Including Propellant Support Means Patents (Class 60/255)
  • Patent number: 11137328
    Abstract: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. This process may be performed over time to determine a lifespan of the propellant grain.
    Type: Grant
    Filed: April 16, 2019
    Date of Patent: October 5, 2021
    Assignee: Goodrich Corporation
    Inventors: Joshua David Carter, Kevin Mueller
  • Patent number: 11112222
    Abstract: A propellant is made from a flexible sheet that in some examples is nitrocellulose. An ignitable material is deposited on one side of the flexible sheet. The ignitable material is a series of triangles having a base adjacent to one edge of the sheet, and an apex adjacent to the other side of the sheet. Some examples of the ignitable material may be thermite compositions. The flexible sheet is rolled around a nonburnable tube and placed within a firearm casing, with the triangle bases being adjacent to the back of the casing, and the triangle apexes being adjacent to the front of the casing. The nonburnable tube is disposed over the primer pocket, so that ignition products from the primer travel through the tube, igniting the propellant adjacent to the front of the casing.
    Type: Grant
    Filed: January 21, 2020
    Date of Patent: September 7, 2021
    Assignees: SPECTRE MATERIALS SCIENCES, INC., UNIVERSITY OF CENTRAL FLORIDA RESEARCH FOUNDATION, INC.
    Inventors: Kevin R. Coffey, Timothy Mohler, Daniel Yates
  • Patent number: 10837407
    Abstract: A hybrid-like liquid fuel motor (the “motor”) may include a port surrounded by a wall. Surrounding the wall are a plurality of chambers and segmented walls to separate the chambers. In some instances, a single helix chamber may surround the wall, and may operate similar to that of a segmental chamber. During operation of the motor, gas flows from one end of the port to another end of the port. As the walls surrounding the port begin to disintegrate, liquid fuel within chambers begins to begin to mix with the flow of gas. As the segmented walls between the chambers begin to disintegrate, liquid from the other chambers begin to mix with the flow of gas, creating a metering of the liquid fuel.
    Type: Grant
    Filed: November 4, 2016
    Date of Patent: November 17, 2020
    Assignee: The Aerospace Corporation
    Inventors: Jerome Keith Fuller, John D DeSain
  • Patent number: 10619794
    Abstract: A pressure vessel includes a shell, a first boss, a second boss, and a reinforcement support. The shell defines an internal cavity. The first and second bosses are disposed within the cavity and respectively extend through opposing longitudinal ends of the shell. The first boss defines a longitudinally extending central orifice. The reinforcement support is disposed within the cavity, is secured to the first boss radially outward of the central orifice, extends from the first boss to the second boss, and is secured to the second boss.
    Type: Grant
    Filed: March 13, 2018
    Date of Patent: April 14, 2020
    Assignee: Ford Global Technologies, LLC
    Inventors: Michael J. Veenstra, Bert Hobein, Stella Papasavva, Julio Orozco Santos Coy, Justin Purewal
  • Patent number: 9038368
    Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor. According to an example embodiment of the invention, a method is provided for producing a multi-fuel hybrid motor. The method can include forming a body, where the body includes one or more intake ports; one or more exit nozzles; one or more channels connecting the one or more intake ports with the one or more exit nozzles; and a plurality of cavities comprising segment walls in communication with the one or more channels. The method also includes depositing a propellant fuel within the plurality of cavities, wherein at least a portion of the propellant fuel is exposed to the one or more channels and wherein the propellant fuel has a higher burn consumption rate than the segment walls.
    Type: Grant
    Filed: August 1, 2011
    Date of Patent: May 26, 2015
    Assignee: THE AEROSPACE CORPORATION
    Inventor: Jerome K. Fuller
  • Patent number: 8826640
    Abstract: Embodiments of a flight vehicle are provided, as are embodiments of a method for manufacturing a flight vehicle. In one embodiment, the flight vehicle includes a solid-propellant rocket motor, control circuitry, and an electrically-interconnective support structure. The electrically-interconnective support structure includes a load-bearing frame and a plurality of electrical conductors embedded within the load-bearing frame. The solid-propellant rocket motor is mounted to the load-bearing frame, and the plurality of electrical conductors embedded within the frame electrically couples the solid-propellant rocket motor to the control circuitry.
    Type: Grant
    Filed: November 12, 2010
    Date of Patent: September 9, 2014
    Assignee: Raytheon Company
    Inventors: Thomas A. Olden, Walter Wrigglesworth
  • Patent number: 8776526
    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: Grant
    Filed: February 1, 2011
    Date of Patent: July 15, 2014
    Assignee: National Applied Research Laboratories
    Inventors: Yen-Sen Chen, Jong-Shinn Wu, Tzu-Hao Chou
  • Patent number: 8613190
    Abstract: The invention relates to a pressure vessel consisting of a housing and an insulating layer lining the inner surface of the housing. The housing is formed from a fiber composite material which has a high mechanical and thermal resistance and the insulating layer is formed from a gas-tight silicone elastomer, with the housing and the insulating layer being bonded to each other. The invention also relates to a method for the manufacture of such pressure vessels.
    Type: Grant
    Filed: November 3, 2009
    Date of Patent: December 24, 2013
    Assignee: MT Aerospace AG
    Inventors: Bernd Murawski, Helmut Maierhofer
  • Patent number: 8539753
    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: Grant
    Filed: June 18, 2007
    Date of Patent: September 24, 2013
    Assignee: SpaceDev, Inc.
    Inventor: Frank Macklin
  • Publication number: 20130042596
    Abstract: Embodiments of the invention relate to systems and methods for fabricating hybrid rocket motor fuel grains. In one embodiment, a method for fabricating a rocket motor fuel grain can be provided. The method can include providing a platform operable to support a rocket motor fuel grain during fabrication. The method can also include disposing at least one fuel material onto the platform to form a material layer. Further, the method can include successively disposing additional fuel material onto the material layer in small amounts, wherein the rocket motor fuel grain is formed on the platform.
    Type: Application
    Filed: August 1, 2012
    Publication date: February 21, 2013
    Applicant: THE AEROSPACE CORPORATION
    Inventor: Jerome Keith Fuller
  • Publication number: 20130031888
    Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor. According to an example embodiment of the invention, a method is provided for producing a multi-fuel hybrid motor. The method can include forming a body, where the body includes one or more intake ports; one or more exit nozzles; one or more channels connecting the one or more intake ports with the one or more exit nozzles; and a plurality of cavities comprising segment walls in communication with the one or more channels. The method also includes depositing a propellant fuel within the plurality of cavities, wherein at least a portion of the propellant fuel is exposed to the one or more channels and wherein the propellant fuel has a higher burn consumption rate than the segment walls.
    Type: Application
    Filed: August 1, 2011
    Publication date: February 7, 2013
    Applicant: THE AEROSPACE CORPORATION
    Inventor: Jerome K. Fuller
  • Patent number: 8281568
    Abstract: A solid fuel rocket motor, a castellated propellant cartridge and a method of controlling a pressure differential in a cartridge-loaded rocket motor are disclosed. The rocket motor may include a housing having an inside surface, a plurality of propellant cartridges disposed within the housing, an igniter disposed to ignite propellant material within the propellant cartridges, and a nozzle disposed to exhaust combustion gases out of the housing. At least some of the propellant cartridges may be castellated propellant cartridges.
    Type: Grant
    Filed: June 9, 2009
    Date of Patent: October 9, 2012
    Assignee: Raytheon Company
    Inventors: Jeremy Danforth, Richard D. Loehr
  • Publication number: 20120117941
    Abstract: Embodiments of a flight vehicle are provided, as are embodiments of a method for manufacturing a flight vehicle. In one embodiment, the flight vehicle includes a solid-propellant rocket motor, control circuitry, and an electrically-interconnective support structure. The electrically-interconnective support structure includes a load-bearing frame and a plurality of electrical conductors embedded within the load-bearing frame. The solid-propellant rocket motor is mounted to the load-bearing frame, and the plurality of electrical conductors embedded within the frame electrically couples the solid-propellant rocket motor to the control circuitry.
    Type: Application
    Filed: November 12, 2010
    Publication date: May 17, 2012
    Applicant: RAYTHEON COMPANY
    Inventors: Thomas A. Olden, Walter Wrigglesworth
  • Publication number: 20120060468
    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: Application
    Filed: September 13, 2011
    Publication date: March 15, 2012
    Applicant: EXPERIMENTAL PROPULSION LAB, LLC
    Inventors: Matthew Dushku, Walter Holemans
  • Patent number: 8127534
    Abstract: There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle.
    Type: Grant
    Filed: February 19, 2008
    Date of Patent: March 6, 2012
    Assignee: Raytheon Company
    Inventors: Robert J. Cavalleri, Thomas A. Olden
  • Patent number: 7980057
    Abstract: An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.
    Type: Grant
    Filed: November 27, 2007
    Date of Patent: July 19, 2011
    Assignee: Raytheon Company
    Inventors: Andrew B. Facciano, Robert T. Moore, Kelly J. Sinnock, Scott T. Caldwell
  • 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
  • Publication number: 20090235640
    Abstract: There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case.
    Type: Application
    Filed: February 19, 2008
    Publication date: September 24, 2009
    Inventors: Robert J. Cavalleri, Thomas A. Olden
  • Patent number: 7578122
    Abstract: A rocket motor case includes a plurality of plank sections which provide a structural key for locking metal and/or composite end enclosures in place as part of the motor case. The plank sections are sized longitudinally to form venting spaces in the motor case sidewall to allow passive venting in the event of propellant ignition during cook-off. The plank sections have plank legs which are surrounded by tailorable roll-bonded sheet material to complete formation of the motor case sidewall.
    Type: Grant
    Filed: February 26, 1997
    Date of Patent: August 25, 2009
    Assignee: Aerojet General Corporation
    Inventors: Irving Edward Figge, Sr., Phillip Henry Graham
  • Publication number: 20090205313
    Abstract: There is disclosed a solid fuel rocket motor which may include a grain disposed within a case. Prior to ignition, a burnable surface of the grain may be defined, at least in part, by a non-circular center perforation. The interior surface of the case may conform to the expected shape of the burnable surface of the grain at a predetermined time after ignition.
    Type: Application
    Filed: February 14, 2008
    Publication date: August 20, 2009
    Inventors: Robert J. Cavalleri, Richard D. Loehr
  • Patent number: 7461503
    Abstract: An insulation material comprising a low-density EPDM polymer, at least one flame-retardant, and an organic filler. The insulation material is used in an insulation layer of a rocket motor. The organic filler is a polymeric, organic filler such as polyvinyl chloride. A rocket motor comprising an insulation material is also disclosed. The insulation material comprises a low-density EPDM polymer, at least one flame-retardant, and a polymeric, organic filler and is applied between an inner surface of a case of the rocket motor and a propellant. A method of insulating a rocket motor is also disclosed.
    Type: Grant
    Filed: June 26, 2003
    Date of Patent: December 9, 2008
    Assignee: Alliant Techsystems Inc.
    Inventor: Himansu M. Gajiwala
  • Patent number: 7360355
    Abstract: A long range artillery shell having a rocket motor which comprises a combustion chamber (shown filled with solid propellant 9, burn inhibitor 10, igniter material 13 and propellant support 11,12) which has at one end a plenum chamber 8 and a rocket nozzle 14 for venting the plenum chamber 8. The propellant 9 is arranged in an end-burn configuration and housed within the combustion chamber and the propellant support 11,12 is located between the propellant 9 and the plenum chamber 8 and is capable of preventing entry of unburnt propellant into the plenum chamber 8 while permitting, in use, the substantially unhindered transfer of propellant combustion products to the plenum chamber 8.
    Type: Grant
    Filed: June 7, 1996
    Date of Patent: April 22, 2008
    Assignee: QinetiQ Limited
    Inventor: Guillaume M. H. J. L. Gadiot
  • Patent number: 7210282
    Abstract: A case-burning rocket booster includes a combustible case containing a solid rocket fuel, a combustion chamber adjustably coupled to the case for burning the case and the solid rocket fuel, a nozzle connected to the combustion chamber for expelling the burned case and fuel to generate thrust, and a drive system for pulling the combustion chamber and nozzle up the case as the case and fuel burn. A hybrid version of the case-burning rocket also includes an oxidizer supply system for supplying varying amounts of oxidizer to the combustion chamber to vary the thrust generated by burning the case and the fuel.
    Type: Grant
    Filed: August 11, 2004
    Date of Patent: May 1, 2007
    Inventor: Brian A. Floyd
  • Patent number: 7117797
    Abstract: A pyrotechnic charge structure, in particular for use as propellant in a rocket motor, is disclosed. The charge structure has a predetermined longitudinal extension and cross sectional area adapted to the intended purpose. The pyrotechnic charge structure (1; 2; 3; 4) is in cross sectional view in cellular form aimed at having similar wall thickness for all the cells of the charge structure. The wall (6) of the cells comprises the pyrotechnic charge, i.e. the propellant, and each cavity of the cells occupies air or oxygen-rich gas.
    Type: Grant
    Filed: November 13, 2001
    Date of Patent: October 10, 2006
    Assignee: Nammo Raufoss AS
    Inventors: Hans B. Biserød, Johans Hamarsnes
  • Patent number: 7012107
    Abstract: A rocket motor insulation including an elastomer-based polymer is improved in its processability by the addition of silica particles treated with a hydrophobic coating. The insulation also preferably includes a metallic coagent cross-linker, which when used in combination with the hydrophobic silica particles increases the tear strength and the elasticity of the insulation, while at the same time not adversely affecting the bonding characteristics of the insulation.
    Type: Grant
    Filed: June 17, 2003
    Date of Patent: March 14, 2006
    Assignee: Alliant Techsystems Inc.
    Inventors: Albert R. Harvey, John W. Ellertson
  • Patent number: 6904749
    Abstract: A vehicle includes at least one polyoxymethylene structural support member. The polyoxymethylene structural support member includes a polyoxymethylene component that is a propellant that provides thrust to the vehicle upon pyrolysis or combustion of the polyoxymethylene component of the product of pyrolysis of the polyoxymethylene component. The vehicle can be a satellite or other type of spacecraft.
    Type: Grant
    Filed: October 17, 2003
    Date of Patent: June 14, 2005
    Assignee: Physical Sciences, Inc.
    Inventors: Prakash B. Joshi, Alan H. Gelb, Bernard L. Upschulte, B. David Green
  • Patent number: 6873945
    Abstract: The present invention comprises a device which is inert and “thermally-equivalent” to actual ordnance. The device can travel with live ordnance and track the propellant temperatures in order to get a more precise propellant temperature for the ordnance. The device comprises a thermally equivalent inert grain instrumented with thermocouples, connected to a data recorder, and packaged in scaled-down ordnance hardware. The hardware is scaled down to enable the device to more easily travel with live munitions.
    Type: Grant
    Filed: December 18, 2000
    Date of Patent: March 29, 2005
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Jonathan R. Ross, Conan R. Schultz, Michael K Oetjen
  • Publication number: 20040128979
    Abstract: A combustion chamber, in particular for a rocket drive, comprises at least one jacket made of a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.
    Type: Application
    Filed: November 21, 2003
    Publication date: July 8, 2004
    Applicant: Astrium GmbH
    Inventors: Steffen Beyer, Helmut Knabe, Dieter Preclik
  • Publication number: 20030213228
    Abstract: A rocket motor insulation including an elastomer-based polymer is improved in its processability by the addition of silica particles treated with a hydrophobic coating. The insulation also preferably includes a metallic coagent cross-linker, which when used in combination with the hydrophobic silica particles increases the tear strength and the elasticity of the insulation, while at the same time not adversely affecting the bonding characteristics of the insulation.
    Type: Application
    Filed: June 17, 2003
    Publication date: November 20, 2003
    Inventors: Albert R. Harvey, John W. Ellertson
  • Patent number: 6606852
    Abstract: A rocket motor insulation including an elastomer base polymer is improved in its processability by the addition of silica particles treated with a hydrophobic coating. The insulation also preferably includes a metallic coagent cross-linker, which when used in combination with the hydrophobic silica particles increases the tear strength and the elasticity of the insulation, while at the same time not adversely affecting the bonding characteristics of the insulation.
    Type: Grant
    Filed: July 11, 2000
    Date of Patent: August 19, 2003
    Assignee: Alliant Techsystems Inc.
    Inventors: Albert R. Harvey, John W. Ellertson
  • Patent number: 6607617
    Abstract: This rocket motor propellant includes a combustible double-base propellant and non-carbonized, non-graphitized polymeric fibers dispersed in the double-base propellant. The double-base propellant is formed from a composition comprising nitrocellulose and at least one nitrate ester. Representative polymeric fibers include polyethylene, polypropylene, polyesters, polyamides, polyacrylonitriles and combinations thereof.
    Type: Grant
    Filed: June 1, 2001
    Date of Patent: August 19, 2003
    Assignee: Alliant Techsystems Inc.
    Inventors: Craig D. Hughes, Reed J. Blau
  • Patent number: 6554936
    Abstract: An elastomerized phenolic resin ablative insulation particularly suitable for use in connection with the thermal insulation of selected components of rocket motors. A composition for making the elastomerized ablative insulation is disclosed. Furthermore, an associated method of forming calendered sheets of material formed of the composition is disclosed. The preferred ingredients of the disclosed composition include acrylonitryle butadiene rubber, zinc borate, and phenol formaldehyde resin which can be cured and bonded to structures such as domes of open-ended rocket motors and other rocket motor components. The subject elastomerized ablative insulation is well suited for use independently or in connection with other insulative materials to form a thermal barrier which is highly resistant to the heat and the erosive nature associated with the combustion of propellant fuels, for example.
    Type: Grant
    Filed: September 8, 1999
    Date of Patent: April 29, 2003
    Assignee: Alliant Techsystems Inc.
    Inventors: Gary S. Metcalf, William E. White
  • Publication number: 20020189233
    Abstract: Insulation for a rocket motor is provided, as is a method for insulating a rocket motor. The insulation includes a cured elastomer and vapor grown carbon fibers dispersed in the cured elastomer. The cured elastomer is preferably formed from a precursor composition comprising an EPDM terpolymer. Generally, the vapor grown carbon fibers have an internal graphitized tube surrounded by a sheath of vapor deposited amorphous carbon.
    Type: Application
    Filed: January 9, 2002
    Publication date: December 19, 2002
    Inventors: Albert R. Harvey, John W. Ellertson
  • Patent number: 6494035
    Abstract: A towing rocket motor assembly has a tubular solid propellant grain defined by exterior surface area and interior surface area. The exterior surface area is inhibited from ignition within a tubular region of a housing. The housing includes a first end and a second end at either end of the tubular region. The first end defines a plenum having an annular region defined by a diameter larger than that of the tubular region. A plurality of holes formed in the first end communicate with the annular region and are directed substantially in the direction of the second end of the housing. A burn-inhibiting baffle is fitted in the propellant grain wherein an annular spacing is defined between the baffle and the interior surface area of the propellant grain. An ignition assembly, mounted at the second end of the housing, is coupled to the interior surface area of the propellant grain so that the propellant grain burns from the inside out upon ignition.
    Type: Grant
    Filed: July 20, 2001
    Date of Patent: December 17, 2002
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventor: Felipe Garcia
  • Patent number: 6430920
    Abstract: A solid rocket motor for accelerating a payload comprises a motor casing and a solid propellant matrix, utilizing a high burn-rate fuel. The use of a high burn rate fuel allows the rocket motor to operate in an end-burning fashion without the use of a constricting aperture to increase the back-pressure upon the burn-front of the fuel matrix. The exhaust gas produced from combustion of the propellant matrix exits directly to the ambient environment through a simple aperture without the use of an expansion nozzle. By eliminating the mass of the nozzle and allowing the use of lighter, less structurally robust motor casings, the needed acceleration of the vehicle can be achieved while using less propellant and a lighter launch vehicle.
    Type: Grant
    Filed: November 23, 1999
    Date of Patent: August 13, 2002
    Assignee: Technanogy, LLC
    Inventors: Joe A. Martin, Larry H. Welch
  • Patent number: 6421999
    Abstract: A modular solid-fuel rocket propellent charge has a combustion-chamber wall, a plurality of separate elements including frozen fuel or oxidizer, and respective rigid casings completely surrounding and enclosing the elements. Respective formations on the casing and on the casings directly engage each other for supporting the elements via the respective casings directly an the wall.
    Type: Grant
    Filed: November 8, 2000
    Date of Patent: July 23, 2002
    Inventor: Roger E. Lo
  • Patent number: 6354075
    Abstract: The present invention comprises a direct replacement for a charge support spacer currently used in rocket motors. The present invention comprises a vented spacer that cools combustion gases through contact and expansion prior to equalizing pressure by transferring these gases from the inside of the propellant grain to the outside of the grain. The vented spacer takes gases from combustion of the propellant from the core flow inside the propellant grain and cools these gases by contact with and ablation of the spacer material. The gases are cooled to the point that they present no hazard to the rocket motor casing or the outside of the propellant grain. The vented spacer accomplishes these tasks in the same amount of area as the current charged support spacer.
    Type: Grant
    Filed: September 27, 2000
    Date of Patent: March 12, 2002
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Randolph T. Johnson, Gerald L. Armstrong, Joseph J. Dulcey
  • Patent number: 6311479
    Abstract: Modular, cryogenic, solid rocket propellants of different fuel components, such as fuels, oxidizers, energy-increasing admixtures, binders, additives, etc., for all applications of solid rockets produce a uniform, stable and complete combustion, This objective is accomplished since one of the fuel elements, due to the special selection of its composition, is provided as a permanent igniter generator of the modular propellant.
    Type: Grant
    Filed: December 13, 1999
    Date of Patent: November 6, 2001
    Inventor: Roger E. Lo
  • Patent number: 6230626
    Abstract: A flashless rocket propellent has a continuous potassium sulfate rod extending though the length of the propellent component. The flashless rocket propellent is particularly useful in the MK 66 Rocket Motor.
    Type: Grant
    Filed: February 23, 2000
    Date of Patent: May 15, 2001
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventor: Steven S. Kim
  • Patent number: 6148606
    Abstract: The present invention relates to a low-vulnerability solid-propellant motor (1) comprising a charge (11) of solid propellant, a heat shield (2) covering the inside of a metal structure with a front end wall (3) and a rear end wall (4) which carries at least one nozzle (10), the said front and rear end walls being fastened to a cylindrical shell (5) having wide apertures which are circumferentially distributed and temporarily sealed by sealing plugs (8). The object of the present invention is to provide a motor which has a simple structure and avoids the use of detection and actuation means for freeing the plugs. The motor according to the invention is such that the sealing plugs (8) are held in the apertures between the heat shield and a composite winding (7) of fibres impregnated in a matrix which surrounds the cylindrical shell (5).
    Type: Grant
    Filed: June 12, 1998
    Date of Patent: November 21, 2000
    Assignee: Celerg
    Inventors: Augustin Grossi, Patrick Fiandesio
  • Patent number: 6054521
    Abstract: The present invention concerns an erosion resistant, low signature liner for solid propellant rocket motors and rocket motors having such a low signature liner. The liner combustion products in the exhaust plume have low visibility in the IR and visible light spectra which is essential for use in low signature solid propellant rocket motors. The liner also forms an in-situ protective layer at elevated temperatures for enhanced erosion resistance. These erosion resistant properties eliminate the need for supplemental case insulation which would contribute additional smoke and combustion products to the exhaust plume as well as add additional costs and inert weight to the motor.
    Type: Grant
    Filed: December 8, 1997
    Date of Patent: April 25, 2000
    Assignee: Cordant Technologies Inc.
    Inventors: Ronald W. Nelson, Merylin B. Lovett, Larry W. Poulter, Elizabeth K. Bonderson
  • Patent number: 6035631
    Abstract: A solid fuel propellant motor casing is described, the casing comprising a body portion for containing the propellant, the body portion also including at least one detachable end closure portion, the closure portion being maintained in position relative to said body portion by retaining means, the retaining means being held in position with engagement means on an inner surface of said body portion and located radially with respect to said body portion by locating means against resilient biasing means, said locating means being responsive to temperature such that said locating means melt at a predetermined temperature allowing said resiliently biased retaining means to move radially inwardly of said body portion and allow said at least one closure portion to be ejected from the casing.
    Type: Grant
    Filed: January 5, 1998
    Date of Patent: March 14, 2000
    Assignee: Royal Ordnance Public Limited Company
    Inventor: Bernard A. Cannon
  • Patent number: 6036144
    Abstract: The disclosed launch systems are formed from mass producible elements that integrate propulsion, pneumatics and structural systems. In one embodiment, a launch system (10) includes multiple stages (12-16) where each stage includes a number of generally wedge-shaped segments (54). Alternating segments (54) form liquid fuel and oxidizer tanks. Each fuel and oxidizer tank pair is associated with a thruster (70). The resulting plurality of thrusters (70) are disposed about a common aerospike thrust structure (30-34). The segments (54) are connected to an internal, hollow structural spine (26) that can also interface with an internal umbilical tower (46). The segments (54) together with their associated thrusters and related components can be mass produced, thereby increasing competition among suppliers, reducing design costs and timeframes.
    Type: Grant
    Filed: October 3, 1997
    Date of Patent: March 14, 2000
    Assignee: Lockheed Martin Corporation
    Inventor: David S. Sisk
  • Patent number: 5564272
    Abstract: The present invention is directed to a novel pressure vessel and process for manufacturing the pressure vessel. In one embodiment, the invention includes a case for a rocket motor which includes a cylindrical, metal shell which has been configured with a plurality of slots positioned in axially extending rows. A fiber reinforced plastic layer is attached to the metal shell. Each slot has a length (L) and is separated by adjacent slots in the same row by an axial distance (A) with adjacent rows of slots separated by a circumferential distance (C) and configured such that L+A.gtoreq.6C and L.gtoreq.4A. The method of the invention comprises using a CO.sub.2 laser to cut a keyhole in the shell and then cutting axially outwardly from the keyhole to form the slot, resulting in slots having a width equal to the cutting width of the laser. The beam is then defocused and used to heat a portion of the metal shell surrounding the ends of each slot to produce a tempered zone.
    Type: Grant
    Filed: July 29, 1994
    Date of Patent: October 15, 1996
    Assignee: Thiokol Corporation
    Inventors: Mark J. Warner, Wayne E. Berndt, O. N. Thompson, Jr., Scott W. Lauritzen, Kevin W. Davis
  • Patent number: 5513489
    Abstract: A pulse detonation engine is provided with at least one detonation combustor selectively coupled to an air inlet and fuel source. The detonation combustors are equipped with either active or passive means to dissipate the heat of detonation. Fuel, air, and an oxidizer can be fed to said detonation combustors either through a rotary valve or through a conically shaped injector head.
    Type: Grant
    Filed: March 4, 1994
    Date of Patent: May 7, 1996
    Assignee: Adroit Systems, Inc.
    Inventor: Thomas R. A. Bussing
  • Patent number: 5402720
    Abstract: A self-aligning adapter used for attaching a booster to a missile includes a hollow tapered receptacle positioned on the missile. A tapered member sized and shaped to fit into and mate with the receptacle is positioned on the booster. The tapered member fits into the tapered receptacle to align and attach the booster to the missile. A linear explosive charge is positioned on the booster around where the tapered member is joined to the booster. Explosion of the charge severs the tapered member from the booster releasing the booster from the missile.
    Type: Grant
    Filed: November 5, 1991
    Date of Patent: April 4, 1995
    Assignee: Northrop Corporation
    Inventors: Marion R. Bottorff, Duane L. Aakre, Brian E. MacDonald, Paul M. Burri, Donald Deverich, William R. Blackhurst, David C. Coe, Anthony J. McEwan
  • Patent number: 5388399
    Abstract: An improved rocket motor and a method for its manufacture are characterized by the provision of a thermoplastic elastomer binder in the outer casing, the insulation layer, and the propellant. When the motor is heated to the melting point of the binder, the bondlines between the propellant and insulation and between the insulation and casing are simultaneously fused to form a unitary motor structure.
    Type: Grant
    Filed: March 11, 1992
    Date of Patent: February 14, 1995
    Assignee: Atlantic Research Corporation
    Inventors: Irving E. Figge, James D. Martin
  • Patent number: 5380570
    Abstract: Para-polyphenylene sulfide, a non-composite, ultrahigh-temperature-resist, thermoplastic resin, is employed for the manufacture of interceptor motor cases. The thermoplastic resin, para-polyphenylene sulfide, has a combination of properties which are of particular interest in the fabrication of interceptor rocket motor cases. Para-polyphenylene sulfide in ribbonized forth is wound directly onto the required mandrel and then fused into a solid mass. The fused, solid mass has the properties which enables it to serve as both insulator and motor case material. The manufacture of a combination insulated motor case is achieved by the following method: The equipment, first, involves the fabrication of a breakout mandrel by one of several methods. The para-polyphenylene sulfide is ribbonized by extrusion and wound down on the breakout mandrel to the required thickness and fused into a solid mass by heating to its melt temperature of about 285.degree. C.
    Type: Grant
    Filed: July 6, 1993
    Date of Patent: January 10, 1995
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: David C. Sayles
  • Patent number: 5352312
    Abstract: Rocket motor insulation compositions are provided. An important component of such insulation compositions is a thermoplastic liquid crystal polymer. Such a polymer provides an ablative insulation which has good performance characteristics during operation of the rocket motor. One such thermoplastic liquid crystal polymer is a wholly aromatic polyester known as VECTRA.RTM.. The insulation may also include fillers such as fibrous fillers and particulate fillers. Typical fibrous fillers include glass or carbon fibers. Typical particulate fillers include materials such as silica, alumina, powdered coal, and the like.
    Type: Grant
    Filed: August 6, 1992
    Date of Patent: October 4, 1994
    Assignee: Thiokol Corporation
    Inventor: David G. Guillot
  • Patent number: 5341638
    Abstract: A composite structure for rocket motors includes a longitudinal element of the composite structure, which is an assembly of segments of clamshell or barrel stave form. The element is held in place by a circumferential element, which is a composite overwrap of reinforcing fibers in a resin matrix. The matrix may be thermoplastic or thermosetting. The reinforcing fiber being high strength polyolefin thereby providing the rocket motor with insensitive munitions capability.
    Type: Grant
    Filed: March 9, 1992
    Date of Patent: August 30, 1994
    Assignee: Thiokol Corporation
    Inventors: Frederick W. Van Name, Michael A. Gerace, Victor Singer, Brendan M. Walsh