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1.发明授权
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
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。
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公开(公告)号：US06186039B1
公开(公告)日：2001-02-13
申请号：US09030511
申请日：1998-02-25
申请人： George E. Mueller , Aaron Cohen , Dale D. Myers , Henry O. Pohl
发明人： George E. Mueller , Aaron Cohen , Dale D. Myers , Henry O. Pohl
IPC分类号： F41A900
摘要： A spacecraft launch system includes a support assembly and a seat coupled to a hinge having a hinge axis. In operation, the support assembly and the seat rotate about the hinge axis to move the spacecraft from a horizontal position to a vertical position for launching. The launch system may incorporate an alignment technique that includes alignment members and actuators.
摘要翻译： 航天器发射系统包括支撑组件和联接到具有铰链轴线的铰链的座椅。 在操作中，支撑组件和座椅围绕铰链轴线旋转以将航天器从水平位置移动到用于发射的垂直位置。 发射系统可以包括对准技术，其包括对准构件和致动器。
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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
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。
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公开(公告)号：US6158693A
公开(公告)日：2000-12-12
申请号：US30724
申请日：1998-02-25
申请人： George E. Mueller , Henry O. Pohl
发明人： George E. Mueller , Henry O. Pohl
摘要： A recoverable/reusable booster stage has a restartable center liquid-fueled rocket engine mounted in the aft portion of a vehicle body in alignment with the center axis of the body. The booster stage may also include two side liquid-fueled rocket engines mounted in the aft portion of the body in symmetrical relation to the center rocket engine. After booster stage separation, the center engine is restarted to direct the booster stage towards a recovery site.
摘要翻译： 可恢复/可重复使用的增压器级具有安装在车身后部与车身中心轴线对齐的可重启中心液体燃料火箭发动机。 升压级还可以包括以与中心火箭发动机对称的方式安装在船体后部的两侧液体燃料火箭发动机。 在升压级分离后，重新启动中心发动机以将增压器引导到恢复位置。
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公开(公告)号：US20090050745A1
公开(公告)日：2009-02-26
申请号：US12041566
申请日：2008-03-03
申请人： George E. Mueller , Gary Lai , Thomas C. Taylor
发明人： George E. Mueller , Gary Lai , Thomas C. Taylor
IPC分类号： B64G1/00
摘要： An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Previously expensive arc jet wind tunnels attempted to simulate the re-entry temperatures and ever changing re-entry flow environment for researchers. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.
摘要翻译： 具有六个不同重新进入实验位置的实验系统，用于测试高温重入物料，创建新的热保护系统，为航天器外表面提供创新的新概念，以及下一代航空材料的增量开发。 往返轨道的商业运输系统为实际重新进入地球大气层的表面提供了24小时的循环。 以前昂贵的电弧喷流风洞试图模拟再入境温度和不断变化的研究人员的再入流环境。 现在在可重复使用的运载火箭的外部使用现有的门，舱口和其他点，实际的重入环境经历了快速转弯的各种不同的重新进入温度范围，用于广泛的测试和开发目的。 可重复使用的运载火箭发射，保持在轨道上24小时，并返回，为外部实验系统提供实际的测试环境。
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公开(公告)号：US07354020B2
公开(公告)日：2008-04-08
申请号：US10698261
申请日：2003-10-31
申请人： George E. Mueller , Gary Lai , Thomas C. Taylor
发明人： George E. Mueller , Gary Lai , Thomas C. Taylor
IPC分类号： B64G1/22
摘要： An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.
摘要翻译： 具有六个不同重新进入实验位置的实验系统，用于测试高温重入物料，创建新的热保护系统，为航天器外表面提供创新的新概念，以及下一代航空材料的增量开发。 往返轨道的商业运输系统为实际重新进入地球大气层的表面提供了24小时的循环。 现在在可重复使用的运载火箭的外部使用现有的门，舱口和其他点，实际的重入环境经历了快速转弯的各种不同的重新进入温度范围，用于广泛的测试和开发目的。 可重复使用的运载火箭发射，保持在轨道上24小时，并返回，为外部实验系统提供实际的测试环境。
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公开(公告)号：US06945498B2
公开(公告)日：2005-09-20
申请号：US10682761
申请日：2003-10-09
申请人： George E. Mueller , Gary Lai , Thomas C. Taylor
发明人： George E. Mueller , Gary Lai , Thomas C. Taylor
摘要： An orbital experiment system with different internal experiment locations within a reusable launch vehicle making daylong delivery trips to space. The experiments get access to the attributes of low earth orbit, the reusable launch vehicle's power and other subsystems. The experimenter utilizes uniform experiment trays having a uniform connector for connection to an experiment management unit mounted on the orbital vehicle. The experiment management unit provides power and data from the orbital vehicle related to the operation of the orbital vehicle and permits an experiment check simulation prior to integration into the launch vehicle. The uniform size and connectivity requirements provide low cost options for the delivery of an experiment into space and the return of the experiment from space. A commercial transportation system to and from orbit delivers a primary payload and provides a 24-hour return cycle for the internal secondary experiments, which provide a quick confirmation of technical experiment exposure to space and quick re-flight opportunities.
摘要翻译： 一个轨道实验系统，在可重复使用的运载火箭内部具有不同的内部实验位置，使得一天的飞行时间到达空间。 实验可以获得低地球轨道的特性，可重复使用的运载火箭的能量等子系统。 实验者使用具有统一连接器的均匀实验托盘连接到安装在轨道车辆上的实验管理单元。 实验管理单元提供与轨道车辆操作相关的轨道车辆的动力和数据，并且允许在集成到运载火箭中之前进行实验检查模拟。 统一的尺寸和连接要求为实验的空间传递和实验的返回提供了低成本的选择。 往返轨道的商业运输系统提供主要有效载荷，并为内部二次实验提供24小时的返回周期，从而快速确认技术实验暴露于空间和快速重新飞行机会。
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公开(公告)号：US20090127399A1
公开(公告)日：2009-05-21
申请号：US11955612
申请日：2007-12-13
申请人： George E. Mueller , Gary Lai , Thomas C. Taylor
发明人： George E. Mueller , Gary Lai , Thomas C. Taylor
摘要： An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.
摘要翻译： 具有六个不同重新进入实验位置的实验系统，用于测试高温重入物料，创建新的热保护系统，为航天器外表面提供创新的新概念，以及下一代航空材料的增量开发。 往返轨道的商业运输系统为实际重新进入地球大气层的表面提供了24小时的循环。 现在在可重复使用的运载火箭的外部使用现有的门，舱口和其他点，实际的重入环境经历了快速转弯的各种不同的重新进入温度范围，用于广泛的测试和开发目的。 可重复使用的运载火箭发射，保持在轨道上24小时，并返回，为外部实验系统提供实际的测试环境。
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公开(公告)号：US20090140100A1
公开(公告)日：2009-06-04
申请号：US12324746
申请日：2008-11-26
申请人： George E. Mueller , Richard H. Kohrs , William B. Duncan , David B. Cochran , Dean L. Misterek , Terrill L. Burlison , Ryan M. Curtis , Thomas Johnson , Richard A. Bailey , Charles D. Limerick
发明人： George E. Mueller , Richard H. Kohrs , William B. Duncan , David B. Cochran , Dean L. Misterek , Terrill L. Burlison , Ryan M. Curtis , Thomas Johnson , Richard A. Bailey , Charles D. Limerick
IPC分类号： B64G1/00
CPC分类号： B64G1/14 , B64G2001/1092
摘要： A reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. A variety of cargo modules of different configurations allow cargo to be uplifted into orbit. In one embodiment, the cargo module is an unpressurized cargo module in which the cargo is exposed to the environment of space during the unloading process. The cargo module may also be a pressurized cargo module. In an alternative embodiment, the cargo module may include both a pressurized cargo module and unpressurized cargo module.
摘要翻译： 可重复使用的模块固定在可重复使用的轨道车辆（OV）上。 可再利用模块的各种配置在连接到OV的区域中具有相同的外部尺寸以允许可互换性。 不同的配置可以适应不同类型和持续时间的各种任务。 不同配置的各种货物模块可以将货物提升到轨道上。 在一个实施例中，货物模块是非加压货物模块，其中货物在卸载过程中暴露于空间环境中。 货物模块也可以是加压货物模块。 在替代实施例中，货物模块可以包括加压货物模块和非加压货物模块。
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公开(公告)号：US6059234A
公开(公告)日：2000-05-09
申请号：US34038
申请日：1998-02-25
摘要： A payload module couples to a forward end of a re-entry vehicle. The payload module includes a cap and a fairing to contain a payload during ascent of the vehicle and to withstand aerodynamic heating from the atmosphere upon re-entry of the vehicle. In a particular embodiment, the fairing has an extended position to contain the payload and a retracted position for re-entry into the atmosphere after payload deployment.
摘要翻译： 有效负载模块耦合到重新进入车辆的前端。 有效载荷模块包括盖和整流罩，以在车辆上升期间容纳有效载荷，并且在车辆重新进入时承受来自大气的空气动力加热。 在特定实施例中，整流罩具有扩展位置以容纳有效载荷和用于在有效载荷部署之后重新进入大气的缩回位置。
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