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公开(公告)号：US07306189B2
公开(公告)日：2007-12-11
申请号：US11609268
申请日：2006-12-11
申请人： Gordon A. Dressler
发明人： Gordon A. Dressler
IPC分类号： B64G1/40
CPC分类号： F03H1/0012 , B64G1/405
摘要： A system and a method for an ambient atmosphere ion thruster having a pair of permeable electrical members for accelerating ambient atmosphere ions which enter the thruster due to a craft's relative velocity. Neutral ambient atmosphere molecules in the intake mass flux may also be ionized and subsequently accelerated by the pair of permeable electrical members. Acceleration of any entering mass comprises an exhaust mass flux which then produces a net thrust. Such net thrust is then vectored by configuring and orienting the thrusters for imparting axial and lateral accelerations as well as pitch, yaw, and roll controls. The present invention is operational in proximity to any celestial body having a sensible atmosphere during a portion of the free trajectory or during orbiting at altitude. Useful net thrust is thereby produced without need for carrying reaction mass onboard a spacecraft.
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公开(公告)号：US06185927B1
公开(公告)日：2001-02-13
申请号：US08995563
申请日：1997-12-22
IPC分类号： F02K952
CPC分类号： F02K9/52
摘要： A tripropellant coaxial pintle injector for a rocket engine which enables smooth transitioning between two types of propellants that are adapted to be alternatively mixed with a third type of propellant in a combustion chamber of a rocket engine. The tripropellant coaxial injector includes a pintle for expelling a first propellant into a combustion chamber in a generally radial direction and two or more concentric metering sleeves which define orifices for expelling two or more different propellants into the combustion chamber in an axial direction thus, such a configuration allows for alternative mixing of two propellants with a third propellant in the combustion chamber of a rocket engine.
摘要翻译： 一种用于火箭发动机的三介质同轴枢轴喷射器，其能够在适合于与火箭发动机的燃烧室中的第三类型推进剂交替混合的两种类型的推进剂之间平稳过渡。 所述三介质同轴喷射器包括用于将第一推进剂沿大体径向排出到燃烧室中的枢栓和两个或更多个同心计量套筒，所述两个或更多个同心计量套筒限定用于沿轴向排出两个或更多个不同推进剂进入燃烧室的孔， 配置允许两个推进剂与火箭发动机的燃烧室中的第三推进剂的混合。
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公开(公告)号：US07270300B2
公开(公告)日：2007-09-18
申请号：US10698847
申请日：2003-10-30
申请人： Gordon A. Dressler
发明人： Gordon A. Dressler
IPC分类号： B64G1/40
CPC分类号： F03H1/0012 , B64G1/405
摘要： A system and a method for an ambient atmosphere ion thruster having a pair of permeable electrical members for accelerating ambient atmosphere ions which enter the thruster due to a craft's relative velocity. Neutral ambient atmosphere molecules in the intake mass flux may also be ionized and subsequently accelerated by the pair of permeable electrical members. Acceleration of any entering mass comprises an exhaust mass flux which then produces a net thrust. Such net thrust is then vectored by configuring and orienting the thrusters for imparting axial and lateral accelerations as well as pitch, yaw, and roll controls. The present invention is operational in proximity to any celestial body having a sensible atmosphere during a portion of the free trajectory or during orbiting at altitude. Useful net thrust is thereby produced without need for carrying reaction mass onboard a spacecraft.
摘要翻译： 一种用于环境大气离子推进器的系统和方法，具有一对可渗透的电气构件，用于加速环境大气中的离子，这些离子由于工艺的相对速度而进入推进器。 进气质量通量中的中性环境大气分子也可被离子化，并随后通过一对可渗透的电气部件加速。 任何进入质量块的加速度包括排气质量通量，然后产生净推力。 然后通过配置和定向推进器以赋予轴向和横向加速度以及俯仰，偏转和滚动控制，这样的净推力被定向。 在自由轨迹的一部分期间或在高度轨道运动期间，本发明在任何具有敏感气氛的天体附近操作。 由此产生有用的净推力，而不需要在航天器上携带反作用物质。
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公开(公告)号：US06964154B1
公开(公告)日：2005-11-15
申请号：US10390253
申请日：2003-03-11
CPC分类号： F02K9/80 , F02K9/56 , F02K9/766 , F02K9/805 , F02K9/97 , F05D2240/1281 , F05D2240/40
摘要： A rocket engine assembly is provided for a vertically launched rocket vehicle. A rocket engine housing of the assembly includes two or more combustion chambers each including an outlet end defining a sonic throat area. A propellant supply for the combustion chambers includes a throttling injector, associated with each of the combustion chambers and located opposite to sonic throat area, which injects the propellant into the associated combustion chamber. A modulator, which may form part of the injector, and which is controlled by a controller, modulates the flow rate of the propellant to the combustion chambers so that the chambers provide a vectorable net thrust. An expansion nozzle or body located downstream of the throat area provides expansion of the combustion gases produced by the combustion chambers so as to increase the net thrust.
摘要翻译： 为垂直发射的火箭车提供火箭发动机总成。 组件的火箭发动机壳体包括两个或更多个燃烧室，每个燃烧室包括限定声音喉部区域的出口端。 用于燃烧室的推进剂供应包括与每个燃烧室相关并且与声音喉部区域相对定位的节流喷射器，其将推进剂喷射到相关联的燃烧室中。 可以形成喷射器的一部分并且由控制器控制的调制器调节推进剂到燃烧室的流速，使得腔室提供可向量的净推力。 位于喉部区域下游的膨胀喷嘴或本体提供由燃烧室产生的燃烧气体的膨胀，以增加净推力。
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公开(公告)号：US06591603B2
公开(公告)日：2003-07-15
申请号：US09802002
申请日：2001-03-08
IPC分类号： B64C1502
摘要： The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A propellant injector (20) is in fluid communication between a propellant line and an inside periphery of the combustion chamber injector end (14). A nozzle throat (18) is formed at the nozzle end (14) of the combustion chamber (12). A nozzle exit cone (22) extends outwardly from the nozzle throat (18). A plug support (30) is coupled between a nozzle plug (28) and the propellant injector (20). The nozzle plug (28) aerodynamically self-compensates for changes in ambient backpressure at the nozzle exit cone (22) such that the nozzle thrust coefficient is maximized for any ambient backpressure.
摘要翻译： 本发明提供了一种火箭发动机（10），其对于改变环境背压的喷嘴推力系数进行自补偿。 火箭发动机（10）包括具有喷射器端（14）和喷嘴端（16）的燃烧室（12）。 推进剂喷射器（20）在推进剂管线和燃烧室喷射器端部（14）的内周边之间流体连通。 在燃烧室（12）的喷嘴端（14）处形成喷嘴喉（18）。 喷嘴出口锥体（22）从喷嘴喉部（18）向外延伸。 插头支撑件（30）联接在喷嘴塞（28）和推进剂喷射器（20）之间。 喷嘴塞（28）在空气动力学上自我补偿喷嘴出口锥体（22）处的环境背压的变化，使得喷嘴推力系数对于任何环境背压最大化。
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公开(公告)号：US6052987A
公开(公告)日：2000-04-25
申请号：US970915
申请日：1997-11-14
申请人： Gordon A. Dressler
发明人： Gordon A. Dressler
CPC分类号： F02K9/64 , F05D2260/205
摘要： A space craft's rocket engines are cooled by a recirculating cooling system containing a non-propellant coolant fluid, such as water and/or ethylene glycol. With that recirculating cooling system to maintain the rocket engine combustion chamber at a lower temperature, spacecraft rocket engines may be constructed less expensively and can operate with greater safety by employing the more common metals in their construction. The cooling system also provides an easy means to warm and/or vaporize a propellant.
摘要翻译： 太空飞船的火箭发动机通过包含非推进剂冷却剂流体（例如水和/或乙二醇）的循环冷却系统来冷却。 利用该再循环冷却系统将火箭发动机燃烧室维持在较低的温度，宇宙飞船火箭发动机的建造成本较低，并且可以通过在其结构中采用更常见的金属在更大的安全性下运行。 冷却系统还提供了一种用于温热和/或蒸发推进剂的简单方法。
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