By Chemical Reaction Patents (Class 60/205)
  • Patent number: 11975851
    Abstract: A hybrid power system for a vertical takeoff and landing (“VTOL”) aircraft including a first power source operable to provide a power output for at least a forward flight mode; and a second power source configured to provide a high specific power output for an altitude adjustment flight mode, the second power source including an auxiliary gas generator coupled to a turbine and a drive system. In other aspects, there is provided a VTOL aircraft and methods for providing power to a VTOL aircraft.
    Type: Grant
    Filed: April 7, 2021
    Date of Patent: May 7, 2024
    Assignee: Bell Textron Inc.
    Inventor: Troy C. Schank
  • Patent number: 10590887
    Abstract: A hardware configuration and related control strategy is disclosed that accepts an electric power input typical of space flight systems and converts that energy into a spark pulse train with fixed/predetermined performance metrics for the following system parameters: time to first spark, peak breakdown voltage amplitude, spark repetition rate and energy delivered per spark, which have all been optimally chosen to reliably ignite certain fuel mixtures, which have been proven to be beneficial for use in aerospace applications.
    Type: Grant
    Filed: May 19, 2017
    Date of Patent: March 17, 2020
    Assignee: Alphaport, Inc.
    Inventors: Anthony J. Miranda, John Heese
  • Patent number: 9035226
    Abstract: An exoatmospheric vehicle uses a control system that includes a thrust system to provide thrust to control flight of the vehicle. A regenerative heat system is used to preheat portions of the thrust system, prior to their use in control of the vehicle. The heat for preheating may be generated by consumption of a fuel of the vehicle, such as a monopropellant fuel. The fuel may be used to power a pump (among other possibilities), to pressurize the fuel for use by thrusters of the thrust system. The preheated portions of the thrust system may include one or more catalytic beds of the thrust system, which may be preheated using exhaust gasses from the pump. The preheating may reduce the response time of the thrusters that have their catalytic beds preheated. Other thrusters of the thrust system may not be preheated at all before operation.
    Type: Grant
    Filed: January 20, 2014
    Date of Patent: May 19, 2015
    Assignee: Raytheon Company
    Inventors: Wayne C Jouse, Mark S Muktoyuk
  • Publication number: 20150013305
    Abstract: A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.
    Type: Application
    Filed: July 15, 2013
    Publication date: January 15, 2015
    Inventors: Charles J. Trefny, Vance F. Dippold
  • Publication number: 20140331682
    Abstract: A high-speed-launch ramjet boost (HSLRB) engine includes a combustion system for igniting fuel pumped by a fuel pump from a fuel tank, where the combustion system includes an igniter, fuel injectors and frame holders. An inlet provides a pathway for air to flow toward the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator is included for exhausting exhaust gas from combustion of the fuel by the combustion system. A processor is coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein the processor provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle.
    Type: Application
    Filed: November 1, 2013
    Publication date: November 13, 2014
    Inventor: MARK BOVANKOVICH
  • Patent number: 8884202
    Abstract: A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks.
    Type: Grant
    Filed: March 9, 2011
    Date of Patent: November 11, 2014
    Assignee: United Launch Alliance, LLC
    Inventor: Frank C. Zeglar
  • Publication number: 20140305098
    Abstract: Systems and methods are described herein for a hybrid liquid propellant rocket engine. In an embodiment, the engine includes a first pump powered by a first turbine, a second pump powered by a second turbine, and a gas generator. An output of the gas generator is connected to the first turbine and the second turbine. The engine further includes a third pump powered by a third turbine, a fourth pump powered by a fourth turbine, and a nozzle having an expander cycle in a wall and a combustion chamber. An output of the third pump is connected to the expander cycle and an output of the wall is connected to the third turbine and the fourth turbine. An output of the fourth pump, an output of the third turbine, and an output of the fourth turbine are connected to the combustion chamber.
    Type: Application
    Filed: March 14, 2014
    Publication date: October 16, 2014
    Applicant: Orbital Sciences Corporation
    Inventor: Antonio L. Elias
  • Publication number: 20140137539
    Abstract: A detonation thrust-producing device includes an explosive located in a recess in an external surface of a body. Detonation of the explosive expels material out of the recess, providing thrust to the body in an opposite direction. A mass, such as a metal disk, may be placed blocking or covering the external opening. The body may be a part of a vehicle, such as an airborne projectile. The thrust-producing device may include multiple detonation motors arrayed around the body, capable of being individually or multiply detonated. Such thrust-producing devices may be used for attitude adjustment, steering, or other control of the flight of the projectile or other air vehicle. The detonation thrust-producing devices have the advantage of a faster-response time than propellant-based devices, and do not need the nozzles that are used with many propellant-based devices.
    Type: Application
    Filed: November 19, 2012
    Publication date: May 22, 2014
    Applicant: RAYTHEON COMPANY
    Inventor: RAYTHEON COMPANY
  • Publication number: 20130186059
    Abstract: A dual fuel propulsion system comprising a gas turbine engine configured to generate a propulsive thrust using a cryogenic liquid fuel.
    Type: Application
    Filed: September 30, 2011
    Publication date: July 25, 2013
    Applicant: General Electric Company
    Inventors: Michael Jay Epstein, Kurt David Murrow, Nicholas Rowe Dinsmore, Samuel Martin, Randy Vondrell, Robert Harold Weisgerber, Narendra Digamber Joshi
  • Publication number: 20130145742
    Abstract: A rocket engine system with a fuel conversion system in communication with a gas generator.
    Type: Application
    Filed: December 13, 2011
    Publication date: June 13, 2013
    Inventors: Robert B. Fowler, Claude R. Joyner
  • Publication number: 20120269633
    Abstract: A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.
    Type: Application
    Filed: April 19, 2011
    Publication date: October 25, 2012
    Applicant: Raytheon Company
    Inventors: Jeremy C. Danforth, Richard D. Loehr, Kevin P. Murphy
  • Publication number: 20120079803
    Abstract: An apparatus for reducing heating effects of an exhaust plume of a jet engine on an impinged surface includes fluid injectors disposed adjacent and aimed into an exhaust plume zone that's to be occupied by an exhaust plume when the engine is running. A flow generator transmits fluid flow into such an exhaust plume through the injectors. Each injector emits fluid in at least two divergent directions to increase the cross-sectional area of the exhaust plume by forming fluidic lobes in the exhaust plume.
    Type: Application
    Filed: September 30, 2010
    Publication date: April 5, 2012
    Applicant: Lockheed Martin Corporation
    Inventors: Daniel N. Miller, Neal D. Domel, Cole W. Schemm
  • Publication number: 20120036829
    Abstract: The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.
    Type: Application
    Filed: October 26, 2011
    Publication date: February 16, 2012
    Applicant: FORET PLASMA LABS, LLC
    Inventor: Todd Foret
  • Patent number: 8024918
    Abstract: Methods and systems are provided for propelling a vehicle. In an embodiment, by way of example only, a method includes flowing a decomposed hydroxylammonium nitrite (HAN)-based propellant into a chamber, introducing an aspirated non-polar fuel into the chamber, and combusting the decomposed HAN-based propellant and the aspirated non-polar fuel to produce an exhaust gas.
    Type: Grant
    Filed: April 29, 2008
    Date of Patent: September 27, 2011
    Assignee: Honeywell International Inc.
    Inventor: Donald L. Mittendorf
  • Patent number: 7959749
    Abstract: A gas generating composition of the present invention contains at least one fuel selected from carboxylic acids, salts of carboxylic acids, and polymers; at least one perchlorate salt; and/or at least one metal oxide or metal hydroxide. A gas generating system 200 containing a gas generant in accordance with the present invention is also contemplated.
    Type: Grant
    Filed: January 31, 2007
    Date of Patent: June 14, 2011
    Assignee: TK Holdings, Inc.
    Inventors: Sean P. Burns, Slaven Domazet
  • Publication number: 20100326043
    Abstract: An expander cycle rocket engine includes a primary nozzle with a heat exchanger formed therein to cool the nozzle and heat up a fluid used to drive a turbo-pump, and a secondary heat exchanger is located within the primary nozzle and includes passages to channel the fluid in order to add additional heat to the fluid used to drive the turbo-pump. The secondary heat exchanger can be a nozzle shaped heat exchanger located within the primary nozzle, and struts that secure the nozzle shaped heat exchanger within the primary nozzle and channel the fluid between nozzles. The concentric arrangement of first and second heat exchangers can transfer more heat from the combustion gases to the fluid that is used to drive the turbo-pump such that higher pressures can be obtained allowing for larger nozzles and much higher thrust than can be obtained with traditional nozzle engines, or provide significantly higher chamber pressures for engines in the prior art thrust class.
    Type: Application
    Filed: January 31, 2007
    Publication date: December 30, 2010
    Applicant: Florida Turbine Technologies, Inc.
    Inventor: Philip C. Pelfrey
  • Patent number: 7824783
    Abstract: The present invention provides a heretofore-unknown use for zirconium nitride as a hydrogen peroxide compatible protective coating that was discovered to be useful to protect components that catalyze the decomposition of hydrogen peroxide or corrode when exposed to hydrogen peroxide. A zirconium nitride coating of the invention may be applied to a variety of substrates (e.g., metals) using art-recognized techniques, such as plasma vapor deposition. The present invention further provides components and articles of manufacture having hydrogen peroxide compatibility, particularly components for use in aerospace and industrial manufacturing applications. The zirconium nitride barrier coating of the invention provides protection from corrosion by reaction with hydrogen peroxide, as well as prevention of hydrogen peroxide decomposition.
    Type: Grant
    Filed: May 5, 2010
    Date of Patent: November 2, 2010
    Assignee: The Boeing Company
    Inventor: Ali Yousefiani
  • Publication number: 20100218478
    Abstract: A counter-rotating blade stage in lieu of a stator stage may compensate for relatively low rotational speed of a gas turbine engine spool. A first spool may have at least one compressor blade stage and at least one turbine blade stage. A combustor is located between the at least one compressor blade stage and the at least one turbine blade stage along a core flowpath. The at least one counter-rotating compressor blade stage is interspersed with the first spool at least one compressor blade stage. A transmission couples the at least one additional compressor blade stage to the first spool for counter-rotation about the engine axis.
    Type: Application
    Filed: June 19, 2006
    Publication date: September 2, 2010
    Inventors: Brian D. Merry, Gabriel L. Suciu, John P. Nikkanen
  • Patent number: 7707819
    Abstract: Hollow RX-08HD cylindrical charges were loaded with boron and PTFE, in the form of low-bulk density powders or powders dispersed in a rigid foam matrix. Each charge was initiated by a Comp B booster at one end, producing a detonation wave propagating down the length of the cylinder, crushing the foam or bulk powder and collapsing the void spaces. The PdV work done in crushing the material heated it to high temperatures, expelling it in a high velocity fluid jet. In the case of boron particles supported in foam, framing camera photos, temperature measurements, and aluminum witness plates suggest that the boron was completely vaporized by the crush wave and that the boron vapor turbulently mixed with and burned in the surrounding air.
    Type: Grant
    Filed: September 22, 2004
    Date of Patent: May 4, 2010
    Assignee: Lawrence Livermore National Security, LLC
    Inventors: James A. Viecelli, Lowell L. Wood, Muriel Y. Ishikawa, John H. Nuckolls, Phillip F. Pagoria
  • Patent number: 7689515
    Abstract: A method of evaluating a power plant having a design life based on operating the plant within an allowable chemical exposure range includes accumulating a history of a chemical exposure of a steam generating portion of the power plant. The method also includes determining a remaining life of the plant based on the history of the chemical exposure and assuming continued operation of the plant within the allowable chemical exposure range. The method may also include evaluating an economic value of operating the plant based on the remaining life of the plant.
    Type: Grant
    Filed: December 10, 2004
    Date of Patent: March 30, 2010
    Assignee: Siemens Energy, Inc.
    Inventors: James C. Bellows, Fred W. Shoemaker
  • Publication number: 20090031700
    Abstract: This invention involves the mixtures of oxides of nitrogen and oxygen (O2) as the oxidizing component in propulsion, gas generation and power generation applications. Advantages of the oxidizers of the inventions may be self pressurization, high density, density impulse, higher operational temperatures, and high Isp performance. The invention provides devices, methods and compositions related to the disclosed oxidizers.
    Type: Application
    Filed: November 12, 2007
    Publication date: February 5, 2009
    Applicant: Space Propulsion Group, Inc.
    Inventor: Arif Karabeyoglu
  • Patent number: 7350482
    Abstract: A non-polluting engine that produces mechanical, rotary motion, and produces oxygen as a principle gaseous byproduct. The engine employs a fuel mixture that includes two components that together produce oxygen. The fuel mixture is introduced to a combustion chamber where it is heated to facilitate the rapid production of oxygen. The expansion of the oxygen within the combustion chamber is translated to rotary mechanical energy. The oxygen produced during the reaction is expelled from the combustion chamber and released into the atmosphere.
    Type: Grant
    Filed: February 24, 2005
    Date of Patent: April 1, 2008
    Inventor: Juan Sanchez, Jr.
  • Patent number: 7279143
    Abstract: A plasmatron-catalyst system. The system generates hydrogen-rich gas and comprises a plasmatron and at least one catalyst for receiving an output from the plasmatron to produce hydrogen-rich gas. In a preferred embodiment, the plasmatron receives as an input air, fuel and water/steam for use in the reforming process. The system increases the hydrogen yield and decreases the amount of carbon monoxide.
    Type: Grant
    Filed: August 13, 2004
    Date of Patent: October 9, 2007
    Assignee: Massachusetts Institute of Technology
    Inventors: Leslie Bromberg, Daniel R. Cohn, Alexander Rabinovich, Nikolai Alexeev
  • Patent number: 7124574
    Abstract: 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 or hole is defined by a tube extending through the face plate. The tube extends through the face plate in a portion of a through bore which also is used to define the second annulus. The second annulus is formed using a throughbore through which the tube extends. This allows the second annulus to always be formed inherently and precisely substantially coaxial with the first annulus. Moreover, the second annulus can be formed with a much greater tolerance than if other independent components needed to be added.
    Type: Grant
    Filed: December 4, 2002
    Date of Patent: October 24, 2006
    Assignee: United Technologies Corporation
    Inventors: Mark D. Horn, Shinjiro Miyata, Shahram Farhangi
  • Patent number: 6957526
    Abstract: A pressure-actuated rocket system comprises a bottom base, a detonator and a rocket body. A top base is placed on a top surface of the bottom base. At least one through hole is located on a side of the top base and extended to an opening of the top surface. The hollow detonator has a closed and an opened ends. The rocket body is a bottle with fins. After soda powder is placed inside the detonator and vinegar is filled into the rocket body, the bottom base, the detonator and the rocket body are held inclined. The openings are aimed at the inclined bottom base in turn, the pressure-actuated rocket system is then turned upside down. Soda powder subsequently falls and reacts with vinegar, and gas is generated. A pressure accumulates inside the rocket body until it is high enough to shoot the rocket body up.
    Type: Grant
    Filed: July 14, 2004
    Date of Patent: October 25, 2005
    Inventor: Chitsan Lin
  • Patent number: 6832471
    Abstract: 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 section of the combustion chamber and the other to a downstream or main section of the chamber. The preburner combustion gas is cooled in a substantially uniform manner to a moderate temperature by cooling the bulk of the gas rather than cooling only the gas in a boundary layer adjacent to the chamber wall. The combustion gas produced in the downstream section is hotter, and heat from that gas is drawn through the chamber wall into a jacket. The limited combustion in the preburner permits the use of a cooling element with highly intimate heat exchange construction, extracting a high level of energy from the preburner gas without damage to the cooling element and an overall improvement in the regenerative cooling.
    Type: Grant
    Filed: March 12, 2003
    Date of Patent: December 21, 2004
    Assignee: Aerojet-General Corporation
    Inventor: Ross A. Hewitt
  • Publication number: 20040177603
    Abstract: 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 section of the combustion chamber and the other to a downstream or main section of the chamber. The preburner combustion gas is cooled in a substantially uniform manner to a moderate temperature by cooling the bulk of the gas rather than cooling only the gas in a boundary layer adjacent to the chamber wall. The combustion gas produced in the downstream section is hotter, and heat from that gas is drawn through the chamber wall into a jacket. The limited combustion in the preburner permits the use of a cooling element with highly intimate heat exchange construction, extracting a high level of energy from the preburner gas without damage to the cooling element and an overall improvement in the regenerative cooling.
    Type: Application
    Filed: March 12, 2003
    Publication date: September 16, 2004
    Applicant: Aerojet-General Corporation
    Inventor: Ross A. Hewitt
  • Patent number: 6779335
    Abstract: An apparatus is provided for burning a fuel and nitrous oxide. The apparatus has a combustor, a catalyst, a nitrous oxide supply passage for directing the nitrous oxide to a contact position with the catalyst, and a fuel supply passage for supplying the fuel to the combustor. The catalyst is for facilitating decomposition of the nitrous oxide, and the combustor is for burning the fuel, the decomposed nitrous oxide and/or further nitrous oxide decomposed in the reaction.
    Type: Grant
    Filed: December 7, 2001
    Date of Patent: August 24, 2004
    Inventor: Joseph Roger Herdy, Jr.
  • Patent number: 6705075
    Abstract: 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 chamber from the feed chamber, and igniting the solid propellant in the combustion chamber while the combustion chamber is isolated from the feed chamber.
    Type: Grant
    Filed: October 30, 2000
    Date of Patent: March 16, 2004
    Assignee: Alliant Techsystems Inc.
    Inventors: Thomas K. Highsmith, Michael D. Blair, Steven R. Wassom, William D. Starrett, Joel Dever
  • Patent number: 6684622
    Abstract: Methods and arrangements for tailoring rocket exhaust plume signatures of rocket exhaust systems are disclosed. The tailoring of the rocket exhaust plume signature is accomplished by providing and locating at least one structure having materials and/or additives that modify the radiant intensity pattern of the rocket exhaust plume upon ablation or melting into the rocket exhaust plume. The materials and/or additives can be manufactured or incorporated into preexisting ablative materials of the rocket exhaust system or be provided as stand-alone structures.
    Type: Grant
    Filed: February 26, 2002
    Date of Patent: February 3, 2004
    Assignee: Northrop Grumman Corporation
    Inventors: Charles A. Vickery, Jerry N. Mason, William D. Kruse, Mark Olmos
  • Patent number: 6662550
    Abstract: A pulsed detonation engine having improved efficiency has a detonation chamber for receiving a detonable mixture, an igniter for igniting the detonable mixture, and an outlet for discharging detonation products. A diverging-converging nozzle is provided at the outlet of the detonation chamber. The geometry of the diverging-converging nozzle is selected to enable a relatively short nozzle to significantly improve efficiency of the pulsed detonation engine.
    Type: Grant
    Filed: April 25, 2002
    Date of Patent: December 16, 2003
    Assignee: Science Applications International Corporation
    Inventors: Shmuel Eidelman, Dmitri Charov
  • Patent number: 6655124
    Abstract: Systems and methods are disclosed for tailoring rocket exhaust plume signatures of fuel-propelled vehicles. An uncombusted fuel is injected or sprayed into the exhaust plume of an ignited rocket. The injected or sprayed fuel modifies the rocket exhaust plume to simulate an exhaust plume of a different vehicle. One or more parameters associated with the injected or sprayed fuel can be modified, so that appropriate tailoring can be achieved.
    Type: Grant
    Filed: February 26, 2002
    Date of Patent: December 2, 2003
    Assignee: Northrop Grumman Corporation
    Inventors: Charles A. Vickery, William D. Kruse, Mark Olmos
  • Patent number: 6644015
    Abstract: A turbojet engine with improved thrust and high-altitude capabilities. Arrangements are provided for injecting liquid oxygen or other oxidizer into the turbojet engine before the compressor section. Cooling the incoming air by the liquid oxygen reduces the air volume, which allows a fixed inlet to be matched to varying flow conditions, allowing a greater mass of air to be ingested by the compressor section and results in a lower compressor outlet temperature. Increased mass flow, combined with more fuel results in higher exhaust gas temperatures and greater thrust. The addition of oxygen to the inlet air flow allows the engine to operate at higher altitudes by preventing flameout due to rarefied air.
    Type: Grant
    Filed: October 29, 2001
    Date of Patent: November 11, 2003
    Assignee: HMX, Inc.
    Inventor: Bevin C. McKinney
  • Patent number: 6519928
    Abstract: A process for the production of a transverse thrust in a flying object in which a defined quantity of a monergol propellent substance is introduced into a propulsion unit, which is arranged transversely relative to a longitudinal axis of the flying object to produce a thrust transverse to the longitudinal axis of the flying object. The propulsion unit has a combustion chamber, a supersonic nozzle connected to the combustion chamber and a source of heat to combust the propellant substance and produce the desired thrust for a prescribed time.
    Type: Grant
    Filed: April 26, 2001
    Date of Patent: February 18, 2003
    Assignee: Strium GmbH
    Inventors: German Munding, Wolfgang Müller, Joachim Reinecke, Peter Gleich
  • Patent number: 6415596
    Abstract: The present invention pertains to the field of rocketry and more precisely to liquid-propellant rocket engines and to rocket power units. This invention essentially relates to a method for increasing the specific impulse in a liquid-propellant rocket engine by using oxygen as well as a hydrocarbon fuel consisting of dicyclobutyl (C8H14). The dicyclobutyl provides for a substantial increase in the specific impulse of the liquid-propellant rocket engine when compared with kerosene. This invention also relates to a power unit for a rocket that has tanks for liquid oxygen and for the hydrocarbon fuel. Since the fuel tank is filled with dicyclobutyl (C8H14), it is thus possible to increase the thrust, the specific impulse, as well as the in-flight operation duration of the engine, and to reduce the weight of the tanks without any substantial change in the circuits of the liquid-propellant rocket engine and of the rocket power unit.
    Type: Grant
    Filed: March 15, 2001
    Date of Patent: July 9, 2002
    Assignee: Otkrytoe Aktsionernoe Obschestvo ″NPO Energomash imeni akademika V.P.
    Inventors: Boris Ivanovich Katorgin, Felix Jurievich Chelkis, Igor Grigorievich Storozhenko, Sergei Prokopievich Chernykh, Oleg Efimovich Batalin, Evgeny Shmerovich Finkelshtein, Alexandr Grigorievich Liakumovich, Benyamin Sinaevich Strelchik, Vladimir Serapionovich Anufriev
  • Publication number: 20020069636
    Abstract: A hybrid rocket engine and a method for propelling a rocket utilizing a vortex flow field. The flow field includes an outer fluid vortex spiraling toward a closed end of the flow field generating apparatus and an inner fluid vortex substantially concentric with the outer vortex spiraling away from the closed end and toward an outlet opening in which the inner vortex spirals in the same direction as the outer vortex, but in the opposite axial direction. The invention also relates to a rocket propulsion system utilizing the flow field in which the propulsion system includes a combustion chamber with a fuel source and an oxidizer source that deliver the said fuel and said oxidizer to the said outer and inner vortexes in a manner to support a combustion process while flowing along the flow field.
    Type: Application
    Filed: September 26, 2001
    Publication date: June 13, 2002
    Inventors: William H. Knuth, Martin J. Chiaverini, Daniel J. Gramer
  • Patent number: 6135393
    Abstract: A rocket propulsion system for spacecraft achieves greater economy, reliability and efficiency rocket by incorporating monopropellant RCS thrusters (1a-1f) for attitude control and bipropellant SCAT thrusters (5a-5c) for velocity control. Both sets of thrusters are designed to use the same liquid fuel, supplied by a pressurized non-pressure regulated tank, and operate in the blow down mode. In the propulsion system such station keeping and attitude control thrusters may function in conjunction with a large thrust apogee kick engine, which may also be of the SCAT thruster construction, that uses the same propellent fuel. Hydrazine and Binitrogen tetroxide are preferred as the fuel and oxidizer, respectively. The new system offers a simple conversion of existing monopropellant systems to a high performance bipropellant dual mode system without the extreme complexity and cost attendant to a binitrogen tetroxide--hydrazine bipropellant system.
    Type: Grant
    Filed: November 25, 1997
    Date of Patent: October 24, 2000
    Assignee: TRW Inc.
    Inventors: Robert L. Sackheim, James S. Bassichis, Dale L. Hook
  • Patent number: 5992825
    Abstract: An expansion device for doing work comprised of a housing including first and second selectively expandable sections defining an internal chamber which contains a chemical motor. Upon activation of the chemical motor, the first and second chamber are driven apart with sufficient force to allow the device to do work. The chemical motor is generally an irreversible reaction which causes the expansion device to be maintained in an expanded position.
    Type: Grant
    Filed: September 29, 1997
    Date of Patent: November 30, 1999
    Assignee: Technical Innovations, Inc.
    Inventor: Edward E. Vollenweider, II
  • Patent number: 5925322
    Abstract: The present invention relates to a combined cycle system of enhanced efficiency. The system comprises a top stage, such as a fuel cell, a partial oxidation reactor or a heat engine, and an oxygen-enriching device, such as a temperature swing adsorption device or a chemical reactor bed device, as its bottom stage. The bottom stage uses waste heat produced by the top stage to enrich the oxygen content of air that is inputted to the bottom stage, thereby producing an oxygen-enriched gas mixture as the bottom stage output. This output mixture constitutes a superior oxidant which is fed back as an input for the top stage, thus enhancing the energy conversion efficiency, cheapness, and compactness of the combined cycle system as compared to that of ordinary fuel cells, partial oxidation reactors and heat engines that use unenriched air as their oxidant input.
    Type: Grant
    Filed: July 18, 1997
    Date of Patent: July 20, 1999
    Assignee: H Power Corporation
    Inventor: John Werth
  • Patent number: 5909001
    Abstract: A high pressure pulsed gas source for accelerating a projectile along a gun barrel comprises a structure including a high voltage electrode for establishing axial electrical discharges in corresponding axial gaps behind an outlet where the projectile is located. Plasma flows at right angles to the discharges into a propellant mass that is converted into a high pressure component of the gas pulse. The gaps are arranged so that after the projectile moves away from its initial position and is in the barrel, power applied to the plasma via gaps close to the outlet is greater than power applied to the plasma via gaps farther from the outlet. To avoid damage to the gun, the gaps are arranged so power applied to the plasma is substantially the same in the discharges when plasma is initially produced. The gaps include walls that are eroded differently by the discharges so gap walls close to the outlet erode faster than gap walls farther from the outlet.
    Type: Grant
    Filed: February 5, 1997
    Date of Patent: June 1, 1999
    Assignee: General Dynamics Land Systems, Inc.
    Inventor: Yeshayahu Shyke A. Goldstein
  • Patent number: 5747730
    Abstract: An essentially particulate-free, non-toxic, odorless and colorless gas is generated in a pyrotechnic inflator device by using a eutectic solution of ammonium nitrate, guanidine nitrate and/or aminoguanidine nitrate, and minor amounts of polyvinyl alcohol and either potassium nitrate or potassium perchlorate. Ballistic modifiers such as triaminoguanidine nitrate (TAGN) or nitroguanidine (NQ) may be used as needed.
    Type: Grant
    Filed: June 7, 1996
    Date of Patent: May 5, 1998
    Assignee: Atlantic Research Corporation
    Inventors: Robert S. Scheffee, Robert Lee Thibodeau, Brian K. Wheatley
  • Patent number: 5592812
    Abstract: Gas generating compositions and methods for their use are provided. Metal complexes are used as gas generating compositions. These complexes are comprised of a cationic metal template, sufficient oxidizing anion to balance the charge of the complex, and a neutral ligand containing hydrogen and nitrogen. The complexes are formulated such that when the complex combusts nitrogen gas and water vapor is produced. Specific examples of such complexes include metal nitrite ammine, metal nitrate ammine, and metal perchlorate ammine complexes, as well as hydrazine complexes. Such complexes are adaptable for use in gas generating devices such as automobile air bags.
    Type: Grant
    Filed: February 9, 1996
    Date of Patent: January 14, 1997
    Assignee: Thiokol Corporation
    Inventors: Jerald C. Hinshaw, Daniel W. Doll, Reed J. Blau, Gary K. Lund
  • Patent number: 5579634
    Abstract: Solid rocket motor propellant formulations are provided which are capable of burning at at least two selected burn rates. The burn rate is controlled by controlling the pressure at which the propellant burns. For example, it is possible to mechanically modify the container, such as a rocket motor casing, in which the propellant is held in order to modify the pressure under which the propellant burns. Alternatively, the propellant may be configured or molded such that the pressure changes at a chosen time due to the process of burning the propellant. The propellant is capable of burning at a relatively constant burn rate at a chosen pressure. Once the pressure changes which chosen limits, the burn rate of the propellant is rapidly modified to another relatively constant burn rate. The solid rocket motor propellant is formulated with the addition of from about 0.5% to about 4.0% TiO.sub.2. The specific operating pressures and burn rates can be selected by modifying the amount of TiO.sub.
    Type: Grant
    Filed: April 1, 1994
    Date of Patent: December 3, 1996
    Assignee: Thiokol Corporation
    Inventor: Robert H. Taylor, Jr.
  • Patent number: 5566543
    Abstract: The amount of particulate matter that is forced into the passenger compartment of an automobile by the deployment of an air bag as it protects the lives of occupants is reduced by improving the filterability of the combustion products of a composition for generating gas to inflate the bag. The filterability is improved by adding a nucleating agent for alkali metal halide vapors formed during said combustion. Silica, alumina, and graphite are representative of the nucleating agents.
    Type: Grant
    Filed: November 17, 1993
    Date of Patent: October 22, 1996
    Assignee: Morton International, Inc.
    Inventors: Robert D. Taylor, Brett Hussey
  • Patent number: 5421153
    Abstract: A hydrodynamic propulsion device possessing an expansion chamber located downstream of a cross-sectional widening for the inflow of a medium which is to be expelled through a discharge nozzle. The propulsion device is constructed as a static propulsion mechanism without movable components, in that the gaseous operating medium is produced in the propulsion device through the reaction of a hydrofuel, such as NaK with water.
    Type: Grant
    Filed: October 8, 1993
    Date of Patent: June 6, 1995
    Assignee: Diehl GmbH & Co.
    Inventors: Ulrich Schleicher, Wolfgang Schwarz, Joseph Spurk
  • Patent number: 5305598
    Abstract: A novel class of energy-generating chemical processes or reactions uses cryogenically Prepared and stored materials exhibiting volcanic ground states having lifetimes exceeding several seconds. Energy generation is provided through activation of cryogenically prepared and stored material characterized by a volcanic ground potential surface in which its lowest rotation-vibration level has a lifetime sufficiently long to permit practical storage and subsequent energy release. Cryogenic preparation and storage provides that the material is kept in these lowest rotation-vibration levels, thereby avoiding thermodynamic population of the higher levels which are short-lived and therefore not suitable for practical use. In one embodiment, the He .sub.2.sup.++ v=0, J=0 level has been found to have a lifetime of 220 minutes making He.sub.2.sup.++ an ideal candidate for a fuel in which laser-induced fragmentation of He.sub.2.sup.++ into He.sup.+ +He.sup.
    Type: Grant
    Filed: October 22, 1991
    Date of Patent: April 26, 1994
    Inventor: Cleanthes A. Nicolaides
  • Patent number: 4920743
    Abstract: A propellant composition and method for limiting the corrosive properties of by-products from initiated crash bag propellant compositions comprising a 1(a) or 2(a) group metal azide salt, an oxidizer in the form of an oxide of a non-toxic transition metal element, and an effective amount of a modifier component of the formulaMe.sub.x (An).sub.owhereinMe is a metal cation selected from iron, copper, cobalt, nickel, and molybdenum;An is an anion group which is chemically compatible with and capable of reacting with the metal of the azide salt to form nitrogen gas and non-toxic by-products less corrosive than the corresponding hydroxide of the azide metal would be; andx and o are individually defined as positive numbers appropriate to indicate the correct chemical formula.
    Type: Grant
    Filed: July 25, 1988
    Date of Patent: May 1, 1990
    Assignee: Hercules Incorporated
    Inventor: Richard V. Cartwright
  • Patent number: 4833267
    Abstract: This invention relates to a method for the production of unsaturated carboxylic acid esters. More particularly, this invention relates to a method for efficient production of a corresponding ester from an acrylic acid or methacrylic acid (hereinafter referred to collectively as "(meth)acrylic acid") by the reaction of the (meth)acrylic acid with an aliphatic alcohol of 1 to 12 carbon atoms in the presence of a strongly acidic cation-exchange resin catalyst.
    Type: Grant
    Filed: March 9, 1988
    Date of Patent: May 23, 1989
    Assignee: Nippon Shokubai Kagaku Kogyo Co., Ltd.
    Inventors: Sumio Nakashima, Hideki Sogabe, Hiroshi Yoshida, Atsushi Okubo
  • Patent number: 4707980
    Abstract: The specification discloses a method and apparatus for generating electricity which substantially eliminates the problem of acid rain as well as the problems associated with nuclear and hydroelectric power. Scrap aluminum and ferric oxide are reacted in a combustion chamber. The heat of the reaction as well as the heat of molten iron flowing from the combustion chamber heats boilers, the generated gas of which is used to drive electric generators. The iron is reoxidized, with the heat of reoxidation also being used to heat boilers which drive generators. The reoxidized iron is then recycled into the combustion chamber.
    Type: Grant
    Filed: March 13, 1985
    Date of Patent: November 24, 1987
    Inventors: Samuel Wabeke, deceased, by Hilda Wabeke, heir
  • Patent number: 4658578
    Abstract: Improved igniter compositions for rocket motors are provided which, when cured, are non-volatile and are capable of igniting under vacuum conditions and burning steadily at reduced pressures. Said igniter compositions comprise:(a) about 11% to about 13% hydroxyl terminated polybutadiene binder prepolymer;(b) about 0.7% to about 2.0% polyfunctional isocyanate curing agent for said binder prepolymer;(c) about 2.0% to about 20% metallic powder fuel;(d) about 20% to about 40% large particle size ammonium perchlorate;(e) about 30% to about 50% small particle size ammonium perchlorate;(f) about 0.05% to about 5.0% non-volatile burning rate catalyst;(g) about 0.05% to about 0.50% bonding agent capable of wetting the solids in the composition by said binder prepolymer and of chemically coupling with said ammonium perchlorate; and(h) about 0.01% to about 0.20% ammonia scavenger wherein all percentages are by weight based on the total weight of the compositions.
    Type: Grant
    Filed: March 21, 1984
    Date of Patent: April 21, 1987
    Assignee: Morton Thiokol Inc.
    Inventor: Graham C. Shaw