| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 241 | Chemically driven hydrogen gun | US11027755 | 2004-12-30 | US07305912B2 | 2007-12-11 | Shyke Goldstein; Michael Raleigh; Michael Bohnet; James Galambos; Mark Machina |
| An electrothermal gun uses an apparatus for generating high gas pressure. The apparatus includes a receiver having a combustion chamber for holding a propellant which produces a gas component and a particle component when the propellant undergoes an exothermic chemical reaction, and a flow passageway positioned downstream of the combustion chamber. An ignition mechanism causes the propellant contained in the combustion chamber to undergo the exothermic chemical reaction. A separator in the flow passageway substantially separates the particle component from the gas component in the flow passageway. The gun includes a barrel connected to the receiver and communicating with the flow passageway. By substantially stopping the particle component, namely metal oxide, from reaching the barrel, wear on the barrel is reduced. | ||||||
| 242 | Combustion-gas-powered paintball marker | US11714168 | 2007-03-06 | US20070175324A1 | 2007-08-02 | Joseph Adams |
| An onboard combustion-gas-powered engine supplies power to a paintball marker or other projectile launcher by generating gas pressure pulses for propelling paintballs and other projectiles. The combustion gases produced by the engine can be allowed to rise in pressure within a confined volume of space before being released through a valve into a barrel for applying enhanced pressure pulses to the projectiles. A loading system is linked to a combustion accelerating system for automatically loading projectiles into the launcher. | ||||||
| 243 | Chemically driven hydrogen gun | US11027755 | 2004-12-30 | US20060144214A1 | 2006-07-06 | Shyke Goldstein; Michael Raleigh; Michael Bohnet; James Galambos; Mark Machina |
| An electrothermal gun uses an apparatus for generating high gas pressure. The apparatus includes a receiver having a combustion chamber for holding a propellant which produces a gas component and a particle component when the propellant undergoes an exothermic chemical reaction, and a flow passageway positioned downstream of the combustion chamber. An ignition mechanism causes the propellant contained in the combustion chamber to undergo the exothermic chemical reaction. A separator in the flow passageway substantially separates the particle component from the gas component in the flow passageway. The gun includes a barrel connected to the receiver and communicating with the flow passageway. By substantially stopping the particle component, namely metal oxide, from reaching the barrel, wear on the barrel is reduced. | ||||||
| 244 | Apparatus and method for firing a projectile | US11202814 | 2005-08-12 | US20060032487A1 | 2006-02-16 | Dennis J. Tippmann |
| Apparatus for firing a projectile comprises a receiver, a barrel, a supply of combustible gas, a combustion chamber, a valve arrangement for controlling flow of combustible gas from the supply to the combustion chamber, an igniter, and a passageway for directing combustion gases from the chamber to propel a projectile from the apparatus. In one embodiment, the barrel has a longitudinally-extending central axis, and the combustion chamber is disposed laterally adjacent the axis. A method of operating the apparatus comprises the steps of providing a combustible mixture of gas and air to the combustion chamber, igniting the mixture so as to generate combustion gases, allowing pressure in the combustion chamber to increase to a predetermined level, and releasing the gases from the combustion chamber and directing the gases to propel the projectile through the barrel. | ||||||
| 245 | Ignition systems for hybrid and solid rocket motors | US10269366 | 2002-10-11 | US20040068979A1 | 2004-04-15 | 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. | ||||||
| 246 | Launching device for training retrieving dogs | US09391499 | 1999-09-08 | US06347476B1 | 2002-02-19 | Bernard Tedford Cullen; Wayne Seyman Lewis |
| A launching device for training dogs to retrieve comprising a plurality of projectiles arranged to be launched by the launching device of the type which can be retrieved by the dog, a projectile mount arranged to support the plurality of projectiles such that the plurality of projectiles can be positioned one at a time to be launched automatically, a gas chamber wherein the gas is arranged to produce a force to launch the projectile, an actuating arrangement to actuate the gas in the gas chamber, at least one gas supply container for supplying the gas to the chamber, a remote operating means to launch the projectiles from a distance and a valve arrangement for controlling the amount of gas entering the gas chamber. The projectile mount is on a shaft having an axis in which the projectile mount can rotate. A motor is arranged to drive the shaft about the axis. A disk is mounted at a respective end of the shaft arranged to rotate about the axis. A plurality of engaging members are on an outer edge of the disk for engaging a switch. The switch is arranged to stop rotation of the motor such that the projectile is in position to be launched. The switch defines the actuating arrangement such that when the engaging members engage the switch the flow of gas to the gas chamber is stopped and ignited. The actuating arrangement has a sparking device defining a spark plug mounted on the gas chamber for igniting the gas and the sparking device is actuated by the switch when engaged by the engaging member. | ||||||
| 247 | Ignitor for use in a liquid monopropellant gas generator | US453112 | 1995-05-30 | US5650585A | 1997-07-22 | Robert Arthur Pate; John Joseph Paul Johnson; Keith James Schaefer; John Mandzy |
| An initiator, for use in a gas generator, includes an enclosed volume in communication with apertures for introducing liquid propellant and pre-pressurization gas into a propellant ignition chamber, and an aperture for introducing combusted gasses into a gas generator. A mechanism for controlling when the gases are allowed to enter the gas generator, and a heater/electrode to initiate combustion of the liquid propellant, also communicate with the enclosed volume. The propellant and the pre-pressurization gas may be introduced together or through separate ports. The heater/electrode thermally decomposes and vaporizes the propellant causing pressurization of the ignition chamber until a critical value is reached and the propellant ignites and burns. The burning propellant increases the chamber pressure beyond a predetermined value thereby opening the controlling mechanism and allowing the combusted gases to be introduced into the gas generator combustion chamber. | ||||||
| 248 | Break action cannon | US239779 | 1994-05-09 | US5591932A | 1997-01-07 | Richard W. Staiert; James E. Wildman |
| The break action cannon invention disclosed herein enables weaponization and integration of complex fire control systems concurrent with projectile loading operations in a gun system such that superior firing cycle and efficient power and thermal management are achieved. A barrel is detachably shifted and tipped at an angle to accept a projectile while breech operations and other firing preparations proceed unencumbered. | ||||||
| 249 | Distillate fuel oil/air-fired, rapid-fire cannon | US393559 | 1995-02-23 | US5499567A | 1996-03-19 | Jordan L. Gay |
| A weapons system that fires projectiles of 20 to 500 millimeters or larger in diameter using a compression-ignition combustion of common fuel oils in conjunction with pre-compressed air as the firing force, in which automatic breech loading occurs during resetting, to enable a continuous, automatic rapid fire. Fuel pumped at a high pressure enters a combustion chamber, previously filled with high pressure air from an external compressor, where an extremely rapid combustion occurs, resulting in compression of the air in a charge chamber. A control valve then opens, allowing compressed air from the charge chamber, where high pressure fuel is then injected and instantly vaporized and combusted to propel a projectile through a barrel. A loading ram concurrently engraves the next round into a breech block chamber. In the resetting process, the valve reseats, air from an external compressor enters the combustion chamber via a check valve, and the combustion chamber is vented to the atmosphere. The breech assembly rotates to position a new projectile in the barrel so that the firing process can repeat. | ||||||
| 250 | Method of confinement of propellants for ignition | US17092 | 1993-02-10 | US5359919A | 1994-11-01 | Richard A. Beyer |
| A method for confinement of a gun propellant during the initial stage of ignition provides the ignition by electrical, pyrotechnic, or laser irradiation means. A liquid and or a solid propellant is placed in a substantially closed chamber. A portion of the propellant in a conduit of the chamber exits from the chamber and is cooled in the exit conduit by a thermoelectric or cryogenic means to a sufficiently low temperature for producing a viscous, glassy, or substantially solidified condition to enhance the propellant containment. An ignition stimulus is then applied. A closure means in the exit conduit selectively varies the amount of flow whereby a relatively high temperature and pressure are reached from the chemical energy release of the propellant. Venting of the formed combustive products is provided through the exit conduit whereby sufficient thermal energy is generated to sustain combustion and to ignite the next stage. | ||||||
| 251 | Combustion instability suppression in regenerative liquid propellant gun | US751362 | 1991-08-19 | US5149908A | 1992-09-22 | Klaus C. Schadow; Ephraim Gutmark; Kenneth J. Wilson; Robert A. Smith |
| A regenerative liquid propellant gun and pertains includes a modified contional fixed bolt extending into a conventional combustion chamber of the regenerative liquid propellant gun. The modified fixed bolt of this invention provides for improved operation of the otherwise conventional regenerative liquid propellant gun and has modified end portion embodiments and internal propellant injection passages, all for the purpose of creating turbulent propellant flow. | ||||||
| 252 | Post burn hydrogen light gas cartridge | US642974 | 1990-11-23 | USH927H | 1991-06-04 | Donald Miller |
| A post burn hydrogen light gas cartridge utilizes a separation tube to prde a high velocity flow to allow for separation of hydrogen gas from the hydrogen-oxygen combustion product water in a high temperature state produced in a primer initiated combustion chamber containing pressurized hydrogen gas. An accumulator is utilized to provide a large volume of hydrogen gas at high pressure and temperature to feed the expansion of the hydrogen. A second oxidant ampoule reacting with the expanded hydrogen provides a secondary propulsion means giving a velocity additive to the velocity resulting from a primary expansion means. | ||||||
| 253 | Sealing for the differential pressure piston-fuel chamber systems of firearms | US532509 | 1983-09-06 | US4993310A | 1991-02-19 | Hans Sackenreuter; Gerhard Onderka |
| A sealing arrangement for differential pressure piston-combustion chamber systems, which serve for the generation of propellant gases for barreled firearms from liquid, in particular hypergolic propellant components (hypergolic diergoles), and which are constructed with a differential pressure piston or ram located in the weapon housing, which is axially movable in coaxial relationship with the weapon barrel, and which includes a support piston projecting into the hollow shaft of the differential pressure piston, as well as propellant infeed and propellant discharge passageways. The combustion chamber which connects to the weapon barrel widens conically at a relatively flat angle, and in which the head of the differential pressure piston (injector), which is provided with overflow passageways and nozzles, has its external contour correlated with the cone of the combustion chamber. Hereby, the conically-shaped outer wall or shell surface of the injector can incorporate annular recesses, grooves or the like. The lower surface of these recesses or grooves, for reasons of simplifying the manufacturing technology and production, can be arranged in parallel with the longitudinal axis of the differential pressure piston. Within the cylindrical injector shaft there can be inserted a support piston, and between the support piston and the inner wall or shell of the injector shaft, as well as between the outer wall or shell of the injector shaft and the housing, there can also be, respectively, provided a labyrinth seal. | ||||||
| 254 | Liquid propellant weapon system | US471310 | 1990-01-22 | US4993309A | 1991-02-19 | Melvin J. Bulman |
| This invention provides a liquid propellant round of ammunition having a traveling charge which is ignited after both such charge and the projectile have received an initial forward acceleration. | ||||||
| 255 | Method and apparatus for initating stable operation of a ram accelerator | US207706 | 1988-06-16 | US4982647A | 1991-01-08 | Abraham Hertzberg; Adam P. Bruckner; David W. Bogdanoff; Carl Knowlen |
| A method and apparatus for supersonically accelerating a projectile in a thermally choked subsonic combustion mode. A projectile (50) is initially preaccelerated using either a tank (24) of compressed helium or a chemical propellant charge preaccelerator (152). The projectile enters a portion of a tube (22) filled with a combustible mixture (54) of a gaseous fuel and an oxidizer and is propelled by a ram acceleration process as the mixture burns. In several different embodiments, various devices are used to control the velocity of a shock wave generated as the projectile enters the combustible mixture and the dynamic impulse pressure immediately behind the projectile, so that the shock wave attaches to the projectile along an aft portion, thereby establishing a stable subsonic combustion zone along the aft end (64) of the projectile, in which combustion of the gaseous fuel accelerates the projectile down the bore of the tube. In one embodiment, a perforated sabot (52) is used to propel the projectile during preacceleration. The sabot has a plurality of passages (114) extending longitudinally between its front and rear surfaces, which are initially closed with a thin plate (110) during the preacceleration of the projectile. However, the plate is dislodged as the projectile enters the combustible mixture, allowing the dynamic pressure of the shock wave caused by the sabot to dissipate through the open passages. | ||||||
| 256 | Liquid propellant weapon system | US263792 | 1981-05-14 | US4967638A | 1990-11-06 | Melvin J. Bulman |
| A feature of this invention is the provision of an ignition mechanism for a main combustion chamber including an ignition antechamber having a first cross-sectional area, an electrode, and an inlet port for liquid propellant; a conduit having a length over diameter ratio greater than one, a second cross-sectional area which is less than said first area, and an inlet which opens into said ignition antechamber and an outlet which opens through an orifice into said main combustion chamber. | ||||||
| 257 | Liquid monopropellant for a gun | US276576 | 1981-06-15 | US4946522A | 1990-08-07 | Larry L. Liedtke; H. Dean Mallory; William R. McBride; Everett M. Bens; Klaus C. Schadow; Thomas L. Boggs |
| A new solution monopropellant for use in liquid propellant guns is composedf ammonium nitrate, hydrazine hydrate, and water in a mole ratio of 1:1:0.05 to 0.30. | ||||||
| 258 | Liquid propellant gun | US677151 | 1984-11-30 | US4945809A | 1990-08-07 | Melvin J. Bulman; David L. Maher |
| This invention provides an annular piston, annular control valve, liquid propellant gun system, having a dual angle injection mechanism to provide both bore and chamber gas requirements with a single injection control valve. The dual angle feature assures a stable combustion zone. A flexible lip on the projectile is used in conjunction with the dual angle injection mechanism to positively eliminate backflow of propellant through the injection mechanism during the ignition phase of the gun cycle. | ||||||
| 259 | Liquid propellant gun | US911044 | 1986-09-08 | US4932327A | 1990-06-12 | Melvin J. Bulman; David L. Maher |
| This invention provides an annular piston, annular control valve, liquid propellant gun system, having a dual angle injection mechanism to provide both bore and chamber gas requirements with a single injection control valve. The dual angle feature assures a stable combustion zone. A flexible lip on the projectile is used in conjunction with the dual angle injection mechanism to positively eliminate backflow of propellant through the injection mechanism during the ignition phase of the gun cycle. | ||||||
| 260 | Method and apparatus for launching a projectile at hypersonic velocity | US157472 | 1988-02-18 | US4932306A | 1990-06-12 | Josef Rom |
| A projectile is accelerated to hypersonic velocity in an initially closed barrel of a diameter considerably larger than the projectile diameter which is filled with a compressed fuel-oxidizer mixture. The projectile comprises a conical nose portion, an intermediate portion formed to generate oblique detonation waves, and a tapering tail portion provided with several radial vanes. The projectile is propelled by an initiator gun at supersonic speed through one of the intitially closed ends in the barrel, were the detonation waves cause detonation and combustion of the fuel-oxidizer mixture. The detonation results in a high pressure increase to the rear of the projectile accelerating it along the barrel and shooting it at the reached hypersonic speed through the other, initially closed end of the barrel into the open. | ||||||
QQ群二维码
意见反馈
意见反馈