Solid And Fluid Propellant Patents (Class 60/251)
  • Patent number: 11060483
    Abstract: A rocket engine with an improved solid fuel segment mainly comprises a combustion chamber, a solid fuel segment installed in the combustion chamber, and an oxidizer injector installed at one end of the combustion chamber. The solid fuel segment surrounds and forms a trajectory to allow the oxidizer injector to inject oxidizer into the trajectory, in particular, on the solid fuel segment is formed with a plurality of protrusions, between the each two protrusions are defined a recess, a flame holding hot-gas region is formed between the protrusion and the recess, so as to produce eddy current in the flame holding hot-gas region when the propellant mixture is burned inside the trajectory, such that the whole solid fuel segment can produce even regression rate and high combustion efficiency.
    Type: Grant
    Filed: March 12, 2019
    Date of Patent: July 13, 2021
    Assignee: Taiwan Innovative Space, Inc.
    Inventor: Yen-Sen Chen
  • Patent number: 10557439
    Abstract: An injection device, a combustor, and a rocket engine include a device main body partitioned into a fuel manifold and an oxidant manifold, and a plurality of injectors arranged at predetermined intervals in the device main body to inject fuel and oxidant into a combustion chamber, each of the injectors includes a LOx channel including a proximal end portion communicating with the oxidant manifold and a distal end portion communicating with the combustion chamber, a restrictor provided on the proximal end portion of the LOx channel and a GH2 channel including a proximal end portion communicating with the fuel manifold and a distal end portion communicating with the combustion chamber, and the restrictors have different shapes.
    Type: Grant
    Filed: October 20, 2016
    Date of Patent: February 11, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Mitsunori Isono, Kazufumi Ikeda, Hiroyasu Manako, Shinichiro Watanabe, Hideto Kawashima
  • Patent number: 10286599
    Abstract: A hybrid rocket solid fuel grain having a cylindrical shape and defining a center port is additive manufactured from a compound of thermoplastic fuel and passivated nanocomposite aluminum additive. The fuel grain comprises a stack of fused layers, each layer formed as a plurality of fused abutting concentric circular beaded structures arrayed to define a center port. During operation, an oxidizer is introduced along the center port, with combustion occurring along the exposed port wall. Each circular beaded structure defines geometry that increases the surface area available for combustion. As each layer ablates the next abutting layer, exhibiting a similar geometry, is revealed, undergoes a gas phase change, and ablates. This process repeats and persists until oxidizer flow is terminated or the fuel grain material is exhausted. To safely achieve this construction, a fused deposition additive manufacturing apparatus, modified to shield the nanocomposite material from the atmosphere, is used.
    Type: Grant
    Filed: November 20, 2017
    Date of Patent: May 14, 2019
    Inventor: Ronald D Jones
  • Patent number: 9957919
    Abstract: An anaerobic propulsion device of hybrid type. The propulsion device includes a combustion chamber into which an oxidant is injected thereto comes into contact with a fuel. The chamber includes an orifice, notably a nozzle, to inject the combustion gases. The fuel takes the form of solids divided into granules, typically grains, powder or beads. The propulsion device further includes a segregation device arranged between a reservoir for granules of solid fuel, and the combustion chamber. The segregation device is configured to prevent granules of fuel in solid form from passing between the reservoir and the combustion chamber. The segregation device includes orifices to allow the passage of the fuel, once the fuel has become pasty, liquid or vaporized.
    Type: Grant
    Filed: September 10, 2013
    Date of Patent: May 1, 2018
    Assignee: AIRBUS DEFENCE AND SPACE SAS
    Inventor: Christophe Figus
  • Patent number: 9890091
    Abstract: An additively manufactured solid fuel grain for a hybrid rocket engine having a cylindrical shape, defining a center combustion port and comprising a stack of fused layers of polymeric material suitable for hybrid rocket fuel. Each layer is formed as a plurality of fused abutting concentric beads of solidified material arrayed around the center port. An oxidizer is introduced into the solid fuel grain through the center port, with combustion occurring along the exposed surface area of the solid fuel grain center port wall. Each concentric bead possesses a surface pattern that increases the combustion surface area and when stacked forms a rifling pattern of undulations that induces oxidizer-fuel gas axial flow to improve combustion efficiency. The port wall surface pattern persists during the rocket engine's operation as the fuel phase changes from solid to gas and is ablated.
    Type: Grant
    Filed: September 12, 2016
    Date of Patent: February 13, 2018
    Inventor: Ronald D Jones
  • Patent number: 9822045
    Abstract: A hybrid rocket solid fuel grain having a cylindrical shape and defining a center port is additive manufactured from a compound of thermoplastic fuel and passivated nanocomposite aluminum additive. The fuel grain comprises a stack of fused layers, each formed as a plurality of fused abutting concentric circular beaded structures of different radii arrayed defining a center port. During operation, an oxidizer is introduced along the center port, with combustion occurring along the exposed port wall. Each circular beaded structure possesses geometry that increases the surface area available for combustion. As each layer ablates the next abutting layer, exhibiting a similar geometry is revealed, undergoes a gas phase change, and ablates. This process repeats and persists until oxidizer flow is terminated or the fuel grain material is exhausted. To safety achieve this construction, a fused deposition additive manufacturing apparatus, modified to shield the nanocomposite material from the atmosphere is used.
    Type: Grant
    Filed: September 25, 2016
    Date of Patent: November 21, 2017
    Inventor: Ronald D Jones
  • Patent number: 9149795
    Abstract: Ceramic catalyst carriers that are mechanically, thermally and chemically stable in a ionic salt monopropellant decomposition environment and high temperature catalysts for decomposition of liquid high-energy-density monopropellants are disclosed. The ceramic catalyst carrier has excellent thermal shock resistance, good compatibility with the active metal coating and metal coating deposition processes, melting point above 1800° C., chemical resistance to steam, nitrogen oxides and acids, resistance to sintering to prevent void formation, and the absence of phase transition associated with volumetric changes at temperatures up to and beyond 1800° C.
    Type: Grant
    Filed: May 25, 2011
    Date of Patent: October 6, 2015
    Assignee: Sienna Technologies, Inc.
    Inventors: Ender Savrun, Stephanie J. Sawhill
  • Patent number: 9086033
    Abstract: Propulsion systems and method for making a propulsion system include additively manufacturing a casing body into a single-piece structure having no bonded or bolted joints. The casing body defines a combustion chamber therein and is at least partially composed of a material useful as a solid rocket fuel and capable of being consumed during combustion. Other embodiments are also described.
    Type: Grant
    Filed: September 13, 2011
    Date of Patent: July 21, 2015
    Inventors: Matthew Dushku, Walter Holemans
  • Patent number: 8887483
    Abstract: Supply of a liquid component in a combustion chamber of a rocket engine is controlled by a feed valve provided with slide valve mobile between an open position and a closed position of at least one supply pipe, which has an inlet that communicates with a tank for containing the liquid component and an outlet that communicates with the combustion chamber. The displacement of the slide valve from its closed position to its open position is triggered by a pressurized fluid supplied to the outlet of the supply pipe.
    Type: Grant
    Filed: December 22, 2010
    Date of Patent: November 18, 2014
    Assignee: Selex Galileo S.p.A.
    Inventor: Dino Petronio
  • Patent number: 8844133
    Abstract: A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design,
    Type: Grant
    Filed: July 23, 2012
    Date of Patent: September 30, 2014
    Assignee: The Aerospace Corporation
    Inventor: Jerome K. Fuller
  • Patent number: 8839600
    Abstract: An igniter for a rocket engine or motor comprising a combustion chamber with a solid fuel, an inlet for supplying an oxidizer to the combustion chamber to ignite the solid fuel and an outlet for discharging exhaust gas, wherein the igniter is arranged to discharge exhaust gas to the rocket engine for igniting the rocket engine. The igniter can be used for multiple ignitions and can also be re-used after re-filling.
    Type: Grant
    Filed: February 23, 2011
    Date of Patent: September 23, 2014
    Assignee: Aerospace Propulsion Products, B.V.
    Inventors: Eduardus Josephus Vermeulen, Bernd Mathias Jozef Brauers, Wilhelmina Helena Maria Welland-Veltmans
  • Patent number: 8707676
    Abstract: A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio.
    Type: Grant
    Filed: February 28, 2008
    Date of Patent: April 29, 2014
    Assignee: The Aerospace Corporation
    Inventor: Jerome K. Fuller
  • Publication number: 20140083081
    Abstract: The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.
    Type: Application
    Filed: August 20, 2012
    Publication date: March 27, 2014
    Inventor: PATRICK R.E. BAHN
  • Publication number: 20140026535
    Abstract: A propulsion device including a chamber that stores a superfluid, a substrate coupled to a portion of the chamber, a plurality of orifices extending through the substrate, each of the plurality of orifices having a first end and a second end opposite the first end, the first end disposed in an interior of the chamber and the second end disposed outside the chamber; and a pressure source that generates a pressure differential between the first end of each of the plurality of orifices and the second end of each of the plurality of orifices.
    Type: Application
    Filed: July 27, 2012
    Publication date: January 30, 2014
    Applicant: Board of Trustees of Northern Illinois University
    Inventors: Michael Wallace VERHULST, Joseph D. Nix, Christopher W. Smith
  • Publication number: 20140026537
    Abstract: The Multiple Use Plug Hybrid (for) Nanosats (“MUPHyN”) prototype thruster is being developed to fill a niche application for NanoSat scale spacecraft propulsion. The MUPHyN thruster uses safe-handling and inexpensive nitrous oxide (N20) and acrylonitrile-butadiene-styrene (ABS) as propellants. The MUPHyN thruster can provide an enhanced propulsive capability that will enable multiple NanoSats to be independently repositioned after deployment from the parent launch vehicle. Because the environmentally benign propellants are mixed only within the combustion chamber once the ignition is initiated, the system is inherently safe and can be piggy-backed on a secondary payload with no overall mission risk increase to the primary payload.
    Type: Application
    Filed: July 30, 2013
    Publication date: January 30, 2014
    Applicant: UTAH STATE UNIVERSITY
    Inventors: Shannon D. Eilers, Stephen Whitmore, Zachary Peterson
  • Patent number: 8601790
    Abstract: A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including buried radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio.
    Type: Grant
    Filed: February 28, 2008
    Date of Patent: December 10, 2013
    Assignee: The Aerospace Corporation
    Inventor: Jerome K. Fuller
  • Patent number: 8596038
    Abstract: A liquid propellant tank for storing a liquid propellant A and supplying vapor produced by evaporation of part of the liquid propellant A to an external location comprises a tank body for storing the liquid propellant A, and a plurality of holder plates arranged inside the tank body, around an axis L of the tank body. The holder plates cause the liquid propellant A to adhere to them by surface tension, thereby establishing, inside the tank body, a liquid propellant holding area LA in which the liquid propellant A is held and a gas accumulation area GA in which vapor produced by evaporation of part of the liquid propellant A accumulates. The tank body has a propellant inlet open into the liquid propellant holding area LA and a gas outlet open into the gas accumulation area GA.
    Type: Grant
    Filed: March 3, 2011
    Date of Patent: December 3, 2013
    Assignee: Japan Aerospace Exploration Agency
    Inventors: Takayuki Yamamoto, Osamu Mori, Yoshihiro Kishino, Masayuki Tamura, Shohei Koga, Ryoji Imai
  • Publication number: 20130305687
    Abstract: A thruster designed to produce thrust by introducing a propellant to a catalyst layer from a propellant valve via a propellant introduction member and spurting out a gas resulting from decomposition of the propellant occurring on the catalyst layer, wherein the thruster comprises a chamber of an Ni alloy for holding the catalyst layer inside, the propellant introduction member is made of an Ni alloy and connects the propellant valve and the chamber, and a propellant valve flange of a Ti alloy with a plurality of columns of a Ti alloy is arranged between the chamber and the propellant valve to support the chamber by the columns.
    Type: Application
    Filed: March 15, 2013
    Publication date: November 21, 2013
    Applicant: IHI AEROSPACE CO., LTD.
    Inventors: Toru Nagao, Naoki Morita
  • Publication number: 20130255223
    Abstract: An apparatus for igniting a larger rocket motor is provided. The apparatus may be a smaller rocket motor that can be ignited hypergolically, when a pressurized oxidizer contacts hypergolic fuel grains of the smaller rocket motor. The hypergolic ignition causes the larger rocket motor to be ignited. The hypergolic ignition of the smaller rocket motor may be stopped after the larger rocket motor is ignited, and the remaining hypergolic fuel grains and the pressurized oxidizer can be reserved for reigniting the larger rocket motor at a later time.
    Type: Application
    Filed: March 29, 2012
    Publication date: October 3, 2013
    Applicant: The Aerospace Corporation
    Inventors: Brian Blaise Brady, John D. Desain
  • 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
  • Patent number: 8387361
    Abstract: The present invention describes a hybrid rocket motor that includes a first solid reactant and at least one thrust nozzle and at least one moveable combustion control member within the hybrid rocket motor that restricts the contact of a first fluid reactant in the combustion chamber. In this way, it is then possible to regulate the exposure of the solid reactant to the fluid reactant and thus control thrust.
    Type: Grant
    Filed: December 7, 2006
    Date of Patent: March 5, 2013
    Assignee: Rocketone Aerospace Pty Ltd.
    Inventor: Sook Ying Ho
  • Publication number: 20130019586
    Abstract: One subject of the present invention is a propulsion method comprising: the injection, into at least one combustion chamber (1), of at least one liquid oxidizer (OX) and of hydrogen (H2); the combustion of said at least one liquid oxidizer (OX) and hydrogen (H2), in said at least one combustion chamber (1), for the generation of combustion gases; and expulsion of said combustion gases. Said process comprises, upstream of said injection: the generation of at least one portion of said hydrogen (H2), advantageously of all said hydrogen (H2), from at least one solid compound (5?); said generation from said at least one solid compound (5?) comprising a combustion reaction between said at least one solid compound (5?) chosen from alkali metal borohydrides, alkaline-earth metal borohydrides, borazane, polyaminoboranes and mixtures thereof and an oxidizing charge (5?). Another subject of the present invention is a propulsion device suitable for the implementation of said method.
    Type: Application
    Filed: December 21, 2010
    Publication date: January 24, 2013
    Applicant: HERAKLES
    Inventors: Pierre Yvart, Pierre-Guy Amand
  • Patent number: 8336287
    Abstract: A solid rocket motor includes a combustion chamber bounded by an outer casing, a propellant grain within the combustion chamber, and an igniter within the outer casing for igniting the propellant grain. A nozzle is coupled to the combustion chamber for releasing hot gasses evolved from burning the propellant grain to provide thrust for propelling the solid rocket motor. The propellant grain is a self-extinguishing propellant grain that includes at least one fuel, at least one oxidizing agent, at least one binder, and at least one surfactant that imparts the self-extinguishing property. The propellant grain provides a burning rate as a function of pressure that includes a negative pressure dependence portion, wherein the burning rate in the negative pressure dependence portion decreases with increasing pressure until a cutoff pressure is reached which results in extinguishment of the propellant grain.
    Type: Grant
    Filed: March 27, 2009
    Date of Patent: December 25, 2012
    Assignee: University of Central Florida Research Foundation, Inc.
    Inventors: Eric L. Petersen, Sudipta Seal, Matthew Stephens, David L. Reid, Rodolphe Carro, Thomas Sammet, Alex Lepage
  • Patent number: 8337765
    Abstract: An apparatus and method to electrocatalytically induce the decomposition of a liquid propellant for propulsion. This is accomplished by providing a reaction chamber filled with catalyst that has a first electrode, such as near the center, and the other electrode disposed away from the first electrode. A charge source that is capable of applying voltage is connected to the electrodes. When the reaction chamber is dosed with a propellant such as an aqueous based amine propellant, such as HAN, an electric current flows between the electrodes and the propellant. This initiates the decomposition of the propellant which is driven to completion by the catalyst bed in order to be used for power generation.
    Type: Grant
    Filed: August 26, 2005
    Date of Patent: December 25, 2012
    Assignee: Honeywell International Inc.
    Inventors: Tihomir G. Tonev, Mark Kaiser, Gary Seminara
  • Patent number: 8245496
    Abstract: Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body.
    Type: Grant
    Filed: March 19, 2010
    Date of Patent: August 21, 2012
    Assignee: Astrium GmbH
    Inventor: Thomas Maier
  • Patent number: 8181444
    Abstract: A motor includes an annular solid fuel between an inside diameter and an outside diameter. The solid fuel has a series of radial notches that define segments of fuel between them. The notches allow for faster burning of the fuel, while still allowing structural integrity of the fuel segments to be retained during the burning process.
    Type: Grant
    Filed: September 29, 2008
    Date of Patent: May 22, 2012
    Assignee: Raytheon Company
    Inventors: James H. Dupont, Richard D. Loehr, Robert N. Renz
  • Patent number: 8099945
    Abstract: Disclosed is a propulsion system having a structural configuration that provides easy and convenient access to the interior regions of a liquid fuel tank and a hybrid rocket motor case. In one embodiment, the propulsion system comprises: a hybrid rocket motor case and a fuel tank coupled to the hybrid motor case. The motor case is configured to hold solid rocket fuel and the fuel tank defines an internal volume configured to hold a fluid oxidizer. A bulkhead is interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the bulkhead. The access passageway provides exterior access to the interior volume of the motor case or the internal volume of the storage tank while the hybrid rocket motor is coupled to the fuel tank.
    Type: Grant
    Filed: March 16, 2009
    Date of Patent: January 24, 2012
    Assignee: Spacedev, Inc.
    Inventors: Frank Macklin, Chris Grainger
  • Publication number: 20110314790
    Abstract: Disclosed is a propulsion system having a structural configuration that provides easy and convenient access to the interior regions of a liquid fuel tank and a hybrid rocket motor case. In one embodiment, the propulsion system comprises: a hybrid rocket motor case and a fuel tank coupled to the hybrid motor case. The motor case is configured to hold solid rocket fuel and the fuel tank defines an internal volume configured to hold a fluid oxidizer. A bulkhead is interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the bulkhead. The access passageway provides exterior access to the interior volume of the motor case or the internal volume of the storage tank while the hybrid rocket motor is coupled to the fuel tank.
    Type: Application
    Filed: March 16, 2009
    Publication date: December 29, 2011
    Inventors: Frank MacKlin, Chris Grainger
  • Patent number: 8056319
    Abstract: An insensitive combined cycle missile propulsion system includes a solid fuel contained within a first section of the missile, a liquid oxidizer contained within a second section of the missile and a solid oxidizer contained within a third section of said missile. A first conduit has a first valve communicating the fuel and the oxidizer and a second conduit, spatially removed from the first conduit, has a second valve communicating the fuel and the oxidizer. An inlet system for delivering atmospheric oxygen for combustion with the fuel rich gases generated within the missile and a nozzle exhausts combustion products that result from combustion of the fuel, the liquid and solid oxidizers, and air.
    Type: Grant
    Filed: November 8, 2007
    Date of Patent: November 15, 2011
    Assignee: Aerojet—General Corporation
    Inventors: Melvin J. Bulman, Adam Siebenhaar
  • Patent number: 8019494
    Abstract: Propellant management systems and methods are provided for controlling the delivery of liquid propellants in a space launch vehicle utilizing multiple rockets. The propellant management systems and methods may be configured to enable substantial simultaneous depletion of liquid propellants in each of a plurality of active rockets during operation of various booster stages of the launch vehicle.
    Type: Grant
    Filed: November 12, 2008
    Date of Patent: September 13, 2011
    Assignee: Lockheed Martin Corporation
    Inventor: Frank S. Mango
  • Publication number: 20110203256
    Abstract: The present invention provides a motor including a combustion chamber, an oxidizer injector, a vortex generators and a nozzle. The combustion chamber can be used to dispose a solid fuel, and the oxidizer injector is used to control the flow rate of an oxidizer and to inject the oxidizer into the combustion chamber. The vortex generators is disposed on the inner wall of the combustion chamber for generating eddies to enhance the mixing of the fuel and the oxidizer. Additionally, the nozzle is connected with the combustion chamber for exhausting the gas generated by the combustion of the propellants.
    Type: Application
    Filed: February 1, 2011
    Publication date: August 25, 2011
    Inventors: Yen-Sen CHEN, Jong-Shinn Wu, Tzu-Hao Chou
  • Patent number: 7997081
    Abstract: A gas delivery system includes a gas booster module for delivering natural gas from a utility gas service to power generation equipment installed in or around a building in a manner that meets the minimum volume and pressure requirements of the power generation equipment. The gas delivery system advantageously uses pipe of a relatively small size for delivering gas to the power generation equipment, thereby substantially reducing installation costs and eliminating the need for a welded gas line. The gas delivery system also provides a control system that facilitates close control over the gas flow and ensures compliance with local building codes and safety regulations and requirements.
    Type: Grant
    Filed: June 28, 2007
    Date of Patent: August 16, 2011
    Assignee: OfficePower, Inc.
    Inventors: Andrew J. Edwards, John S. Pifer
  • Publication number: 20110167793
    Abstract: Provided is a hybrid rocket using catalytic decomposition of oxidizer, which generates thrust by injecting high temperature oxygen and steam formed by catalytic decomposing liquid oxidizer into solid fuel and thereby auto igniting and combusting the solid fuel without a separate igniter.
    Type: Application
    Filed: September 20, 2010
    Publication date: July 14, 2011
    Applicant: KOREA ADVANCED INSTITUTE OF SCIENCE AND TECHNOLOGY
    Inventors: Sejin KWON, Sungyong AN, Jungkun JIN, Eunsang JUNG
  • Patent number: 7966809
    Abstract: A hybrid rocket motor is formed from a single piece of material, such as, for example, by extrusion or injection molding. The rocket motor includes various components, such as casing, structure, oxidizer tank, combustion chamber, fuel, port and nozzle that are all formed from a single piece of material. The material can be, for example, a material that can be used as solid rocket fuel.
    Type: Grant
    Filed: January 30, 2007
    Date of Patent: June 28, 2011
    Assignee: Spacedev, Inc.
    Inventor: Jim Benson
  • Patent number: 7921638
    Abstract: A bi-propellant rocket motor having controlled thermal management is disclosed. The rocket motor produces thrust using a solid or gel-phase primary propellant that can be either fuel- or oxidizer-rich, with a complementary self-pressurizing secondary propellant selected to balance the primary propellant in terms of the equivalence ratio. The motor houses multiple propellant grains arranged in such a configuration that each chamber containing a primary grain serves as both propellant storage and the main combustion chamber for that propellant grain as it burns with the secondary propellant. The secondary propellant is stored separately, and the flow routed past the primary propellant chamber to provide cooling for adjacent primary propellant chambers limiting the temperature rise in the motor structure.
    Type: Grant
    Filed: April 20, 2007
    Date of Patent: April 12, 2011
    Assignee: Combustion Propulsion & Ballistic Technology Corp.
    Inventors: Kenneth K. Kuo, J. Eric Boyer, Peter J. Ferrara
  • Patent number: 7898097
    Abstract: Activation of a propellant in a constant volume container causes a phase change material to rapidly expand so that the pressure in the container increases. Programmability and sequential actuation are enabled by patterning the phase change material into the integrated device. The pressure generated may be used to activate an energy transducer such as a high pressure turbine, a piezoelectric material, and an elastic strain material. This provides a hybrid actuation system of electrical energy, pneumatic and hydraulic power. The pressure change in a constant volume container is also harnessed to provide a microbattery.
    Type: Grant
    Filed: April 30, 2009
    Date of Patent: March 1, 2011
    Assignee: University of South Florida
    Inventors: David P. Fries, Chad Lembke
  • 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
  • Patent number: 7815146
    Abstract: A fixed sized bell rocket nozzle is lined with a layer of combustible material that is ignited during launch ignition and burns to outgas into the rocket exhaust for spatially variably confining the exhaust and perfecting an effective variably sized altitude compensating exhaust nozzle that maximizes lift during the launch of a spacecraft into orbit.
    Type: Grant
    Filed: August 29, 2001
    Date of Patent: October 19, 2010
    Assignee: The Aerospace Corporation
    Inventors: Gary F. Hawkins, John W. Murdock
  • Patent number: 7762058
    Abstract: An ultra-compact aerovortical swirl-enhanced combustion (ASC) system features an aerovortical swirl generator for use in rocket thrusters utilizing hypergolic or non-hypergolic propellants. The ACS thruster can be sized for diameters ranging from about 0.5 to about 2.0 inches, and producing thrust levels of approximately 5 lbf to about 250 lbf. A plurality of helicoid flow channels in the swirl generator introduces swirl into a flow stream of a first propellant within ultra-compact sized rocket thrusters. The ASC system also includes injectors for introducing a second liquid propellant into the swirling flowfield to promote rapid and efficient atomization, mixing and vigorous combustion, which, results in major improvements in combustion and propulsion performance over current rocket thrusters, but in much shorter combustor systems.
    Type: Grant
    Filed: April 17, 2007
    Date of Patent: July 27, 2010
    Assignee: Pratt & Whitney Rocketdyne, Inc.
    Inventors: Robert J. Pederson, Stephen N. Schmotolocha
  • Patent number: 7707820
    Abstract: Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body.
    Type: Grant
    Filed: September 19, 2005
    Date of Patent: May 4, 2010
    Assignee: Astrium GmbH
    Inventor: Thomas Maier
  • Patent number: 7690192
    Abstract: A rocket engine includes a combustor assembly for carrying out a combustion process of fuel and oxidizer rocket propellants to produce thrust. A swirl generator is positioned within the combustor assembly to produce a turbulent flowfield of the fuel and oxidizer rocket propellants within the combustor assembly.
    Type: Grant
    Filed: May 22, 2007
    Date of Patent: April 6, 2010
    Assignee: Pratt & Whitney Rocketdyne, Inc.
    Inventors: Robert J. Pederson, Stephen N. Schmotolocha
  • Publication number: 20090217525
    Abstract: A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design,
    Type: Application
    Filed: February 28, 2008
    Publication date: September 3, 2009
    Inventor: Jerome K. Fuller
  • Publication number: 20090217642
    Abstract: A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio.
    Type: Application
    Filed: February 28, 2008
    Publication date: September 3, 2009
    Inventor: Jerome K. Fuller
  • Publication number: 20090211226
    Abstract: A hybrid rocket motor includes a supply of oxidizer, a first solid fuel element positioned around the supply of oxidizer, a second solid fuel element positioned concentrically around the first solid fuel element, and a combustion port positioned between the first and second solid fuel elements. The oxidizer interacts with the first and second solid fuel elements within the combustion port to produce a combustion product. A nozzle is in communication with the combustion port for combustion discharge of the combustion product.
    Type: Application
    Filed: June 18, 2007
    Publication date: August 27, 2009
    Inventor: Frank Macklin
  • Publication number: 20090205311
    Abstract: An insensitive combined cycle missile propulsion system includes a solid fuel contained within a first section of the missile, a liquid oxidizer contained within a second section of the missile and a solid oxidizer contained within a third section of said missile. A first conduit has a first valve communicating the fuel and the oxidizer and a second conduit, spatially removed from the first conduit, has a second valve communicating the fuel and the oxidizer. An inlet system for delivering atmospheric oxygen for combustion with the fuel rich gases generated within the missile and a nozzle exhausts combustion products that result from combustion of the fuel, the liquid and solid oxidizers, and air.
    Type: Application
    Filed: November 8, 2007
    Publication date: August 20, 2009
    Inventors: Melvin J. Bulman, Adam Siebenhaar
  • Publication number: 20090139204
    Abstract: The present invention describes a hybrid rocket motor that includes a first solid reactant and at least one thrust nozzle and at least one moveable combustion control member within the hybrid rocket motor that restricts the contact of a first fluid reactant in the combustion chamber. In this way, it is then possible to regulate the exposure of the solid reactant to the fluid reactant and thus control thrust.
    Type: Application
    Filed: December 7, 2006
    Publication date: June 4, 2009
    Applicant: ROCKETONE AEROSPACE PTY LTD.
    Inventor: Sook Ying Ho
  • Patent number: 7540145
    Abstract: The hybrid rocket system of this invention is characterized by use of an oxidizer tank having a cylindrical midsection surrounded by a skirt and bonded thereto by a layer of elastomeric adhesive. The skirt outer surface is in turn adhesively secured to a spacecraft inner surface. An elongated solid-fuel motor case is mechanically rigidly secured to a central rear surface of the tank, and the case terminates in a throat and nozzle. The elastomeric-adhesive bonding of tank to skirt, and rigid adhesion of skirt to spacecraft forms the sole support for the rocket system, and separate support for the motor case is not required.
    Type: Grant
    Filed: March 29, 2004
    Date of Patent: June 2, 2009
    Assignee: Mojave Aerospace Ventures, LLC
    Inventor: Elbert L. Rutan
  • Patent number: 7531908
    Abstract: Activation of a propellant in a constant volume container causes a phase change material to rapidly expand so that the pressure in the container increases. Programmability and sequential actuation are enabled by patterning the phase change material into the integrated device. The pressure generated may be used to activate an energy transducer such as a high pressure turbine, a piezoelectric material, and an elastic strain material. This provides a hybrid actuation system of electrical energy, pneumatic and hydraulic power. The pressure change in the constant volume container is also harnessed to provide a microbattery.
    Type: Grant
    Filed: September 7, 2006
    Date of Patent: May 12, 2009
    Assignee: University of South Florida
    Inventors: David P. Fries, Chad Lembke
  • Patent number: 7525072
    Abstract: A heated O-ring that has particular application for providing sealing in the connector region of a compressed hydrogen storage tank in a fuel cell system. In one embodiment, an electrical heating wire is wound through the O-ring so that resistive heating is provide by applying an electrical potential to the wire so that the temperature of the O-ring does not decrease below a predetermined temperature. In another embodiment, electrical heating elements are provided adjacent to and in contact with the O-ring, where an electrical potential applied to the heating elements causes the heating elements to maintain the temperature of the O-ring.
    Type: Grant
    Filed: July 13, 2005
    Date of Patent: April 28, 2009
    Assignee: GM Global Technology Operations, Inc.
    Inventors: Rainer Pechtold, Thorsten Rohwer
  • Patent number: 7506500
    Abstract: 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 fuel. Preferred methods and systems can include a storage chamber for storing solid propellant pellets, a feeding system having a pellet feeding channel and a pellet feeding mechanism connected to the storage chamber and to a gun assembly, which is positioned along a longitudinal axis to eject the pellets at a certain velocity. A triggering system positioned between gun assembly and thrust chamber can initiate the propellant pellet-projectile, and a thrust chamber having a combustion chamber for combustion of propellant pellet-projectile with an exhaust nozzle.
    Type: Grant
    Filed: November 10, 2006
    Date of Patent: March 24, 2009
    Inventor: Vinu B. Krishnan