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1. 发明授权

EP3299279B1 AIRCRAFT WITH A FUSELAGE-MOUNTED ENGINE AND WING STOW 有权
公开(公告)号：EP3299279B1
公开(公告)日：2018-10-17
申请号：EP16203012.6
申请日：2016-12-08
申请人： Bell Helicopter Textron Inc.
发明人： IVANS, Steven Ray , ROSS, Brent Chadwick
IPC分类号： B64C3/56 , B64C29/00 , B64C39/02 , B64D35/04 , B64D27/14
CPC分类号： B64C3/56 , B64C29/0033 , B64C39/024 , B64C2201/021 , B64C2201/024 , B64C2201/102 , B64C2201/108 , B64D27/14 , B64D35/04 , Y02T50/14
摘要： An aircraft (100) has a fuselage (102), an engine (112) disposed within the fuselage (102), a rotatable wing (104) disposed above the fuselage (102) and selectively rotatable about a wing rotation axis, and a plurality of interconnect driveshafts (128) disposed within the rotatable wing (104), and at least one drive system component that is connected between the engine (112) and the interconnect driveshaft (128) is disposed along the wing rotation axis.

2. 发明公开

EP3374260A1 AERIAL VEHICLE WITH DEPLOYABLE COMPONENTS 有权转让
公开(公告)号：EP3374260A1
公开(公告)日：2018-09-19
申请号：EP16864692.5
申请日：2016-04-21
申请人： Area-I Inc.
发明人： ALLEY, Nicholas Robert , STEELE, Joshua Lemming , WILLIAMS, Jesse Owen , KUEHME, Daniel , PHILLIPS, Jonathan Caleb
IPC分类号： B64C3/56
CPC分类号： B64C3/40 , B64C1/36 , B64C3/54 , B64C3/546 , B64C3/56 , B64C5/02 , B64C5/12 , B64C5/16 , B64C11/28 , B64C13/24 , B64C13/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/12 , B64C2201/123 , B64C2201/127 , B64C2211/00 , Y02T50/14 , Y02T50/44
摘要： An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

3. 发明授权

EP3112259B1 KRUEGER FLAP ASSEMBLY SYSTEMS AND METHODS 有权
公开(公告)号：EP3112259B1
公开(公告)日：2018-09-12
申请号：EP16169854.3
申请日：2016-05-17
申请人： The Boeing Company
发明人： SALMON, Huw James , GOMEZ, Roberto J.
IPC分类号： B64C3/50 , B64C7/02 , B64C9/24
CPC分类号： B64C9/22 , B64C3/48 , B64C3/50 , B64C7/02 , B64C9/24 , Y02T50/14 , Y02T50/32
摘要： Systems and methods according to one or more embodiments are provided for a Krueger flap (104) assembly with dual Krueger seal assemblies (310,312). In certain embodiments, the dual Krueger seal assemblies (310,312) may seal a space between a Krueger flap main body (104) and an aircraft engine (108). Further seals may be provided to seal any gaps between the dual Krueger seal assemblies (310,312). In certain embodiments, one or both of the dual Krueger seal assemblies (310,312) may include centrally grounded springs (418a,418b,420a,420b). The dual Krueger seal assemblies may include a plurality of springs supporting each Krueger seal assembly.

4. 发明公开

EP3281866A3 A ROTATIONAL JOINT FOR AN AIRCRAFT FOLDING WING 有权
公开(公告)号：EP3281866A3
公开(公告)日：2018-05-23
申请号：EP17175292.6
申请日：2017-06-09
申请人： Airbus Operations Limited , Airbus Operations GmbH
发明人： BISHOP, Benjamin , WINKELMANN, Christoph , RUPP, Johannes
IPC分类号： B64C23/06
CPC分类号： B64C3/56 , B64C23/072 , F16C11/10 , Y02T50/14 , Y02T50/164
摘要： An aircraft (2) comprising a wing (1) which comprises a fixed wing (3) and a wing tip device (4) that is rotatable between a flight configuration and a ground configuration, the aircraft having a rotational joint (10) rotatably coupling the wing tip device to the fixed wing (3) and a locking mechanism (46) for locking the rotation mechanism (11) such that the wing tip device is locked in the flight and ground configurations. The locking mechanism (11) comprises first and second locking members (51, 52) and first and second receiving members (53, 54), the locking mechanism (46) locking the wing tip device in a flight configuration or ground configuration by receiving the locking members in the receiving members respectively, and to lock the wing tip device (4) in the other of the flight configuration and ground configuration by receiving the first locking member (51) in the second receiving member (54).

5. 发明公开

EP3287364A1 LATCHING AND LOCKING MECHANISM FOR A FOLDABLE WING ARRANGEMENT 有权
标题翻译：可折叠翼片安装的锁紧和锁紧机构
公开(公告)号：EP3287364A1
公开(公告)日：2018-02-28
申请号：EP16185948.3
申请日：2016-08-26
申请人： Airbus Operations GmbH
发明人： Lorenz, Christian
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , Y02T50/14
摘要： A wing arrangement for an aircraft is described comprising a latching arrangement (29, 29', 29") having a latching member (31, 31', 31") and an engagement device (33), wherein the latching member (31, 31', 31") is fixed to the tip section (13), wherein the engagement device (33) comprises a base member (35) which is supported in a predetermined position on the base section (7) and which comprises an abutment surface (43), and an engagement member (45, 45', 63) which is supported on the base section (7) and which is movable between a release position and a latching position by means of an actuator (49, 49') coupled to the engagement member (45, 45', 63) and the base section (7), wherein when the tip section (13) is in the deployed position, the latching member (31, 31', 31") abuts on the abutment surface (43) and the engagement member (45, 45', 63) can be moved between the release position and the latching position, wherein when the latching member (31, 31', 31") abuts on the abutment surface (43) and the engagement member (45, 45', 63) is in the latching position, the engagement member (45, 45', 63) abuts on a surface section of the latching member (31, 31', 31") facing away from the abutment surface (43) so as to prevent a pivot movement of the tip section (13) about the pivot axis (19) out of the deployed position towards the stowed position.
摘要翻译：描述了用于飞行器的机翼装置，其包括具有闭锁构件（31,31'，31“）和接合装置（33）的闭锁装置（29,29'，29”），其中闭锁构件（31,31 （33）包括基座构件（35），所述基座构件（35）支撑在所述基座部分（7）上的预定位置中，并且所述基座构件（35）包括抵靠表面（31）和一个支承在基部（7）上的接合构件（45,45'，63），该接合构件借助于联接到基部（7）上的致动器（49,49'）可在释放位置和锁定位置之间移动，所述接合构件（45,45'，63）和所述基部（7），其中当所述末端部分（13）处于展开位置时，所述闩锁构件（31,31'，31“）邻接所述接合表面（43）和所述接合构件（45,45'，63）可在所述释放位置与所述闩锁位置之间移动，其中当所述闩锁构件（31,31'，31“）邻接所述支座时所述接合构件（45,45'，63）与所述接合构件（45,45'，63）处于所述闩锁位置时邻接所述闩锁构件（31,31'，31“）的表面区段）远离所述邻接表面（43），从而防止所述末端部分（13）围绕所述枢转轴线（19）枢转运动离开所述展开位置朝向所述收起位置。

6. 发明公开

EP2727827A3 Horizontal folding wingtip 审中-公开
标题翻译：水平折叠翼梢
公开(公告)号：EP2727827A3
公开(公告)日：2018-01-03
申请号：EP13189783.7
申请日：2013-10-22
申请人： The Boeing Company
发明人： Santini, Gregory M , Sakurai, Seiya
IPC分类号： B64C3/56 , B64C23/06 , B64C3/54
CPC分类号： B64C3/56 , B64C3/546 , B64C23/072 , Y02T50/14 , Y02T50/164
摘要： An apparatus of an aircraft (100), the apparatus may include a wing (102,104) comprising an unfixed portion (120) and a fixed portion (124). The unfixed portion movably may connect to the fixed portion. The unfixed portion may include a rotating portion to rotate the unfixed portion between a flight position and a folded position. The fixed portion may connect to the unfixed portion of the wing. A joint may allow rotation of the unfixed portion of the wing with respect to the fixed portion of the wing about a rotation axis.
摘要翻译：一种飞行器（100）的设备，所述设备可以包括包括未固定部分（120）和固定部分（124）的机翼（102,104）。未固定部分可移动地连接到固定部分。未固定部分可以包括旋转部分以在飞行位置和折叠位置之间旋转未固定部分。固定部分可以连接到机翼的未固定部分。接头可允许机翼的未固定部分相对于机翼的固定部分围绕旋转轴线旋转。

7. 发明授权

EP2676878B1 Swing tip assembly rotation joint 失效
标题翻译：旋转头组件旋转接头
公开(公告)号：EP2676878B1
公开(公告)日：2017-11-15
申请号：EP13171165.7
申请日：2013-06-10
申请人： The Boeing Company
发明人： Sakurai, Seiya , Jones, Kelly T. , Fox, Stephen J. , Fox, Bruce R. , Bennett, Nicholas I. , Good, Mark S.
IPC分类号： B64C3/40 , B64C5/14 , B64C23/06 , B64C3/56
CPC分类号： B64C3/56 , Y02T50/14 , Y10T29/49826 , Y10T403/32254 , Y10T403/32327 , Y10T403/32361 , Y10T403/32606
摘要： A rotation joint (304) and methods for rotationally coupling a swing tip assembly (306) to a fluid-dynamic body (302) are presented. A rotation plate (940) configured to couple to the swing tip assembly (306) comprises a slide ring (1008) comprising an open center (1010), an upper slide surface (1012), an inner slide surface (1014), and a lower slide surface (1016). An upper joint plate is slidably coupled to the upper slide surface (1012) and the inner slide surface (1014) is configured to couple the fluid-dynamic body (302). A lower joint plate (960) is slidably coupled to the lower slide surface (1016) and the inner slide surface (1014), and is coupled to the upper joint plate through the open center. The lower joint plate (960) is configured to couple to the fluid-dynamic body (302).

8. 发明公开

EP3197770A1 MORPHING SKIN FOR AN AIRCRAFT 审中-公开
标题翻译：变形皮肤为飞机
公开(公告)号：EP3197770A1
公开(公告)日：2017-08-02
申请号：EP15775003.5
申请日：2015-09-24
申请人： Bombardier Inc. , Short Brothers Plc
发明人： XI, Fengfeng , MOOSAVIAN, Amin , FINISTAURI, Allan Daniel
IPC分类号： B64C3/38 , B64C3/40 , B64C3/42 , B64C3/52 , B64C5/10 , B64C5/14 , B64C3/44 , B64C3/54
CPC分类号： B64C3/38 , B64C3/26 , B64C3/385 , B64C3/40 , B64C3/42 , B64C3/52 , B64C3/54 , B64C5/10 , B64C5/14 , B64C2003/445 , B64C2003/543 , Y02T50/14
摘要： A skin for an aircraft is configured to be disposed on a first rigid member (182). The first rigid member has at least a portion of a structural frame for the aircraft. The skin is configured to be disposed on a second rigid member (184) that has at least a portion of the structural frame for the aircraft. The second rigid member (184) is movable with respect to the first rigid member (182) and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member compensates for at least one of a change in the distance and a change in an orientation between the first rigid member and the second rigid member.
摘要翻译：用于飞行器的蒙皮被配置为设置在第一刚性构件（182）上。第一刚性构件具有用于飞机的结构框架的至少一部分。蒙皮构造成布置在具有用于飞机的结构框架的至少一部分的第二刚性构件（184）上。第二刚性构件（184）能够相对于第一刚性构件（182）移动，并且在第一刚性构件和第二刚性构件之间限定一定距离。表皮的变形构件在第一刚性构件和第二刚性构件之间延伸。变形构件补偿第一刚性构件和第二刚性构件之间的距离变化和取向变化中的至少一个。

9. 发明授权

EP2899119B1 System for latching and locking a folding wing 有权
标题翻译：用于锁定和锁定折叠翼的系统
公开(公告)号：EP2899119B1
公开(公告)日：2017-04-26
申请号：EP14192920.8
申请日：2014-11-12
申请人： The Boeing Company
发明人： Good, Mark S. , Walker, Steven Paul , Lassen, Matthew A. , Pietersen, Quentin T.
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , Y02T50/14 , Y10T403/32254
摘要： A folding wing comprises a fixed section, a folding section, and a latch system for latching the folding section to the fixed section. The latch system includes a plurality of latch pins, and a corresponding plurality of non-backdriveable mechanical actuators for extending the latch pins to engage the folding section.
摘要翻译：折叠翼（300）包括固定部分，折叠部分和用于将折叠部分锁定到固定部分的闩锁系统（320）。闩锁系统包括多个闩锁销（322）以及用于延伸闩锁销（322）以接合折叠部分的相应多个非反向机械致动器（324）。

10. 发明公开

EP3126222A1 AN AIRCRAFT COMPRISING A FOLDABLE AERODYNAMIC STRUCTURE AND A METHOD OF MANUFACTURING A FOLDABLE AERODYNAMIC STRUCTURE FOR AN AIRCRAFT 有权
标题翻译：根据上述制造折叠动力学结构用于飞行器的折叠动力学结构和方法PLANE
公开(公告)号：EP3126222A1
公开(公告)日：2017-02-08
申请号：EP15714916.2
申请日：2015-04-02
申请人： Airbus Operations Limited
发明人： ALEXANDER, Stuart , RANDALL, John
IPC分类号： B64C3/40 , B64C3/42 , B64C3/56
CPC分类号： B64C3/56 , B64C3/40 , B64C3/42 , B64F5/10 , Y02T50/14
摘要： A method of manufacturing a foldable aerodynamic structure, such as a wing, for an aircraft. The wing (1) including an inner region (1) and an outer region (3) rotatable relative to the inner region between a flight configuration and a ground configuration. The method includes designing the foldable aerodynamic structure by determining the location and orientation of an Euler axis of rotation (11) about which the outer region rotates to achieve the ground configuration and determining a cut plane (13), perpendicular to that Euler axis, separating the inner and outer regions; and iteratively repeating this process until a preferred cut plane (13) is obtained that satisfies at least one design criteria.
摘要翻译：如机翼，在飞机：制造的可折叠的空气动力学结构，颜色的方法。所述翼（1）包括所述帧内区域（1），并在外部区域（3）相对于飞行的配置和接地之间配置所述内部区域可旋转基体。该方法包括通过确定开采设计可折叠空气动力学结构围绕该外区域旋转以实现地面配置和确定性采矿的切割平面（13）的旋转（11）的欧拉轴的位置和方向垂直于并欧拉轴，分离所述内部和外部区域; 并且迭代地重复此过程，直到一个优选的切割面（13），获得没有SATIS外资企业至少一个设计标准。

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