| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 221 | Hiram stevens maxim | US424119D | US424119A | 1890-03-25 | ||
| 222 | Cyc lone-destroyer | US370845D | US370845A | 1887-10-04 | ||
| 223 | Best available copy | US347984D | US347984A | 1886-08-24 | ||
| 224 | Improvement in battery-guns | US113996D | US113996A | 1871-04-25 | ||
| 225 | Improvement in breech-loading ordnance | US46259D | US46259A | 1865-02-07 | ||
| 226 | Improvement in removing spikes from guns | US40051D | US40051A | 1863-09-22 | ||
| 227 | Light gas gun projectile | US15869414 | 2018-01-12 | US10119780B1 | 2018-11-06 | 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. The system includes a projectile assembly that stores light gas from the firing and injects it into the boundary layer, reducing drag, increasing range and lethality, and decreasing acoustic signature of the projectile down range. | ||||||
| 228 | Viscous liquid monopropellant | US13419810 | 2012-03-14 | US09970740B2 | 2018-05-15 | Peter Joseph Beck; Adam Michael Berry |
| This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomized and then ignited. The atomization step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidizers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion while doing so. | ||||||
| 229 | Launch vehicle and system and method for economically efficient launch thereof | US15251408 | 2016-08-30 | US09862506B2 | 2018-01-09 | 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. | ||||||
| 230 | Launch vehicle and system and method for economically efficient launch thereof | US14211779 | 2014-03-14 | US09617016B2 | 2017-04-11 | 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. | ||||||
| 231 | RAM ACCELERATOR SYSTEM | US15292011 | 2016-10-12 | US20170030143A1 | 2017-02-02 | 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. | ||||||
| 232 | RAM ACCELERATOR SYSTEM WITH ENDCAP | US15246414 | 2016-08-24 | US20160362936A1 | 2016-12-15 | 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 impacts a working face. A downhole end of the tube may be displaced laterally within the hole to change the direction of the hole. | ||||||
| 233 | Launch vehicle and system and method for economically efficient launch thereof | US14211698 | 2014-03-14 | US09463881B2 | 2016-10-11 | 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. | ||||||
| 234 | Ram accelerator system with endcap | US14708932 | 2015-05-11 | US09458670B2 | 2016-10-04 | 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. | ||||||
| 235 | Projectile launcher | US13331470 | 2011-12-20 | US09222737B1 | 2015-12-29 | Bruce D. Lund; Michael D. Starrick |
| This application relates to a projectile launcher in which the amount of fuel supplied to the combustion chamber can be varied to shoot the projectile in a lethal or non-lethal mode. The amount of fuel determines the velocity at which the projectile is fired. A low velocity launch on the order of 150 feet per second will be non-lethal at all but very short distance whereas a high velocity launch on the order of 450 feet per second will be non-lethal at a typical range of 100-150 meters but may possibly be lethal at a range of the order of 30 meters or less. | ||||||
| 236 | ELECTRODE IGNITION AND CONTROL OF ELECTRICALLY IGNITABLE MATERIALS | US14299889 | 2014-06-09 | US20150047526A1 | 2015-02-19 | 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. | ||||||
| 237 | LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF | US14211698 | 2014-03-14 | US20140306064A1 | 2014-10-16 | 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. | ||||||
| 238 | Viscous Liquid Monopropellant | US13419810 | 2012-03-14 | US20120234196A1 | 2012-09-20 | Peter Joseph Beck; Adam Michael Berry |
| This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomised and then ignited. The atomisation step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidisers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion whilst doing so. | ||||||
| 239 | Projectile launcher | US11839339 | 2007-08-15 | US08015907B2 | 2011-09-13 | Dennis J. Tippmann, Sr. |
| An apparatus for launching a projectile, such as a paintball. The apparatus uses energy generated from the combustion of fuel to propel a projectile out of the apparatus. | ||||||
| 240 | Projectile Launcher | US11839339 | 2007-08-15 | US20080190275A1 | 2008-08-14 | Dennis J. Tippmann |
| An apparatus for launching a projectile, such as a paintball. The apparatus uses energy generated from the combustion of fuel to propel a projectile out of the apparatus. | ||||||
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