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7472544 |
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...
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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....
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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...
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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...
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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...
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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...
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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....
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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 ( 14 A, 14...
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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...
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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...
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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...
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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...
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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...
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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...
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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....
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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6226980 |
Liquid-propellant rocket engine with turbine gas afterburning
The engine comprises a chamber, fuel and oxidizer booster pumps, a turbopump unit, a gas generator, an electrically driven thrust regulator, and a fuel throttle. A programmable starting and...
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6220016 |
Rocket engine cooling system
A rocket engine comprises first and second combustion chambers with respective combustion chamber liners bounding respective annular passages, wherein the first combustion chamber discharges into...
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6189315 |
Low-cost gas generator and ignitor
A gas generator and ignitor assembly for powering a turbine of a turbopump assembly for a rocket engine comprises an injector and a combustion chamber, the injector having a body member including a...
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6125763 |
Integral solid booster and hybrid thrust sustaining system and projectile incorporating the same
A rocket according to the invention includes a motor having a fuel chamber and an oxidizer tank, a nose portion provided forward of the motor, and a nozzle surrounded by fins provided aft of the...
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6073437 |
Stable-combustion oxidizer 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...
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6047541 |
HAN TEAN (xm-46) mixing gas generator propellant tank pressurizer for launch vehicles and spacecraft
A HAN TEAN mixing gas generator pressurization system is proposed for use on pressure-fed rockets. HAN (hydroxyl ammonium nitrate) and TEAN (triethanol ammonium nitrate) are salts dissolved in...
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5961074 |
Method and apparatus for pressurized feeding of liquid propellants to a rocket engine
A method and system for delivering pressurized propellants to a rocket engine, that has significant advantages over the current state-of-the-art. One of the propellants, the "pressurizing...
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5921167 |
Hermetic shear seal for piston displacement fuel tank
In space exploration, an attitude control engine or a thruster may have an extended period, such as years, of inactivity prior to being required to complete a desired mission. The fuel for this...
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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...
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5873241 |
Rocket engine auxiliary power system
Disclosed is a rocket engine which uses pressurized, vaporized propellant from the engine cycle to drive the boost pumps that provide propellants to the primary pumps. Additionally, an accumulator...
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5839463 |
Valve assembly for fluid transfer system
A valve assembly for transferring fluid from a fluid supply tank to a fluid holding tank. The valve assembly includes a housing having a first port for communication with the fluid supply tank and...
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5823478 |
Pressure feed for liquid propellant
One of the propellants used in a bipropellant rocket engine has a vapor pressure sufficiently high under prevailing condition to generate vapor at a pressure sufficiently high to pressurize both...
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5768885 |
Regenerative piston liquid propellant rocket motor
A regenerative liquid propellant rocket motor including a body having an integrally formed central tube. A primary combustion chamber is disposed in the body. A secondary combustion chamber is...
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5755091 |
Regenerative piston engine for combustion of liquid monopropellant
A regenerative liquid propellant engine system includes a body having opposed ends. A combustion chamber is disposed in the body. A reservoir of liquid propellant is also disposed in the body. A...
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5746050 |
Gaseous product delivery system
There is provided a system for the delivery of a gaseous product to a reaction chamber. The system includes a fuel tank containing a hypergolic liquid displaced from the fuel tank by a pressurized...
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5722232 |
Hybrid helium heater pressurization system and electrical ignition system for pressure-fed hybrid rockets
A system for pressurizing a liquid oxygen tank (20) in a pressure-fed hybrid rocket (100) provides pressure at a first end of the tank (20) so that liquid oxygen can exit the second end. A hybrid...
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5697212 |
Rocket propellant tank self-pressurization
A device for pressurizing at least one propellant tank feeding the combustion members of a space vehicle, the tank(s) being connected to one or more pipes for feeding said combustion members, and...
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5661970 |
Thrust-generating device
Thrust-generating device with rocket engines arranged in pairs opposite each other for multiple ignition as well as individual and group activation and with an amount of fuel sufficient for the...
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5640844 |
Pressurization and control devices using high vapor pressure liquids
There is provided a system for expelling a liquid fuel component from a tank to a rocket engine utilizing a pressurized gas to displace the propellant. A pressurized high vapor pressure liquid is...
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5636513 |
Two stage pressurization system for aerospace applications
There is provided a two-stage system for expelling a liquid fuel component from a main fuel tank to a rocket engine. A first vessel contains a first gas pressurized to the desired operating...
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5598762 |
Fluid storage tank employing an isolation seal
A fluid storage tank utilizing an isolation seal in which a leak proof isolation seal covers the entire head of the piston of the storage tank requiring only a single fluid tight seam to seal off...
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5551230 |
Heat induced high pressure lox pump rocket engine cycle
A liquid hydrogen-liquid oxygen (LH 2 -LOX) rocket engine system wherein a conventional oxidizer turbo pump is replaced with a jet pump--a jet oxidizer pump. Beneficial features of the jet...
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5531067 |
Optimized system for feeding a reignitable rocket engine
The present invention relates to a system for feeding the engines of a space vehicle with at least one liquid propellant, the system comprising for the purpose of storing said liquid propellant...
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5471833 |
Rocket propellant pressurization system using high vapor pressure liquids
There is provided a system for expelling a liquid fuel component from a tank to a rocket engine utilizing a pressurized gas to displace the propellant. A pressurized high vapor pressure liquid is...
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5469701 |
Fluid storage and expulsion system
A fluid storage and expulsion system having a rigid tank, the tank having two propellant chambers and two independently operable piston assemblies slidable in their propellant chambers for...
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5444973 |
Pressure-fed rocket booster system
Disclosed is a space launch system having a main engine which uses turbopumps to provide fuel and oxidizer to the main engine combustion chamber, and one or more booster engines that use high...
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5410884 |
Combustor for gas turbines with diverging pilot nozzle cone
A gas turbine combustor suppresses the generation of NOx by mixing a fuel and air homogeneously. A pilot nozzle is provided at the center of the gas turbine combustor. A plurality of main nozzles...
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5410874 |
Method and apparatus for increasing combustion chamber pressure in a high pressure expander cycle rocket engine
Disclosed is a method and apparatus for producing combustion chamber pressure in excess of 1500 psia at thrust levels in excess of 100,000 pounds in an expander cycle rocket engine.
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