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1. 发明申请

US20190248515A1 TRANSPORT METHOD, TRANSPORT SHIP, METHOD FOR MANUFACTURING TRANSPORT SHIP, LANDER, NAVIGATION METHOD, METHOD FOR MANUFACTURING COMPONENT OF LANDER, METHOD FOR MANUFACTURING LANDER, LANDING METHOD, MONITORING METHOD AND FUEL SUPPLY METHOD 审中-公开
公开(公告)号：US20190248515A1
公开(公告)日：2019-08-15
申请号：US16324539
申请日：2017-08-08
申请人： ispace, inc.
发明人： Takeshi HAKAMADA , Takahiro NAKAMURA , Toshiki TANAKA , Daisuke FURUTOMO , John WALKER , Mohamed RAGAB , Daishi MATSUKURA , Abdelkader HAOUCHINE , Damien HAIKAL , Chit Hong YAM , Julian Jakub GRAMATYKA
IPC分类号： B64G1/00 , B64G1/40
CPC分类号： B64G1/007 , B64G1/14 , B64G1/242 , B64G1/40 , B64G1/402 , B64G1/405 , B64G1/443
摘要： A first step of propelling a transport ship from a low earth orbit or a geostationary transfer orbit to a targeted orbit or a destination with electric propulsion is provided.

2. 发明授权

US09963248B2 Spin stabilization of a spacecraft for an orbit maneuver 有权
公开(公告)号：US09963248B2
公开(公告)日：2018-05-08
申请号：US15016204
申请日：2016-02-04
申请人： The Boeing Company
发明人： Qinghong W. Wang , Alexander Jacob Sobel , Gary Lemke , Timothy Lui , Kangsik Lee , Glenn N. Caplin , Troy Allen Fontana
IPC分类号： B64G1/24 , B64G1/28 , B64G1/26 , B64G1/36 , B64G1/40
CPC分类号： B64G1/24 , B64G1/007 , B64G1/26 , B64G1/281 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/36 , B64G1/405 , B64G2001/245
摘要： Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a momentum subsystem that stores angular momentum relative to a center of mass of the spacecraft, and a propulsion subsystem that includes electric thrusters. A controller identifies a target spin axis for the spacecraft, determines gimbal angles for electric thruster(s) that so that thrust forces from the electric thrusters are parallel to the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles. The controller controls the momentum subsystem to compensate for a thruster torque produced by the burn of the electric thrusters. The momentum subsystem is able to produce a target angular momentum about the center of mass, where a coupling between the target angular momentum and an angular velocity of the spacecraft creates an offset torque to counteract the thruster torque.

3. 发明申请

US20170247124A1 STATIONKEEPING TECHNIQUES FOR SPACECRAFT IN INCLINED GEOSYNCHRONOUS ORBIT 审中-公开
公开(公告)号：US20170247124A1
公开(公告)日：2017-08-31
申请号：US15441037
申请日：2017-02-23
申请人： Space Systems/Loral, LLC
发明人： Darren R. Stratemeier , Andrew E. Turner , Robert S. Day, JR.
IPC分类号： B64G1/24 , B64G1/10
CPC分类号： B64G1/242 , B64G1/007 , B64G1/1007 , B64G1/1085 , B64G1/40 , B64G1/405
摘要： A constellation of Earth-orbiting spacecraft, the constellation having an orbital maneuver lifetime life (OML), includes a first spacecraft disposed in a first orbit and a second spacecraft disposed in a second orbit, each of orbit being substantially circular with a radius of approximately 42,164 km and having a respective inclination with respect to the equator specified within a range of 10° to 20°. The first orbit has, at beginning of life (BOL), a first right ascension of ascending node (BOL-RAAN1) and the second orbit has, at BOL, a second RAAN (BOL-RAAN2) the BOL-RAAN1 and the BOL-RAAN2 being separated by a first angular separation Δ-RAAN1. A first stationkeeping delta-V (ΔV1) applied over the OML to the first spacecraft, in combination with a second delta-V (ΔV2) applied over the OML to the second spacecraft, maintains the Δ-RAAN1 approximately constant and an actual inclination within specification, and ΔV1 approximately equals ΔV2.

4. 发明申请

US20170029138A1 REMOVABLE ORBITAL TOWING ASSISTANCE DEVICE, AND RELATED METHOD 审中-公开
标题翻译：可移动的基线辅助装置及相关方法
公开(公告)号：US20170029138A1
公开(公告)日：2017-02-02
申请号：US15303898
申请日：2015-04-03
申请人： CENTRE NATIONAL D'ETUDES SPATIALES
发明人： Pascal Bultel
IPC分类号： B64G1/00 , B64G1/64 , B64G1/40
CPC分类号： B64G1/007 , B64G1/402 , B64G1/646 , B64G2001/1092
摘要： The invention relates to a method for transferring a space payload from a first orbit to a second orbit. Said method is characterized in that the space payload, moving about the first orbit, is attached to a removable orbital towing assistance device including at least one fuel pouch. Said method includes the steps of: —attaching (E1) an orbital transfer vehicle to the removable orbital towing assistance device; and —transferring (E2) the space payload and the removable orbital towing assistance device to the second orbit by means of the orbital transfer vehicle. The invention also relates to a removable orbital towing assistance device intended for a space payload and an orbital transfer vehicle and enabling direct supply of fuel to the vehicle and/or the space payload.
摘要翻译：本发明涉及一种将空间有效载荷从第一轨道传送到第二轨道的方法。所述方法的特征在于，围绕第一轨道移动的空间有效载荷附接到包括至少一个燃料袋的可拆卸轨道牵引辅助装置。所述方法包括以下步骤：将轨道转移车辆（E1）附接到可拆卸轨道牵引辅助装置; 并通过轨道转运车辆（E2）将空间有效载荷和可移动轨道牵引辅助装置（E2）传送到第二轨道。本发明还涉及一种用于空间有效载荷和轨道转运车辆并且能够直接向车辆和/或空间有效载荷提供燃料的可拆卸的轨道牵引辅助装置。

5. 发明申请

US20160318636A1 SYSTEM AND METHOD FOR ASSEMBLING AND DEPLOYING SATELLITES 有权
标题翻译：用于组装和部署卫星的系统和方法
公开(公告)号：US20160318636A1
公开(公告)日：2016-11-03
申请号：US14700504
申请日：2015-04-30
申请人： WorldVu Satellites Limited
发明人： Daniel W. Field , Armen Askijian , James Grossman , Alexander D. Smith
IPC分类号： B64G1/64 , B64G1/24
CPC分类号： B64G1/641 , B64G1/007 , B64G1/40 , B64G1/402 , B64G1/503 , B64G1/645 , B64G1/66 , B64G2001/643
摘要： A satellite deployment system has a plurality of releasable dispenser modules that are attached to each other with each module carrying satellites. Each dispenser module acts as an individual final stage with its own propulsion unit and deploys a subset of satellites to the appropriate altitude and orbit. Since each dispenser module can deploy its satellites far from other dispenser modules, the risk of collision among the satellites is greatly reduced, which allows a large number of satellites to be launched in a safe, timely and cost-effective manner.
摘要翻译：卫星部署系统具有多个可释放的分配器模块，每个模块携带卫星，彼此相连。每个分配器模块充当具有其自己的推进单元的单独的最终级，并将一部分卫星部署到适当的高度和轨道。由于每个分配器模块可以将其卫星远离其他分配器模块，所以卫星之间的碰撞风险大大降低，这样可以以安全，及时和成本有效的方式启动大量的卫星。

6. 发明授权

US09463882B1 System and method for assembling and deploying satellites 有权
标题翻译：组装和部署卫星的系统和方法
公开(公告)号：US09463882B1
公开(公告)日：2016-10-11
申请号：US14700504
申请日：2015-04-30
申请人： WorldVu Satellites Limited
发明人： Daniel W. Field , Armen Askijian , James Grossman , Alexander D. Smith
IPC分类号： G01C23/00 , G05D1/00 , G05D3/00 , G06F7/00 , G06F17/00 , B64G1/64 , B64G1/24
CPC分类号： B64G1/641 , B64G1/007 , B64G1/40 , B64G1/402 , B64G1/503 , B64G1/645 , B64G1/66 , B64G2001/643
摘要： A satellite deployment system has a plurality of releasable dispenser modules that are attached to each other with each module carrying satellites. Each dispenser module acts as an individual final stage with its own propulsion unit and deploys a subset of satellites to the appropriate altitude and orbit. Since each dispenser module can deploy its satellites far from other dispenser modules, the risk of collision among the satellites is greatly reduced, which allows a large number of satellites to be launched in a safe, timely and cost-effective manner.
摘要翻译：卫星部署系统具有多个可释放的分配器模块，每个模块携带卫星，彼此相连。每个分配器模块充当具有其自己的推进单元的单独的最终级，并将一部分卫星部署到适当的高度和轨道。由于每个分配器模块可以将其卫星远离其他分配器模块，所以卫星之间的碰撞风险大大降低，这样可以以安全，及时和成本有效的方式启动大量的卫星。

7. 发明申请

US20160046394A1 METHODS AND APPARATUS FOR PERFORMING PROPULSION OPERATIONS USING ELECTRIC PROPULSION SYSTEMS 有权
标题翻译：使用电动推进系统执行推进操作的方法和装置
公开(公告)号：US20160046394A1
公开(公告)日：2016-02-18
申请号：US14828462
申请日：2015-08-17
申请人： The Boeing Company
发明人： James J. Peterka, III , Glenn N. Caplin , Richard W. Aston
IPC分类号： B64G1/24 , B64G1/40 , B64G1/00 , B64G1/26 , B64G1/10
CPC分类号： B64G1/242 , B64G1/002 , B64G1/007 , B64G1/10 , B64G1/26 , B64G1/283 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/40 , B64G1/402 , B64G1/405 , B64G1/422 , B64G1/428 , B64G1/44 , B64G1/503 , B64G1/641 , B64G2001/643
摘要： Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.
摘要翻译：公开了使用电推进系统执行推进操作的方法和装置的方法和装置。示例性方法包括部署包括电推进系统的空间车辆; 并采用电动推进系统进行姿态控制和轨道控制，无需提供其他推进系统，实现姿态控制和轨道控制。

8. 发明申请

US20160001898A1 SPACE PROPULSION MODULE HAVING BOTH ELECTRIC AND SOLID FUEL CHEMICAL PROPULSION 审中-公开
标题翻译：具有电动和固体燃料化学推进剂的空间推进模块
公开(公告)号：US20160001898A1
公开(公告)日：2016-01-07
申请号：US14770329
申请日：2014-02-26
申请人： SNECMA , HERAKLES
发明人： Olivier Bernard Duchemin , Dominique Indersie , Pascal Benoit Caubet , Pierre Yvart
IPC分类号： B64G1/40 , F02K9/76
CPC分类号： B64G1/404 , B64G1/007 , B64G1/403 , B64G1/405 , B64G1/641 , F02K9/08 , F02K9/76 , F03H1/0075
摘要： A space propulsion module in particular for fitting to spacecraft such as satellites, probes, or indeed the upper stages of rockets. According to the invention, the space propulsion module comprises a solid propellant chemical thruster (10) having a main body (11), and at least one electric thruster (30), said at least one electric thruster (30) being mounted on said main body (11) of the solid propellant chemical thruster (10).
摘要翻译：空间推进模块，特别适用于诸如卫星，探测器或实际上火箭上段的航天器。根据本发明，空间推进模块包括具有主体（11）的固体推进剂化学推进器（10）和至少一个电推进器（30），所述至少一个电推进器（30）安装在所述主体固体推进剂化学推进器（10）的主体（11）。

9. 发明授权

US09108748B2 Satellite orbit raising using electric propulsion 有权
标题翻译：使用电力推进卫星轨道提升
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
IPC分类号： B64G1/24 , B64G1/00 , B64G1/40 , B64G1/36
CPC分类号： B64G1/007 , B64G1/24 , B64G1/36 , B64G1/361 , B64G1/405
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。

10. 发明申请

US20150210407A1 LIFTING ENTRY/ATMOSPHERIC FLIGHT (LEAF) UNIFIED PLATFORM FOR ULTRA-LOW BALLISTIC COEFFICIENT ATMOSPHERIC ENTRY AND MANEUVERABLE ATMOSPHERIC FLIGHT AT SOLAR SYSTEM BODIES 审中-公开
标题翻译：提升进入/大气飞行（LEAF）统一的平台，用于超低温度系统大气入口和可转换的太阳系系统大气层飞行
公开(公告)号：US20150210407A1
公开(公告)日：2015-07-30
申请号：US14297370
申请日：2014-06-05
申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION
发明人： KRISTEN S. GRIFFIN , JON CARPENTER , GREGORY J. LEE , AMY LO , RONALD POLIDAN , DANIEL SOKOL , BARNABY WAINFAN , WARREN JAMES , DENNIS POULOS
IPC分类号： B64G1/62 , B64B1/12 , B64B1/24 , B64B1/20
CPC分类号： B64G1/62 , B64B1/12 , B64B1/20 , B64B1/24 , B64B2201/00 , B64D2211/00 , B64G1/007 , B64G1/242 , B64G2001/1064 , B64G2001/224 , Y02T50/55
摘要： An aerial vehicle including a collapsible and inflatable vehicle body capable of being filled with a lighter than air gas so as to make the vehicle semi-buoyant or 100% buoyant at a predetermined altitude in an atmosphere above a solar system body. The vehicle body has a shape suitable to provide aerodynamic lift. The vehicle may include a propulsion device coupled to and extending from the vehicle body, where the device provides power to aerodynamically lift the vehicle above the 100% buoyant altitude to a higher altitude where the vehicle can maintain that altitude through the aerodynamic lift and vehicle buoyancy. The vehicle is configured to be deployed/inflated from a collapsed and stowed configuration to a deployed/inflated configuration in an orbit above the atmosphere of the solar system body, and is configured to enter the atmosphere in the inflated configuration and descend without propulsion.
摘要翻译：一种飞行器，其包括可折叠且可充气的车身，其能够充满比空气更轻的车辆，以使得车辆在太阳系体上方的气氛中在预定高度上半浮力或100％浮力。车体具有适于提供气动升力的形状。车辆可以包括联接到车身并从车身延伸的推进装置，其中该装置提供动力以将车辆空气动力地提升到高于100％浮力高度的高度，其中车辆可以通过空气动力升力和车辆浮力保持高度。车辆被构造成从塌陷和收起的构造展开/充气到位于太阳系体内的空气上方的轨道上的展开/膨胀构造，并且被构造成以膨胀构型进入大气并且不推动下降。

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