公开(公告)号：US06766638B1

公开(公告)日：2004-07-27

申请号：US10048115

申请日：2002-01-28

申请人： John R Tilston ,  Wai S Cheung

发明人： John R Tilston ,  Wai S Cheung

IPC分类号： C06D504

CPC分类号： F02K9/74 ,  F02K9/68 ,  F05D2250/82

摘要： A micro air vehicle is propelled by a bipropellant micro engine supplied with hydrogen peroxide and a hydrocarbon fuel. The hydrogen peroxide is decomposed to produce steam and oxygen at high temperature and the hydrocarbon fuel is burnt within a combustion chamber with oxygen produced from such decomposition. Products of such decomposition and combustion are exited through a nozzle to produce thrust. In a preferred embodiment there is also a ducted turbofan located downstream of the nozzle exit.

摘要翻译： 微型空气载体由提供有过氧化氢和烃燃料的双组元推进剂微型发动机推动。 过氧化氢在高温下分解产生蒸汽和氧气，并且烃燃料在燃烧室内被燃烧，其中由这种分解产生的氧气。 这种分解和燃烧的产物通过喷嘴排出以产生推力。 在优选实施例中，还存在位于喷嘴出口下游的导管涡轮风扇。

公开(公告)号：US06314718B1

公开(公告)日：2001-11-13

申请号：US09837819

申请日：2001-04-17

申请人： Steven J. Schneider

发明人： Steven J. Schneider

IPC分类号： C06D504

CPC分类号： C06B47/06 ,  C06D5/08

摘要： A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decomposing element (26) of an ACS thruster. The ACS decomposing element is operative to decompose the reduced toxicity propellant into hot propulsive gases. In addition the system includes suitable valves and conduits (18) for supplying the reduced toxicity propellant to an axial decomposing element (24) of the axial thruster. The axial decomposing element is operative to decompose the reduced toxicity propellant into hot gases. The system further includes suitable valves and conduits (20) for supplying a second propellant (12) to a combustion chamber (28) of the axial thruster, whereby the hot gases and the second propellant auto-ignite and begin the combustion process for producing thrust.

摘要翻译： 一种减毒的燃料卫星推进系统，包括用于在轴向级推进器（14）和ACS类推进器（16）中消耗的减少毒性的推进剂供应（10）。 该系统包括用于向ACS推进器的ACS分解元件（26）供应减毒的推进剂的合适的阀和管道（22）。 ACS分解元件用于将降低毒性的推进剂分解成热推进气体。 此外，该系统包括用于将减毒的推进剂供应到轴向推进器的轴向分解元件（24）的合适的阀和管道（18）。 轴向分解元件用于将减毒的推进剂分解成热气体。 系统还包括用于将第二推进剂（12）供应到轴向推进器的燃烧室（28）的合适的阀和导管（20），由此热气体和第二推进剂自动点燃并开始燃烧过程以产生推力 。

公开(公告)号：US06272846B1

公开(公告)日：2001-08-14

申请号：US09291883

申请日：1999-04-14

申请人： Steven J. Schneider

发明人： Steven J. Schneider

IPC分类号： C06D504

CPC分类号： C06B47/06 ,  C06D5/08

摘要： A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decomposing element (26) of an ACS thruster. The ACS decomposing element is operative to decompose the reduced toxicity propellant into hot propulsive gases. In addition the system includes suitable valves and conduits (18) for supplying the reduced toxicity propellant to an axial decomposing element (24) of the axial thruster. The axial decomposing element is operative to decompose the reduced toxicity propellant into hot gases. The system further includes suitable valves and conduits (20) for supplying a second propellant (12) to a combustion chamber (28) of the axial thruster, whereby the hot gases and the second propellant auto-ignite and begin the combustion process for producing thrust.

摘要翻译： 一种减毒的燃料卫星推进系统，包括用于在轴向级推进器（14）和ACS类推进器（16）中消耗的减少毒性的推进剂供应（10）。 该系统包括用于向ACS推进器的ACS分解元件（26）供应减毒的推进剂的合适的阀和管道（22）。 ACS分解元件用于将降低毒性的推进剂分解成热推进气体。 此外，该系统包括用于将减毒的推进剂供应到轴向推进器的轴向分解元件（24）的合适的阀和管道（18）。 轴向分解元件用于将减毒的推进剂分解成热气体。 系统还包括用于将第二推进剂（12）供应到轴向推进器的燃烧室（28）的合适的阀和导管（20），由此热气体和第二推进剂自动点燃并开始燃烧过程以产生推力 。

公开(公告)号：US06519928B2

公开(公告)日：2003-02-18

申请号：US09843155

申请日：2001-04-26

申请人： German Munding ,  Wolfgang Müller ,  Joachim Reinecke ,  Peter Gleich

发明人： German Munding ,  Wolfgang Müller ,  Joachim Reinecke ,  Peter Gleich

IPC分类号： C06D504

CPC分类号： F42B10/66

摘要： A process for the production of a transverse thrust in a flying object in which a defined quantity of a monergol propellent substance is introduced into a propulsion unit, which is arranged transversely relative to a longitudinal axis of the flying object to produce a thrust transverse to the longitudinal axis of the flying object. The propulsion unit has a combustion chamber, a supersonic nozzle connected to the combustion chamber and a source of heat to combust the propellant substance and produce the desired thrust for a prescribed time. The monergol propellent substance, introduced tangentially into the combustion chamber to form a film of the propellent substance on an inside surface of a wall of the combustion chamber; and the film of propellent substance on the wall is combusted by a pyrotechnic source of heat arranged in the wall of the combustion chamber in the vicinity of a throat of the supersonic nozzle to produce hot gases by the combustion of the propellant substance and transverse thrust in the supersonic nozzle. An automatically operated non-return valve without moving parts prevents backflow of combustion gases to the inlet valve.

摘要翻译： 一种用于在飞行物体中产生横向推力的方法，其中将限定量的芒果醇推进剂物质引入到推进单元中，该推进单元相对于飞行物体的纵向轴线横向布置以产生横向于 飞行物体的纵轴。 推进单元具有燃烧室，连接到燃烧室的超音速喷嘴和用于燃烧推进剂物质并产生所需推力达规定时间的热源。 所述芒果型推进剂物质切向地引入燃烧室以在燃烧室的壁的内表面上形成推进剂物质的膜; 并且壁上的推进物质膜被布置在燃烧室壁中的烟火源在超音速喷嘴的喉部附近燃烧，以通过推进剂物质的燃烧产生热气体和横向推力 超音速喷嘴。 没有移动部件的自动操作的止回阀防止燃烧气体回流到入口阀。

公开(公告)号：US06378291B1

公开(公告)日：2002-04-30

申请号：US09837822

申请日：2001-04-17

申请人： Steven J. Schneider

发明人： Steven J. Schneider

IPC分类号： C06D504

CPC分类号： C06B47/06 ,  C06D5/08

摘要： A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decomposing element (26) of an ACS thruster. The ACS decomposing element is operative to decompose the reduced toxicity propellant into hot propulsive gases. In addition the system includes suitable valves and conduits (18) for supplying the reduced toxicity propellant to an axial decomposing element (24) of the axial thruster. The axial decomposing element is operative to decompose the reduced toxicity propellant into hot gases. The system further includes suitable valves and conduits (20) for supplying a second propellant (12) to a combustion chamber (28) of the axial thruster, whereby the hot gases and the second propellant auto-ignite and begin the combustion process for producing thrust.

摘要翻译： 一种减毒的燃料卫星推进系统，包括用于在轴向级推进器（14）和ACS类推进器（16）中消耗的减少毒性的推进剂供应（10）。 该系统包括用于向ACS推进器的ACS分解元件（26）供应减毒的推进剂的合适的阀和管道（22）。 ACS分解元件用于将降低毒性的推进剂分解成热推进气体。 此外，该系统包括用于将减毒的推进剂供应到轴向推进器的轴向分解元件（24）的合适的阀和管道（18）。 轴向分解元件用于将减毒的推进剂分解成热气体。 系统还包括用于将第二推进剂（12）供应到轴向推进器的燃烧室（28）的合适的阀和导管（20），由此热气体和第二推进剂自动点燃并开始燃烧过程以产生推力 。