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1. 发明授权

US08689537B1 Micro-cavity discharge thruster (MCDT) 有权
标题翻译：微腔排气推进器（MCDT）
公开(公告)号：US08689537B1
公开(公告)日：2014-04-08
申请号：US12589182
申请日：2009-10-19
申请人： Rodney L. Burton , James Gary Eden , Sung-Jin Park , David L. Carroll
发明人： Rodney L. Burton , James Gary Eden , Sung-Jin Park , David L. Carroll
IPC分类号： F03H1/00 , H05H1/02
CPC分类号： H05H1/54
摘要： It is disclosed herein a breakthrough concept for in-space propulsion for future Air Force, NASA and commercial systems. The invention combines the fields of micro-electrical-mechanical (MEMs) devices, optical physics, and nonequilibrium plasmadynamics to reduce dramatically the size of electric thrusters by 1-2 orders of magnitude, which when coupled with electrodeless operation and high thruster efficiency, will enable scalable, low-cost, long-life distributable propulsion for control of microsats, nanosats, and space structures. The concept is scalable from power levels of 1 W to tens of kilowatts with thrust efficiency exceeding 60%. Ultimate specific impulse would be 500 seconds with helium, with lower values for heavier gases.
摘要翻译：这里披露了未来空军，NASA和商业系统的空间推进的突破性概念。本发明结合了微机电（MEM）装置的领域，光学物理学和非平衡等离子体动力学，将电推进器的尺寸大大减小了1-2个数量级，当与无电极操作和高推进器效率相结合时，将会实现可扩展，低成本，长寿命的可分配推进，用于控制微型，纳米级和空间结构。该概念可从1 W的功率水平扩展到几十千瓦，推力效率超过60％。氦气的最终冲量为500秒，较重的气体值为较低值。

2. 发明授权

US4821508A Pulsed electrothermal thruster 失效
标题翻译：脉冲电热推进器
公开(公告)号：US4821508A
公开(公告)日：1989-04-18
申请号：US743150
申请日：1985-06-10
申请人： Rodney L. Burton , Yeshayahu S. A. Goldstein , Derek A. Tidman , Niels K. Winsor
发明人： Rodney L. Burton , Yeshayahu S. A. Goldstein , Derek A. Tidman , Niels K. Winsor
IPC分类号： F03H1/00
CPC分类号： F03H1/00 , F03H1/0087
摘要： A plasma electrothermal thruster includes a capillary passage in which a plasma discharge is formed and directed out of an open end of the passage into a supersonic nozzle. Liquid supplied to the capillary passage becomes partially atomized to cool a confining surface of the passage. The plasma discharge is formed as the atomized liquid flows out of the open end into a supersonic equilibrium nozzle. The discharge can have a duration greater than the two way travel time of acoustic energy in the capillary to cause the plasma to flow continuously through the nozzle during the time of the discharge pulse.
摘要翻译：等离子体电热推进器包括毛细通道，其中形成等离子体放电并且从通道的开口端引导到超音速喷嘴中。供应到毛细管通道的液体被部分雾化以冷却通道的限制表面。当雾化液体从开口端流出到超音速平衡喷嘴中时，形成等离子体放电。放电可以具有大于毛细管中的声能的双向行进时间的持续时间，以在放电脉冲期间使等离子体连续流过喷嘴。

3. 发明授权

US06808145B2 Dual-mode airbreathing propulsion system 失效
标题翻译：双模式呼吸推进系统
公开(公告)号：US06808145B2
公开(公告)日：2004-10-26
申请号：US10360672
申请日：2003-02-07
申请人： Rodney L. Burton
发明人： Rodney L. Burton
IPC分类号： F03H500
CPC分类号： B64G1/402 , B64G1/401 , F02K7/18 , F02K9/78 , F25J3/04084 , F25J3/0426 , F25J3/04993
摘要： The present invention includes a method for a dual-mode propulsion system. During the first mode of operation, intake air is liquefied through a cooling heat exchanger and condenser using a combination of stored liquid hydrogen (LH2) and stored liquid nitrogen (LN2) as coolants. The liquefied air is then separated into separated liquid oxygen (SLO2) and separated liquid nitrogen (SLN2), which may contain molecules of each other or other elements commonly found in air. The stored liquid nitrogen is replaced with SLO2, while the SLN2 is pumped back through the system with the stored nitrogen in a regeneration process. The SLN2, LN2, and LH2 become gaseous as they pass through the condenser and heat exchanger and are burned in the dual mode rocket thrust chamber to produce thrust. In the second mode, the same thrust chamber is operated as a liquid hydrogen-oxygen rocket, where the liquid oxygen is the SLO2 collected during the first mode.
摘要翻译：本发明包括一种双模推进系统的方法。在第一操作模式中，通过冷却热交换器和冷凝器将吸入空气通过存储的液态氢（LH2）和储存的液氮（LN2）的组合作为冷却剂液化。然后将液化的空气分离成分离的液氧（LO 2）和分离的液态氮（LN），其可以包含彼此的分子或通常在空气中发现的其它元素。存储的液氮被替换为LO 2，而在再生过程中，将N 2用储存的氮气泵送回系统。当LN2，LN2和LH2通过冷凝器和热交换器并在双模式火箭推进室中燃烧以产生推力时，它们变得气态。在第二模式中，相同的推力室作为液体氢氧火箭运行，其中液态氧是在第一模式期间收集的LO 2。

4. 发明授权

US4821509A Pulsed electrothermal thruster 失效
公开(公告)号：US4821509A
公开(公告)日：1989-04-18
申请号：US133154
申请日：1987-12-07
申请人： Rodney L. Burton , Yeshayahu S. A. Goldstein , Derek A. Tidman , Niels K. Winsor
发明人： Rodney L. Burton , Yeshayahu S. A. Goldstein , Derek A. Tidman , Niels K. Winsor
IPC分类号： F03H1/00
CPC分类号： F03H1/0087 , F03H1/0012
摘要： A plasma electrothermal thruster includes a capillary passage in which a plasma discharge is formed and directed out of an open end of the passage into a supersonic nozzle. Liquid supplied to the capillary passage becomes partially atomized to cool a confining surface of the passage. The plasma discharge is formed as the atomized liquid flows out of the open end into a supersonic equilibrium nozzle. The discharge can have a duration greater than the two way travel time of acoustic energy in the capillary to cause the plasma to flow continuously through the nozzle during the time of the discharge pulse.

5. 发明授权

US06295804B1 Pulsed thruster system 失效
标题翻译：脉冲推进器系统
公开(公告)号：US06295804B1
公开(公告)日：2001-10-02
申请号：US09176495
申请日：1998-10-21
申请人： Rodney L. Burton , Gary Willmes
发明人： Rodney L. Burton , Gary Willmes
IPC分类号： F03H100
CPC分类号： F03H1/00
摘要： A thruster system includes a power supply and a pulse forming circuit coupled to the power supply. The pulse forming circuit includes a capacitor and first and second diodes. The positively-charged plate of the capacitor is coupled to the anode of the first diode, the negatively-charged of the capacitor is coupled to the anode of the second diode, and the cathode of the first diode is coupled to the cathode of the second diode. A low-impedance thruster is coupled in parallel to the second diode.
摘要翻译：推进器系统包括耦合到电源的电源和脉冲形成电路。脉冲形成电路包括电容器和第一和第二二极管。电容器的带正电极的板耦合到第一二极管的阳极，负电荷的电容器耦合到第二二极管的阳极，并且第一二极管的阴极耦合到第二二极管的阴极二极管。低阻抗推进器与第二二极管并联耦合。

6. 发明授权

US5425231A Gas fed pulsed electric thruster 失效
标题翻译：气体脉冲电动推进器
公开(公告)号：US5425231A
公开(公告)日：1995-06-20
申请号：US288803
申请日：1994-08-12
申请人： Rodney L. Burton
发明人： Rodney L. Burton
IPC分类号： F03H1/00 , B63H11/00
CPC分类号： F03H1/0087 , F03H1/0012
摘要： The present invention relates to a thruster for propelling a mass using a propellant gas which is repetitively converted to a pressurized plasma by pulses of electrical energy.
摘要翻译：本发明涉及一种用推进剂气体推进质量的推进器，推进剂气体通过电能脉冲重复转换成加压等离子体。

7. 发明授权

US4974487A Plasma propulsion apparatus and method 失效
标题翻译：等离子推进装置及方法
公开(公告)号：US4974487A
公开(公告)日：1990-12-04
申请号：US252551
申请日：1988-10-03
申请人： Yeshayahu S. A. Goldstein , Derek A. Tidman , Rodney L. Burton , Dennis W. Massey , Niels K. Winsor
发明人： Yeshayahu S. A. Goldstein , Derek A. Tidman , Rodney L. Burton , Dennis W. Massey , Niels K. Winsor
IPC分类号： F41B6/00
CPC分类号： F41B6/00
摘要： A projectile is accelerated in a barrel bore by applying a plasma jet to a projectile propelling fluid. The plasma jet is derived from a structure forming a capillary passage having a wall formed by a low molecular weight, dielectric powdery filler or water in many rigid containers, shaped as spheres or straw-like tubes having axes parallel to the passage longitudinal axis. The fluid and jet interact so the fluid is heated by the jet, whereby low atomic weight constituents of the fluid are sufficiently heated to become mixed with the plasma to form a high pressure mixture that is injected into the bore to accelerate the projectile. The fluid is dragged into the plasma during mixing to cool the plasma and form a boundary layer between the plasma and the barrel walls so that the mixture does not cause substantial damage to the walls of the bore. The plasma is energized by applying voltage from an electric pulse source to electrodes at opposite ends of the passage. The pulse has a wave shape and duration for initially igniting the plasma source and for thereafter applying energy to the ignited plasma to control the pressure of the mixture. Initially, the fluid cools the plasma without the mixture developing sufficient pressure to accelerate the projectile appreciably. The wave shape and duration are such that the pressure applied to the projectile remains substantially constant while the projectile is being accelerated through the barrel, as occurs during about one-half of the projectile travel time in the barrel.
摘要翻译：通过将等离子体射流施加到抛射体推进流体，炮弹在炮筒内加速。等离子体射流源于形成毛细管通道的结构，该通道具有由许多刚性容器中的低分子量介电粉末填料或水形成的壁，其形状为具有平行于通道纵向轴线的轴的球形或稻草状管。流体和射流相互作用使得流体被射流加热，由此流体的低原子量组分被充分加热以与等离子体混合以形成注入到孔中的高压混合物以加速射弹。在混合期间将流体拖入等离子体以冷却等离子体并在等离子体和筒壁之间形成边界层，使得混合物不会对孔的壁造成实质损坏。通过将来自电脉冲源的电压施加到通道的相对端处的电极来激发等离子体。脉冲具有用于初始点燃等离子体源的波形和持续时间，并且此后将能量施加到点火等离子体以控制混合物的压力。最初，流体冷却等离子体，而不会产生足够的压力使混合物明显加速。波浪形状和持续时间使得当射弹在枪管中的大约一半的射弹行进时间期间发生时，施加到射弹的压力保持基本上恒定，同时射弹被加速通过枪管。

8. 发明授权

US07935176B2 Oxygen extraction apparatus and process 有权
标题翻译：氧气提取装置及工艺
公开(公告)号：US07935176B2
公开(公告)日：2011-05-03
申请号：US12256877
申请日：2008-10-23
申请人： Rodney L. Burton , Peter J. Schubert , Filip Rysanek , Paul Fenoglio , Mike Hutches
发明人： Rodney L. Burton , Peter J. Schubert , Filip Rysanek , Paul Fenoglio , Mike Hutches
IPC分类号： B01D53/00
CPC分类号： B01D53/002 , B01D2256/12 , C01B13/0248
摘要： A facility and process capable of extracting oxygen in extraterrestrial environments from materials available in extraterrestrial environments, for example, on planets, planetoids, etc. The facility extracts oxygen from a mineral-containing solid material and is configured to form a free-falling molten stream of the solid material, evaporate at least a portion of the molten stream and produce a vapor containing gaseous oxygen, create a supersonic stream of the vapor, condense constituents of the supersonic stream to form particulates within the supersonic stream, separate the gaseous oxygen from the particulates, and then collect the gaseous oxygen.
摘要翻译：能够从外星环境中可用的材料（例如行星，飞机等）中提取地球环境中的氧的设备和方法。该设施从含矿物的固体材料中提取氧气并且被配置成形成自由落下的熔融流蒸发至少一部分熔融流并产生含有气态氧气的蒸汽，产生蒸汽的超音速流，冷凝超声流的成分以在超音速流内形成颗粒，将气态氧从颗粒，然后收集气态氧气。

9. 发明授权

US07926258B1 Advanced pulsed plasma thruster with high electromagnetic thrust 有权
公开(公告)号：US07926258B1
公开(公告)日：2011-04-19
申请号：US12177244
申请日：2008-07-22
申请人： Rodney L. Burton , Gabriel F. Benavides , Julia K. Laystrom
发明人： Rodney L. Burton , Gabriel F. Benavides , Julia K. Laystrom
IPC分类号： F03H1/00 , H05H1/00
CPC分类号： F03H1/0087
摘要： A pulsed plasma thruster provides for an advanced lightweight design with solid propellant and predominately electromagnetic thrust in a coaxial geometry. Electromagnetic forces are generated in a plasma by current flowing from a small central electrode to an electrically conducting diverging nozzle electrode. The thruster employs a series of electric current pulses of limited duration and varying frequency between the pair of electrodes creating a series of electric arcs. The electric arcs pass over a propellant surface located between the electrodes, forming a plasma, which is then exhausted from the device to produce thrust. The thruster maintains a low plasma resistance and cavity pressure, which in turn yields strong electromagnetic body forces, resulting in a high efficiency and consistent pulse-to-pulse performance.

10. 发明授权

US07926257B1 Advanced pulsed plasma thruster with high electromagnetic thrust 有权
标题翻译：具有高电磁推力的先进脉冲等离子体推进器
公开(公告)号：US07926257B1
公开(公告)日：2011-04-19
申请号：US12177217
申请日：2008-07-22
申请人： Rodney L. Burton , Gabriel F. Benavides , Julia K. Laystrom
发明人： Rodney L. Burton , Gabriel F. Benavides , Julia K. Laystrom
IPC分类号： F03H1/00 , H05H1/00
CPC分类号： F03H1/0087
摘要： A pulsed plasma thruster provides for an advanced lightweight design with solid propellant and predominately electromagnetic thrust in a coaxial geometry. Electromagnetic forces are generated in a plasma by current flowing from a small central electrode to an electrically conducting diverging nozzle electrode. The thruster employs a series of electric current pulses of limited duration and varying frequency between the pair of electrodes creating a series of electric arcs. The electric arcs pass over a propellant surface located between the electrodes, forming a plasma, which is then exhausted from the device to produce thrust. The thruster maintains a low plasma resistance and cavity pressure, which in turn yields strong electromagnetic body forces, resulting in a high efficiency and consistent pulse-to-pulse performance.
摘要翻译：脉冲等离子体推进器提供具有固体推进剂的先进轻质设计，并且主要以同轴几何形式的电磁推力。通过从小的中心电极流向导电发散的喷嘴电极的电流在等离子体中产生电磁力。推进器采用一系列有限持续时间的电流脉冲和一对电极之间变化的频率，产生一系列电弧。电弧通过位于电极之间的推进剂表面，形成等离子体，然后从装置中排出以产生推力。推进器维持低等离子体电阻和腔体压力，这又产生强大的电磁体力，从而产生高效率和一致的脉冲 - 脉冲性能。

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