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51. 发明申请

US20160001899A1 Gas Envelope Propulsion System and Related Methods 审中-公开
标题翻译：气体信封推进系统及相关方法
公开(公告)号：US20160001899A1
公开(公告)日：2016-01-07
申请号：US14733096
申请日：2015-06-08
申请人： Daniel J. Adcock
发明人： Daniel J. Adcock
IPC分类号： B64G1/40
CPC分类号： B64G1/40 , B64G1/005 , B64G1/403 , B64G1/404
摘要： Disclosed are exemplary embodiments of systems and methods for gas envelope propulsion. In an exemplary embodiment, a propulsion system generally includes a power plant, and an inelastic gas envelope configured to receive a gas independently of the power plant. The power plant is configured to provide thrust for moving the gas envelope skyward, and the gas envelope is further configured to expel at least some of the gas to provide additional thrust.
摘要翻译：公开了用于气体包壳推进的系统和方法的示例性实施例。在示例性实施例中，推进系统通常包括发电厂和非弹性气体外壳，其构造成独立于发电厂接收气体。发电厂被配置成提供用于将气体包围天空移动的推力，并且气体包络被进一步构造成排出至少一些气体以提供额外的推力。

52. 发明授权

US08826640B2 Flight vehicles including electrically-interconnective support structures and methods for the manufacture thereof 有权
标题翻译：包括电互连支撑结构的飞行车辆及其制造方法
公开(公告)号：US08826640B2
公开(公告)日：2014-09-09
申请号：US12945440
申请日：2010-11-12
申请人： Thomas A. Olden , Walter Wrigglesworth
发明人： Thomas A. Olden , Walter Wrigglesworth
IPC分类号： B64G1/40 , B64G1/26 , F42B10/66 , F02K9/34
CPC分类号： B64G1/403 , B64G1/26 , F42B10/661 , Y10T29/49346
摘要： Embodiments of a flight vehicle are provided, as are embodiments of a method for manufacturing a flight vehicle. In one embodiment, the flight vehicle includes a solid-propellant rocket motor, control circuitry, and an electrically-interconnective support structure. The electrically-interconnective support structure includes a load-bearing frame and a plurality of electrical conductors embedded within the load-bearing frame. The solid-propellant rocket motor is mounted to the load-bearing frame, and the plurality of electrical conductors embedded within the frame electrically couples the solid-propellant rocket motor to the control circuitry.
摘要翻译：提供了一种飞行器车辆的实施例，如制造飞行器车辆的方法的实施例。在一个实施例中，飞行器车辆包括固体推进剂火箭发动机，控制电路和电互连支撑结构。电互连支撑结构包括承载框架和嵌入承载框架内的多个电导体。固体推进剂火箭发动机安装到承重框架上，并且嵌入框架内的多个电导体将固体推进剂火箭发动机电耦合到控制电路。

53. 发明授权

US08789795B2 Propulsion system and method using a combustion chamber discharging a concentrated mass 有权
标题翻译：推进系统和方法使用燃烧室排出浓缩物质
公开(公告)号：US08789795B2
公开(公告)日：2014-07-29
申请号：US12716483
申请日：2010-03-03
申请人： Alon Gany , Dan Michales
发明人： Alon Gany , Dan Michales
IPC分类号： B64G1/40
CPC分类号： F02K9/97 , B64G1/401 , B64G1/403 , B64G1/641 , F02K9/62 , F42B10/661 , F42B15/36
摘要： A propulsion system and method are described configured to exert a force upon a vehicle. The system includes a concentrated mass which may be discharged from the vehicle by a propellant typically via an ejection tube. The system is optimized so that the discharged concentrated-mass imparts a large impulse upon the vehicle. The system and method may be used to alter the momentum of vehicles for propulsion, attitude correction, vehicle separation and the like.
摘要翻译：描述了构造成对车辆施加力的推进系统和方法。该系统包括可以通过推进剂从车辆排出的集中质量，通常通过喷射管。该系统被优化，使得排放的浓缩物质在车辆上施加大的冲击。该系统和方法可用于改变用于推进，姿态校正，车辆分离等的车辆的动量。

54. 发明申请

US20140158830A1 DEVICE FOR MOVING OR REMOVING ARTIFICIAL SATELLITES 有权
标题翻译：移动或移除人为卫星的设备
公开(公告)号：US20140158830A1
公开(公告)日：2014-06-12
申请号：US14232869
申请日：2012-07-18
申请人： Luca Rossettini , Giuseppe Jussef Tussiwand , Renato Panesi , Thomas Panozzo
发明人： Luca Rossettini , Giuseppe Jussef Tussiwand , Renato Panesi , Thomas Panozzo
IPC分类号： B64G1/24 , B64G1/26
CPC分类号： B64G1/242 , B64G1/10 , B64G1/26 , B64G1/40 , B64G1/403 , B64G1/64
摘要： A device for coupling with a space satellite before the satellite is launched for the purpose of de-orbiting said satellite and/or returning it to Earth. The device includes: controller for controlling the device; propulsion system operatively connected with the control means; receiver for receiving control signals operatively connected with the control means; powering system for electrically powering the device; coupler for mechanically coupling the device with the satellite before the satellite is launched. The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.
摘要翻译：在卫星发射之前与空间卫星耦合的装置，用于绕行所述卫星和/或将其返回到地球。该装置包括：用于控制装置的控制器; 推进系统与控制装置可操作地连接; 接收器，用于接收与控制装置可操作地连接的控制信号; 用于为设备供电的供电系统; 耦合器，用于在卫星发射之前将设备与卫星机械耦合。控制器在接收到用于对卫星进行脱轨并将其转移到给定轨道的控制信号时启用推进系统。

55. 发明申请

US20100224731A1 PROPULSION SYSTEM AND METHOD USING A COMBUSTION CHAMBER DISCHARGING A CONCENTRATED MASS 有权
标题翻译：推进系统和使用燃烧室释放浓度大小的方法
公开(公告)号：US20100224731A1
公开(公告)日：2010-09-09
申请号：US12716483
申请日：2010-03-03
申请人： Alon GANY , Dan Michales
发明人： Alon GANY , Dan Michales
IPC分类号： F42B15/00 , B64G1/40 , F02K9/00 , F02K9/70 , F02K9/42
CPC分类号： F02K9/97 , B64G1/401 , B64G1/403 , B64G1/641 , F02K9/62 , F42B10/661 , F42B15/36
摘要： A propulsion system and method are described configured to exert a force upon a vehicle. The system includes a concentrated mass which may be discharged from the vehicle by a propellant typically via an ejection tube. The system is optimized so that the discharged concentrated-mass imparts a large impulse upon the vehicle. The system and method may be used to alter the momentum of vehicles for propulsion, attitude correction, vehicle separation and the like.
摘要翻译：描述了构造成对车辆施加力的推进系统和方法。该系统包括可以通过推进剂从车辆排出的集中质量，通常通过喷射管。该系统被优化，使得排放的浓缩物质在车辆上施加大的冲击。该系统和方法可用于改变用于推进，姿态校正，车辆分离等的车辆的动量。

56. 发明申请

US20070044450A1 Powder propellant-based space propulsion device 审中-公开
标题翻译：粉末推进剂空间推进装置
公开(公告)号：US20070044450A1
公开(公告)日：2007-03-01
申请号：US11431452
申请日：2006-05-09
申请人： Hitoshi Kuninaka
发明人： Hitoshi Kuninaka
IPC分类号： F02K9/68
CPC分类号： B64G1/406 , B64G1/403 , F03H99/00
摘要： Disclosed is a powder propellant-based space propulsion device using a powder propellant having high density and excellent handleability. The powder propellant-based space propulsion device comprises a powder-propellant storage container for storing a powder propellant, a powder-propellant attracting surface for attracting the powder propellant thereto through an opening of the powder-propellant storage container and attractively holding the attracted powder propellant thereon, powder-propellant transfer means for transferring the held powder propellant to a release position for releasing the powder propellant, and propulsive-energy supply means for energizing the transferred powder propellant to release the powder propellant from the powder-propellant attracting surface, toward a downstream side thereof as a propulsive jet, while accelerating the powder propellant in a direction approximately perpendicular to the powder-propellant attracting surface at said release position. The powder-propellant transfer means is designed to move the powder-propellant attracting surface in such a manner that a powder-propellant holding area of the powder-propellant attracting surface is returned to a position adjacent to the opening of the powder-propellant storage container in a repetitive manner.
摘要翻译：公开了使用具有高密度和优异的可操作性的粉末推进剂的基于粉末推进剂的空间推进装置。基于粉末推进剂的空间推进装置包括用于储存粉末推进剂的粉末推进剂储存容器，用于通过粉末推进剂储存容器的开口吸引粉末推进剂的粉末推进剂吸附表面并且吸引地保持吸引的粉末推进剂用于将保持的粉末推进剂转移到用于释放粉末推进剂的释放位置的推进剂转移装置以及用于激励所转移的粉末推进剂以将粉末推进剂从粉末推进剂吸附表面释放的推进能量供给装置，其下游侧作为推进射流，同时在所述释放位置沿着大致垂直于粉末 - 推进剂吸引表面的方向加速粉末推进剂。粉末推进剂转移装置设计成以粉末推进剂吸附表面的粉末推进剂保持区域返回到与粉末推进剂储存容器的开口相邻的位置的方式移动粉末推进剂吸附表面以重复的方式。

57. 发明申请

US20030200656A1 Rocket assembly ablative materials, and method for insulating or thermally protecting a rocket assembly 审中-公开
标题翻译：火箭组件烧蚀材料，以及绝热或热保护火箭组件的方法
公开(公告)号：US20030200656A1
公开(公告)日：2003-10-30
申请号：US09896439
申请日：2001-06-29
发明人： Kenneth P Wilson
IPC分类号： F02K001/00
CPC分类号： F02K9/974 , B64G1/403 , B64G1/58 , F02K9/346 , F05D2300/433 , F05D2300/44 , F05D2300/603 , F05D2300/614 , F05D2300/702 , Y10T29/49346 , Y10T156/1028
摘要： A rocket motor ablative material (e.g., an insulation liner, bulk material, or the like) of this invention is formed from, as a precursor of the carbon reinforcement structure, one or more polyarylamides configured as a suitable reinforcing structure, such as a yarn, flock, and/or felt. Aramid yarns can be prepared by twisting/spinning aramid filaments, and/or by carding and yarn-spinning staple aramid fibers. In particular, the insulation may be used, for example, for a rocket motor nozzle or as a rocket motor heat shield subjected to conditions comparable to those of continuous filament viscose rayon.
摘要翻译：本发明的火箭发动机烧蚀材料（例如，绝缘衬垫，散装材料等）由碳增强结构的前体形成为一种或多种被配置为合适的增强结构的聚芳酰胺，例如纱线，羊群和/或感觉。芳族聚酰胺纱线可以通过加捻/纺丝芳族聚酰胺长丝和/或通过梳理和纺丝编织芳族聚酰胺纤维来制备。特别地，绝缘可以用于例如火箭发动机喷嘴或作为与连续长丝粘胶人造丝相当的条件的火箭发动机隔热罩。

58. 发明授权

US06543723B1 Electric orbit raising with variable thrust 有权
标题翻译：具有可变推力的电动轨道提升
公开(公告)号：US06543723B1
公开(公告)日：2003-04-08
申请号：US09947186
申请日：2001-09-04
申请人： David Oh
发明人： David Oh
IPC分类号： B64G140
CPC分类号： B64G1/007 , B64G1/242 , B64G1/401 , B64G1/403 , B64G1/406
摘要： Systems and methods for launching a satellite into orbit that optimize the mass of the satellite delivered into orbit. A satellite carrying one or more chemical propulsion devices and one or more electric propulsion devices is launched into a transfer orbit using a launch vehicle. In one embodiment, a selected chemical propulsion device is fired to raise the orbit of the satellite from the transfer orbit to an intermediate orbit. One or more electric propulsion device is fired to raise the orbit of the satellite from the intermediate orbit to final geosynchronous orbit and the one or more electric propulsion device is throttled to produce variable thrust levels so as to operate at all optimum specific impulse level to optimize the mass of the satellite delivered into orbit. In another embodiment, the electric propulsion device may deliver the satellite into a near-geosynchronous orbit instead of final geosynchronous orbit. In this case, a selected chemical propulsion device is fired to place the satellite in its final orbit. In yet another embodiment, the launch vehicle may be used to deliver the satellite into the intermediate starting orbit after which the electric propulsion device is used to achieve final orbit. In this case, the transfer orbit raising step is omitted.
摘要翻译：将卫星发射到轨道的系统和方法，优化传送到轨道的卫星的质量。携带一个或多个化学推进装置和一个或多个电推进装置的卫星使用运载火箭发射到转移轨道中。在一个实施例中，选择的化学推进装置被发射以将卫星的轨道从转移轨道升高到中间轨道。一个或多个电力推进装置被发射以将卫星的轨道从中间轨道升高到最终的地球同步轨道，并且一个或多个电动推进装置被节流以产生可变的推力水平，以便以所有最佳特定脉冲水平运行以优化卫星的质量进入轨道。在另一个实施例中，电力推进装置可以将卫星输送到近地球同步轨道，而不是最终的地球同步轨道。在这种情况下，发射选定的化学推进装置将卫星置于其最终轨道中。在另一个实施例中，运载火箭可以用于将卫星递送到中间起始轨道，之后使用电推进装置来实现最终轨道。在这种情况下，省略了转移轨道提升步骤。

59. 发明授权

US06332592B1 Method for velocity precision pointing in spin-stabilized spacecraft or rockets 失效
标题翻译：速度精度指向旋转稳定的航天器或火箭的方法
公开(公告)号：US06332592B1
公开(公告)日：2001-12-25
申请号：US09635225
申请日：2000-08-09
申请人： James M. Longuski , Daniel Javorsek, II
发明人： James M. Longuski , Daniel Javorsek, II
IPC分类号： F02K972
CPC分类号： B64G1/403 , B64G1/26 , B64G1/281
摘要： A method of velocity precision pointing of spin-stabilized spacecraft or rockets is disclosed. This method involves softening the ignition transient of the ramp up phase of thrust, which may be achieved by modification of the solid propellant, applying a coating of slow burning material upon the solid propellant varying the grain density of the solid propellant over an exposed surface area or as a function of propellant depth, where depth is defined in the direction of the burn surface area regression, pre-pressurizing the combustion chamber with a gas having a molecular mass smaller than that of the combustion products and which is unreactive with the propellant, installing one or more relief valves in the combustion chamber to regulate the pressure, forming a ring of an ablative material on the throat section of the nozzle, having a rubber fitting at a throat section of the nozzle to regulate the pressure of the combustion chamber, pulsing the engine, or using a pyrogen igniter to soften the ignition transient.
摘要翻译：公开了一种自旋稳定的航天器或火箭的速度精度指向的方法。这种方法包括软化推力斜坡上升阶段的点火瞬变，这可以通过固体推进剂的改进来实现，将缓慢燃烧的材料涂覆在固体推进剂上，使固体推进剂的颗粒密度在暴露的表面积上变化或作为推进剂深度的函数，其中在燃烧表面积回归方向上限定深度，用具有小于燃烧产物的分子量的气体对燃烧室进行预加压，并且与推进剂不反应，在燃烧室中安装一个或多个安全阀以调节压力，在喷嘴的喉部上形成可消除材料的环，在喷嘴的喉部处具有橡胶配件以调节燃烧室的压力，脉冲发动机，或使用热源点火器软化点火暂态。

60. 发明授权

US5816539A Orbital assist module and interstage 失效
标题翻译：轨道辅助模块和级间
公开(公告)号：US5816539A
公开(公告)日：1998-10-06
申请号：US511346
申请日：1995-08-04
申请人： Allan L. Chan , James J. Connors , Kenneth W. Epstein , Robert M. Heath , Gene Spencer Ogden , Michael B. Prewitt , Michael Wong , Edward W. Szeto , David P. Kennon , Michael J. Vogel , Larry Y. Hsu , Daniel H. Hada , Douglas B. Pereyda , Robert J. MacDonald
发明人： Allan L. Chan , James J. Connors , Kenneth W. Epstein , Robert M. Heath , Gene Spencer Ogden , Michael B. Prewitt , Michael Wong , Edward W. Szeto , David P. Kennon , Michael J. Vogel , Larry Y. Hsu , Daniel H. Hada , Douglas B. Pereyda , Robert J. MacDonald
IPC分类号： B64F1/04 , B64G1/00 , B64G1/40 , B64G1/64 , B64G5/00 , F02K9/34 , B64D37/04 , B64G1/42 , F02K9/00
CPC分类号： B64F1/04 , B64G1/002 , B64G1/007 , B64G1/401 , B64G1/641 , B64G5/00 , F02K9/343 , F42B15/36 , F42B15/38 , B64G1/402 , B64G1/403 , B64G2001/1092 , B64G2005/005
摘要： An orbital assist module and an interstage for a launch vehicle. The orbital assist module includes a cylindrical outer wall and a support structure secured to an inner surface of the cylindrical outer wall. The support structure defines a plurality of fuel tank supporting zones, at least one of the zones supporting a fuel tank by means of securing formations. A plurality of nozzles are connected to the fuel tanks by means of fuel lines and a plurality of valves are mounted in the fuel lines. The interstage comprises a cylinder having a leading and a trailing end and an explosive connector at the leading end for connecting the interstage to a trailing end of a launch vehicle motor. A connecting bracket is secured to the trailing end of the cylinder for connecting a second launch vehicle motor to the cylinder.
摘要翻译：轨道辅助模块和运载火箭的级间。轨道辅助模块包括圆柱形外壁和固定到圆柱形外壁的内表面的支撑结构。支撑结构限定多个燃料箱支撑区域，至少一个区域通过固定地层支撑燃料箱。多个喷嘴通过燃料管线连接到燃料箱，并且多个阀安装在燃料管线中。级间包括具有前端和后端的气缸和在前端的爆炸连接器，用于将级间连接到运载火箭车辆的后端。连接支架固定在气缸的后端，用于将第二运送车辆马达连接到气缸。

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