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公开(公告)号：US09180981B2
公开(公告)日：2015-11-10
申请号：US13509611
申请日：2009-11-13
摘要： A pod for flights to and/or from space or near-space, including a pressurized body for hosting passengers, the pressurized body having a substantially ring-like shape provided around a central axis and having a central opening, wherein the pressurized body includes one or more windows.
摘要翻译： 用于从空间或近空间飞行和/或从空间或近空间的飞行器的舱，包括用于托管乘客的加压体，所述加压体具有围绕中心轴线设置并具有中心开口的大致环状，其中所述加压体包括一个 或更多窗口。
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82.发明申请SYSTEM AND METHOD FOR MATCHING OF SPACE LAUNCH, SATELLITE, AND MISSION PAYLOAD OPPORTUNITIES 有权空间发射，卫星和任务挂载机会的系统与方法公开(公告)号：US20150284109A1
公开(公告)日：2015-10-08
申请号：US14247512
申请日：2014-04-08
摘要： A system and a related method are disclosed for matching space launch vehicle, satellite, and mission hosted payload opportunities utilizing multi-level, priority algorithms. The potential matches include numerous mission-matching scenarios, e.g., 1) matching hosted payload and host spacecraft, and 2) matching spacecraft(s) and launch opportunities, to include rideshare opportunities. The matching opportunities can be pursued by any interested project team, e.g., hosted payload, spacecraft, and space launch vehicle.
摘要翻译： 公开了一种系统和相关方法，用于利用多级优先级算法来匹配空间运载火箭，卫星和任务托管的有效负载机会。 潜在的匹配包括许多任务匹配场景，例如，1）匹配托管的有效载荷和主机航天器，以及2）匹配航天器和启动机会，以包括乘车机会。 任何有兴趣的项目团队，例如托管的有效载荷，航天器和太空运载火箭可以追求匹配的机会。
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公开(公告)号：US09108748B2
公开(公告)日：2015-08-18
申请号：US12925386
申请日：2010-10-20
申请人： Saghir Munir , Darren Stratemeier , Xen Price , Yassir Azziz , Jorge Delgado , Justo Jacinto
发明人： Saghir Munir , Darren Stratemeier , Xen Price , Yassir Azziz , Jorge Delgado , Justo Jacinto
摘要： Apparatus and methods for raising the orbit of a satellite having electric propulsion thrusters, an Earth sensor and an inertial reference sensor such as a gyro. A satellite positioning system generates orbital data and a profile generator generates an ideal electric orbit raising profile of the satellite. The ideal profile is one that the satellite must follow so that the perigee, apogee and inclination of the satellite can be adjusted simultaneously in a mass-efficient manner. A state machine processes the ideal profile and a true anomaly to generate a desired electric orbit raising profile. Steering apparatus generates signals that are used to control the attitude of the satellite to follow the desired profile. The desired profile places the satellite in an Earth-pointed attitude when the satellite is at a predefined point in the orbit, slews the satellite from the Earth-pointed attitude to an ideal orbit raising attitude, steers the satellite according to the ideal profile during orbit raising, and steers the satellite from the desired attitude to the Earth-pointed attitude.
摘要翻译： 用于升高具有电力推进推进器的卫星的轨道的装置和方法，地球传感器和诸如陀螺仪的惯性参考传感器。 卫星定位系统产生轨道数据，轮廓发生器产生卫星的理想的电轨道升高轮廓。 理想的配置是卫星必须遵循的，以便能够以高效率的方式同时调整卫星的近地点，远地点和倾斜度。 状态机处理理想轮廓和真实异常以产生期望的电轨道提升轮廓。 转向装置产生用于控制卫星遵循所需轮廓的姿态的信号。 当卫星在轨道上的预定义点处时，所需的轮廓将卫星置于地球姿态，将卫星从地面倾斜姿态转换为理想的轨道提升姿态，在卫星轨道上根据理想轮廓引导卫星 将卫星从理想的态度引导到地球尖锐的态度。
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公开(公告)号：US20150217848A1
公开(公告)日：2015-08-06
申请号：US14667068
申请日：2015-03-24
申请人： Kevin Arash Peyman , Nazmi Peyman
发明人： Kevin Arash Peyman , Nazmi Peyman
CPC分类号： B64G1/002 , B64B1/40 , B64B1/62 , B64C1/34 , B64C37/02 , B64G1/005 , B64G1/22 , B64G1/401 , B64G2001/224
摘要： An aerospace vehicle comprising an airplane or spacecraft, operatively coupled to an airship balloon containing lighter than air gas adapted to elevate the vehicle. A control system adapted to deflate the balloon upon reaching a specific altitude by directing the gas to a propulsion system and high pressure gas chambers for powering the vehicle at a greater speed or to a greater altitude. The balloon can be retracted into the vehicle to achieve a better aerodynamic shape and further re-inflated for decreasing the speed of the vehicle upon reaching a destination.
摘要翻译： 一种航空航天车辆，其包括飞行器或航天器，其可操作地联接到包含比适于提升车辆的空气气体更轻的飞艇气球。 一种控制系统，其适于通过将气体引导到推进系统达到特定高度而放气，并且高压气体室以更高的速度或更高的高度向车辆供电。 气囊可以缩回到车辆中以获得更好的空气动力学形状，并进一步重新充气以便在到达目的地时降低车辆的速度。
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公开(公告)号：US20150204273A1
公开(公告)日：2015-07-23
申请号：US13590164
申请日：2012-08-20
申请人： PATRICK R.E. BAHN
发明人： PATRICK R.E. BAHN
CPC分类号： F02K9/605 , B64G1/002 , B64G1/40 , B64G1/52 , F02K9/08 , F02K9/46 , F02K9/72 , F02K9/96 , F05D2220/80 , Y10T29/49346
摘要： The present invention relates to an improved rocket stage and a method of improving an existing rocket stage. In an embodiment, the improved rocket stage is where one can take existing rocket stages and re-propellant them. In another embodiment, the present invention is a method of improving an existing rocket stage.
摘要翻译： 本发明涉及一种改进的火箭级和改进现有火箭级的方法。 在一个实施例中，改进的火箭级是可以采取现有火箭级并重新推进它们的地方。 在另一个实施方案中，本发明是改进现有火箭级的方法。
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公开(公告)号：US20150136913A1
公开(公告)日：2015-05-21
申请号：US14084006
申请日：2013-11-19
申请人： David G. DILLON
发明人： David G. DILLON
摘要： Systems and methods for launching space vehicles into orbit involve placing a space vehicle into a protective container. The protective container is placed on a sled in a maglev tunnel and then launched into the atmosphere. Once the protective container reaches a certain height the space vehicle is released from the protective container and the space vehicle then proceeds to the desired orbital position.
摘要翻译： 将空间车辆发射进入轨道的系统和方法涉及将空间车辆放入保护容器中。 将保护容器放置在磁悬浮隧道中的雪橇上，然后发射到大气中。 一旦保护容器达到一定高度，空间车辆就从保护容器中释放出来，然后空间车辆进入所需的轨道位置。
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87.发明授权Adaptive multiple shooting optimization method for determining optimal spacecraft trajectories 有权用于确定最佳航天器轨迹的自适应多重拍摄优化方法公开(公告)号：US09031818B2
公开(公告)日：2015-05-12
申请号：US13518790
申请日：2009-12-24
申请人： Andrea Bolle , Christian Circi , Giuseppe Corrao
发明人： Andrea Bolle , Christian Circi , Giuseppe Corrao
CPC分类号： B64G1/007
摘要： Disclosed herein is a method for determining a trajectory for a transfer of a spacecraft from a starting space body to a target space body with respect to a given central space body, wherein the determined trajectory is optimal with respect to a given space mission requirement to be met by the transfer of the spacecraft. The method comprises providing, according to the Pontryagin maximum principle, a physical-mathematical model relating model quantities and physical quantities representing the transfer of the spacecraft with respect to the given central space body.
摘要翻译： 本文公开了一种用于确定航空器相对于给定中心空间主体从起始空间体向目标空间体传递的轨迹的方法，其中所确定的轨迹相对于给定的空间任务要求是最佳的 遇到了航天器的转移。 该方法包括根据Pontryagin最大原理提供一个物理数学模型，该物理数学模型将模型数量和表示航天器相对于给定中心空间体的传递的物理量相关联。
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公开(公告)号：US09016635B2
公开(公告)日：2015-04-28
申请号：US13318330
申请日：2010-04-30
申请人： Robert Hoyt , Ian Barnes , Nestor Voronka , Jeffrey Thor Slostad
发明人： Robert Hoyt , Ian Barnes , Nestor Voronka , Jeffrey Thor Slostad
摘要： A deorbit device comprising a passive electrodynamic conductive tape connected at one end to a spacecraft.
摘要翻译： 一种包括在一端连接到航天器的无源电动导电带的脱轨装置。
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89.发明授权Landing device for a space probe, and landing method for a probe provided with such a device 有权用于空间探针的着陆装置，以及具有这种装置的探针的着陆方法公开(公告)号：US08991764B2
公开(公告)日：2015-03-31
申请号：US13257267
申请日：2010-03-05
CPC分类号： B64G1/62 , B64G1/16 , B64G1/58 , B64G2001/1064 , B64G2001/1071
摘要： A space probe including a descent module with a mobile exploration vehicle, wherein the descent module is a landing module inside which the mobile exploration vehicle is fastened, the landing module being provided with landing legs which can be deployed under the lower level of the mobile exploration vehicle.
摘要翻译： 一种包括具有移动探测车辆的下降模块的空间探测器，其中所述下降模块是其中所述移动探测车辆被固定的着陆模块，所述着陆模块设置有可以部署在所述移动探测器的较低水平下的着陆腿 车辆。
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公开(公告)号：US08960590B2
公开(公告)日：2015-02-24
申请号：US13944971
申请日：2013-07-18
申请人： Elbert L. Rutan
发明人： Elbert L. Rutan
摘要： A launch system and method improve the launch efficiency of a booster rocket and payload. A launch aircraft atop which the booster rocket is mounted in a cradle, is flown or towed to an elevation at which the booster rocket is released. The cradle provides for reduced structural requirements for the booster rocket by including a compressible layer, that may be provided by a plurality of gas or liquid-filled flexible chambers. The compressible layer contacts the booster rocket along most of the length of the booster rocket to distribute applied pressure, nearly eliminating bending loads. Distributing the pressure eliminates point loading conditions and bending moments that would otherwise be generated in the booster rocket structure during carrying. The chambers may be balloons distributed in rows and columns within the cradle or cylindrical chambers extending along a length of the cradle. The cradle may include a manifold communicating gas between chambers.
摘要翻译： 发射系统和方法提高了升压火箭和载荷的发射效率。 助推火箭安装在支架上的发射飞机飞行或拖曳到升压火箭被释放的高度。 支架通过包括可由多个气体或液体填充的柔性腔室提供的可压缩层来提供对增强火箭的结构要求的降低。 可压缩层沿着助推器火箭的大部分长度接触助推器火箭，以分配施加的压力，几乎消除弯曲载荷。 分配压力消除了在载运过程中否则会在助推器火箭结构中产生的点载荷条件和弯矩。 腔室可以是分布在托架内的行和列中的气球或沿支架的长度延伸的圆柱形腔室。 支架可以包括在腔室之间连通气体的歧管。
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