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| Number | Title | Issue Date |
| 7997060 | Rocket engine power cycle An expander heat exchanger cycle system provides a fuel or oxidizer routed through a heat exchanger to cool and condense a coolant/turbine drive fluid. ... | 08/16/2011 |
| 7784268 | Partial superheat cycle for operating a pump in a rocket system A system and method of driving a fuel pump and/or an oxidizer pump in a propulsion system includes pumping an oxidizer from an oxidizer supply to a rocket engine with the oxidizer pump. A first portion of the pumped oxidizer is used for combustion in the rocket engi... | 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 |
| 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 |
| 7257940 | Device and method for pumping a fluid A method of pumping a fluid includes: providing a pressurizer for pressurizing the fluid, the pressurizer including at least two storage tanks, where, for each storage tank, the pressurizer includes a propellant entrance valve, a propellant exit valve, a pressurant ... | 08/21/2007 |
| 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 |
| 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 |
| 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 |
| 7194853 | Pressurizer for a rocket engine A pump for pressurizing a fluid includes an engine portion including a first pressure vessel, a first piston movable inside the first pressure vessel, at least two pressurant entrance valves connected to the first pressure vessel, and at least two pressurant exit va... | 03/27/2007 |
| 7145052 | Decontamination apparatus and methods Decontamination apparatus and methods involve catalytic decomposition of hydrogen peroxide to drive additional hydrogen peroxide to a contaminated location. ... | 12/05/2006 |
| 7145836 | Underwater acoustic generator using pulse engine and gas disperser A high-pressure, moving-piston pulse engine (modified HIPPE) 10 is used to produce one or a series of pulses of acoustic energy in a marine environment for acoustic communication, detection, classification or jamming. The HIPPE engine 10 is modified by... | 12/05/2006 |
| 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 |
| 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 |
| 7007456 | Dual chamber pump and method Disclosed is a pneumatically powered high-pressure and lightweight fluid pump. The pump is useful for pumping fuel for liquid rocket engines and for pumping water, such as for fire suppression. During operation of the pump, liquid is drained from a tank into a pump ... | 03/07/2006 |
| 6973773 | Propellant supply device A propellant supply device (10) is provided for a vehicle (11) having a main propulsion motor (12) and having an attitude control system (11) including a plurality of thrusters (14A, 14B, 14C, . . . , 14F). The... | 12/13/2005 |
| 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 |
| 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 |
| 6935109 | Monoprolellant/hypergolic powered proportional actuator Systems and methods involving monopropellant and hypergolic powered proportional actuators that may be used in applications such as robotics. A blowdown tank delivers fuel to a reaction site, produce gaseous products. Those gaseous products are transported to a pres... | 08/30/2005 |
| 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 |
| 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 |
| 6907735 | Hydrogen fueled electrical generator system and method thereof A system and method are provided for generating electricity for use with liquid hydrogen storage facility. The system includes a liquid hydrogen storage tank with a pressure relief. An energy conversion device is connected to the pressure relief valve an converts th... | 06/21/2005 |
| 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 |
| 6834493 | System for reducing pump cavitation Cavitation is reduced in a rotary pump while the pump performance is maintained by utilizing a low-temperature fluid source already present in the pump system. The fluid from the low-temperature fluid source receives heat from the fluid flowing to the pump, thereby ... | 12/28/2004 |
| 6751945 | Pressurizer for a rocket engine A pressurizer for pressurizing a fluid includes: a pressurant entrance configured for the introduction of a pressurant; a fluid entrance configured for the introduction of the fluid; a fluid exit configured for the expulsion of the fluid; and at least one transfer c... | 06/22/2004 |
| 6691504 | Gaseous-fuel breathing rocket engine A gaseous-fuel rocket engine in which an expanding oxidizer driven turbine or electric motor drives the an axial gaseous-fuel turbine compressor. The oxidizer is subsequently injected into a gaseous-fuel duct surrounding the axial gaseous-fuel compressor ... | 02/17/2004 |
| 6655127 | Pre-burner for low temperature turbine applications A method is provided for using high concentrations of hydrogen peroxide to drive a turbine (20') in a turbopump fed rocket engine (12'). The method includes the steps of: (a) receiving fuel into a fuel rich pre-burner (50); (b) receiving high concentratio... | 12/02/2003 |
| 6640536 | Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent A hybrid rocket motor includes a storage tank which stores an oxidizer under relatively low pressure, a turbopump preferably directly coupled to an outlet of the storage tank which pressurizes the oxidizer to a relatively high pressure, a combustion chamb... | 11/04/2003 |
| 6606853 | Rocket propulsion system A rocket propulsion system, comprising: a rocket engine; and a turbopump supplying fuel or oxidizer to the rocket engine. The turbopump can supply an; adjustable flow of the fuel or oxidizer to throttle the rocket engine. The turbopump includes a catalyst... | 08/19/2003 |
| 6591603 | Pintle injector rocket with expansion-deflection nozzle The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A pr... | 07/15/2003 |
| 6532741 | Gas generator for producing adjustable flow A gas generator, comprising a catalyst section and a mixer section. The catalyst section has openings through which a material enters and reacts with a catalyst to decompose and to produce heat. The mixer section, located downstream of the catalyst sectio... | 03/18/2003 |
| 6505463 | Pre-burner operating method for rocket turbopump A method is provided for using high concentrations of hydrogen peroxide to drive a turbine (20') in a turbopump fed rocket engine (12'). The method includes the steps of: (a) receiving fuel into a fuel rich pre-burner (50); (b) receiving high concentratio... | 01/14/2003 |
| 6499287 | Integrated tankage for propulsion vehicles and the like The present invention provides apparatus and methods for integrating structural members inside the body of a propulsion vehicle with tankage used to store fluid propellant and the like. Propulsion vehicles may be made lighter, more compact, cheaper, and e... | 12/31/2002 |
| 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 |
| 6470670 | Liquid fuel rocket engine with a closed flow cycle A liquid fuel rocket engine with a closed direct auxiliary flow cycle has a combustion chamber connected to each liquid fuel source through a respective main liquid fuel supply line. A turbo pump is provided in each main fuel supply line. The turbo pump i... | 10/29/2002 |
| 6341762 | Service valve and use of same in reaction control system Various types of valves are disclosed, as well as the use of the same in a reaction control system for space travel vehicle applications. Multiple functions are provided by one of these valve designs by providing multiple flowpaths through the valve. An i... | 01/29/2002 |
| 6321528 | Turbine, for a liquid-propellant rocket engine mainly The invention relates to the field of power machine building and concerns the improvements in turbines for liquid-propellant rocket engines. A turbine includes a casing enclosing a working chamber and a propellant feed passage communicating with the worki... | 11/27/2001 |
| 6298868 | Multifunctional valve and use of same in reaction control system Various types of valves are disclosed, as well as the use of the same in a reaction control system for space travel vehicle applications. Multiple functions are provided by one of these valve designs by providing multiple flowpaths through the valve. An i... | 10/09/2001 |
| 6289671 | Plug for a liquid-propellant rocket engine chamber Plugs for protecting internal spaces of rocket combustion chambers against moisture, dust, and other environmental factors. Each plug includes a central rod with a bracket fastened to it. The plug also includes a sleeve with radially extending structural ... | 09/18/2001 |
| 6269647 | Rotor system A rotor system for a rocket engine comprises a first hollow shaft portion and a surrounding annular duct. The interior of the first hollow shaft portion is adapted to receive a first propellant component, and is in fluid communication with a first rotary ... | 08/07/2001 |
