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1. 发明授权

US10359005B2 Solid propellant rocket motor 有权
公开(公告)号：US10359005B2
公开(公告)日：2019-07-23
申请号：US15129396
申请日：2015-04-02
申请人： AVIO S.P.A.
发明人： Paolo Bellomi , Vincenzo Mancini
IPC分类号： F02K9/08 , F02K9/36 , F02K7/10 , F02K9/10 , F02K9/26 , F02K9/32 , F02K9/34 , F02K9/38 , F02K9/86
摘要： A solid propellant rocket motor has a tubular casing accommodating a mass of solid propellant material and at least one opening for the space in the casing to communicate with the outside closed by a closing head; the closing head being coupled to the casing by means of one or the other of two blocking portions with different strength both carried by a movement device which can be elastically deformed and operated from the outside.

2. 发明授权

US09541031B2 Device for modulating a gas ejection section 有权
标题翻译：用于调制气体喷射部的装置
公开(公告)号：US09541031B2
公开(公告)日：2017-01-10
申请号：US14773042
申请日：2014-03-04
申请人： HERAKLES
发明人： Mathieu Clermont , Alain Remigi , Jean-Michel Larrieu , Philippe Marlin
IPC分类号： F02K9/08 , F02K9/86 , F02K9/26
CPC分类号： F02K9/86 , F02K9/08 , F02K9/26
摘要： A modulator device for modulating a gas ejection section, includes a shutter member for partially shutting a nozzle throat, a control guide of the shutter member, a main piston, and a primer piston. The control guide is movable between a retraction position for retracting the partial shutter element relative to the nozzle throat and a shutting position in which the partial shutter element is in contact with the nozzle throat. The primer piston is movable between a rest position and a priming position for priming the main piston when the pressure in the modulator device reaches a first predetermined value. The main piston is movable between a first position for locking the control guide against movement in its retraction position, and a second position for locking the control guide when the pressure in the modulator device reaches a second predetermined value less than the first predetermined value.
摘要翻译：用于调制气体喷射部分的调制装置包括用于部分地关闭喷嘴喉部的挡板部件，挡板部件的控制导向件，主活塞和底漆活塞。控制引导件可在用于使局部快门元件相对于喷嘴喉部缩回的缩回位置和其中部分快门元件与喷嘴喉部接触的关闭位置之间移动。当调节装置中的压力达到第一预定值时，底漆活塞可在静止位置和起动位置之间移动，用于使主活塞起动。主活塞可在第一位置和第二位置之间移动，第一位置用于锁定控制引导件以避免其在缩回位置的移动;以及第二位置，用于当调制器装置中的压力达到小于第一预定值的第二预定值时锁定控制引导件。

3. 发明申请

US20050223695A1 Thrust vector control system for a plug nozzle rocket engine 失效
标题翻译：用于插头喷嘴火箭发动机的推力矢量控制系统
公开(公告)号：US20050223695A1
公开(公告)日：2005-10-13
申请号：US10823380
申请日：2004-04-13
申请人： Charles Sota , George Callis , Robert Masse
发明人： Charles Sota , George Callis , Robert Masse
IPC分类号： F02K1/78 , F02K9/86 , F02K9/97
CPC分类号： F02K9/978 , F02K9/86 , F05D2250/232 , F05D2250/26 , F05D2250/27
摘要： A thrust vector control system for a plug nozzle rocket engine for propelling and maneuvering a vehicle is disclosed. The plug nozzle rocket engine includes a housing having a nozzle throat, a plug disposed within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat, and a thrust diverter moveably disposed relative to the housing to define an asymmetric pressure distribution along the plug for thrust-vectoring. In one embodiment, the thrust diverter is normally biased to a non-thrust-vectoring position, but is moveable in a plane substantially perpendicular to an axis extending longitudinally through the plug.
摘要翻译：公开了一种用于推进和操纵车辆的塞子喷嘴火箭发动机的推力矢量控制系统。塞子喷嘴火箭发动机包括具有喷嘴喉部的壳体，设置在壳体内并且定位在喷嘴喉部内以限定塞子和喷嘴喉部之间的空间的塞子以及相对于壳体可移动地设置的推力分流器，沿插头的不对称压力分布用于推力矢量。在一个实施例中，推力分流器通常被偏压到非推力矢量位置，但是可以在基本上垂直于纵向延伸穿过插塞的轴线的平面中移动。

4. 发明授权

US4777795A Device for varying the thrust of a propulsion system using a solid propellant 失效
标题翻译：用于改变使用固体推进剂的推进系统的推力的装置
公开(公告)号：US4777795A
公开(公告)日：1988-10-18
申请号：US15940
申请日：1987-02-18
申请人： Alain M. Le Corre , Max Jean-Pierre Calabro , Gilles B. Vigier , Patrick Comtesse , Jean-Francois Beau
发明人： Alain M. Le Corre , Max Jean-Pierre Calabro , Gilles B. Vigier , Patrick Comtesse , Jean-Francois Beau
IPC分类号： F02K9/86 , F02K1/06
CPC分类号： F02K9/86
摘要： The device comprises, at the outlet of the combustion chamber 3, a movable assembly comprising a hollow closure member 26 constituting a needle 27, a thermal shield 22 and an annular piston 14. This closure member acts as a piston under the effect of the pressure of the gases and drives the annular piston so as to expel a hydraulic fluid from a jack chamber 33 having an adjustable outlet 34. The closure member 26 defines a chamber 28 for calming the gases.
摘要翻译：该装置包括在燃烧室3的出口处的可移动组件，其包括构成针27的中空闭合构件26，热屏蔽22和环形活塞14.该闭合构件在压力作用下用作活塞的气体并且驱动环形活塞，以从具有可调节出口34的千斤顶室33排出液压流体。封闭构件26限定用于使气体平静的室28。

5. 发明授权

US4753392A Two dimensional gas turbine engine exhaust nozzle 失效
标题翻译：二维燃气轮机发动机排气喷嘴
公开(公告)号：US4753392A
公开(公告)日：1988-06-28
申请号：US667708
申请日：1984-11-02
申请人： Edward B. Thayer , George H. McLafferty
发明人： Edward B. Thayer , George H. McLafferty
IPC分类号： F02K9/86 , F02K1/12 , F02K1/60 , F02K1/62
CPC分类号： F02K1/60 , F02K1/12 , F02K1/1223
摘要： A two dimensional exhaust nozzle for a gas turbine engine having reverse thrust capability includes a pair of spaced apart converging flaps which are able to rotate about their respective axes until their downstream edges meet along the engine centerline to block the flow of gases through the engine and to redirect the flow through fixed area reverser outlet ports. The axes about which each convergent flap rotates are spaced inwardly from their respective convergent flap surfaces. The flaps themselves cover the outlet ports when the flaps are in forward thrust operating positions. The flaps move away from and unblock the outlets as they rotate to their reverse thrust position. The distance between the flap axis and its convergent surface is critical to being able to use short flaps while obtaining large reverser outlet areas.
摘要翻译：用于具有反向推力能力的燃气涡轮发动机的二维排气喷嘴包括一对间隔开的会聚翼片，其能够围绕它们各自的轴线旋转，直到它们的下游边缘沿着发动机中心线相遇，以阻挡气体通过发动机的流动，将流量重定向通过固定区域反向器出口端口。每个收敛翼片旋转的轴线与它们各自的收敛翼片表面间隔开。当襟翼处于向前推力操作位置时，襟翼本身覆盖出口。当它们旋转到其反向推力位置时，翼片离开和解除插座。襟翼轴与其收敛表面之间的距离对于能够在获得大的逆向出口区域时能够使用短襟翼是至关重要的。

6. 发明授权

US4632336A Lateral gas jet piloting device 失效
标题翻译：横向气体喷射引导装置
公开(公告)号：US4632336A
公开(公告)日：1986-12-30
申请号：US561801
申请日：1983-12-15
申请人： Roger Crepin
发明人： Roger Crepin
IPC分类号： F02K9/60 , B64G1/26 , F02K9/86 , F02K9/90 , F42B10/66 , F42B15/033 , F02K9/80
CPC分类号： F42B10/663 , F02K9/90
摘要： The invention provides a lateral gas jet piloting device comprising at least one pair of diametrically opposite nozzles and a sliding bar comprising bistable pneumatic means ensuring reciprocal movement thereof so that the ends of said bar close alternately coupling ducts disposed between the nozzles and an external gas generator.
摘要翻译：本发明提供了一种横向气体喷射引导装置，其包括至少一对直径相对的喷嘴和包括双稳态气动装置的滑动杆，其确保其往复运动，使得所述杆的端部交替地联接设置在喷嘴之间的管道和外部气体发生器。

7. 发明授权

US4452395A Nozzle assembly for a reaction engine 失效
标题翻译：用于反应发动机的喷嘴组件
公开(公告)号：US4452395A
公开(公告)日：1984-06-05
申请号：US326496
申请日：1981-12-02
申请人： Patrick J. Kelly , Robert D. Hackett
发明人： Patrick J. Kelly , Robert D. Hackett
IPC分类号： F02K7/10 , F02K9/86 , F02K9/97 , F02K1/42
CPC分类号： F02K7/10 , F02K9/86 , F02K9/978
摘要： A reaction engine, such as a ramjet engine, has a nozzle assembly which maintains acceptable combustion chamber pressures during both high thrust and low thrust modes of flight. To this end, the engine has a primary nozzle in which a swing disc is located, and the disc turns from an open position in which it lies parallel to the axis of the primary nozzle to a closed position in which it lies across and blocks the primary nozzle. The disc contains secondary nozzles which are considerably smaller than the primary nozzle and are only effective when the disc is in its open position. The secondary nozzles may initially be filled with a flow smoothing material to prevent turbulence when the swing disc is in its initial open position, but this material is dislodged when the disc moves to its closed position.
摘要翻译：诸如冲压喷气发动机的反应发动机具有喷嘴组件，其在高推力和低推力模式下均保持可接受的燃烧室压力。为此，发动机具有主旋转盘所在的主喷嘴，并且盘从其平行于主喷嘴的轴线的打开位置转动到关闭位置，在该关闭位置处，主喷嘴盘包含比主喷嘴小得多的二次喷嘴，并且仅在盘处于其打开位置时有效。次级喷嘴可以最初填充有流动平滑材料，以防止当旋转盘处于其初始打开位置时的湍流，但是当盘移动到其关闭位置时该二次喷嘴被移除。

8. 发明授权

US4102498A Ring lock actuation system 失效
标题翻译：环锁致动系统
公开(公告)号：US4102498A
公开(公告)日：1978-07-25
申请号：US566018
申请日：1975-04-07
申请人： Charles C. Cherry
发明人： Charles C. Cherry
IPC分类号： F02K9/86 , B63H11/10
CPC分类号： F02K9/86
摘要： A mechanical actuation system for secondary centerbody nozzle actuation commonly associated with a dual area solid rocket nozzle configuration that utilizes a rotating ring in combination with at least one piston connected to pins that are affixed to the movable centerbody. The ends of the pins adjacent the rotating ring are misaligned with holes in the rotating ring such that the ring lock prevents the centerbody from moving to a closed or blocking position until such time as the ring lock is rotated by ring actuation means to align the holes with the pins. The pins then simultaneously slide through the holes moving the centerbody to the closed position.
摘要翻译：用于二次中心体喷嘴致动的机械致动系统通常与双区域固体火箭喷嘴配置相关联，该配置利用旋转环与连接到固定到可移动中心体的销的至少一个活塞组合。与旋转环相邻的销的端部与旋转环中的孔不对准，使得环形锁定防止中心体移动到闭合或阻塞位置，直到环锁定被环形致动装置旋转以对准孔与引脚。然后，销钉同时滑过将中心体移动到关闭位置的孔。

9. 发明授权

US3970253A Flow area modulator and flow deflector 失效
标题翻译：流域调制器和导流器
公开(公告)号：US3970253A
公开(公告)日：1976-07-20
申请号：US587022
申请日：1975-06-16
申请人： William M. Burkes , William H. Miller
发明人： William M. Burkes , William H. Miller
IPC分类号： F02K9/86 , B63H11/10 , B64C15/06 , F16K1/228
CPC分类号： F02K9/86
摘要： This device is essentially a butterfly type valve which acts as a flow constriction by rotating a disc body with its planar axis parallel to or at right angles to fluid flow through a channel. The disc body has an additional capability of extending sectors from the body beyond the original boundary or peripheral edge of the body, thereby increasing the restriction of the flow area surrounding the disc.
摘要翻译：该装置基本上是蝶形阀，其作为流动收缩，其通过旋转盘体，其平面轴线与通过通道的流体流动平行或成直角。盘体具有从身体延伸超出身体的原始边界或周边边缘的扇区的附加能力，从而增加了围绕盘的流动区域的限制。

10. 发明授权

US3929289A Plug for plug nozzles 失效
标题翻译：插头用于插头喷嘴
公开(公告)号：US3929289A
公开(公告)日：1975-12-30
申请号：US78898968
申请日：1968-12-23
申请人： US NAVY
发明人： KARDON SAMUEL , CURRY CARLTON J
IPC分类号： F02K9/86 , B63H11/00
CPC分类号： F02K9/86 , F05D2240/1281
摘要： A plug for rocket motor plug nozzles has a shell constructed of a thermally anisotropic material, bulk preoriented pyroltic graphite. The shell material is oriented to serve as both an insulator and as a heat conductor to divert heat to various heat sinks. Resilient fastening means are employed to allow relative movement of parts to minimize the effects of thermal stresses.
摘要翻译：用于火箭发动机塞子喷嘴的塞子具有由热各向异性材料构成的外壳，大块预先取向的热解石墨。外壳材料被定向为既用作绝缘体又用作热导体以将热量转移到各种散热器。使用弹性紧固装置来允许部件的相对运动以最小化热应力的影响。

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