| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | JPH0439600B2 - | JP23048784 | 1984-11-02 | JPH0439600B2 | 1992-06-30 | |
| 62 | Electric accelerator | JP8746489 | 1989-04-06 | JPH02267369A | 1990-11-01 | OYA NOBUMICHI; YONEYAMA OSAMU |
| PURPOSE: To disuse a peculiar switch in a device wherein arc discharge is performed upto discharge electrodes of negative and positive electrodes, and projectile is accelerated by means of a high pressure plasma generated thereby, by setting at least one of the discharge electrodes to be a sliding electrode. CONSTITUTION: A supporting part of a projectile 2, a plasma forming space, and an electrode supporting part which supports a fixed electrode 3 and plays a role of a nozzle are arranged in a plasma chamber 1 composed of a cylindrical electro-conductive body, to an end part of which chamber 1 an insulative electrode guide 4 is fitted while the electrode 3 is fixed to the chamber 1. A barrel 5 which emits the projectile 2 is connected to the funnel-shaped end part of the chamber 1. A sliding electrode 6 is slidably arranged in an introducing hole of the electrode guide 4, and excited in the direction of the fixed electrode 3 by means of a compression coil spring 8 in an outer cylinder 10. Gap between the electrodes 3 and 6 are almost eliminated by the sliding of the electrode 6, and electric discharge is performed between both the electrodes 3 and 6. COPYRIGHT: (C)1990,JPO&Japio | ||||||
| 63 | Propellant casing assembly | JP11763989 | 1989-05-12 | JPH0264400A | 1990-03-05 | MARUKUSU REEFUREERU |
| PURPOSE: To reduce energy loss at the time of charging an electric charging element significantly by evaporating an encased coil at a specified current density to produce gas for propelling a projectile entirely or partially. CONSTITUTION: A propellant casing assembly 20 comprises a container or casing 21 made of steel, glass fiber reinforced synthetic material or other high strength material, an insulating jacket 22, and a coil 23. The coil 23 is formed of a wire made of aluminum, lithium, graphite, or the like. Remaining volume of the assembly 20 is filled with an appropriate propellant fuel 25 composed of a low molecular weight substance, e.g. methanol, lithium hydride, lithium, water or coal ash. The assembly 20 charged with a projectile 24 is loaded to a barrel 10 and secured internally by closing a tail plug 11. The other end of the coil 23 is connected through the casing 21 and the barrel 10 with a power supply 31 via a wire 41 to complete an electric circuit. Magnetic energy in the evaporation coil is converted into heat through ohmic resistance of plasma. COPYRIGHT: (C)1990,JPO | ||||||
| 64 | Rotary type fuel injection device | JP16467188 | 1988-06-30 | JPH0217391A | 1990-01-22 | OKUMURA TOSHIHARU |
| PURPOSE:To reduce the vibration of combustion and improve combustion efficiency as well as the stability of combustion by a method wherein the title device is constituted of an injection piston, injecting fuel, and an injection piston rotating means, equipped on the injection piston and providing the same with a rotary motion. CONSTITUTION:Fuel, leaked from an injection hole 1 into a combustion chamber 6c, is ignited by an ignition plug 9. After the ignition, an injection piston 1 is pushed rearward by a combustion pressure generated in the combustion chamber 6c whereby the fuel in a fuel chamber 6d is compressed. The fuel is injected into the combustion chamber 6c through the injection port 1d of the opening 1a of a piston 1 by the compression and is bursted while a missile 8 is flown by the gas of the bursting through a bore 7a. In this case, a rotation driving unit 1c, engaged through a steel ball 4, is turned by the spiral grove 3b of a rotation guide 3, fitted into and fixed to the second inner tube unit 6b of a breech ring 6 when the piston is retreated. As a result, the opening 1a is rotated and, therefore, the injected fuel becomes rotating jet stream and is diffused widely into the combustion chamber 6c whereby the fuel is bursted. | ||||||
| 65 | Impulsively supplying device for high pressure gas | JP11048888 | 1988-05-09 | JPH01281400A | 1989-11-13 | IWATA ITSU |
| PURPOSE:To provide an impulsively supplying device for high pressure gas of which handling is facilitated and of which safety is high by a method wherein a rupture plate is explosively opened with a combustion gas pressure generated by an explosive combustion of combustion mixture gas and the combustion gas pressure is applied to a pressure receiving part of a device connected to the opening. CONSTITUTION:In a life saving rope injecting device, combustible mixture gas is filled in a pressure-proof container 1. While a burret 34 is filled in an injection cylinder 31, the combustible mixture gas is ignited by an igniter 6. With this ignition, the combustible mixture gas filled in the pressure-proof container 1 is explosively burst to break a breaking plate 2. With this breaking, the high pressure combustion gas within the pressure-proof container 1 is injected from the opening into the injection cylinder 31. The gas may act against the injection cylinder 31 to project the burret 34. The life saving rope 35 resiliently connected through an injection of the burret 34 can be expanded. Accordingly, it is possible to use it in place of the conventional type of energy source of powder and hydraulic oil and the like and the device can easily be handled. | ||||||
| 66 | JPS6119920B2 - | JP6801377 | 1977-06-10 | JPS6119920B2 | 1986-05-20 | MERUIN JON BURUMAN; ARUFURETSUDO RATSUPU GURAHAMU |
| 67 | Two-element propellant gun and discharging method thereof | JP10947785 | 1985-05-23 | JPS614000A | 1986-01-09 | ROBAATO ESU GURIFUINGU; DEIBITSUDO DABURIYU SARIBAN |
| 68 | Regenerated injection liquid propellant gun structure | JP7362285 | 1985-04-09 | JPS60251396A | 1985-12-12 | MAGOON INDER KUMAR |
| 69 | Direct jet regeneration type liquid propellant gun structure | JP23048884 | 1984-11-02 | JPS60132066A | 1985-07-13 | ROBAATO YUUGEN MEIYA; INDAA KUMAA MAGUUN; HAABAATO JIEI UESUTO |
| 70 | JPS6027918B2 - | JP6801577 | 1977-06-10 | JPS6027918B2 | 1985-07-02 | DAGURASU PUREI TASHI; ARURETSUDO RATSUPU GURAHAMU |
| 71 | JPS5918589B1 - | JP5386672 | 1972-06-01 | JPS5918589B1 | 1984-04-27 | TASSIE DOUGLAS P |
| 72 | Free piston generator | JP5148282 | 1982-03-31 | JPS57173366A | 1982-10-25 | ROJIE BUARON |
| 73 | Gun employing regenerative liquid propelling agent | JP3140681 | 1981-03-06 | JPS5714199A | 1982-01-25 | ROBAATO YUUJIN MEIYAA |
| 74 | Gun | JP6801377 | 1977-06-10 | JPS532000A | 1978-01-10 | MERUBUIN JIYON BURUMAN; ARUFURETSUDO RATSUPU GURAHAMU |
| 75 | JPS4852022A - | JP10725172 | 1972-10-27 | JPS4852022A | 1973-07-21 | |
| 76 | LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF | EP14721639.4 | 2014-03-14 | EP2969773B1 | 2018-05-30 | PALMER, Miles R.; BROWN, JR., Glenn William |
| 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. | ||||||
| 77 | PROJECTILE PROPULSION SYSTEM | EP09816631.7 | 2009-06-02 | EP2307846B1 | 2016-05-04 | RIGGS, Jeffrey L.; OLEYNIK, Vladislav; BOROVIKOV, Valery; ALBUL, Gennadiy |
| 78 | RAM ACCELERATOR SYSTEM | EP14770528.9 | 2014-01-21 | EP2971431A1 | 2016-01-20 | RUSSEL, Mark, C. |
| 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. | ||||||
| 79 | PROJECTILE PROPULSION SYSTEM | EP09816631 | 2009-06-02 | EP2307846A4 | 2013-12-25 | 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. | ||||||
| 80 | Monopropellant reactor system and operating method for a reactor system | EP04252759.8 | 2004-05-12 | EP1477663A2 | 2004-11-17 | Berg, Gerald R.; Mueller, Donn C.; Parish, Mark W. |
An apparatus and method are provided for decomposition of a propellant (24). The propellant (24) includes an ionic salt and an additional fuel. Means (60) are provided for decomposing a major portion of the ionic salt. Means (48) are provided for combusting the additional fuel and decomposition products of the ionic salt. |
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