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公开(公告)号：US08016211B2
公开(公告)日：2011-09-13
申请号：US12041810
申请日：2008-03-04
申请人： Dustin C. Barr , Michael D. Lynch
发明人： Dustin C. Barr , Michael D. Lynch
IPC分类号： B63H11/10
CPC分类号： F02K9/86 , F01D17/141 , F02K9/97 , F05D2250/41 , F05D2250/411 , F05D2260/96
摘要： A propulsion system with a divergent-convergent nozzle is provided with variable thrust by a pintle whose position relative to the nozzle throat is controlled by an actuator that includes a rotor that external to, and encircling, the nozzle, and that is coupled to either the pintle or to the nozzle shell by a linkage that translates the rotary movement of the rotor into linear movement of either the pintle or the shell.
摘要翻译： 具有发散会聚喷嘴的推进系统由枢轴提供可变的推力，枢轴相对于喷嘴喉部的位置由致动器控制，该致动器包括在喷嘴外部和环绕喷嘴的转子，并且其连接到 枢轴或通过将转子的旋转运动转换为枢轴或壳体的线性运动的联动件连接到喷嘴壳体。
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公开(公告)号：US20090230212A1
公开(公告)日：2009-09-17
申请号：US12041810
申请日：2008-03-04
申请人： Dustin C. Barr , Michael D. Lynch
发明人： Dustin C. Barr , Michael D. Lynch
IPC分类号： F02K1/00
CPC分类号： F02K9/86 , F01D17/141 , F02K9/97 , F05D2250/41 , F05D2250/411 , F05D2260/96
摘要： A propulsion system with a divergent-convergent nozzle is provided with variable thrust by a pintle whose position relative to the nozzle throat is controlled by an actuator that includes a rotor that external to, and encircling, the nozzle, and that is coupled to either the pintle or to the nozzle shell by a linkage that translates the rotary movement of the rotor into linear movement of either the pintle or the shell.
摘要翻译： 具有发散会聚喷嘴的推进系统由枢轴提供可变的推力，枢轴相对于喷嘴喉部的位置由致动器控制，该致动器包括在喷嘴外部和环绕喷嘴的转子，并且其连接到 枢轴或通过将转子的旋转运动转换为枢轴或壳体的线性运动的联动件连接到喷嘴壳体。
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83.发明申请Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles 审中-公开用于改变火箭发动机和发动机的推力的系统和方法，同时使用可移动的塞子喷嘴保持更高的效率公开(公告)号：US20090211225A1
公开(公告)日：2009-08-27
申请号：US11699617
申请日：2007-01-29
申请人： Donald Gerrit Nyberg , Thomas Adrian Groudle , Richard Doyle Smith , John A. Shuba , Richard T. Smith
发明人： Donald Gerrit Nyberg , Thomas Adrian Groudle , Richard Doyle Smith , John A. Shuba , Richard T. Smith
摘要： The thrust of a rocket motor can be varied to optimize Nozzle Pressure Ratio (NPR) using a design that allows for adjusting the relative position of a plug and a combustion chamber exit. The plug or the exit may be attached to an adaptive control system for position modification. The relative position of the plug and exit may be adjusted to optimize NPR to account for changing propellant flow and/or changing ambient pressure.
摘要翻译： 可以改变火箭发动机的推力，以使用允许调节塞子和燃烧室出口的相对位置的设计来优化喷嘴压力比（NPR）。 插头或出口可以附接到自适应控制系统以进行位置修改。 可以调整插塞和出口的相对位置以优化NPR以考虑改变推进剂流动和/或改变环境压力。
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公开(公告)号：US07509796B2
公开(公告)日：2009-03-31
申请号：US11531655
申请日：2006-09-13
申请人： William E. Hansen
发明人： William E. Hansen
IPC分类号： F02K1/08
CPC分类号： F02K9/30 , F02K9/26 , F02K9/32 , F02K9/86 , G05D7/0635
摘要： A propulsion system with a pintle for variable thrust is constructed such that the pintle contains a shaft at its fore end which passes through an opening in the thrust chamber wall and extends into a boss on the outside surface of the thrust chamber. A dynamic seal that maintains the pressurization of the thrust chamber while allowing movement of the pintle is positioned inside the boss, between the pintle shaft and the boss, and actuation of the pintle is achieved by a rack affixed to the fore end of the pintle and a gear that engages the rack. The dynamic seal, rack and gear are thus external to the thrust chamber, providing the thrust chamber with a compact external envelope, a greater thermal standoff, or both.
摘要翻译： 具有用于可变推力的枢轴的推进系统被构造成使得枢轴在其前端处包含轴，该轴穿过推力室壁中的开口并且延伸到推力室的外表面上的凸台中。 保持推力室的加压同时允许枢轴运动的动态密封件定位在凸台内部，在枢轴和凸台之间，并且枢轴的致动通过固定到枢轴的前端的齿条实现，并且 一个啮合机架的齿轮。 因此，动态密封件，齿条和齿轮在推力室外部，为推力室提供紧凑的外壳，更大的散热间隔或两者。
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公开(公告)号：US07287725B2
公开(公告)日：2007-10-30
申请号：US11113511
申请日：2005-04-25
IPC分类号： B64C1/24
CPC分类号： F42B10/666 , F02K9/30 , F02K9/805 , F02K9/86 , F05D2240/128 , F05D2250/323 , F05D2250/324 , F05D2250/41 , F05D2260/60 , F16K3/085 , F42B10/663
摘要： A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.
摘要翻译： 导弹包括具有转向和姿态控制系统推进器的控制系统，其具有控制阀。 每个控制阀具有在其中具有多个小喷嘴的喷嘴板。 喷嘴板包括一对部分，其中一个部分可相对于另一个部分旋转。 通过喷嘴板的流动的控制可以通过喷嘴板的部分的相对定位来实现。 喷嘴板的上游收敛部分可以相对于导弹固定，喷嘴板的下游喉部和/或发散部分可移动。 可以通过使用在导弹体外部的致动器来实现喷嘴板的可移动部分的移动。 控制阀提供了一种控制来自转向推进器的流量的简单，轻便和紧凑的方式。
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公开(公告)号：US06227247B1
公开(公告)日：2001-05-08
申请号：US09501701
申请日：2000-02-10
申请人： Stephen G. Abel
发明人： Stephen G. Abel
IPC分类号： F16K3102
CPC分类号： F02K9/86 , F02K9/805 , F15C3/14 , F42B10/66 , F42B10/668 , Y10T137/8122 , Y10T137/86598
摘要： A thruster valve has a continuously positionable piston between a closed position and a maximum open position. The piston moves in response to the difference in pressure between the pressure in the intermediate annulus and the pressure behind the piston. A pivotable flapper valve regulates this pressure difference. When a change in thrust is required, the position of the flapper is changed causing a change in this pressure difference which causes the piston to move until the desired thrust level is obtained.
摘要翻译： 推进器阀在关闭位置和最大打开位置之间具有可连续定位的活塞。 活塞响应于中间环中的压力和活塞后面的压力之间的压力差而移动。 可枢转的挡板阀调节该压力差。 当需要改变推力时，挡板的位置改变，导致该压差的变化，这导致活塞移动直到获得所需的推力水平。
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87.发明授权
公开(公告)号：US5749559A
公开(公告)日：1998-05-12
申请号：US732704
申请日：1996-10-18
摘要： A device for controlling a spacecraft by gating gas, the device comprising a nozzle, a gas feed duct, a gate having a seat and a plunger interposed between the feed duct and the nozzle, and control means for opening and closing the gate in order to put the feed duct selectively into communication with the nozzle. The seat of the gate is secured to the nozzle and the nozzle is movable such that the gate is opened and closed by displacement of the nozzle, which displacement is driven directly by the hot gas, without calling on an auxiliary fluid.
摘要翻译： 一种用于通过门控气体来控制航天器的装置，该装置包括一个喷嘴，一个供气管道，一个具有一个座和一个置于进料管道和喷嘴之间的柱塞的闸门，以及用于打开和关闭闸门的控制装置，以便 将进料管选择性地与喷嘴连通。 门的座位固定在喷嘴上，并且喷嘴是可移动的，使得门通过喷嘴的位移而打开和关闭，该位移直接由热气驱动，而不需要辅助流体。
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88.依法登记的发明Active control of solid propellant generators using throat modulation techniques and programmable compensation 失效使用喉部调制技术和可编程补偿主动控制固体推进剂发生器
公开(公告)号：USH747H
公开(公告)日：1990-02-06
申请号：US383403
申请日：1982-06-01
申请人： Paul L. Jacobs , J. C. Dunaway
发明人： Paul L. Jacobs , J. C. Dunaway
摘要： A system for controlling solid propellant gas generators including a microcessor which has inputs such as the sensed temperature of the gases in the solid propellant gas generator, the pressure within the solid propellant gas generator and/or pre-programmed input control signals to the microprocessor for causing the microprocessor to produce signals that are used to control a modulation valve which in turn controls a thrust nozzle device that controls exhaust gases from the solid propellant gas generator.
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公开(公告)号：US4109460A
公开(公告)日：1978-08-29
申请号：US674089
申请日：1976-04-06
申请人： Gunther Schmidt
发明人： Gunther Schmidt
摘要： A liquid fuel rocket engine comprises a housing having an outer annular wall and an inner annular wall which define therebetween a combustion chamber of substantially uniform cross section and leading to a converging wall section and a nozzle throat of narrow dimension. Means are provided to vary the nozzle throat section during operation of the engine in order to obtain better performance operation of the engine. The means for varying the dimension comprises a thermal arrangement whereby the cooling of the housing walls are divided up into sectors through which a propellant component is circulated. The temperature of the circulated component and the quantity of component which is circulated are advantageously controlled in order to vary the thermal expansion of the various sector portions and thereby change the axial and radial position of the walls defining the nozzle throat section. This is done either by controlling the propellant component which is directed through each of four separate sectors of the housing parts making up the outer and inner walls of the housing or by controlling only the cooling rate of the outer walls to vary the boundaries of the nozzle throat. The control is accomplished by a globe valve member which is pivoted in order to vary the distribution flow of a propellant component through each of a plurality of flow paths for regulating the cooling of the various portions of the inner and outer housing walls. In addition a mechanical means may be provided to actually vary the position of one or both of the outer and inner walls so as to control the nozzle throat section.
摘要翻译： 液体燃料火箭发动机包括具有外部环形壁和内部环形壁的壳体，其在其间限定具有基本上均匀横截面的燃烧室，并且导致会聚壁部分和窄尺寸的喷嘴喉部。 提供了在发动机运转期间改变喷嘴喉部的装置，以获得发动机的更好的性能运行。 用于改变尺寸的装置包括一种热安排，其中壳体壁的冷却被分成推进剂组分通过其循环的扇区。 有利地控制循环组分的温度和循环的组分的量以改变各扇形部分的热膨胀，从而改变限定喷嘴喉部的壁的轴向和径向位置。 这可以通过控制推进剂部件来完成，推进剂部件被引导通过构成壳体的外壁和内壁的壳体部分的四个独立部分中的每一个，或通过仅控制外壁的冷却速率来改变喷嘴的边界 喉。 控制是通过一个截止阀构件实现的，所述截止阀构件被枢转以改变通过多个流动路径中的每一个的推进剂部件的分配流量，以调节内壳体和外壳体壁的各个部分的冷却。 此外，可以提供机械装置来实际改变外壁和内壁之一或两者的位置，以便控制喷嘴喉部。
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公开(公告)号：US3948042A
公开(公告)日：1976-04-06
申请号：US788990
申请日：1968-12-23
CPC分类号： F02K9/86
摘要： A system for controlling the annular nozzle throat area (and hence the tht) of a solid-propellant rocket by means of a pintle or plug the position of which is caused to vary in response to pressure variations within the combustion chamber of the rocket.
摘要翻译： 一种用于通过枢轴或塞子来控制固体推进剂火箭的环形喷嘴喉部区域（以及因此的推力）的系统，其引导位置响应于火箭的燃烧室内的压力变化而变化。
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