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1. 发明授权

EP3009650B1 THRUST CONTROL VALVE AND FLYING OBJECT 有权
标题翻译：推力控制阀和飞行物体
公开(公告)号：EP3009650B1
公开(公告)日：2018-03-21
申请号：EP13891432.0
申请日：2013-10-18
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： HIDAKA, Shozo , MORIWAKI, Atsushi , FUTAHASHI, Kensuke , HOSAKA, Shuhei , NAGASE, Masaaki , KOJIMA, Kohei , INADA, Mitsuru
IPC分类号： F02K9/80 , F02K9/86 , F16K1/54
CPC分类号： F02K9/86 , B64D27/023 , B64D31/00 , F02K9/80 , F02K9/94 , F05D2250/75
摘要： A thrust control valve equipped with: a valve element (15), in which a gas injection passage (L), through which an operating gas (G) is injected, is formed, with a valve-seating surface (P1) being formed in the gas injection passage (L); and a valve stem (16), which is provided in the interior of the gas injection passage (L) and has a seated surface (P5) that makes contact with the valve-seating surface (P1). A guide surface (P4) which makes contact with the inner circumferential surface of the gas injection passage of the valve element (15) is formed on the outer circumferential surface of the valve stem (16). The guide surface (P4) is formed downstream from the seated surface (P5) in the direction of flow of the operating gas (G). A V-groove (31) through which the operating gas (G) flows is formed at the tip of the valve stem (16), downstream from the seated surface (P5) in which the guide surface (P4) is formed.

2. 发明授权

EP2159403B1 Variable slope exhaust nozzle 有权
标题翻译：可变坡度排气喷嘴
公开(公告)号：EP2159403B1
公开(公告)日：2017-06-21
申请号：EP09167793.0
申请日：2009-08-13
申请人： General Electric Company
发明人： Dindar, Mustafa , Burton, Scott Andrew , Blodgett, Keith Edward James , Cedar, Richard David
IPC分类号： F02K1/08 , F02K1/52
CPC分类号： F02K3/06 , B64D33/04 , F02K1/08 , F02K1/52 , F02K3/02 , F02K3/04 , F02K9/86 , F05D2250/14 , F05D2250/231

3. 发明授权

EP3025046B1 TUYÈRE D'ÉJECTION DE GAZ DE COMBUSTION D'UN MOTEUR FUSÉE POURVUE D'UN DISPOSITIF D'ÉTANCHÉITÉ ENTRE UNE PARTIE FIXE ET UNE PARTIE MOBILE DE LA TUYÈRE 有权转让
标题翻译： VERBRENNUNGSGASENTLADUNGSDÜSE具有密封元件之间的相关和可变组分喷管火箭发动机
公开(公告)号：EP3025046B1
公开(公告)日：2017-05-31
申请号：EP14742508.6
申请日：2014-07-23
申请人： Airbus Safran Launchers SAS
发明人： DUTHEIL, Jean-Philippe
IPC分类号： F02K1/80 , F02K9/90 , F02K9/97
CPC分类号： F02K9/86 , F02K1/805 , F02K9/90 , F02K9/97 , F02K9/978 , F05D2220/80 , F05D2240/128 , F05D2240/55

4. 发明授权

EP2681439B1 ENGINE FOR USE IN AN AERIAL VEHICLE 失效
标题翻译： EINEMFLUGGERÄT电机ZUR VERWENDUNG
公开(公告)号：EP2681439B1
公开(公告)日：2017-04-05
申请号：EP12752853.7
申请日：2012-02-29
申请人： Grollo Aerospace
发明人： GROLLO, Mark
IPC分类号： F02K7/18 , F02K9/76 , F02K9/78 , F02K1/12 , F02K9/86 , F02K9/97
CPC分类号： F02K7/18 , F02K1/1223 , F02K9/78 , F02K9/86 , F02K9/972

5. 发明公开

EP3146270A1 PULSDETONATIONSANTRIEB 有权转让
公开(公告)号：EP3146270A1
公开(公告)日：2017-03-29
申请号：EP15724927.7
申请日：2015-05-18
申请人： Explo Engineering AG
发明人： RÜEGG, Hans
IPC分类号： F23R7/00 , F02K7/02 , F02K7/06 , F02K1/08 , F02B71/06 , F02K9/58 , F02K9/44 , F02K9/52
CPC分类号： F02K7/06 , F02B71/06 , F02K1/08 , F02K1/15 , F02K7/02 , F02K9/44 , F02K9/52 , F02K9/58 , F02K9/86 , F02K9/97 , F05D2220/323 , F05D2220/80 , F05D2240/35 , F05D2250/41 , F23R7/00
摘要： The invention relates to a device serving for repeated production of explosions. The device comprises: an explosion chamber (11), a feed line for feeding a free-flowing explosive material, a vent opening for directed venting of a gas pressure produced by ignition of the explosive material in the explosion chamber (11), and a movable closure element (21, 31) for partial or complete closure of the vent opening (17). The device has an outlet nozzle (15) having a nozzle inlet area (13) and a nozzle outlet area (14), and has an adjustment device (23). The adjustment device (23) is designed such that, after the vent opening (17) is opened and explosion gases flow out through the outlet nozzle (15), an area ratio between the nozzle inlet area (13) and the nozzle outlet area (14) is adjusted to at least approximately correspond to an ideal area ratio for producing a maximum exit velocity of the explosion gases as a function of the pressure in the explosion chamber (11).
摘要翻译：用于重复产生爆炸的装置包括爆炸空间，用于馈送可流动的爆炸性材料的进料管道，用于定向排放由爆炸空间中的爆炸物质点燃产生的气体压力的排放口，以及用于部分或完全关闭排放口的活动闭合元件。该装置包括具有喷嘴入口区域和喷嘴出口区域的出口喷嘴以及致动装置。致动装置适于在排出口打开和爆炸气体通过出口喷嘴流出之后，调节喷嘴入口区域和喷嘴出口区域之间的面积比。根据爆炸空间中的压力，面积比至少近似于产生爆炸气体的最大出口速度的理想面积比。

6. 发明公开

EP0265600A3 BI-Level thruster 失效
标题翻译：双电位器
公开(公告)号：EP0265600A3
公开(公告)日：1989-04-12
申请号：EP87110626.6
申请日：1987-07-22
申请人： ROCKWELL INTERNATIONAL CORPORATION
发明人： Gillon, Willard Andrew, Jr
IPC分类号： F02K9/86 , F02K9/80
CPC分类号： F02K9/805 , B64G1/26 , B64G1/401 , F02K9/86 , Y10T137/87378 , Y10T137/87507
摘要： A compact, lightweight thruster assembly (10) is provided consisting of a dual armature piston assembly (24). A single solenoid coil (46) operates either or both armatures (26),(34) depending on the level of applied current to effect either of two levels of predetermined impulse emitting from the thruster nozzle (20).

7. 发明公开

EP0265600A2 BI-Level thruster 失效
标题翻译： Zweistufen-Strahlantrieb。
公开(公告)号：EP0265600A2
公开(公告)日：1988-05-04
申请号：EP87110626.6
申请日：1987-07-22
申请人： ROCKWELL INTERNATIONAL CORPORATION
发明人： Gillon, Willard Andrew, Jr
IPC分类号： F02K9/86 , F02K9/80
CPC分类号： F02K9/805 , B64G1/26 , B64G1/401 , F02K9/86 , Y10T137/87378 , Y10T137/87507
摘要： A compact, lightweight thruster assembly (10) is provided consisting of a dual armature piston assembly (24). A single solenoid coil (46) operates either or both armatures (26),(34) depending on the level of applied current to effect either of two levels of predetermined impulse emitting from the thruster nozzle (20).
摘要翻译：提供由双电枢活塞组件（24）组成的紧凑，重量轻的推进器组件（10）。单个螺线管线圈（46）根据所施加的电流的水平来操作电枢（26），（34）中的任一个或两个电极，以实现从推进器喷嘴（20）发射的两个预定脉冲水平。

8. 发明授权

EP1875153B1 MISSILE CONTROL SYSTEM AND METHOD 有权
标题翻译：制导武器控制制度和相关程序
公开(公告)号：EP1875153B1
公开(公告)日：2016-05-18
申请号：EP06738579.9
申请日：2006-03-16
申请人： RAYTHEON COMPANY
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

9. 发明公开

EP3009650A1 THRUST CONTROL VALVE AND FLYING OBJECT 有权
标题翻译：推力控制阀和飞行物体
公开(公告)号：EP3009650A1
公开(公告)日：2016-04-20
申请号：EP13891432.0
申请日：2013-10-18
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： HIDAKA, Shozo , MORIWAKI, Atsushi , FUTAHASHI, Kensuke , HOSAKA, Shuhei , NAGASE, Masaaki , KOJIMA, Kohei , INADA, Mitsuru
IPC分类号： F02K9/80 , F02K9/86
CPC分类号： F02K9/86 , B64D27/023 , B64D31/00 , F02K9/80 , F02K9/94 , F05D2250/75
摘要： A thrust control valve equipped with: a valve element (15), in which a gas injection passage (L), through which an operating gas (G) is injected, is formed, with a valve-seating surface (P1) being formed in the gas injection passage (L); and a valve stem (16), which is provided in the interior of the gas injection passage (L) and has a seated surface (P5) that makes contact with the valve-seating surface (P1). A guide surface (P4) which makes contact with the inner circumferential surface of the gas injection passage of the valve element (15) is formed on the outer circumferential surface of the valve stem (16). The guide surface (P4) is formed downstream from the seated surface (P5) in the direction of flow of the operating gas (G). A V-groove (31) through which the operating gas (G) flows is formed at the tip of the valve stem (16), downstream from the seated surface (P5) in which the guide surface (P4) is formed.
摘要翻译：一种推力控制阀，该推力控制阀配备有：阀元件（15），其中形成有供工作气体（G）注入的气体注入通道（L），阀座表面（P1）形成在阀元件气体注入通道（L）; 和设置在所述气体注入通路（L）的内部且具有与所述阀座面（P1）接触的座面（P5）的阀杆（16）。在阀杆（16）的外周面形成有与阀芯（15）的气体喷射通路的内周面抵接的引导面（P4）。引导表面（P4）在工作气体（G）的流动方向上形成在就座表面（P5）的下游。工作气体（G）流动通过的V形槽（31）形成在阀杆（16）的尖端处，形成有引导表面（P4）的就座表面（P5）的下游。

10. 发明公开

EP2681439A4 ENGINE FOR USE IN AN AERIAL VEHICLE 失效
标题翻译：发动机用在飞行大队
公开(公告)号：EP2681439A4
公开(公告)日：2015-01-14
申请号：EP12752853
申请日：2012-02-29
申请人： GROLLO AEROSPACE
发明人： GROLLO MARK
IPC分类号： F02K7/18 , F02K1/12 , F02K9/76 , F02K9/78 , F02K9/86
CPC分类号： F02K7/18 , F02K1/1223 , F02K9/78 , F02K9/86 , F02K9/972
摘要： This invention relates to an engine (2) for use in aerial vehicle (1) including a rocket (9) and ram jet engine formed from an intake (8) and a combustion chamber (10). The rocket engine (9) includes an oxidiser combustion chamber (21) which exhausts through the combustion chamber (10). The engine also includes a nozzle (12). Both the intake (8) and nozzle (12) include rectilinear ducts which are defined in part by baffles (16) and panels (33) respectively. Both the baffles (16) and panels (33) are adjustable to adjust the airflow characteristics therethrough.

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