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1. 发明公开

EP4410679A3 PROPULSION SYSTEM, AIRCRAFT HAVING A PROPULSION SYSTEM, AND METHOD OF MANUFACTURING AN AIRCRAFT 审中-实审
公开(公告)号：EP4410679A3
公开(公告)日：2024-10-16
申请号：EP24183634.5
申请日：2021-05-03
申请人： Gulfstream Aerospace Corporation
发明人： Freund, Donald , Muzychka, Derek , Klutzke, Douglas
IPC分类号： B64D27/00 , B64D27/02 , B64D29/00 , B64D29/04 , F02C7/32
CPC分类号： B64D29/00 , B64D27/02 , F02C7/32
摘要： A propulsion system for an aircraft is taught herein. The propulsion system includes, but is not limited to, an engine. The propulsion system further includes, but is not limited to, an outer cover associated with the engine. The engine and the outer cover are configured for coupling to the aircraft. The propulsion system further includes, but is not limited to, an external engine component. The propulsion system still further includes, but is not limited to, a coupler that operatively couples the external engine component to the engine. The external engine component is configured to be coupled to the aircraft at a location spaced apart from the engine.

2. 发明授权

EP4126672B1 SYSTÈME DE PROPULSION POUR AÉRONEF À VOILURE FIXE, ET AÉRONEF ASSOCIÉ 有权
公开(公告)号：EP4126672B1
公开(公告)日：2024-04-24
申请号：EP21717152.9
申请日：2021-03-23
IPC分类号： B64D27/02 , B64D27/24 , B64C23/06
CPC分类号： B64D27/02 , B64D27/24 , B64C23/065 , Y02T50/60 , Y02T50/10 , B64D27/026

3. 发明授权

EP3057867B1 VERTICAL TAKE-OFF AND LANDING AIRCRAFT 有权
公开(公告)号：EP3057867B1
公开(公告)日：2018-08-29
申请号：EP14878419.2
申请日：2014-10-10
申请人： Swift Engineering, Inc.
发明人： GODLASKY, Robert , OGAWA, Nate , STREETT, Andrew
IPC分类号： B64C29/00 , B64C3/56 , B64D27/02 , B64C29/02 , B64C5/02
CPC分类号： B64D27/02 , B64C29/02 , B64C39/024 , B64C2201/021 , B64C2201/088 , B64C2201/102
摘要： A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

4. 发明公开

EP3348470A1 CONFIGURATION OF A T JUNCTION OF A FLOW OBSTACLE ON A WALL BOUNDING A FLOW 有权
公开(公告)号：EP3348470A1
公开(公告)日：2018-07-18
申请号：EP17151606.5
申请日：2017-01-16
申请人： Deutsches Zentrum für Luft- und Raumfahrt e.V.
发明人： Eitelberg, Georg , Dwight, Richard , Belligoli, Zeno
IPC分类号： B64C1/26 , B64C1/36 , B64C21/00 , B64D27/02
CPC分类号： B64C1/26 , B64C1/36 , B64C21/00 , B64D27/02 , Y02T50/166
摘要： A T junction (1) of a flow obstacle (6) on a wall (3) bounding a flow having a main flow direction (5) comprises a concavity (7) of the wall (3) neighboring the flow obstacle (6). The concavity (7) terminates at a first distance (11) downstream the flow obstacle (6) and starts at a second distance (9) upstream the flow obstacle (6).

5. 发明公开

EP3315839A1 COMPRESSOR SURGE PROTECTION 有权
标题翻译：压缩机浪涌保护
公开(公告)号：EP3315839A1
公开(公告)日：2018-05-02
申请号：EP17195706.1
申请日：2017-10-10
申请人： The Boeing Company
发明人： RICHARDSON, Marcus Karel , SMITH, David M.
IPC分类号： F16K31/122 , F16K3/24 , F16K3/26 , F16K17/04 , B64D43/00 , B64D41/00
CPC分类号： F16K17/046 , B64D27/02 , B64D41/00 , B64D43/00 , F02C7/277 , F16K3/24 , F16K3/265 , F16K17/04 , F16K31/122 , F16K31/1221 , F16K31/1223
摘要： A pressure relief system (400) is provided and a corresponding method (600) for relieving pressure from a duct (402) routing a gas from a compressor (103) to a load utilizing the same. According to one aspect, a pressure relief assembly (104), located near the load, and independent of the primary load compressor pressure relief valve (104), for use with the duct includes a cover (222), first and second chambers (212, 214), and a piston (220). The piston provides a moveable wall between the chambers and is coupled to the cover. As gas from the duct enters the two chambers, the configuration of the chambers provides for a pressure differential that moves the piston and the corresponding cover. This movement transitions the cover from a closed configuration that seals the duct to an open configuration that allows gas within the duct to escape.
摘要翻译：提供了一种压力释放系统（400）以及用于从管道（402）中释放压力的相应方法（600），所述管道将来自压缩机（103）的气体引导至利用其的负载。根据一个方面，位于负载附近且独立于主负载压缩机压力释放阀（104）的用于与管道一起使用的卸压组件（104）包括盖（222），第一和第二腔室（212），214）和活塞（220）。活塞在腔室之间提供可移动的壁并与盖连接。随着来自管道的气体进入两个腔室，腔室的构造提供了压差，该压差使活塞和相应的盖子移动。该运动将盖从封闭管道的封闭结构过渡到允许管道内的气体逸出的打开结构。

6. 发明公开

EP3299290A1 ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT 有权
标题翻译：转向架飞行器的旋转传动装置
公开(公告)号：EP3299290A1
公开(公告)日：2018-03-28
申请号：EP16206787.0
申请日：2016-12-23
申请人： Bell Helicopter Textron Inc.
发明人： IVANS, Steven Ray , ROSS, Brent Chadwick
IPC分类号： B64C29/00
CPC分类号： B64C29/0033 , B64C3/18 , B64C39/024 , B64C2201/104 , B64C2201/108 , B64C2201/165 , B64D27/02 , B64D33/02 , B64D33/04 , B64D35/04 , B64D35/08 , F16H1/203 , F16H35/008
摘要： A propulsion system includes an engine (116) disposed within a fuselage (102), a first gearbox (130) coupled to the engine (116), a wing member having an upper wing skin and torque box formed by a first rib (172), a second rib (174), a first spar (176) and second spar (178), a drive shaft (132) coupled to the first gearbox (126) and disposed within the wing member, a second gear box (134) coupled to the drive shaft (132) and disposed outboard from the second rib (174) or inboard from the first rib (172), and a rotatable proprotor (106) coupled to the second gear box (134). The rotatable proprotor (106) includes a plurality of rotor blades (114), a rotor mast (140) having a mast axis of rotation (180), and a proprotor gearbox (136) coupled to the rotor mast (140). The proprotor gearbox (136) is rotatable about a conversion axis (156), which intersects with the mast axis of rotation (180) at a point within a central region of the torque box and above the upper wing skin.
摘要翻译：推进系统包括布置在机身（102）内的发动机（116），联接到发动机（116）的第一变速箱（130），具有上翼蒙皮和扭矩箱的翼构件，所述上翼蒙皮和扭矩箱由第一肋（172），第二肋（174），第一翼梁（176）和第二翼梁（178），联接到第一变速箱（126）并设置在翼构件内的驱动轴（132），联接第二齿轮箱（132）并且设置在第二肋（174）的外侧或第一肋（172）的内侧，以及联接到第二齿轮箱（134）的可旋转的转速传感器（106）。可旋转的旋翼桨叶（106）包括多个转子叶片（114），具有井架旋转轴线（180）的转子井架（140）以及联接到转子井架（140）的旋翼桨传动装置（136）。推进器变速箱136可绕转换轴线156旋转，所述转换轴线156在转矩箱的中心区域内并且位于上机翼蒙皮上方的点处与转动轴线180相交。

7. 发明授权

EP2714512B1 ROCKET OR BALLISTIC LAUNCHED ROTARY WING UNMANNED AIR VEHICLE 有权转让
标题翻译：火箭或弹道式发射旋翼无人驾驶飞机
公开(公告)号：EP2714512B1
公开(公告)日：2018-02-21
申请号：EP12723862.4
申请日：2012-05-23
申请人： Blue Bear Systems Research Limited
发明人： GREEN, John , GEOGHEGAN, Philip , SNOOK, Michael Alexander
IPC分类号： B64C39/02 , B64C27/605 , B64C27/32 , B64C27/58
CPC分类号： B64C27/605 , B64C27/00 , B64C27/08 , B64C27/32 , B64C27/50 , B64C27/58 , B64C27/59 , B64C39/024 , B64C2201/027 , B64C2201/042 , B64C2201/102 , B64C2201/108 , B64D27/02 , B64D27/24 , B64F1/04
摘要： Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.

8. 发明授权

EP2914490B1 UNBEMANNTES LUFTFAHRZEUG UND BETRIEBSVERFAHREN 有权
公开(公告)号：EP2914490B1
公开(公告)日：2017-05-24
申请号：EP13811348.5
申请日：2013-10-22
申请人： AIRBUS DEFENCE AND SPACE GMBH
发明人： STEINWANDEL, Jürgen , STAGLIANO, Florian , VAN TOOR, Jan
IPC分类号： B64C39/02 , B64D27/02 , B64D27/24 , B64D31/00 , B64D41/00 , F02D29/02
CPC分类号： F02D29/02 , B64C39/024 , B64C2201/024 , B64C2201/042 , B64C2201/044 , B64C2201/066 , B64C2201/086 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/16 , B64D27/02 , B64D27/24 , B64D31/00 , B64D41/00 , B64D2027/026 , Y02T50/44 , Y02T50/64

9. 发明公开

EP3048048A1 AN AIRCRAFT 失效
公开(公告)号：EP3048048A1
公开(公告)日：2016-07-27
申请号：EP15201624.2
申请日：2015-12-21
申请人： Rolls-Royce plc
发明人： Moxon, Matthew
IPC分类号： B64D27/02 , B64D27/14
CPC分类号： B64D27/10 , B64C39/10 , B64C2039/105 , B64D27/02 , B64D27/14
摘要： An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32 - 42) defining a respective rotational plane (D 32 - D 42 ). The rotational plane (D 32 - D 42 ) of at least one of the rotors (32 - 42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b).
摘要翻译：一种飞行器（2）包括至少第一和第二燃气涡轮发动机（10a，10b），所述第一和第二燃气涡轮发动机（10a，10b）布置成大致垂直于飞机纵轴线（A）延伸的直线，每个发动机（10a，10b）包括至少一个压缩机或涡轮转子盘（32-42）限定相应的旋转平面（D32-D42）。至少一个发动机（10a，10b）的至少一个转子（32-42）的旋转平面（D32-D42）相对于飞机纵向线（A）倾斜，使得爆破盘平面相应的发动机（10a，10b）与另一个发动机（10a，10b）不相交。

10. 发明公开

EP3006334A1 A system and a method for connecting an all-wing carrier with parasite flying units 有权
标题翻译：系统和Verfahren zur Verbindung einesNurflügelträgersmitparasitärenFlugeinheiten
公开(公告)号：EP3006334A1
公开(公告)日：2016-04-13
申请号：EP14461575.4
申请日：2014-10-06
申请人： Patents Factory Ltd. Sp. z o.o.
发明人： Paczkowski, Jacek , Nalewa, Tomasz , Kramek, Krzysztof
IPC分类号： B64C39/02 , B64C39/10 , B64D5/00
CPC分类号： B64D5/00 , B64B2201/00 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/042 , B64C2201/063 , B64C2201/066 , B64C2201/082 , B64C2201/206 , B64D27/02 , B64D39/00 , B64D2211/00
摘要： A system for connecting an all-wing carrier with a parasite flying unit, characterized in that the carrier (1) and the parasite flying unit (2) are connected via energy distribution means (11 a, 21a, 11b, 21b) configured to exchange energy bi-directionally, wherein the system further comprises a controller (41) configured to control the direction of the flow and the amount of said energy.
摘要翻译：一种用于连接全翼载体与寄生飞行单元的系统，其特征在于，所述载体（1）和所述寄生虫飞行单元（2）通过经配置以交换的能量分配装置（11a，21a，11b，21b）连接其中所述系统还包括被配置为控制所述流动方向和所述能量的控制器（41）。

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