子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | ジェットエンジン、飛しょう体及びジェットエンジンの動作方法 | JP2014074491 | 2014-03-31 | JP6310302B2 | 2018-04-11 | 上野 祥彦; 古谷 正二郎 |
| 22 | 爆燃チャンバを含んだラムジェット及びそのラムジェットを搭載した飛行体 | JP2014510848 | 2012-05-09 | JP6165717B2 | 2017-07-19 | ファレンパン,フランソワ; ル ナウール,ブルーノ |
| 23 | 連続爆轟波エンジンおよびそのエンジンを搭載した航空体 | JP2014510849 | 2012-05-09 | JP6006785B2 | 2016-10-12 | ファレンパン,フランソワ |
| 24 | ノズル構造体およびノズル構造体の製造方法 | JP2014527208 | 2012-08-17 | JP2014528534A | 2014-10-27 | ティモシー・アール・コナーズ; プレストン・エー・ヘンネ; ドナルド・シー・ハウ |
| ノズル構造体が、排気ガスのプルームを生成するように構成された超音速ジェットエンジンで使用するために開示される。ノズル構造体は、後縁部を備えるノズルと、ノズルに一部配置されたプラグ本体とを備えているが、それらに限定されることはない。プラグ本体は、膨張面と、膨張面の下流の圧縮面とを備える。プラグ本体の突出部は、従来のプラグ本体の長さを超える長さで後縁部の下流に延出する。プラグ本体は、排気ガスを、ノズルの後縁部から流れ去る空気の自由流れと実質的に平行に流れるように形成するように構成され、また、排気ガスのプルームが、空気の自由流れを、プラグ本体の長手方向軸線と平行な方向に移動させるように等エントロピで転向させるように構成される。 | ||||||
| 25 | Propulsion system and propulsive force generating method | JP2005207933 | 2005-07-19 | JP2006046332A | 2006-02-16 | MINICK ALAN B; GOLDBERG BENJAMIN; KNAUER LARRY |
| PROBLEM TO BE SOLVED: To provide an improved method for creating a propulsive force. SOLUTION: A propulsion system 10 for creating a propulsive force, has a combustion chamber 12, a pair of electrodes 18, 20 within the combustion chamber, and a power supply 16 attached to the electrodes to create a high voltage field within an initiation zone of the combustion chamber, and injectors 26, 30 for introducing a propellant, preferably in atomized form, into a high voltage field for creating the propulsive force. In a preferred embodiment of the present invention, the propellant is hydrogen peroxide. In another embodiment of the present invention, a second propellant is introduced into the combustion chamber for increasing the propulsive force. COPYRIGHT: (C)2006,JPO&NCIPI | ||||||
| 26 | Detonation engine and flight vehicle equipped with the same | JP2004191793 | 2004-06-29 | JP2006009764A | 2006-01-12 | HIDA AKIHIRO; FUJIWARA TOSHITAKA; PIOTR WALANSKI |
| <P>PROBLEM TO BE SOLVED: To provide a detonation engine simplifying structure of whole engine and providing continuous output. <P>SOLUTION: This detonation engine 10 producing propulsion force by generating detonation wave is provided with a swirl generation means 13 generating swirl of mixture of atmospheric air and fuel or mixture of oxygen and fuel around axial line, a detonation chamber 14 arranged in a downstream of the swirl generation device 13 and formed in a ring shape extending in a radial direction and connecting in a circumference direction and burning mixture of which swirl is generated by the swirl generation means 13 continuously in a circumference direction to generate detonation wave and sucking air from a radial direction inside and discharging air to a radial direction outside, and a nozzle 15 connected to the detonation chamber 14 and jetting high temperature and high pressure combustion gas generated by detonation wave made flow out of the detonation chamber 14 backward while the same is being expanded to convert the same to propulsion force. <P>COPYRIGHT: (C)2006,JPO&NCIPI | ||||||
| 27 | Ramjet including a detonation chamber and aircraft comprising such a ramjet | US14116003 | 2012-05-09 | US09816463B2 | 2017-11-14 | François Falempin; Bruno Le Naour |
| The invention relates to a ramjet including a detonation chamber and an aircraft comprising such a ramjet. According to the invention, the ramjet (S1) comprises an annular detonation chamber (2) having a continuous detonation wave and fuel injection means (6) for continuously injecting fuel (F2) directly into the chamber (2) just downstream of an air injection base (3). The fuel (F2) and the air (F1) are injected separately into the detonation chamber (2) in a permanent manner throughout the operation of the ramjet (S1). | ||||||
| 28 | Continuous detonation wave engine and aircraft provided with such an engine | US14115530 | 2012-05-09 | US09599065B2 | 2017-03-21 | François Falempin |
| The invention relates to a continuous detonation wave engine and aircraft provided with such an engine. The continuous detonation wave engine (1) operates with a detonation mixture of fuel and oxidant and includes, in particular, a detonation chamber (3) comprising an injection base (10), the length of which is defined along an open line (17), such as to form a detonation chamber (3) having an elongate form in a transverse plane, as well as an injection system (4) arranged such as to inject the fuel/oxidant mixture into the detonation chamber (3) at at least one segment of the injection base (10). | ||||||
| 29 | Air inlet arrangement and method of making the same | US13541482 | 2012-07-03 | US09353704B2 | 2016-05-31 | Timothy R. Conners; Preston A. Henne; Donald C. Howe |
| An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate. | ||||||
| 30 | SYSTEM FOR THE RECOVERY, STORAGE AND UTILISATION OF ATMOSPHERIC GAS FOR USE AS A VEHICLE PROPELLANT | US13876547 | 2011-07-27 | US20130192194A1 | 2013-08-01 | Jaime Simon Reed |
| A system for the recovery and management of atmospheric gas is disclosed, such as for use as a vehicle propellant in a vehicle propulsion system. The system can include a compressor configured to compress atmospheric gas and first and second storage tanks configured to store liquefied atmospheric gas from the compressor. The second storage tank can have a heater operable to heat liquefied atmospheric gas therein to convert it to a high pressure gas. The second storage tank includes an outlet duct fluidly coupled to the first storage tank for supplying high pressure gas to the first storage tank. | ||||||
| 31 | Magnetic gas engine and method of extracting work | US11362928 | 2006-02-28 | US07602096B2 | 2009-10-13 | Patrick Craig Muldoon |
| The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject matter compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field and can also be extracted in the form of mechanical work. | ||||||
| 32 | Energetic detonation propulsion | US10895777 | 2004-07-21 | US20060016168A1 | 2006-01-26 | Alan Minick; Benjamin Goldberg; Larry Knauer |
| A propulsion system for creating a propulsive force has a combustion chamber, a pair of electrodes within the combustion chamber and a power supply attached to the electrodes to create a high voltage field within an initiation zone of the combustion chamber, and an injector for introducing a propellant, preferably in atomized form, into the high voltage field for creating the propulsive force. In a preferred embodiment of the present invention, the propellant is hydrogen peroxide. In another embodiment of the present invention, a second propellant is introduced into the combustion chamber for increasing the propulsive force. | ||||||
| 33 | Shaped charge engine | US10687452 | 2003-10-15 | US20040134184A1 | 2004-07-15 | Ronnie J. Duncan |
| A shaped charge engine includes multiple blast forming chambers, each chamber having a primary convergence zone that is variably shape to alter the shape of the exhaust gas emanating from each chamber. Thereafter, each chamber's variably shaped exhaust is merged at a secondary convergence zone into a shape further modified to alter the thrust characteristics of the exiting exhaust gases from the shaped charged engine. | ||||||
| 34 | Apparatus powered using laser supplied energy | US265385 | 1994-06-24 | US5542247A | 1996-08-06 | Boyd B. Bushman |
| A method and apparatus are providing for converting energy into thrust, and directing the thrust to move an object. The apparatus includes a chamber having air disposed therein, a pulsed laser for converting an energy source into light pulses, and a lens for receiving the light pulses and directing the light pulses toward a focal point within the chamber. Each light pulse converges in a region which is proximate to the focal point and causes molecules within the air which are at the region to disassociate. Disassociation of the molecules generates pressure waves which provide thrust for powering the object to move. | ||||||
| 35 | Electrical propulsion unit for use in rarefied atmospheres | US37774564 | 1964-06-24 | US3304717A | 1967-02-21 | HENRI GUTTON; JOSEPH FOURNET MAURICE PIERRE |
| 36 | Method of producing energy in a reaction engine | US43122565 | 1965-02-08 | US3217491A | 1965-11-16 | DIEHL THOMAS N |
| 37 | Aerodynamic propulsion unit | US4290660 | 1960-07-14 | US3047251A | 1962-07-31 | LEWIS WILLIAM L |
| 38 | Aircraft propulsion mechanism | US57401645 | 1945-01-22 | US2514749A | 1950-07-11 | DOBBINS DAVID T |
| 39 | Utilization of gas flow | US56955344 | 1944-12-23 | US2486429A | 1949-11-01 | GEORGES MONNET |
| 40 | Jet propulsion system for aircraft | US53254644 | 1944-04-24 | US2444318A | 1948-06-29 | WARNER DOUGLAS K |
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