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1. 发明申请

WO2008067000A3 PINTLE-CONTROLLED PROPULSION SYSTEM WITH EXTERNAL DYNAMIC SEAL 审中-公开
标题翻译：具有外部动态密封的紧固控制推进系统
公开(公告)号：WO2008067000A3
公开(公告)日：2008-10-30
申请号：PCT/US2007078098
申请日：2007-09-11
申请人： AEROJET GENERAL CO , HANSEN WILLIAM E
发明人： HANSEN WILLIAM E
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。

2. 发明申请

WO2014058525A1 SLOTTED MULTI-NOZZLE GRID WITH INTEGRATED COOLING CHANNELS 审中-公开
标题翻译：带集成式冷却通道的多孔多孔网
公开(公告)号：WO2014058525A1
公开(公告)日：2014-04-17
申请号：PCT/US2013/054401
申请日：2013-08-09
申请人： RAYTHEON COMPANY
发明人： CHASMAN, Daniel , HAIGHT, Stephen D. , VILLARREAL, James K.
IPC分类号： F02K9/30 , F02K9/97
CPC分类号： F02K9/30 , F02K9/97 , F02K9/972 , Y10T29/49346
摘要： An apparatus includes a slotted multi-nozzle grid with a plate (102) having multiple elongated slotlettes (104) through the plate. At least some of the slotlettes have a convergent input (202), a divergent output (204), and a narrower throat portion (206). At least some of the slotlettes are arranged in multiple rows (106). The plate further includes multiple cooling channels (116). At least some of the cooling channels are located between the rows of slotlettes. Each cooling channel is configured to transport coolant through the plate in order to cool the plate, such as to cool the plate as hot combustion gases pass through the plate. Each of at least some of the rows may include at least two slotlettes, and two adjacent slotlettes in one row may be separated by a structural ligament (108), which may have a tear¬ drop cross-sectional shape.
摘要翻译：一种装置包括一个带槽的多喷嘴格栅，其具有通过该板的具有多个细长槽形件（104）的板（102）。至少一些小缝隙具有收敛输入（202），发散输出（204）和较窄的喉部（206）。至少一些小插槽被布置成多行（106）。板还包括多个冷却通道（116）。至少一些冷却通道位于行槽之间。每个冷却通道被构造成运输冷却剂通过板以便冷却板，例如当热燃气体通过板时冷却板。至少一些行中的每一行可以包括至少两个开槽元件，并且一行中的两个相邻的开槽元件可以由可能具有泪滴横截面形状的结构韧带（108）分开。

3. 发明申请

WO2004099601A2 MULTI-NOZZLE GRID MISSILE PROPULSION SYSTEM 审中-公开
标题翻译：多级喷射式雷达推进系统
公开(公告)号：WO2004099601A2
公开(公告)日：2004-11-18
申请号：PCT/US2003/035150
申请日：2003-11-04
申请人： CHASMAN, Daniel
发明人： CHASMAN, Daniel
IPC分类号： F02K
CPC分类号： F02K9/30 , F02K9/97 , F05D2240/40 , F05D2300/21 , F05D2300/224 , F05D2300/603 , F05D2300/614 , F42B15/10
摘要： A jet propulsion outlet device is disclosed that has a grid plate having a plurality of densely clustered nozzlettes, the nozzlettes of the grid plate being configured to operably couple to a pressurized gas source to efficiently expand the pressurized gas.
摘要翻译：公开了一种具有多个密集聚集的喷嘴的格栅板的喷射推进出口装置，格栅板的喷嘴构造成可操作地耦合到加压气体源以有效地膨胀加压气体。

4. 发明申请

WO2018234766A1 AIRCRAFT THRUSTER 审中-公开
公开(公告)号：WO2018234766A1
公开(公告)日：2018-12-27
申请号：PCT/GB2018/051671
申请日：2018-06-15
申请人： ACTIVE VTOL CRASH PREVENTION LIMITED
发明人： SLOMAN, Roger Mark
IPC分类号： F02K9/08 , F02K9/26 , F02K9/30 , F02K9/34
CPC分类号： F02K9/08 , F02K9/26 , F02K9/30 , F02K9/34
摘要： A rocket motor for a vertical take-off and landing (VTOL) aircraft is provided, along with control circuitry and computer programs for controlling the rocket motor, the methods of using the rocket motor. The rocket motor may define an elongate chamber for storing propellant, the elongate chamber having a length dimension, a width dimension and a depth dimension, wherein the length dimension is greater than the width dimension and greater than the depth dimension. The rocket motor may also comprise propellant and at least one fluid injector. The propellant may be located in the elongate chamber and be configured to enable the rocket motor to generate thrust in a direction that is substantially perpendicular to the length dimension of the elongate chamber by causing ejection of gas through a plurality of gas efflux apertures in the casing. The fluid injector(s) may be for injecting a fluid fire suppressant into the elongate chamber.

5. 发明申请

WO2008067000B1 PINTLE-CONTROLLED PROPULSION SYSTEM WITH EXTERNAL DYNAMIC SEAL 审中-公开
标题翻译：带有外部动态密封的点控式推进系统
公开(公告)号：WO2008067000B1
公开(公告)日：2008-12-18
申请号：PCT/US2007078098
申请日：2007-09-11
申请人： AEROJET GENERAL CO , HANSEN WILLIAM E
发明人： HANSEN WILLIAM E
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延伸到推力室外表面上的凸台。保持推力腔的加压同时允许枢轴运动的动态密封位于凸台内，轴销和凸台之间，并且通过固定在枢轴的前端上的齿条来实现枢轴的致动，以及一个啮合齿条的齿轮。动态密封，齿条和齿轮因此位于推力室的外部，为推力室提供紧凑的外部封套，更大的热距离，或两者。

6. 发明申请

WO2008067000A2 PINTLE-CONTROLLED PROPULSION SYSTEM WITH EXTERNAL DYNAMIC SEAL 审中-公开
标题翻译：带有外部动态密封的点控式推进系统
公开(公告)号：WO2008067000A2
公开(公告)日：2008-06-05
申请号：PCT/US2007/078098
申请日：2007-09-11
申请人： AEROJET-GENERAL CORPORATION , HANSEN, William E.
发明人： HANSEN, William E.
IPC分类号： F02K1/00
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延伸到外表面上的凸台推力室。保持推力腔的加压同时允许枢轴运动的动态密封位于凸台内，轴销和凸台之间，并且通过固定在枢轴的前端上的齿条来实现枢轴的致动，以及一个啮合齿条的齿轮。动态密封，齿条和齿轮因此位于推力室的外部，为推力室提供紧凑的外部封套，更大的热距离，或两者兼而有之。

7. 发明申请

WO2012032273A1 SYSTEME DE PROPULSION POUR ENGIN VOLANT, EN PARTICULIER POUR MISSILE 审中-公开
标题翻译：一种用于飞机的推进系统，特别适合于飞机
公开(公告)号：WO2012032273A1
公开(公告)日：2012-03-15
申请号：PCT/FR2011/052063
申请日：2011-09-08
申请人： MICROTURBO , MBDA France , ROXEL France , GUYADER, Gilles, Aimé, Yann , RIDEAU, Jean-François , PFIFFER, André , DOUALLE, Jean-François
发明人： GUYADER, Gilles, Aimé, Yann , RIDEAU, Jean-François , PFIFFER, André , DOUALLE, Jean-François
IPC分类号： F02C7/27 , F02K9/30 , F02K9/78 , F42B15/10
CPC分类号： F02K9/00 , F02C7/27 , F02K9/30 , F02K9/78 , F41A33/02 , F42B15/10
摘要： Le système de propulsion (1) comporte un accélérateur (2) et un turboréacteur (3), l'accélérateur(2)comprenant une enceinte (6) qui est fixée à un carter arrière (7) du turboréacteur (3) en étant agencée selon l'axe longitudinal (L) de ce dernier, qui est munie d'une tuyère (8) à l'arrière, et qui est pourvue d'au moins une charge(9) et de moyens de déclenchement de ladite charge (9), ledit système de propulsion (1) comportant de plus des tubes de piquage de gaz (10, 11) qui sont reliés à l'accélérateur (2) et qui sont destinés,soit à l'allumage de la chambre de combustion du turboréacteur (3), soit au démarrage de la turbine du turboréacteur (3).
摘要翻译：推进系统（1）包括增压器（2）和涡轮喷气发动机（3），增压器（2）包括通过以下方式固定到涡轮喷气发动机（3）的后壳体（7）的室（6）沿着其纵向轴线（L）布置，该室在后部装配有喷射管（8），并且设置有至少一个电荷（9），并且具有启动所述电荷（9）的装置，所述推进系统 1）还包括连接到增压器（2）并且用于点燃涡轮喷气发动机（3）的燃烧室或用于启动涡轮喷气发动机（3）的涡轮机的排气管（10,11）。

8. 发明申请

WO2006115605A1 MISSILE CONTROL SYSTEM AND METHOD 审中-公开
标题翻译： MISSILE控制系统和方法
公开(公告)号：WO2006115605A1
公开(公告)日：2006-11-02
申请号：PCT/US2006/009539
申请日：2006-03-16
申请人： RAYTHEON COMPANY , CHASMAN, Daniel, B. , LEAL, Michael , HAIGHT, Stephen, D.
发明人： CHASMAN, Daniel, B. , LEAL, Michael , HAIGHT, Stephen, D.
IPC分类号： F42B10/66 , F02K9/30 , F02K9/80 , F16K3/08
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 (12) includes a control system (10) having divert and attitude control system thrusters (16, 18) with control valves (20). Each of the control valves has a nozzle plate (26) having a plurality of small nozzles (24) therein. The nozzle plate includes a pair of portions (30, 32), 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（12）包括具有带有控制阀（20）的转向和姿态控制系统推进器（16,18）的控制系统（10）。每个控制阀具有在其中具有多个小喷嘴（24）的喷嘴板（26）。喷嘴板包括一对部分（30,32），其中一个部分可相对于另一个旋转。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。

9. 发明申请

WO2004099601A3 MULTI-NOZZLE GRID MISSILE PROPULSION SYSTEM 审中-公开
标题翻译：多级喷射式锥形推进系统
公开(公告)号：WO2004099601A3
公开(公告)日：2005-02-10
申请号：PCT/US0335150
申请日：2003-11-04
申请人： CHASMAN DANIEL
发明人： CHASMAN DANIEL
IPC分类号： F02K20060101 , F42B15/10
CPC分类号： F02K9/30 , F02K9/97 , F05D2240/40 , F05D2300/21 , F05D2300/224 , F05D2300/603 , F05D2300/614 , F42B15/10
摘要： A jet propulsion outlet device is disclosed that has a grid plate (16) having a plurality of densely clustered nozzlettes (43), the nozzlettes of the grid plate being configured to operably couple to a pressurized gas source to efficiently expand the pressurized gas.
摘要翻译：公开了一种喷射推进出口装置，其具有具有多个密集聚集的喷嘴（43）的格栅板（16），格栅板的喷嘴构造成可操作地耦合到加压气体源以有效地膨胀加压气体。

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