专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

21. 发明授权

US09180985B1 Nuclear thermal propulsion rocket engine 有权
标题翻译：核热力推进火箭发动机
公开(公告)号：US09180985B1
公开(公告)日：2015-11-10
申请号：US14692349
申请日：2015-04-21
申请人： Richard Hardy , Jonathan Hardy
发明人： Richard Hardy , Jonathan Hardy
IPC分类号： F03H99/00 , B64G1/40 , F02K7/08
CPC分类号： B64G1/40 , B64G1/408 , B64G1/409 , F02K7/08 , F02K9/42 , F03H99/00 , F05D2210/12
摘要： A fission based nuclear thermal propulsion rocket engine. An embodiment provides a source of fissionable material such as plutonium in a carrier gas such as deuterium. A neutron source is provided, such as from a neutron beam generator. By way of engine design geometry, various embodiments may provide for intersection of neutrons with the fissionable material injected by way of the carrier gas, while in a reactor provided in the form of a reaction chamber. Impact of neutrons on fissionable material results in a nuclear fission in sub-critical mass reaction conditions in the reactor, resulting in release of heat energy to the materials within the reactor. The reactor is sized and shaped to receive the reactants and an expandable fluid such as hydrogen, and to confine heated and pressurized gases for discharge out through a throat, into a rocket engine expansion nozzle for propulsive discharge.
摘要翻译：基于裂变的核热推进火箭发动机。一个实施例提供了诸如氘等载气中的可裂变材料的来源，例如钚。提供中子源，例如来自中子束发生器。通过发动机设计几何形状，各种实施例可以提供中子与通过载气注入的可裂变材料的交点，而在以反应室形式提供的反应器中。中子对可裂变材料的影响导致反应堆中亚临界质量反应条件下的核裂变，导致热能释放到反应器内的材料。反应器的尺寸和形状被设计成接收反应物和可膨胀流体例如氢，并且将加热和加压的气体限制通过喉部排放到用于推进排放的火箭发动机膨胀喷嘴中。

22. 发明申请

US20150204273A1 ROCKET STAGE AND METHOD OF IMPROVING AN EXISTING ROCKET STAGE 有权
标题翻译：摇摆舞台和改进现有摇滚舞台的方法
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
IPC分类号： F02K9/60 , F02K9/96 , B64G1/00
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。

23. 发明申请

US20150152812A1 VAPOR JETTING DEVICE AND SPACECRAFT 有权
标题翻译：蒸气喷射装置和空间
公开(公告)号：US20150152812A1
公开(公告)日：2015-06-04
申请号：US14617341
申请日：2015-02-09
申请人： IHI Corporation , IHI AEROSPACE CO., LTD.
发明人： Taku IZUMIYAMA , Hatsuo MORI , Kozue HASHIMOTO , Toru NAGAO
IPC分类号： F02K7/02 , B64G1/26
CPC分类号： F02K7/02 , B64G1/26 , B64G1/40 , F02K9/44 , F02K9/94 , F05D2210/12
摘要： Provided is a vapor jetting device including: a box-shaped casing; a propellant holding unit that is placed in the casing and forms a space for holding a propellant; a gas storing unit that is placed in the casing, forms a space that is divided from the propellant holding unit by a partition wall including a communication hole, and stores gas; a machine housing unit that is placed in the casing, forms a space that is divided from the propellant holding unit and the gas storing unit by partition walls, and houses machines; a nozzle that is connected to the casing and ejects the gas to an outside; a gas flow path that is formed in the casing and supplies the gas stored in the gas storing unit to the nozzle; and a heater that is placed in the casing and heats at least the gas storing unit.
摘要翻译：本发明提供一种蒸汽喷射装置，包括：箱形壳体; 推进剂保持单元，其放置在壳体中并形成用于保持推进剂的空间; 放置在壳体内的气体存储单元形成通过包括连通孔的隔壁与推进剂保持单元分隔开的空间，并储存气体; 放置在壳体内的机器壳体单元通过分隔壁形成与推进剂保持单元和气体存储单元分开的空间，并容纳机器; 连接到壳体并将气体喷射到外部的喷嘴; 气体流路，其形成在所述壳体中，并将储存在所述气体存储单元中的气体供给到所述喷嘴; 以及放置在壳体中并加热至少气体存储单元的加热器。

24. 发明授权

US08876061B1 Methods and systems for beam powered propulsion 有权
标题翻译：梁式动力推进方法与系统
公开(公告)号：US08876061B1
公开(公告)日：2014-11-04
申请号：US13297893
申请日：2011-11-16
申请人： Brian J. Tillotson
发明人： Brian J. Tillotson
IPC分类号： B64G1/40 , B64G1/44 , F03H1/00 , C06D5/00 , F02K9/64 , F01K27/00 , F01K15/00
CPC分类号： B64G1/40 , F02K9/00
摘要： A method for producing a heated fluid for use within an engine for propulsion of a vehicle is described. The method includes receiving cooled fluid from a fluid source, directing the cooled fluid between a first window configured to operate as a structural member of the engine and a second window configured to separate the cooled fluid from a heated fluid, passing an electromagnetic beam through the first window and the second window, absorbing the passed electromagnetic beam with a heat exchanger within the engine, and directing the cooled fluid through the heat exchanger to become heated fluid.
摘要翻译：描述了用于在用于车辆推进的发动机内使用的加热流体的制造方法。该方法包括从流体源接收冷却的流体，将被冷却的流体引导至构造成作为发动机的结构构件操作的第一窗口和被构造成将冷却的流体与加热流体分离的第二窗口，第一窗口和第二窗口，用发动机内的热交换器吸收通过的电磁波束，并将冷却的流体引导通过热交换器以变成加热流体。

25. 发明申请

US20140139152A1 ELECTRIC ACTUATOR DRIVE DEVICE AND ACTUATOR USING SAME 审中-公开
标题翻译：电动执行器驱动装置和执行器使用相同
公开(公告)号：US20140139152A1
公开(公告)日：2014-05-22
申请号：US14122127
申请日：2012-04-05
申请人： IHI AEROSPACE CO. LTD.
发明人： Hitoshi Oyori , Masaya Wakita , Yukio Shimomura
IPC分类号： H02P3/14
CPC分类号： H02P3/14 , B64G1/40 , B64G1/66 , H02P3/18 , H02P27/06 , H02P29/0241
摘要： To bring an actuator driving motor having a malfunction such as failure to a stop in a shorter time without employing a mechanical braking system. The present invention is an electric actuator driver, including: a power supply; an actuator driving motor (11A, 11B) to be supplied with power from the power supply to drive an actuator (B1); a motor braking circuit (C) to apply a regenerative brake on the actuator driving motor (11A, 11B); a malfunction occurrence determining means (D1) to determine whether there is a malfunction in a necessary component; and a regenerative braking means (D3) to apply the regenerative brake on the actuator driving motor (11A, 11B) by means of the motor braking circuit (C).
摘要翻译：在不使用机械制动系统的情况下，使具有故障的致动器驱动电动机在较短时间内发生故障。本发明是一种电动执行器驱动器，包括：电源; 致动器驱动电动机（11A，11B），从电源供给动力以驱动致动器（B1）; 在所述致动器驱动电动机（11A，11B）上施加再生制动的电动机制动回路（C）; 故障发生确定装置（D1），用于确定是否存在必要部件中的故障; 以及通过马达制动电路（C）将再生制动施加在致动器驱动马达（11A，11B）上的再生制动装置（D3）。

26. 发明授权

US08727284B2 Turbine powered electromechanical actuation system 有权
标题翻译：涡轮动力机电驱动系统
公开(公告)号：US08727284B2
公开(公告)日：2014-05-20
申请号：US12692269
申请日：2010-01-22
申请人： David G. Hill
发明人： David G. Hill
IPC分类号： B64G1/40
CPC分类号： H02P29/00 , B64G1/40 , B64G1/421 , F01D17/24 , F02K9/805
摘要： An electromechanical actuation system (10) for a space vehicle includes a propellant source (18) and at least one turbine (14) operably connected to the propellant source (18) and rotatable by a flow of propellant (16) therefrom. At least one electrical generator (20) is operably connected to the at least one turbine (14) and is configured to convert rotation of the turbine (14) into electrical energy. At least one electromechanical actuator (12) is operably connected to the at least one electrical generator (20) such that electrical energy from the at least one electrical generator (20) drives operation of the at least one electromechanical actuator (12). A method of operating a turbine powered electromechanical actuator (12) for a space vehicle includes rotating the at least one turbine (14) via a flow of propellant (16) therethrough. Electrical energy is generated in at least one electrical generator (20) operably connected to the at least one turbine (14) and the electromechanical actuator (12) is operated with the electrical energy generated therein.
摘要翻译：用于空间飞行器的机电致动系统（10）包括推进剂源（18）和可操作地连接到推进剂源（18）并且可由其中的推进剂流（16）旋转的至少一个涡轮机（14）。至少一个发电机（20）可操作地连接到所述至少一个涡轮机（14）并被构造成将涡轮机（14）的旋转转换成电能。至少一个机电致动器（12）可操作地连接到所述至少一个发电机（20），使得来自所述至少一个发电机（20）的电能驱动所述至少一个机电致动器（12）的操作。操作用于空间飞行器的涡轮机动力机电致动器（12）的方法包括经由推进剂流（16）从其中旋转所述至少一个涡轮机（14）。在能够与至少一个涡轮机（14）可操作地连接的至少一个发电机（20）中产生电能，并且机电致动器（12）与其中产生的电能一起工作。

27. 发明授权

US08727283B2 Launch abort and orbital maneuver system 有权
标题翻译：发射中止和轨道机动系统
公开(公告)号：US08727283B2
公开(公告)日：2014-05-20
申请号：US13154873
申请日：2011-06-07
申请人： Dennis E. Morris , Alfred Little
发明人： Dennis E. Morris , Alfred Little
IPC分类号： B64G1/40
CPC分类号： B64G1/40 , B64G1/002 , B64G1/12 , B64G1/62
摘要： A spacecraft includes a first engine configured to provide primary launch abort thrust and a second engine disposed radially from a center of gravity, the second engine configured to provide a secondary launch abort thrust, a primary orbital maneuvering thrust, and a primary control thrust.
摘要翻译：航天器包括被配置为提供主要发射中止推力的第一引擎和从重心径向设置的第二引擎，所述第二引擎被配置为提供次级发射中止推力，主轨道机动推力和主控制推力。

28. 发明申请

US20140053531A1 METALLIC WALL HALL THRUSTERS 有权
标题翻译：金属墙壁锤
公开(公告)号：US20140053531A1
公开(公告)日：2014-02-27
申请号：US13768788
申请日：2013-02-15
申请人： Dan Michael Goebel , Richard Robert Hofer , Ioannis G. Mikellides
发明人： Dan Michael Goebel , Richard Robert Hofer , Ioannis G. Mikellides
IPC分类号： F03H1/00
CPC分类号： F03H1/0075 , B64G1/40 , B64G1/405 , F03H1/00 , F03H1/0012 , F03H1/0037 , F03H1/0062 , F03H1/0068 , F03H1/0081
摘要： A Hall thruster apparatus having walls constructed from a conductive material, such as graphite, and having magnetic shielding of the walls from the ionized plasma has been demonstrated to operate with nearly the same efficiency as a conventional non-magnetically shielded design using insulators as wall components. The new design is believed to provide the potential of higher power and uniform operation over the operating life of a thruster device.
摘要翻译：已经证明具有由诸如石墨的导电材料构成的壁并且具有壁与电离等离子体的磁屏蔽的霍尔推进器设备以与使用绝缘体作为壁部件的常规非磁屏蔽设计几乎相同的效率来运行。相信这种新设计可以在推进器装置的使用寿命内提供更高功率和统一的操作的潜力。

29. 发明申请

US20120312927A1 LAUNCH ABORT AND ORBITAL MANEUVER SYSTEM 有权
标题翻译：发起人和ORBITAL MANEUVER系统
公开(公告)号：US20120312927A1
公开(公告)日：2012-12-13
申请号：US13154873
申请日：2011-06-07
申请人： Dennis E. Morris , Alfred Little
发明人： Dennis E. Morris , Alfred Little
IPC分类号： B64G1/40
CPC分类号： B64G1/40 , B64G1/002 , B64G1/12 , B64G1/62
摘要： A spacecraft includes a first engine configured to provide primary launch abort thrust and a second engine disposed radially from a center of gravity, the second engine configured to provide a secondary launch abort thrust, a primary orbital maneuvering thrust, and a primary control thrust.
摘要翻译：航天器包括被配置为提供主要发射中止推力的第一引擎和从重心径向设置的第二引擎，所述第二引擎被配置为提供次级发射中止推力，主轨道机动推力和主控制推力。

30. 发明授权

US08056863B2 Unified attitude control for spacecraft transfer orbit operations 有权
标题翻译：航天器转移轨道作战统一态度控制
公开(公告)号：US08056863B2
公开(公告)日：2011-11-15
申请号：US12611658
申请日：2009-11-03
申请人： H. Grant Wang , Rongsheng Li
发明人： H. Grant Wang , Rongsheng Li
IPC分类号： B64G1/24
CPC分类号： B64G1/281 , B64G1/00 , B64G1/007 , B64G1/10 , B64G1/24 , B64G1/242 , B64G1/26 , B64G1/28 , B64G1/283 , B64G1/285 , B64G1/288 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/40 , B64G1/401 , B64G1/405 , B64G1/44 , B64G1/443 , G01C21/02 , G01C21/025 , G05D1/08 , G05D1/0883
摘要： A method of controlling attitude of a spacecraft during a transfer orbit operation is provided. The method includes providing a slow spin rate, determining the attitude of the spacecraft using a unified sensor set, and controlling the attitude of the spacecraft using a unified control law. The use of a unified set of sensors and a unified control law reduces spacecraft complexity, cost, and weight.
摘要翻译：提供了一种在转移轨道操作期间控制航天器姿态的方法。该方法包括提供缓慢的旋转速率，使用统一的传感器组来确定航天器的姿态，并使用统一的控制律来控制航天器的姿态。使用统一的传感器和统一的控制规则可以降低航天器的复杂性，成本和重量。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式