| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | In-line annular piston fixed bolt regenerative variable charge liquid propellant gun with variable hydraulic control of piston | EP85103915 | 1985-04-01 | EP0161448A3 | 1987-02-04 | Magoon, Inder Kumar |
A regenerative liquid propellant gun structure in which the differential area piston is annular, has an open peripheral cylindrical skirt extending away from the combustion chamber to define a propellant reservoir, and has an aperture in the piston head permitting overrunning of a fixed bolt. The fixed bolt is cylindrical with an enlarged band to fit the aperture to block flow of propellant until firing and to define with the edge of the aperture a variable annual orifice for propellant injection as the piston moves. There is a second free piston overrunning the bolt having a forward portion mating with both the inside of the differential area piston and the exterior of the cylindrical skirt so that the skirt constitutes a piston in a circular dashpot in the second piston. The second piston also contains a fluid accumulator, fluid conduit means interconnecting the accumulator and the dashpot and means for changing the cross sectional area of the fluid conduit means to provide a variable hydraulic resistance to the differential area piston during firing. |
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| 122 | In-line annular piston fixed bolt regenerative variable charge liquid propellant gun with variable hydraulic control of piston | EP85103915.6 | 1985-04-01 | EP0161448A2 | 1985-11-21 | Magoon, Inder Kumar |
A regenerative liquid propellant gun structure in which the differential area piston is annular, has an open peripheral cylindrical skirt extending away from the combustion chamber to define a propellant reservoir, and has an aperture in the piston head permitting overrunning of a fixed bolt. The fixed bolt is cylindrical with an enlarged band to fit the aperture to block flow of propellant until firing and to define with the edge of the aperture a variable annual orifice for propellant injection as the piston moves. There is a second free piston overrunning the bolt having a forward portion mating with both the inside of the differential area piston and the exterior of the cylindrical skirt so that the skirt constitutes a piston in a circular dashpot in the second piston. The second piston also contains a fluid accumulator, fluid conduit means interconnecting the accumulator and the dashpot and means for changing the cross sectional area of the fluid conduit means to provide a variable hydraulic resistance to the differential area piston during firing. |
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| 123 | PROJECTILE PROPULSION SYSTEM | PCT/US2009045936 | 2009-06-02 | WO2010036413A3 | 2010-06-10 | RIGGS JEFFREY L; OLEYNIK VLADISLAV; BOROVIKOV VALERY; ALBUL GENNADIY |
| A projectile propulsion system includes a launch tube, multiphase material, and a membrane. The launch tube has an interior cavity, the multiphase material disposed therein. The launch tube also has an opening to receive the multiphase material. The membrane seals the opening while the multiphase material is disposed in the interior cavity of the launch tube so as to allow the launch tube to be pressurized. When the membrane is broken, a supersonic wave thrusts the contents of the interior cavity, such as a projectile, outwards with a high velocity and force. | ||||||
| 124 | METHOD OF WILDLIFE CONTROL BY MEANS OF CHILLI GAS DISPENSER | PCT/IB2009007045 | 2009-10-06 | WO2010041115A3 | 2010-05-27 | LA GRANGE MICHAEL; MOSTERT JOSHUA JOHN |
| An animal deterrent device (10) which includes a tube (12) with a barrel (14) and a chamber (16) which is filled with a flammable gas which is electrically- ignited to direct a capsaicin- containing capsule (38) from the barrel towards the animal. | ||||||
| 125 | UNIVERSAL CANNON | PCT/DE2008000534 | 2008-03-20 | WO2008116460A3 | 2008-11-27 | TEVKUER TALIP |
| The invention relates to a universal cannon comprising chambers for a propellant and a working medium, in addition to a seal, situated between said chambers, which can be opened by a trigger mechanism in order to expel the working medium. The interior of a hollow cylindrical body (1) with at least one jacket opening (8, 9) is provided with a tubular body (2) with a smaller cross-section, thus forming an annular chamber (3) that contains working medium and/or propellant or that can be filled with working medium and/or propellant. The tubular body (2) is located so that it can be displaced in the longitudinal direction of the outer hollow cylindrical body (1), from a position, in which the passages (7) from the annular chamber (3) to the tubular body (2) are sealed, into a working position, in which the passages (7) are open. The universal cannon can be used in a building as a stationary emergency appliance or as a combat appliance on vehicles, or on a frame that is carried by a person. | ||||||
| 126 | LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF | US15852815 | 2017-12-22 | US20180162559A1 | 2018-06-14 | Miles R. Palmer |
| The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor. | ||||||
| 127 | Light gas gun | US14205064 | 2014-03-11 | US09915496B2 | 2018-03-13 | David Wayne Bergeron |
| An improved light gas gun launches a projectile in a light gas atmosphere as it travels through a frictionless barrel to achieve high muzzle velocities, decreased acoustic signatures, and increased ranges. The light gas atmosphere is introduced by a purge valve prior to firing or by a muzzle valve that holds a positive light gas pressure on the barrel and breech. The muzzle valve also routes the majority of propellant gases through a suppression canister, reducing the light gas gun's acoustic signature. The frictionless barrel uses light gas propellant routed through gas bearings to keep the projectile centered in the barrel and preclude the projectile from contacting the barrel walls, eliminating barrel wear. | ||||||
| 128 | RAM ACCELERATOR SYSTEM WITH BAFFLES | US15135452 | 2016-04-21 | US20160356087A1 | 2016-12-08 | MARK C. RUSSELL; TIMOTHY JOHN ELDER; JONATHAN M. WOLFF |
| One or more ram accelerator devices may be used to form one or more holes in geologic or other material. These holes may be used for drilling, tunnel boring, excavation, and so forth. The ram accelerator includes one or more baffles that are downhole. The ram accelerator devices propel projectiles which are accelerated by combustion of one or more combustible gasses in a ram effect to reach velocities exceeding 500 meters per second. An endcap may be deployed within a tube of the ram accelerator device to prevent incursion of formation pressure products such as oil, water, mud, gas, and so forth into a guide tube of the ram accelerator. The endcap may be maintained in place within the hole at least in part by the one or more baffles. During operation the projectile penetrates the endcap and at least a portion thereof impact a working face. | ||||||
| 129 | Mechanisms for firing projectiles and methods of their use | US14399744 | 2013-03-18 | US09459059B2 | 2016-10-04 | Peter John Hamilton |
| A method of firing projectiles without the use of cartridge cases by electronically controlling the dynamics of internal ballistics created by combustion of Nitrous Oxide and a fuel injected under high pressure at oxygen rich or stoichiometric ratios. The shape of injector nozzles and the combustion chamber as well as a timed sequence of Nitrous Oxide injection, fuel injection and their ignition are used to create correct ballistics. The timing of the injection and ignition sequence is automatically altered dynamically by an electronic control unit that obtains information from sensors and from an operator to tune the combustion for each firing so that the internal ballistic pressure versus time curve is favorable. | ||||||
| 130 | System and Method for Accelerating a Mass Using a Pressure Produced by a Detonation | US15003525 | 2016-01-21 | US20160216387A1 | 2016-07-28 | Larry W. Fullerton; James L. Teel; Herman M. Thompson, JR. |
| The present invention pertains to a system and method for accelerating a mass using a pressure produced by a detonation, where the mass is accelerated over a movement range using a detonation of a pressure wave generator that produces a pressure within a coupling component that is applied to a piston having a surface area that produces a resultant force, where the acceleration of the mass determines the resulting force. The resulting force may be directed vertically and perpendicular to a target media to conduct an acoustic wave into the target media. The system may be configured to direct the resulting force horizontally and parallel to a target media to conduct a plane shear wave into the target media. Two systems may be configured to direct two resulting forces horizontally and parallel to a target media to conduct a spherical shear wave into a target media, where the two resulting forces are directed in opposite directions and separated by some distance. | ||||||
| 131 | GAS GENERATORS, LAUNCH TUBES INCLUDING GAS GENERATORS AND RELATED SYSTEMS AND METHODS | US14606601 | 2015-01-27 | US20160161226A1 | 2016-06-09 | James D. Dunaway; Duane J. Garbe; William P. Sampson; Robert L. Hatch |
| Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile. | ||||||
| 132 | RAM ACCELERATOR SYSTEM WITH ENDCAP | US14708932 | 2015-05-11 | US20150330147A1 | 2015-11-19 | MARK C. RUSSELL |
| One or more ram accelerator devices may be used to form one or more holes in geologic or other material. These holes may be used for drilling, tunnel boring, excavation, and so forth. The ram accelerator devices propel projectiles which are accelerated by combustion of one or more combustible gasses in a ram effect to reach velocities exceeding 500 meters per second. An endcap may be deployed within a tube of the ram accelerator device to prevent incursion of formation pressure products such as oil, water, mud, gas, and so forth into a guide tube of the ram accelerator. During operation the projectile penetrates the endcap and at least a portion thereof impact a working face. In some implementations a purge gas may be used to form a ullage between the endcap and the working face. | ||||||
| 133 | Gas generators, launch tubes including gas generators and related systems and methods | US13690040 | 2012-11-30 | US08967046B2 | 2015-03-03 | James D. Dunaway; Duane J. Garbe; William P. Sampson; Robert L. Hatch |
| Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile. | ||||||
| 134 | LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF | US14211779 | 2014-03-14 | US20140306065A1 | 2014-10-16 | Miles R. Palmer; Glenn William Brown, JR. |
| The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided. | ||||||
| 135 | GAS GENERATORS, LAUNCH TUBES INCLUDING GAS GENERATORS AND RELATED SYSTEMS AND METHODS | US13690040 | 2012-11-30 | US20140150683A1 | 2014-06-05 | James D. Dunaway; Duane J. Garbe; William P. Sampson; Robert L. Hatch |
| Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile. | ||||||
| 136 | Projectile propulsion system | US13449859 | 2012-04-18 | US08327747B2 | 2012-12-11 | Jeffrey L. Riggs; Vladislav Oleynik; Valery Borovikov; Gennadiy Albul |
| A projectile propulsion system includes a launch tube, multiphase material, and a pressure barrier member. The launch tube has an interior cavity, the multiphase material disposed therein. The launch tube also has an opening to receive the multiphase material. The pressure barrier member seals the opening while the multiphase material is disposed in the interior cavity of the launch tube so as to allow the launch tube to be pressurized. When the pressure barrier member is broken, a shock wave allows the contents of the interior cavity, such as a projectile, to be expelled from the tube with a high velocity and force. | ||||||
| 137 | ELECTRODE IGNITION AND CONTROL OF ELECTRICALLY IGNITABLE MATERIALS | US12989639 | 2009-05-15 | US20110259230A1 | 2011-10-27 | Wayne N. Sawka; Charles Grix |
| Apparatus for providing electrically initiated and/or controlled combustion of electrically ignitable propellants is provided. In one example, the apparatus includes a volume of electrically ignitable propellant (liquid and/or gas) capable of self sustaining combustion, and electrodes operable to ignite the propellant. The apparatus may further include a power supply and controller in electrical communication with the electrodes for supplying a potential across the electrodes to initiate combustion of the propellant and/or control the rate of combustion of the propellant. Various configurations and geometries of the propellant, electrodes, and apparatus are possible. In one example, the electrodes are supplied a direct current, which causes combustion of the propellant at the positive electrode. In another example, the electrodes are supplied an alternating current, which initiates combustion of the propellant at both electrodes. | ||||||
| 138 | Multivalve hypervelocity launcher (MHL) | US11327479 | 2006-01-09 | US07775148B1 | 2010-08-17 | Patrick P. McDermott |
| Launching payloads at high velocity uses high-pressure gas or combustion products for propulsion, with injection of high pressure gas at intervals along the path behind the payload projectile as it accelerates along the barrel of the launcher. An inner barrel has an interior diameter equal to the projectile diameter or sabot containing the projectile. An outer casing surrounds the inner barrel. Structures at intervals attach the outer casing and the inner barrel. An axial gas containment chamber (AGC) stores high pressure gas between the inner barrel wall, the outer casing wall, and enclosure bulkheads. Pressure-activated valves along the barrel sequentially release the high pressure gas contained in the AGC in to the barrel to create a continuously refreshed high energy pressure heads behind the projectile as it moves down the barrel. A frangible cover at the exit end of the barrel allows the barrel to be evacuated prior to launch. The launcher is rapidly recyclable. The valves close automatically after the projectile has exited the barrel, allowing a new projectile to be introduced into the breech and the AGC to be recharged with high-pressure gas. | ||||||
| 139 | Ignition systems for hybrid and solid rocket motors | US10269366 | 2002-10-11 | US06912839B2 | 2005-07-05 | Korey R. Kline; Derek Dee Deville |
| An ignition system for a rocket motor includes a soft plastic tube that extends up into the combustion chamber and is coupled to an oxidizer source. Ignition source wires extend through the tube and terminate at a first end at a location which is set back from the end of the tube, and have a second end coupled to an electric power supply. In operation, an oxidizer is introduced into the tube simultaneously with activation of the power supply. The set back portion of the plastic tube becomes fuel for the oxidizer and is consumed, introducing a fire plume into the combustion chamber. The tube introduces additional fuel distinct from the fuel grain or propellant which is in contact with the both the ignition source wires and oxidizer. In addition, the tube will not damage the nozzle as it is being blown of the rocket during the main propulsion phase. | ||||||
| 140 | Monopropellant combustion system | US10436861 | 2003-05-13 | US20040226280A1 | 2004-11-18 | Gerald R. Berg; Donn C. Mueller; Mark W. Parish |
| An apparatus and method are provided for decomposition of a propellant. The propellant includes an ionic salt and an additional fuel. Means are provided for decomposing a major portion of the ionic salt. Means are provided for combusting the additional fuel and decomposition products of the ionic salt. | ||||||
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