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1. 发明申请

WO2013025625A1 TERRESTRIAL POWER AND PROPULSION FROM NUCLEAR OR RENEWABLE METAL FUELS WITH MAGNETOHYDRODYNAMICS 审中-公开
标题翻译：来自核磁体或可再生能源的金属燃料的地面动力和推进
公开(公告)号：WO2013025625A1
公开(公告)日：2013-02-21
申请号：PCT/US2012/050617
申请日：2012-08-13
申请人： ZAUDERER, Bert
发明人： ZAUDERER, Bert
IPC分类号： F02G3/00
CPC分类号： F02K9/24 , F02K9/70 , G21C1/07 , H02K44/08
摘要： A propulsion system is disclosed that uses metal fuel particles heated to a range from 3000°K to 6000°K by reaction with oxygen in air inside a cyclone combustor to form metal oxides that are retained and removed from the combustor for re-conversion to metal, while nitrogen in the air is heated to the temperatures that on supersonic exhaust propels 50,000 ton monohull ships to from 50 to 100knots. The ship can accelerate by electromagnetic force from a MHD generator-accelerator rendered electrically conducting by alkali metal seed injection into the gas. Also disclosed are 10 MW to 1000 MW Closed Cycle MHD power plants fired by natural gas into a top half of a falling pebble bed heat exchanger that transfers 2000°K to 3000°K heat to a noble or diatomic gas in a bottom half of the exchanger that on exit is seeded with an alkali metal rendering the gas conducting.
摘要翻译：公开了一种推进系统，其使用通过与旋风分离器燃烧室内的空气中的氧反应而加热到3000°K至6000°K范围内的金属燃料颗粒，以形成金属氧化物，其被从燃烧器中保留和移除以重新转化为金属而空气中的氮气则被加热到超音速排气口将5万吨单体船的行驶速度从50升到100千克的温度。该船可以通过电磁力从由金属种子注入气体导致的MHD发生器加速器加速。还公开了将10兆瓦至1000兆瓦的封闭循环MHD发电厂由天然气发射到落下的卵石床热交换器的上半部分，该热交换器将2000°K转换为3000°K的热量，使其在下半部分的高温或双原子气体交换器在出口处接种碱性金属，使气体导通。

2. 发明申请

WO2011131493A3 AIR BREATHING REACTION PROPULSION ENGINE 审中-公开
标题翻译：空气呼吸反应推进发动机
公开(公告)号：WO2011131493A3
公开(公告)日：2012-03-08
申请号：PCT/EP2011055443
申请日：2011-04-07
申请人： ROLLS ROYCE PLC , ROWE ARTHUR L , MASON SAMUEL ALEXANDER
发明人： ROWE ARTHUR L , MASON SAMUEL ALEXANDER
IPC分类号： F02K3/08 , F02K3/02 , F02K7/08 , F02K9/08 , F02K9/70 , F02K9/72 , F02K9/95
CPC分类号： F02K9/95 , F02K3/02 , F02K3/08 , F02K7/08 , F02K9/08 , F02K9/70 , F02K9/72
摘要： An air breathing reaction propulsion engine has: an open-ended cylindrical combustion chamber having an upstream end and a downstream end, an exhaust propulsion nozzle located at the downstream end of the combustion chamber, and an ejector system located at the upstream end of the combustion chamber. The ejector system comprises an open-ended cylindrical structure having an upstream end through which air is drawn into its interior, and a downstream end in open communication with the combustion chamber. The engine further has a fuel supply system comprising a fuel injector located within the ejector system, a source of pressurised fluid fuel, and a fuel heating coil disposed around the wall of the cylindrical combustion chamber through which the pressurised fluid fuel is supplied to the fuel injector. Under normal running operation, the pressurised fluid fuel is heated in the coil, and the heated fuel is expelled at the fuel injector into the cylindrical structure thereby establishing a pressure differential which draws air into the ejector system to form a combustible fuel/air mixture which is supplied to the combustion chamber. The fuel supply system further comprises a charge-carrying section adapted to carry a charge of a solid fuel which is combusted during start-up operation to produce combustion products that pre-heat the heating coil.
摘要翻译：空气呼吸反应推进发动机具有：具有上游端和下游端的开放式圆柱形燃烧室，位于燃烧室下游端的排气推进喷嘴和位于燃烧上游端的喷射器系统室。喷射器系统包括开口的圆柱形结构，其具有上游端，空气被吸入其内部，下游端与燃烧室开放连通。发动机还具有燃料供给系统，该燃料供给系统包括位于喷射器系统内的燃料喷射器，加压流体燃料源和设置在圆筒形燃烧室壁周围的燃料加热线圈，加压流体燃料通过该燃料加热线圈供应到燃料注射器。在正常运行操作下，加压流体燃料在线圈中被加热，并且加热的燃料在燃料喷射器处被排出到圆柱形结构中，从而形成压力差，其将空气吸入喷射器系统以形成可燃燃料/空气混合物，被供应到燃烧室。燃料供给系统还包括充电部分，其适于承载在启动操作期间燃烧的固体燃料的电荷，以产生对加热线圈进行预热的燃烧产物。

3. 发明申请

WO0040919B1 IMPROVED PROPULSION SYSTEM 审中-公开
标题翻译：改进的推进系统
公开(公告)号：WO0040919B1
公开(公告)日：2000-08-17
申请号：PCT/US9930831
申请日：1999-12-27
申请人： ALLIANT TECHSYSTEMS INC
发明人： GLASSER ALAN Z
IPC分类号： F02K9/70 , F41A1/00 , F42B5/16
CPC分类号： F42B5/181 , F02K9/70 , F41A1/00 , F42B5/16
摘要： A propellant burning system and method useful in a rocket motor or projectile firing device burns a continuous main propellant grain (122) of relatively soft propellant material selected from uncatalyzed or partially catalyzed propellants. A separating device (112) divides the propellant grain into a large number of fragments of high-surface area during the burn and an activation mechanism (120, 124, 126) for causing said separating device to operate on the main propellant grain and to ignite and control the burning thereof.
摘要翻译：用于火箭发动机或射弹发射装置的推进剂燃烧系统和方法燃烧选自未催化或部分催化的推进剂的相对较软的推进剂材料的连续主推进剂颗粒（122）。在燃烧过程中，分离装置（112）将推进剂颗粒分成大量高表面积的碎片和激活机构（120,124,126），用于使所述分离装置在主推进剂颗粒上操作并点燃并控制其燃烧。

4. 发明申请

WO2013070292A2 NUCLEAR ENERGY, METAL FUEL, H2 / O2 FROM H2O, WITH MHD POWER AND PROPULSION FOR ONE MONTH ASTRONAUT ROCKET VOYAGES TO MARS 审中-公开
标题翻译：核能，金属燃料，H 2 / O 2从H 2 O，具有MHD功率和推进用于一个月的ASTRONAUT ROCKET VOYAGES到MARS
公开(公告)号：WO2013070292A2
公开(公告)日：2013-05-16
申请号：PCT/US2012/050621
申请日：2012-08-13
申请人： ZAUDERER, Bert
发明人： ZAUDERER, Bert
IPC分类号： G21C1/07 , C01F3/02 , C01B
CPC分类号： F02K9/24 , F02K9/70 , G21C1/07 , H02K44/08

5. 发明申请

WO2011131493A2 AIR BREATHING REACTION PROPULSION ENGINE 审中-公开
标题翻译：空气呼吸反应推进发动机
公开(公告)号：WO2011131493A2
公开(公告)日：2011-10-27
申请号：PCT/EP2011/055443
申请日：2011-04-07
申请人： ROLLS-ROYCE plc , ROWE, Arthur L , MASON, Samuel Alexander
发明人： ROWE, Arthur L , MASON, Samuel Alexander
IPC分类号： F02K7/08
CPC分类号： F02K9/95 , F02K3/02 , F02K3/08 , F02K7/08 , F02K9/08 , F02K9/70 , F02K9/72
摘要： An air breathing reaction propulsion engine has: an open-ended cylindrical combustion chamber having an upstream end and a downstream end, an exhaust propulsion nozzle located at the downstream end of the combustion chamber, and an ejector system located at the upstream end of the combustion chamber. The ejector system comprises an open-ended cylindrical structure having an upstream end through which air is drawn into its interior, and a downstream end in open communication with the combustion chamber. The engine further has a fuel supply system comprising a fuel injector located within the ejector system, a source of pressurised fluid fuel, and a fuel heating coil disposed around the wall of the cylindrical combustion chamber through which the pressurised fluid fuel is supplied to the fuel injector. Under normal running operation, the pressurised fluid fuel is heated in the coil, and the heated fuel is expelled at the fuel injector into the cylindrical structure thereby establishing a pressure differential which draws air into the ejector system to form a combustible fuel/air mixture which is supplied to the combustion chamber. The fuel supply system further comprises a charge-carrying section adapted to carry a charge of a solid fuel which is combusted during start-up operation to produce combustion products that pre-heat the heating coil.
摘要翻译：空气呼吸反应推进发动机具有：具有上游端和下游端的开放式圆柱形燃烧室，位于燃烧室下游端的排气推进喷嘴和位于燃烧上游端的喷射器系统室。喷射器系统包括开口的圆柱形结构，其具有上游端，空气被吸入其内部，下游端与燃烧室开放连通。发动机还具有燃料供给系统，其包括位于喷射器系统内的燃料喷射器，加压流体燃料源和设置在圆筒形燃烧室壁周围的燃料加热线圈，加压流体燃料通过该燃料加热线圈供应到燃料注射器。在正常运行操作下，加压流体燃料在线圈中被加热，并且加热的燃料在燃料喷射器处被排出到圆柱形结构中，从而形成压力差，其将空气吸入喷射器系统以形成可燃燃料/空气混合物，被供应到燃烧室。燃料供给系统还包括充电部分，其适于承载在启动操作期间燃烧的固体燃料的电荷，以产生对加热线圈进行预热的燃烧产物。

6. 发明申请

WO2007003270A1 ANTRIEBSVORRICHTUNG AUF BASIS GELFÖRMIGEN TREIBSTOFFS UND VERFAHREN ZUR TREIBSTOFF-FÖRDERUNG 审中-公开
标题翻译：驱动装置基于凝胶型推进剂AND METHOD FOR FUEL促进
公开(公告)号：WO2007003270A1
公开(公告)日：2007-01-11
申请号：PCT/EP2006/005925
申请日：2006-06-21
申请人： DEUTSCHES ZENTRUM FÜR LUFT-UND RAUMFAHRT E.V. , CIEZKI, Helmut, Konrad , MADLENER, Klaus , HAIDN, Oskar
发明人： CIEZKI, Helmut, Konrad , MADLENER, Klaus , HAIDN, Oskar
IPC分类号： F02K9/44 , F02K9/70 , F02K9/72
CPC分类号： F02K9/72 , F02K9/44 , F02K9/70 , F05D2210/13 , F05D2260/20
摘要： Um eine Antriebsvorrichtung auf Basis gelförmigen Treibstoffs, insbesondere für einen Flugkörper, umfassend mindestens einen Tank für gelförmigen Treibstoff, eine Brennkammer und eine Zuführungseinrichtung von Treibstoff zur Brennkammer, bereitzustellen, welche einfach aufgebaut ist, wird vorgeschlagen, dass mindestens eine Strahlungsbeaufschlagungseinrichtung zur Beaufschlagung von gelförmigem Treibstoff mit elektromagnetischer Strahlung und/oder mindestens eine Heizeinrichtung zur Erwärmung von gelförmigem Treibstoff vorgesehen ist, um das Fließverhalten zu verbessern.
摘要翻译：凝胶型推进剂的基础上，特别是用于导弹上的驱动装置，其包括以提供凝胶型燃料，燃烧器和燃料到燃烧室中，其结构简单的馈电的至少一个槽，所以建议至少一个辐射的凝胶型推进剂的冲击撞击设置有电磁辐射和/或用于凝胶型推进剂的加热至少一个加热装置，以改善流动特性。

7. 发明申请

WO0236955A8 METHOD AND DEVICE FOR A MULTIPLE STEP ROCKET 审中-公开
标题翻译：用于多个步骤的方法和装置
公开(公告)号：WO0236955A8
公开(公告)日：2005-11-10
申请号：PCT/SE0102381
申请日：2001-10-30
申请人： SAAB AB , NILSSON LARS , AX LARS
发明人： NILSSON LARS , AX LARS
IPC分类号： F02K9/08 , F02K9/32 , F02K9/70 , F02K9/76 , F02K9/95 , F02K9/97 , F42B15/36
CPC分类号： F42B15/36 , F02K9/08 , F02K9/32 , F02K9/70 , F02K9/76 , F02K9/763 , F02K9/95 , F02K9/978
摘要： The present invention relates to a method and an arrangement for, in multi-stage rockets (3) provided with a number of successively ignitable rocket engines (7, 13) arranged one in front of another in the flying direction of the rocket and joined together detachably with one another, each following rocket engine (13) in the ignition sequence depending, for its ignition, on being initiated after a preceding rocket engine (7) has been able to bun out, causing each preceding rocket engine (7) included in the ignition sequence to be jettisoned by virtue of the next engine having reached its working pressure. According to the invention, each preceding rocket engine is designed with a preferably conical guide part (11) which is directed forwards in the flying direction of the rocket and geometrically adapted to the exhaust nozzle (12) of the following rocket engine (13) and which, in the initial position, is fitted into said exhaust nozzle (12) and fixed in this position by means of at least one blocking part (15) which is deformable or capable of elastic recovery.
摘要翻译：本发明涉及一种多级火箭（3）中的方法和装置，该多级火箭（3）具有在火箭的飞行方向上一个在另一个前方排列并连接在一起的若干连续可点燃的火箭发动机（7,13）每个随后的火箭发动机（13）在点火顺序中依赖于其点火，在先前的火箭发动机（7）能够蹦出之后被启动，使得每个先前的火箭发动机（7）包括在由于下一个发动机已经达到其工作压力而要排出的点火顺序。根据本发明，每个先前的火箭发动机被设计成具有优选的圆锥形引导部分（11），其沿着火箭的飞行方向向前指向并几何地适应于随后的火箭发动机（13）的排气喷嘴（12）和其在初始位置被装配到所述排气喷嘴（12）中并且通过至少一个可变形或能够弹性恢复的阻挡部分（15）固定在该位置。

8. 发明申请

WO02036955A1 METHOD AND DEVICE FOR A MULTIPLE STEP ROCKET 审中-公开
标题翻译：用于多个步骤的方法和装置
公开(公告)号：WO02036955A1
公开(公告)日：2002-05-10
申请号：PCT/SE2001/002381
申请日：2001-10-30
IPC分类号： F02K9/08 , F02K9/32 , F02K9/70 , F02K9/76 , F02K9/95 , F02K9/97 , F42B15/36
CPC分类号： F42B15/36 , F02K9/08 , F02K9/32 , F02K9/70 , F02K9/76 , F02K9/763 , F02K9/95 , F02K9/978
摘要： The present invention relates to a method and an arrangement for, in multi-stage rockets (3) provided with a number of successively ignitable rocket engines (7, 13) arranged one in front of another in the flying direction of the rocket and joined together detachably with one another, each following rocket engine (13) in the ignition sequence depending, for its ignition, on being initiated after a preceding rocket engine (7) has been able to bun out, causing each preceding rocket engine (7) included in the ignition sequence to be jettisoned by virtue of the next engine having reached its working pressure. According to the invention, each preceding rocket engine is designed with a preferably conical guide part (11) which is directed forwards in the flying direction of the rocket and geometrically adapted to the exhaust nozzle (12) of the following rocket engine (13) and which, in the initial position, is fitted into said exhaust nozzle (12) and fixed in this position by means of at least one blocking part (15) which is deformable or capable of elastic recovery.
摘要翻译：本发明涉及一种多级火箭（3）中的方法和装置，该多级火箭（3）具有在火箭的飞行方向上一个在另一个前方排列并连接在一起的若干连续可点燃的火箭发动机（7,13）每个随后的火箭发动机（13）在点火顺序中依赖于其点火，在先前的火箭发动机（7）能够蹦出之后被启动，使得每个先前的火箭发动机（7）包括在由于下一个发动机已经达到其工作压力而要排出的点火顺序。根据本发明，每个先前的火箭发动机被设计成具有优选的圆锥形引导部分（11），其沿着火箭的飞行方向向前指向并几何地适应于随后的火箭发动机（13）的排气喷嘴（12）和其在初始位置被装配到所述排气喷嘴（12）中并且通过至少一个可变形或能够弹性恢复的阻挡部分（15）固定在该位置。

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