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An aircraft having vertical takeoff and landing capability provided with at least first and second laterally extending paddle wheels rotatable on a central axis perpendicular to the longitudinal axis of the aircraft fuselage and between its nose and tail.
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| Number | Title | Issue Date |
| 7900436 | Gas-generator augmented expander cycle rocket engine An augmented expander cycle rocket engine includes first and second turbopumps for respectively pumping fuel and oxidizer. A gas-generator receives a first portion of fuel output from the first turbopump and a first portion of oxidizer output from the second turbopu... | 03/08/2011 |
| 7784269 | System and method for cooling rocket engines A propulsion system for a rocket engine and a method of cooling a rocket engine includes a propellant tank fluidically coupled to the rocket engine to hold a pressurized propellant, a coolant tank to hold a coolant, a first heat exchanger thermally coupled to the ro... | 08/31/2010 |
| 7418814 | Dual expander cycle rocket engine with an intermediate, closed-cycle heat exchanger A dual expander cycle (DEC) rocket engine with an intermediate closed-cycle heat exchanger is provided. A conventional DEC rocket engine has a closed-cycle heat exchanger terhamlly coupled thereto. The heat exchanger utilizes heat extracted from the engine's fuel ci... | 09/02/2008 |
| 7389636 | Booster rocket engine using gaseous hydrocarbon in catalytically enhanced gas generator cycle A process and a system for delivering a propellant combination to a rocket engine is described. The process comprises the steps of providing a flow of a hydrocarbon propellant fuel, raising the pressure of the hydrocarbon propellant fuel, cracking the hydrocarbon pr... | 06/24/2008 |
| 7370469 | Rocket chamber heat exchanger A rocket engine chamber has a back structure and a heat exchanger structure located radially inwardly of the back structure. The heat exchanger structure has a plurality of integrally formed cooling passageways with adjacent ones of the passageways having a common s... | 05/13/2008 |
| 7334396 | Method and apparatus for a rocket engine power cycle A system for providing an oxidizer and a fuel to a rocket engine is provided. The system includes a fuel supply system. The fuel supply system includes a fuel pump that pumps fuel to the rocket engine. The system includes a coolant supply system that supplies a cool... | 02/26/2008 |
| 7332123 | Method for manufacturing composite articles and the articles obtained therefrom A method of molding an article comprises inserting a mandrel into the cavity of the mold; placing a niobium based refractory metal intermetallic composite powder into a cavity of a mold; consolidating the niobium based refractory metal intermetallic composite around... | 02/19/2008 |
| 7302794 | Rocket engine member and a method for manufacturing a rocket engine member Method and arrangement for providing a liquid fuel rocket engine member having a load bearing wall structure (11,14) including a plurality of cooling channels (11) for handling a coolant flow. Each cooling channel (11) is provided with a flow gu... | 12/04/2007 |
| 7299622 | Component for being subjected to high thermal load during operation and a method for manufacturing such a component Method and arrangement for providing a component (1) for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part (5) tha... | 11/27/2007 |
| 7299551 | Method of assembling a rocket engine with a transition zone between the combustion chamber and the coolant system An improved engine construction, such as a rocket engine construction is provided. The engine construction comprises a combustion chamber, a smooth wall nozzle, and a transition zone between the chamber and the smooth wall nozzle. The transition zone has a coolant s... | 11/27/2007 |
| 7287725 | Missile control system and method A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rota... | 10/30/2007 |
| 7234294 | Outlet nozzle and a method for manufacturing an outlet nozzle Method and arrangement for providing an outlet nozzle (10) for use in a liquid fuel rocket engine. The nozzle forms a body of revolution having an axis (11) of revolution and a cross section that varies in diameter along said axis. The nozzle has a wal... | 06/26/2007 |
| 7216477 | Method and apparatus for a rocket engine power cycle A system for cooling a portion of a rocket engine with an inert compound and transferring the thermal energy from the inert compound to the propellants. The energy absorbed by the coolant is used also to power the turbines which powers the pumps that pump the fuel, ... | 05/15/2007 |
| 7188417 | Advanced L-channel welded nozzle design A fluid flow nozzle is formed by a plurality of adjacent L-shaped channels forming successive channel pairs. Each channel has a linking member joined to a radial member. Each linking member is welded to an adjacent linking member forming a contiguous surface of link... | 03/13/2007 |
| 7137244 | Reactor for decomposition of ammonium dinitramide-based liquid monopropellants and process for the decomposition The present invention relates to a reactor for the decomposition of ammonium dinitramide-based liquid monopropellants into hot, combustible gases for combustion in a combustion chamber, and more particularly a rocket engine or thruster comprising such reactor and a ... | 11/21/2006 |
| 7069717 | Hybrid propulsion system Disclosed is a propulsion system for a spacecraft. The propulsion system includes a supply of oxidizer and at least one nozzle. A conduit fluidly couples the supply of oxidizer and the nozzle. The conduit provides a pathway for oxidizer to flow in a downstream direc... | 07/04/2006 |
| 7051513 | Rocket engine tubular chamber with single piece jacket A method for forming a coolant system for a rocket engine combustion chamber is provided. The method comprises the steps of providing a plurality of tubes formed and shaped into the profile of a nozzle with each of the tubes having a constantly expanding cross secti... | 05/30/2006 |
| 7052648 | Method for manufacturing flange for compressor To manufacture a flange for a compressor with a relief groove by using powder metallurgy in order to prevent deformation of the compressor in operation, powder material for the flange is charged into a mold; an ablative member having a melting point lower than that ... | 05/30/2006 |
| 7028478 | Method and apparatus for the production of energy The invention provides processes and apparatuses for safely, rapidly, cost-effectively and efficiently producing a superheated steam. These processes and apparatuses involve the combustion of one or more fuels containing the element hydrogen, the element carbon or t... | 04/18/2006 |
| 7028484 | Nested channel ducts for nozzle construction and the like A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel is formed in a surface of a gas turbine engine component, and the channel is adapted for conveying a fluid flow from... | 04/18/2006 |
| 7021061 | Heat shield arrangement for a hot-gas conducting component, in particular for structural pieces of gas turbines and method for production of said arrangement The invention relates to a heat shield arrangement for a hot gas conducting structure, in particular a metal component of a gas turbine unit or combustion chamber, with the heat shield elements anchored adjacently on a support structure to cover a surface. Said heat... | 04/04/2006 |
| 7013636 | System and method for controlling the temperature and infrared signature of an engine A system and method for cooling at least a portion of an engine are provided. The engine is cooled using a fuel, such as a high heat sink fuel, that is subsequently used for combustion in the engine. The fuel can be used to cool one or more of the gases and/or compo... | 03/21/2006 |
| 6968673 | Cool gas generator and ultra-safe rocket engine A gas generator or rocket engine includes: a first storage tank configured to contain a high-pressure liquid propellant; a nozzle connected to the first storage tank; a heat source connected between the first storage tank and the nozzle and configured to add heat to... | 11/29/2005 |
| 6945032 | Method for manufacturing outlet nozzles for rocket engines A wall structure capable of withstanding high thermal load, including a wall structure with an inner wall, an outer wall positioned about the inner wall, and distancing elements located between the inner and outer walls. The distancing elements are joined to at leas... | 09/20/2005 |
| 6931832 | Monopropellant combustion system An apparatus and method are provided for decomposition of a propellant. The propellant includes an ionic salt and an additional fuel. Means are provided for decomposing a major portion of the ionic salt. Means are provided for combusting the additional fuel and deco... | 08/23/2005 |
| 6912857 | Torch igniter An improved torch igniter for use in devices such as thrust augmenters, gas turbine engines, ramjets, combined-cycle engines and industrial burners. The torch igniter includes a housing with a combustion chamber. Fuel and oxidizer are delivered into the combustion c... | 07/05/2005 |
| 6907920 | Heat exchanger panel The present invention relates to a heat exchanger panel which has broad utility in high temperature environments. The heat exchanger panel has a first panel, a second panel, and at least one fluid containment device positioned intermediate the first and second panel... | 06/21/2005 |
| 6783824 | Actively-cooled fiber-reinforced ceramic matrix composite rocket propulsion thrust chamber and method of producing the same An actively-cooled, fiber-reinforced ceramic matrix composite thrust chamber for liquid rocket propulsion systems is designed and produced with internal cooling channels. The monocoque tubular structure consists of an inner wall, which is fully integrated to an oute... | 08/31/2004 |
| 6536208 | Device for supplying fuel for a rocket propulsion unit and heat exchanger to be used in said device Device for supplying fuel for a rocket propulsion unit has a first and at least a second fuel circuit for respective different fuels. Each fuel is brought to an increased energy level by a pump and is supplied for combustion by way of injection elements. ... | 03/25/2003 |
| 6105370 | Method and apparatus for rejecting waste heat from a system including a combustion engine A method and apparatus are provided for rejecting waste heat (12) from a system (10) including a combustion engine (14), an oxidizer supply (16), and a fuel supply (18). The method includes the steps of providing a fuel flow (32) from the fuel supply (18)... | 08/22/2000 |
| 6052987 | Non-propellant fluid cooled space craft rocket engine A space craft's rocket engines are cooled by a recirculating cooling system containing a non-propellant coolant fluid, such as water and/or ethylene glycol. With that recirculating cooling system to maintain the rocket engine combustion chamber at a lower... | 04/25/2000 |
| 5918460 | Liquid oxygen gasifying system for rocket engines For a liquid rocket engine including the SSME the gaseous heat exchanger that is in the liquid oxygen turbopump exit flow path that serves to gasify the liquid oxygen for pressurizing the liquid oxygen tank and the POGO is modified by changing the flow ci... | 07/06/1999 |
| 5794435 | Stable-combustion oxidizer vaporizer for hybrid rockets A hybrid heater vaporization system (280, 380) including hybrid heaters (250, 350) can be used to vaporize liquid oxygen as it enters a motor (200, 300) to improve the combustion characteristics of a hybrid rocket (11). The motor (200, 300) preferably inc... | 08/18/1998 |
| 5765360 | Process for cooling engine walls and wall structure for carrying out the process Cooling of engine walls with fuel, wherein the walls have a structure which has an inner wall, to which hot gas is admitted during the operation, a colder outer wall, as well as a plurality of webs which connect the walls and divide the hollow space prese... | 06/16/1998 |
| 5718113 | Fuel strip A fuel member comprises a continuous, elongated, flexible and combustible structural component that has a length to width of ratio greater than 100:1, and contains within the structural component, either as a part thereof or as a separate component, an ox... | 02/17/1998 |
| 5572865 | Satellite propulsion and power system In the preferred embodiment of the invention, a cooled bipropellant thruster 70 for controlling the on-orbit position and orientation of a spacecraft is provided. The cooled bipropellant thruster 70 uses a liquid fuel and liquid oxidizer. The liquid fuel ... | 11/12/1996 |
| 5557928 | Tube rocket thrust chamber construction and method Each of the tubes of the tube thrust chamber of a rocket engine is hooked at either end with the end at the outlet oriented horizontally relative to the rocket engine's center line and the end at the inlet oriented vertically and bent outwardly away from ... | 09/24/1996 |
| 5533331 | Safe propulsion system for missile divert thrusters and attitude control thrusters and method for use of same A propulsion system for use with a missile or like aerial projectile is disclosed which is suitable for use to operate the divert thrusters and the attitude control thrusters of such a missile while using non-toxic propellants which are entirely non-react... | 07/09/1996 |
| 5417049 | Satellite propulsion and power system In the preferred embodiment of the invention, a cooled bipropellant thruster 70 for controlling the on-orbit position and orientation of a spacecraft is provided. The cooled bipropellant thruster 70 uses a liquid fuel and liquid oxidizer. The liquid fuel ... | 05/23/1995 |
| 5417056 | Axially translating screen suppressor for a gas turbine engine augmentor An augmentor screech suppressor for a gas turbine engine includes a screech suppressor liner mounted on a screech housing and an actuator for translating the screech suppressor liner axially forward and aft, with the actuator located outside the outer duc... | 05/23/1995 |
