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公开(公告)号：US20160194089A1
公开(公告)日：2016-07-07
申请号：US14322752
申请日：2014-07-02
摘要： Attitude and/or attitude rate of a vehicle may be controlled using jet paddles and/or movable masses. Thrust direction generally may also be controlled using jet paddles. The jet paddles may be moved into and/or sufficiently close to the exhaust flow, and out of the exhaust flow, to change the thrust direction. Movable masses may also be used in addition to, or in lieu of, jet paddles. Movement of the movable masses alters a center-of-mass of the vehicle, generating torque that changes vehicle attitude.
摘要翻译： 可以使用喷射桨和/或移动质量块来控制车辆的姿态和/或姿态速率。 推力方向一般也可以使用喷射桨来控制。 喷射桨可以移动到和/或足够靠近排气流并且排出排气流，以改变推力方向。 除了或代替喷射桨之外，还可以使用活动的质量块。 可移动质量块的移动改变车辆的质心，产生改变车辆姿态的转矩。
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公开(公告)号：US20160114908A1
公开(公告)日：2016-04-28
申请号：US14921984
申请日：2015-10-23
申请人： Airbus DS GmbH
发明人： Ulrich KNIRSCH , Matti HAEBERLEIN
CPC分类号： B64G1/405 , B64G1/26 , F02K9/84 , F02K9/90 , F03H1/0006
摘要： An electrically powered propulsion system for a spacecraft includes a first center of gravity at a first time of operation and a second center of gravity at a second time of operation, where the second center of gravity is different from the first center of gravity. The electrically powered propulsion system includes a thruster realignment mechanism and at least two thrusters coupled to the thruster realignment mechanism. Each of the at least two thrusters has an individual thrust vector. The thruster realignment mechanism is adapted such that, in a first position, the individual thrust vectors of the at least two thrusters pass through the first center of gravity and that, in a second position, the individual thrust vectors of the at least two thrusters pass through the second center of gravity. The thruster realignment mechanism holds the first position in the event all of the at least two thrusters are without any failure. In addition, the thruster realignment mechanism realigns the thrusters to the second position in the event of at least one of (i) a failure of one of the at least two thrusters, and (ii) a predetermined time criterion is fulfilled.
摘要翻译： 一种用于航天器的电动推进系统在第一次操作时包括第一重心和在第二次操作时的第二重心，其中第二重心与第一重心不同。 电动推进系统包括推进器重新对准机构和联接到推进器重新对准机构的至少两个推进器。 至少两个推进器中的每个具有单独的推力矢量。 推进器重新对准机构被适配成使得在第一位置中，至少两个推进器的各个推力向量通过第一重心，并且在第二位置，至少两个推进器的各个推力向量通过 通过第二个重心。 在所有至少两个推进器没有任何故障的情况下，推进器重新对准机构保持第一位置。 另外，在（i）至少两个推进器之一的故障中的至少一个，以及（ii）满足预定时间标准中的至少一个的情况下，推进器重新对准机构将推进器重新对准第二位置。
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公开(公告)号：US20110083418A1
公开(公告)日：2011-04-14
申请号：US12903504
申请日：2010-10-13
申请人： Helmut Ciezki , Ralf Stark
发明人： Helmut Ciezki , Ralf Stark
IPC分类号： F02K9/90
CPC分类号： F42B10/64 , F02K9/90 , F42B10/665
摘要： In order to provide a flying object with an engine comprising a combustion chamber with a combustion space and a nozzle with a nozzle space following the combustion chamber, the transition between combustion chamber and nozzle lying in a plane in which a cross-section of the combustion space converges, in which thrust control in terms of magnitude and/or thrust vector can be carried out in a simple manner, it is provided that a centre body adapted to have combustion products flowing around it is at least partially arranged in the nozzle space, outside of the combustion space, and at least three jet vanes are arranged at the centre body.
摘要翻译： 为了提供具有发动机的飞行物体，发动机包括具有燃烧空间的燃烧室和具有跟随燃烧室的喷嘴空间的喷嘴，燃烧室和喷嘴之间的过渡位于其中燃烧截面的平面中 空间会聚，其中以幅度和/或推力矢量为基础的推力控制可以以简单的方式进行，其中，适于具有围绕其流动的燃烧产物的中心体至少部分地布置在喷嘴空间中， 在燃烧空间外部，并且至少三个喷射叶片布置在中心体。
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公开(公告)号：US20100327108A1
公开(公告)日：2010-12-30
申请号：US12745177
申请日：2008-11-21
申请人： Marco Prampolini
发明人： Marco Prampolini
摘要： An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.
摘要翻译： 用于在飞行器后部配备有至少一个火箭发动机的航天器的后体装置包括设计成采取第一位置的至少一个可移动盖元件，掩蔽并减少车辆的后阻力，其中至少延长了车辆的机身 车辆的火箭发动机喷嘴的一部分并且延伸超出车辆机身的后部，并且进行完全展开的第二位置，增加车辆的空气动力学阻力。
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公开(公告)号：US20070119151A1
公开(公告)日：2007-05-31
申请号：US11287297
申请日：2005-11-28
IPC分类号： F02K1/00
CPC分类号： F02K1/002 , F02K1/1207 , F02K9/90 , F05D2240/12
摘要： A nozzle assembly for thrust or thrust vector control of a rocket or ramjet, comprising an elongated nozzle housing and a pair of vane members mounted for pivotal movement within a central portion of the nozzle housing. The vane members extend vertically or transversely between the upper and lower portions of the nozzle housing near the forward portion thereof, and extend longitudinally in the nozzle housing from the forward end portion thereof to a point near the rear end portion thereof. The vane members are pivotable about axes disposed between the forward and rear ends thereof, and are movable between an open position wherein they are in substantially parallel relation and a closed position wherein their forward ends are in engagement with each other and their rear ends are in engagement with the adjacent inner surface of the nozzle housing. An operating mechanism is operatively connected to the vane members to move them simultaneously or individually between the open and closed positions for thrust control or thrust vector control.
摘要翻译： 一种用于火箭或冲压式喷气发动机的推力或推力矢量控制的喷嘴组件，包括细长喷嘴壳体和安装成在喷嘴壳体的中心部分内枢转运动的一对叶片构件。 叶片构件在其前部附近在喷嘴壳体的上部和下部之间垂直或横向延伸，并且在喷嘴壳体中从其前端部纵向延伸到靠近其后端部分的点。 叶片构件可围绕设置在其前端和后端之间的轴线枢转，并且可在其基本平行的关闭位置和关闭位置之间移动，其中它们的前端彼此接合并且其后端处于 与喷嘴壳体的相邻内表面接合。 操作机构可操作地连接到叶片构件，以在打开和关闭位置之间同时或单独地移动它们，用于推力控制或推力矢量控制。
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公开(公告)号：US20050017132A1
公开(公告)日：2005-01-27
申请号：US10712656
申请日：2003-11-13
申请人： Charl Janeke
发明人： Charl Janeke
CPC分类号： B64G1/40 , B64G1/002 , B64G1/401 , F02K9/82 , F02K9/90 , F02K9/97 , F05D2240/1281 , F05D2260/2212
摘要： A space plane including a main body, an aerospike engine attached to the main body, and a bell-shaped nozzle primary thrust engine attached to the main body.
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公开(公告)号：US06648275B2
公开(公告)日：2003-11-18
申请号：US09829043
申请日：2001-04-09
申请人： Charl E. Janeke
发明人： Charl E. Janeke
IPC分类号： B64G140
CPC分类号： B64G1/40 , B64G1/002 , B64G1/401 , F02K9/82 , F02K9/90 , F02K9/97 , F05D2240/1281 , F05D2260/2212
摘要： A linear aerospike rocket engine has a tapered body, a slanted or curved reaction plane, a leading end, and a trailing end. A first fuel injector is located at the leading end and directs a first fuel towards the reaction plane. A second fuel injector is located in between the leading end and trailing end and directs a second fuel towards the reaction plane. The second fuel injector helps to increase propulsive pressure across the reaction plane and inhibit boundary layer separation. A vortex may be induced parallel to the reaction plane to help increase propulsive pressure across the reaction plane. The vortex is induced using a flap or spoiler, a rotatable turbine, or at least two fuel injectors that direct fuel in counter current directions across the reaction plane. The reaction plane may be corrugated, dimpled, grooved, or coated with a special material to inhibit boundary layer separation from the reaction plane.
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公开(公告)号：US06548794B2
公开(公告)日：2003-04-15
申请号：US09804897
申请日：2001-03-13
IPC分类号： F42B1000
CPC分类号： F42B10/665 , F02K9/90 , F02K9/974 , F05C2225/08 , F05D2230/90 , F05D2300/21 , F05D2300/224 , F05D2300/433 , F05D2300/434 , F05D2300/44 , F05D2300/603 , F05D2300/611 , F05D2300/702
摘要： A dissolvable jet vane (22/30) is a composite structure, having a support frame (38), a plug leading edge (40) connected to the forward edge (42) of the frame (38), and an insulation layer (44) on the side walls of the support frame (38). The dissolvable jet vane materials withstand the pressure and thermal loads associated with missile steering during the first few seconds of rocket boost until the missile attains sufficient speed to use conventional external aerodynamic control fins for steering control. Once control passes to the external fins, the jet vanes rapidly and uniformly dissolve in the exhaust stream. The dissolvable jet vane provides a lightweight, reliable means of removing steering jet vanes from the exhaust stream of a solid rocket motor nozzle.
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9.发明授权Apparatus and method for controlling the motion of a solid body or fluid stream 失效用于控制固体或流体流的运动的装置和方法公开(公告)号：US06250586B1
公开(公告)日：2001-06-26
申请号：US09091753
申请日：1998-06-24
申请人： Avi Seifert , Israel Wygnanski
发明人： Avi Seifert , Israel Wygnanski
IPC分类号： B64B136
CPC分类号： F02K9/90 , F02K9/80 , F02K9/82 , F42B10/66 , F42B10/665
摘要： This invention discloses a fluid dynamic system including a fluid medium separated from a solid medium by a solid boundary, one of which media is moving with respect to the other, apparatus for controlling the motion of the moving medium, comprising, a perturbation-producing element at solid boundary, and a drive for cyclically driving the perturbation-producing element to produce cyclical fluid perturbations in the fluid medium sufficient to alter the motion of the moving medium. A method for including a fluid medium separated from a solid medium by a solid boundary in a fluid dynamic system is also disclosed.
摘要翻译： 本发明公开了一种流体动力学系统，其包括通过固体边界从固体介质分离的流体介质，其中一个介质相对于另一个介质移动，用于控制移动介质的运动的装置，包括扰动产生元件 以及用于循环驱动扰动产生元件以在流体介质中产生足以改变移动介质的运动的循环流体扰动的驱动器。 还公开了一种用于在流体动力系统中包括通过固体边界从固体介质分离的流体介质的方法。
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公开(公告)号：US3786993A
公开(公告)日：1974-01-22
申请号：US3786993D
申请日：1972-05-22
CPC分类号： F02K9/90
摘要： Thrust vector control system for a rocket motor comprising at least one spoiler blade pivotally mounted adjacent the exit end of the motor nozzle, the blade comprising an exhaust gas impingement element of refractory metallic material, a rigid metallic support, and an interposed layer of heat insulating material.
摘要翻译： 用于火箭发动机的推力矢量控制系统包括至少一个靠近电动机喷嘴的出口端可枢转地安装的扰流板，该叶片包括耐火金属材料的废气冲击元件，刚性金属支撑件和隔热层 材料。
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