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1. 发明授权

US4882465A Arcjet thruster with improved arc attachment for enhancement of efficiency 失效
标题翻译： Arcjet推进器具有改进的电弧附件，以提高效率
公开(公告)号：US4882465A
公开(公告)日：1989-11-21
申请号：US103471
申请日：1987-10-01
申请人： William W. Smith , Steven C. Knowles
发明人： William W. Smith , Steven C. Knowles
IPC分类号： F03H1/00
CPC分类号： B64G1/406
摘要： An arcjet thruster has a constrictor and nozzle defining an arc chamber. The constrictor has an insulator and an anode. The constrictor defines a subsonic-to-supersonic transition zone axially coextensive with the inculator and anode. The anode is disposed side-by-side with the insulator and located upstream therefrom. A rod defines a cathode spaced from the anode by a gap. An electrical potential is applied to the anode and cathode to generate an electrical arc in the chamber which produces thermal heating of propellant gases flowing through the chamber and expansion thereof through the nozzle. Location of the insulator downstream from the anode causes diffusion and attachment of the arc to occur at the region of the anode in the constrictor and prevents movement of the arc diffusion and attachment region downstream past the insulator to the nozzle in response to propellant gas mass flow variations through the constrictor. The thruster can also include an expansion and compression cavity in the arc chamber to provide a low pressure region at the anode for arc attachment and diffusion. Further, a zone of thermal and mechanical isolation can be provided between the anode and insulator to reduce the temperature at the insulator and displace its location farther away from the region of arc attachment and diffusion at the anode. Still further, a passage is defined through the insulator to provide a path for secondary flow of propellant gas into the chamber downstream of the arc attachment and diffusion region in order to reclaim frozen flow losses.
摘要翻译：电弧喷射推进器具有限定电弧室的缩颈和喷嘴。收缩器具有绝缘体和阳极。缩颈器限定了与扰流器和阳极轴向共同延伸的亚音速到超音速过渡区。阳极与绝缘体并排放置并位于其上游。杆通过间隙限定与阳极间隔开的阴极。向阳极和阴极施加电势，以在腔室中产生电弧，其产生流过腔室的推进剂气体的热加热并通过喷嘴膨胀。在阳极下游的绝缘体的位置使电弧扩散并附着在收缩器中的阳极区域处，并且防止电弧扩散和附着区域沿绝缘体下游移动到喷嘴，以响应于推进剂气体质量流通过压缩器的变化。推进器还可以包括在电弧室中的膨胀和压缩空腔，以在阳极处提供用于电弧附接和扩散的低压区域。此外，可以在阳极和绝缘体之间提供热和机械隔离区域，以降低绝缘体处的温度，并使其位置远离阳极处的电弧附着和扩散区域。此外，通过绝缘体限定通道以提供用于将推进剂气体二次流入电弧附着和扩散区域下游的腔室以回收冷冻流动损失的路径。

2. 发明授权

US06513760B1 Logistics module system and method 失效
标题翻译：物流模块系统及方法
公开(公告)号：US06513760B1
公开(公告)日：2003-02-04
申请号：US09735201
申请日：2000-12-11
申请人： George E. Mueller , Richard H. Kohrs , David B. Cochran , Joseph W. Cuzzupoli , Charles D. Limerick , Richard A. Bailey , Thomas G. Johnson , Steven C. Knowles
发明人： George E. Mueller , Richard H. Kohrs , David B. Cochran , Joseph W. Cuzzupoli , Charles D. Limerick , Richard A. Bailey , Thomas G. Johnson , Steven C. Knowles
IPC分类号： F03H500
CPC分类号： B64G1/646 , B64G1/002 , B64G1/1078 , B64G1/12 , B64G1/401 , B64G1/62 , B64G1/641
摘要： An orbital vehicle (34) having a propulsion module (33) and a logistics module (36). The logistics module includes a generally cylindrical outer shell (56, 541, 542) with first and second ends. An openable cover (58) is coupled with the outer shell at the first end, thereby providing access to the interior of the logistics module. The second end is adapted to couple to the propulsion module. A cargo container (54) is disposed generally within the outer shell, the cargo container including a berthing mechanism (70) disposed to be accessible when the cover is opened. A retractable grapple fixture (176) is provided on the logistics module, selectively positionable between an extended position and a retracted position. When the grapple fixture is in the extended position a grapple shaft (78) can be accessed to secure the orbital vehicle. When the grapple fixture is retracted, it is enclosed within the orbital vehicle.
摘要翻译：具有推进模块（33）和物流模块（36）的轨道车辆（34）。后勤模块包括具有第一端和第二端的大致圆柱形外壳（56,541,542）。可开启盖（58）在第一端与外壳结合，从而提供进入物流模块内部的通路。第二端适于联接到推进模块。货物集装箱（54）通常设置在外壳内，货物集装箱包括设置成当盖打开时可接近的停泊机构（70）。在物流模块上设置有可伸缩抓斗夹具（176），其可选择性地定位在延伸位置和缩回位置之间。当抓斗固定装置处于伸出位置时，抓斗轴（78）可以被接近以固定轨道车辆。当抓斗夹具缩回时，它被包围在轨道车辆内。

3. 发明授权

US5927653A Two-stage reusable earth-to-orbit aerospace vehicle and transport system 失效
标题翻译：两级可重用地球对轨道航空航天车辆和运输系统
公开(公告)号：US5927653A
公开(公告)日：1999-07-27
申请号：US632786
申请日：1996-04-17
申请人： George E. Mueller , Walter P. Kistler , Thomas G. Johnson , Henry O. Pohl , Chris McLain , Allan S. Hill , Jason E. Andrews , Thomas C. Taylor , Aaron Cohen , Dale Myers , Adam P. Bruckner , Steven C. Knowles , Richard Warwick
发明人： George E. Mueller , Walter P. Kistler , Thomas G. Johnson , Henry O. Pohl , Chris McLain , Allan S. Hill , Jason E. Andrews , Thomas C. Taylor , Aaron Cohen , Dale Myers , Adam P. Bruckner , Steven C. Knowles , Richard Warwick
IPC分类号： B64G1/00 , B64G1/14 , B64G1/40 , B64G1/62 , B64G1/64 , B64G5/00
CPC分类号： B64G1/401 , B64G1/14 , B64G1/402 , B64G1/62 , B64G1/641 , B64G5/00
摘要： A two-stage wingless reusable aerospace vehicle having upper and lower stages that take off from a take-off area and separate at a separation point along a first trajectory. The separation forces are generated by air retained between the upper and lower stages, which is at a pressure higher than ambient pressure at the separation point. The lower stage is then propelled along a return trajectory to a landing area. After separation from the lower stage, the upper stage continues to an Earth orbit for deployment of a payload. After deploying the payload, the upper stage moves out of the Earth orbit, re-enters the Earth's atmosphere, and returns to the take-off and landing area. The upper and lower stages are powered by liquid oxygen and kerosene engines. The aerospace vehicle is transported to a take-off area by a transport vehicle having a first fixed carriage and a second translatable carriage that is adapted to move the upper stage relative to the lower stage for assembly of the aerospace vehicle while in the horizontal position. The transport vehicle then pivots the aerospace vehicle from the horizontal to the vertical position for launching.
摘要翻译：一种两级无翼可重复使用的航空航天器，具有从起飞区域起飞并且沿着第一轨迹在分离点分离的上段和下段。分离力由保持在上部和下部之间的空气产生，其处于高于分离点处的环境压力的压力。然后，下阶段沿着返回轨迹被推进到着陆区域。在与下级分离之后，上级继续到地球轨道，用于部署有效载荷。部署有效载荷后，上级移出地球轨道，重新进入地球大气层，返回起飞和着陆区域。上层和下层由液氧和煤油发动机提供动力。航空航天车辆通过具有第一固定支架和第二可平移滑架的运输车辆被运送到起飞区域，该第二可平移滑架适于在水平位置组装航空航天器时相对于下部台阶移动。然后，运输车辆将航空航天器从水平轴枢转到用于发射的垂直位置。

4. 发明授权

US4800716A Efficiency arcjet thruster with controlled arc startup and steady state attachment 失效
标题翻译：效率电弧喷射推进器，具有可控弧启动和稳态附件
公开(公告)号：US4800716A
公开(公告)日：1989-01-31
申请号：US889451
申请日：1986-07-23
申请人： William W. Smith , Steven C. Knowles
发明人： William W. Smith , Steven C. Knowles
IPC分类号： F03H1/00
CPC分类号： B64G1/406
摘要： An improved efficiency arcjet thruster has a constrictor and electrically-conductive nozzle anode defining an arc chamber, and an electrically-conductive rod having a tip spaced upstream from the constrictor and defining a cathode spaced from the anode by a gap generally coextensive with the arc chamber. An electrical potential is applied to the anode and cathode to generate an electrical arc in the arc chamber from the cathode to anode. Catalytically decomposed hydrazine is supplied to the arc chamber with generation of the arc so as to produce thermal heating and expansion thereof through the nozzle. The constrictor can have a electrically insulative portion disposed between the cathode tip and the nozzle anode, and an electrically-conductive anode extension disposed along the insulative portion so as to define an auxiliary gap with the cathode tip substantially smaller than the gap defined between the cathode and nozzle anode for facilitating startup of arc generation. The constrictor can also include an electrically-conductive electrode with a variable electrical potential to vary the shape of the arc generated in the arc chamber. Also, the cathode is mounted for axial movement such that the gap between its tip and the nozzle anode can be varied to facilitate a generally nonerosive generation of the electrical arc at startup and reliable steady state operation. Further, the arc chamber can have a nonparallel subsonic-to-supersonic transition configuration, or alternatively solely a nonparallel supersonic configuration, for improved arc attachment.
摘要翻译：改进的效率电弧喷射推进器具有限定电弧室的压缩和导电喷嘴阳极，以及导电棒，其具有在与压缩器的上游间隔开的顶端，并且限定与阳极间隔开的与阴极腔大致共同延伸的间隙。向阳极和阴极施加电势，以在电弧室中从阴极到阳极产生电弧。通过产生电弧将催化分解的肼供应到电弧室，以通过喷嘴产生热加热和膨胀。收缩器可以具有设置在阴极尖端和喷嘴阳极之间的电绝缘部分，以及沿着绝缘部分设置的导电阳极延伸部，以便限定与阴极尖端的辅助间隙，该间隙基本上小于阴极之间限定的间隙和用于促进电弧产生启动的喷嘴阳极。收缩器还可以包括具有可变电势的导电电极，以改变在电弧室中产生的电弧的形状。此外，阴极被安装用于轴向运动，使得其尖端和喷嘴阳极之间的间隙可以变化，以便于在起动和可靠的稳态操作时电弧的大体上不会产生。此外，电弧室可以具有非平衡的亚音速到超音速转换配置，或者替代地，仅仅是非平行的超音速配置，用于改进的电弧附着。

5. 发明授权

US5560779A Apparatus for synthesizing diamond films utilizing an arc plasma 失效
标题翻译：利用电弧等离子体合成金刚石膜的装置
公开(公告)号：US5560779A
公开(公告)日：1996-10-01
申请号：US90842
申请日：1993-07-12
申请人： Steven C. Knowles , Alan E. Kull , George W. Butler , David O. King
发明人： Steven C. Knowles , Alan E. Kull , George W. Butler , David O. King
IPC分类号： C23C16/27 , C23C16/452 , C23C16/513 , H05H1/48 , C23C16/26 , C23C16/50
CPC分类号： C23C16/276 , C23C16/452 , C23C16/513 , H05H1/48
摘要： There is provided a system for the manufacture of a diamond film. A plasma generator generates a hydrogen atom containing plasma stream into which a hydrocarbon containing gas is fed. The plasma dissociates the hydrocarbon to carbon radicals and carbon which are deposited on a substrate where the carbon crystallizes to a diamond film. The efficiency of the system is increased by heating the hydrogen source gas prior to generation of the plasma. Other means to increase the effectiveness of the system include using a plurality of plasma streams and shaping the plasma stream, A low internal strain, high quality optical film is generated by depositing the carbon on a substrate supported by a heat sink having nonuniform thermal conductivity such that the thermal gradient across the surface of the heat sink is less than about 8.degree. C./centimeter.
摘要翻译：提供了用于制造金刚石膜的系统。等离子体发生器产生含有含烃气体的含有氢原子的等离子体流。等离子体将碳氢化合物解离成碳原子和沉积在基底上的碳，其中碳结晶到金刚石膜。通过在产生等离子体之前加热氢源气体来提高系统的效率。提高系统有效性的其他方法包括使用多个等离子体流并对等离子体流进行成形。通过将碳沉积在由具有不均匀导热性的散热器支撑的基板上而产生低内应变，高质量的光学膜，散热片表面的热梯度小于约8℃/厘米。

6. 发明授权

US4805400A Non-erosive arcjet starting control system and method 失效
标题翻译：非腐蚀性电弧喷射启动控制系统及方法
公开(公告)号：US4805400A
公开(公告)日：1989-02-21
申请号：US42994
申请日：1987-04-27
申请人： Steven C. Knowles
发明人： Steven C. Knowles
IPC分类号： F03H1/00
CPC分类号： B64G1/406
摘要： A non-erosive arcjet starting control system and method are provided in combination with an arcjet thruster which includes an anode, a cathode and a gap defined therebetween. The starting control system and method include the operative steps of, first, actuating a valve in a propellant gas feed path to an opened position thereby permitting flow of propellant gas at a predetermined pressure into the thruster past the gap therein, second, applying to the anode and cathode an electrical potential of a predetermined magnitude being less than that required to generate an electrical arc across the gap through propellant gas at the predetermined flow pressure and, concurrently, actuating the valve to its closed position thereby preventing flow of propellant gas into the thruster past the gap and thereby lowering the flow pressure of the propellant gas in the thruster below the predetermined pressure such that an electrical arc is now generated in the thruster across the gap and, finally, actuating the valve to its opened position thereby permitting propellant gas to flow again at the predetermined pressure into the thruster past the gap and force the electrical arc to move downstream within the thruster so as to minimize erosion in the constrictor. The flow of propellant into the thruster is prevented for only a short period of time.
摘要翻译：提供了一种非侵蚀性电弧喷射起动控制系统和方法，其与包括阳极，阴极和在其间限定的间隙的电弧喷射推进器组合提供。启动控制系统和方法包括以下操作步骤：首先，将推进剂气体进料路径中的阀致动到打开位置，从而允许推进剂气体以预定压力流过其中的间隙，其次施加到阳极和阴极具有预定大小的电势小于在预定流量压力下通过推进剂气体跨越间隙产生电弧所需的电势，并且同时致动阀到其关闭位置，从而防止推进剂气体流入推进器超过间隙，从而将推进器中的推进剂气体的流动压力降低到预定压力以下，使得现在在推进器中跨过间隙产生电弧，最后将阀致动到其打开位置，从而允许推进剂气体以预定压力再次流入推进器经过间隙并迫使电气 c在推进器内向下游移动，以最大限度地减小收缩器的侵蚀。推进剂进入推进器的流量只能在短时间内被阻止。

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