an accumulator system, an ignition system, and a propulsion control system. The combustion chamber defines an upper portion and a lower portion. The accumulato... | 11/26/2002 |
| 6419771 | Non-toxic hypergolic miscible fuel with stable storage characteristics The non toxic bipropellent of the present invention contains a non-toxic hypergolic miscible fuel (hereinafter referred to as "NHMF") and a rocket grade hydrogen peroxide. This NHMF has rapid ignition capability and minimizes the formation of precipitate,... | 07/16/2002 |
| 6253539 | Convective and turbulent shear mixing injector A method for using an injector to combust a first fluid and a second fluid comprises a directing the first fluid step and a shrouding step. The directing step comprises directing the first fluid in a central coaxial flow generally perpendicularly through ... | 07/03/2001 |
| 6230491 | Gas-generating liquid compositions (persol 1) A family of water-based gas-generating liquid compositions is described. A composition of the present invention includes: hydrogen peroxide; ammonium nitrate; and water. Compositions of the present invention may be mixed with fuels to make monopropellants... | 05/15/2001 |
| 6212876 | Simplified high-efficiency propulsion system A simplified rocket engine a rocket engine has a rotor assembly with an ultracentrifugal (over 200 meters/second tangential velocity) liquid pump arranged around a combustion chamber so as to provide both forced convective and Coriolis-effect and centripe... | 04/10/2001 |
| 6210504 | Tertiary amine azides in liquid or gel fuels in gas generator systems A liquid gas generator system supplies gas pressure only when it is needed. Hydrazine and hydrazine blends have been considered for liquid gas generators because of their ability to decompose at ambient conditions on an iridium catalyst to form warm (1000... | 04/03/2001 |
| 6050085 | Method of injecting a first and a second fuel component and injection head for a rocket In order to improve a method of injecting a first and a second fuel component into a combustion chamber, particularly of a rocket engine, wherein an injection element guides the first fuel component in an inner cylindrical stream and the injection element... | 04/18/2000 |
| 6013143 | Tertiary amine azides in hypergolic liquid or gel fuels propellant systems Inhibited Red Fuming Nitric Acid (IRFNA) type IIIB and monomethyl hydrazine (MMH) ignite when contacted with each other because of a hypergolic chemical reaction and are the preferred oxidizer and fuel for bipropellant rocket propulsion systems. These pro... | 01/11/2000 |
| 5932837 | Non-toxic hypergolic miscible bipropellant The non-toxic bipropellent of the present invention contains a non-toxic ergolic miscible fuel (NHMF) and a rocket grade hydrogen peroxide. This non-toxic hypergolic miscible fuel (NHMF) has rapid ignition capability. The non-toxic hypergolic miscible fu... | 08/03/1999 |
| 5873240 | Pulsed detonation rocket engine A pulse detonation rocket engine, having at least two detonation chambers. The rocket propelled vehicle includes at least one fuel delivery system in fluid communication with each of the at least two detonation chambers, and at least one oxidant delivery ... | 02/23/1999 |
| 5780765 | Pyrogen compound kit for an electrical model rocket ignitor The invention is directed to an electrical ignitor for a model rocket, including two insulated lead wires, with each lead wire having an uninsulated end. An element wire interconnects the uninsulated ends from each lead wire. The element wire forms a plur... | 07/14/1998 |
| 5747665 | Tungsten as a hypergolic fuel gel additive Tungsten is added to fuel gels to increase the density specific impulse. l gels contain monomethylhydrazine or other hypergolic liquids well known in the art. The quantity of tungsten employed can vary from 10%-98% weight percent depending on the specifi... | 05/05/1998 |
| 5665272 | Multifuel combustion engine and use in generating obscurant smoke The multifuel combustion engine is a Lenoir cycle (constant volume), pulst combustion engine capable of operating on gasoline, diesel or kerosene based fuels. Although the preferred embodiment is described in terms of Lenoir cycle pulsejet engines, the p... | 09/09/1997 |
| 5622046 | Multiple impinging stream vortex injector Current state-of-the art injection methodologies for bipropellant engines ly on either impingement or turbulence to mix the fuel and oxidizer streams. The multiple impinging stream vortex injector combines both mixing schemes into a single injector. Both ... | 04/22/1997 |
| 5621156 | Hypergolic fuel formulation: diethylethanolamine, triethylamine, and carbon A hypergolic fuel formulation which is consistently hypergolic with inhibd red fuming nitric acid is comprised of diethylethanolamine from about 44-72 weight percent, triethylamine from about 11-18 weight percent, and carbon from about 45-10 weight perce... | 04/15/1997 |
| 5582001 | Hybrid rocket combustion enhancement The combustion of a hybrid engine is improved by continuously injecting into a precombustion chamber a hypergolic fluid such as triethyl aluminum which exothermically reacts with and vaporizes the oxidizer such as liquid oxygen. The prevaporized oxidizer ... | 12/10/1996 |
| 4901525 | Booster-sustainer rocket engine and method A bi-propellant self-contained propulsion system is provided for powering rockets. A plurality of turbopump assemblies are provided to take liquid propellants from low pressure storage tanks to a substantially higher pressure thrust chamber. Substantially... | 02/20/1990 |
| 4777794 | Mass flow rate regulation of propellant fluid in the feed system of a bi-propellant, pressure-fed rocket engine A method and apparatus 10 for self-regulating the mass flow rate of a fluid comprises a housing 12 defining an upper chamber 14 and a lower chamber 16, a sealed and pressurized bellows 30 contained within the upper chamber 14, spring bias means 58 contain... | 10/18/1988 |
| 4739613 | Bi-propellant blade valve assembly A compact, valve assembly (10) is provided having multiple chambers. A forward chamber (14) retains dual T-shaped blades (36) having shaped orifices (38) for controllably metering at least two fluids passing through the valve assembly. The valve assembly ... | 04/26/1988 |
| 4499723 | Tris(2-azidoethyl)amine and method of preparation thereof A new compound tris(2-azidoethyl)amine, N-(CH2 CH2 N3)3, and its method of preparation is disclosed. The subject azido derivative of a tertiary amine has the empirical formula C6 H12 N... | 02/19/1985 |
| 4320621 | Prevention of ammonia formation in rocket motors and laser pumping systems Disclosed is a method for the prevention of the formation of ammonia as a product in the reaction of hydrazine and a halogen oxidizer used in a liquid-propelled rocket engine and in chemical laser pumping systems. The method employs vanadium pentafluoride... | 03/23/1982 |
| 4316359 | Method of imparting hypergolicity to non-hypergolic rocket propellants Disclosed is a method of converting non-hypergolic, liquid, rocket propellants into hypergolic propellants. The method to accomplish the conversion relates to the use of ammonium metavanadate as an additive to the liquid oxidant, such as, red fuming nitri... | 02/23/1982 |
| 4275254 | Dimerization of norbornadiene to a mixture of exo-endo and endo-endo hexacyclic dimers Norbornadiene [bicyclo (2.2.1) heptadiene-2,5] is dimerized to a mixture of mainly the exo-endo stereoisomer of the hexacylic dimer of norbornadiene at both an excellent selectivity and conversion using an effective amount of a two component catalytic sys... | 06/23/1981 |
