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公开(公告)号：EP3400167A1
公开(公告)日：2018-11-14
申请号：EP16777761.4
申请日：2016-09-29
发明人： WILSON, Thomas , HERRING, Martin , PATTINSON, John , COOPER, Jonathan , CASTRICHINI, Andrea , AJAJ, Rafic , DHORU, Hitul
CPC分类号： B64C23/065 , B64C3/546 , B64C3/56 , B64C23/072 , Y02T50/14 , Y02T50/164
摘要： An aircraft 1 comprising a wing 5 having a fixed wing 7 with a wing tip device 9 moveably mounted about a hinge 11 (e.g. a double hinge allowing upward and downward rotation). The aircraft comprises a restraining assembly 17 operable between a restraining mode holding the wing tip device in a flight configuration using a restraining force (e.g. by a brake 19) and a releasing mode wherein the restraining force is released, such that the wing tip device is moved relative to the fixed wing into a load alleviating configuration and the wing load is reduced. The load may be due to a gust or a dive. Preferably a biasing member (e.g. a rotation spring 23) exerts a force to urge the wing tip device towards the load alleviating configuration. A control system may switch operation of the restraining assembly in response to an aircraft angle of attack. The wing tip device may also be operable to a ground configuration wherein the span of the aircraft wing is reduced. The hinge may be orientated perpendicular to swept mean chord axis (13, figure 1b) and hence non-parallel to flight direction.
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公开(公告)号：EP2895388A1
公开(公告)日：2015-07-22
申请号：EP13762851.7
申请日：2013-09-17
CPC分类号： B64C3/546 , B64C3/40 , B64C3/54 , B64C39/024 , B64C2003/543 , B64C2201/102 , Y02T50/14
摘要： Embodiments of the present invention relate to an adaptable wing having a variable geometry for influencing aerodynamic performance, the wing comprising a jointed leading edge having a main pivot, and a wrist joint, with a wing arm therebetween, 5 and a distal wing hand depending from the wrist joint; the wing being reciprocally actuable, via the main pivot and wrist joint, between a first state having an extended wing planform and a second state having a tucked wing planform.
摘要翻译： 本发明的实施例涉及一种具有可变几何形状以用于影响空气动力学性能的适应翼，所述机翼包括具有主枢轴的接合前缘和在其间具有翼臂的腕关节5，并且远侧翼手从 腕关节; 所述机翼通过所述主枢轴和腕关节在具有延伸机翼平面图的第一状态和具有卷起的机翼平面图的第二状态之间可往复地起动。
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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.
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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
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。
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公开(公告)号：EP3134314B1
公开(公告)日：2018-09-12
申请号：EP15714912.1
申请日：2015-04-02
发明人： AXFORD, Tim , FONG, Tony , ALEXANDER, Stuart
CPC分类号： B64C23/072 , B64C3/185 , B64C3/54 , B64C3/546 , B64C3/56 , Y02T50/14 , Y02T50/164
摘要： An aircraft including a wing (1) and a wing tip device (6). The wing tip device (6) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is folded inwardly from the flight configuration such that the span of the aircraft is reduced. The wing tip device (6) is connected to the wing along a hinge axis (14) by spar beams (10 and 12) of the wing tip device, one of the beams being mounted for pivoting about a fixed axis and the other beam being mounted on a spherical bearing (15) to provide greater freedom of movement. Various actuator arrangements may be provided to pivot the wing tip device.
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6.发明公开VERTICAL TAKEOFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) 审中-公开无人机（无人机）麻省理工学院VERTIKALEM TAKEOFF UND LANDUNG（VTOL）
公开(公告)号：EP3140188A2
公开(公告)日：2017-03-15
申请号：EP15784502.5
申请日：2015-04-24
发明人： CREASMAN, Son F.
CPC分类号： G05D1/102 , B64C3/546 , B64C3/56 , B64C9/00 , B64C11/48 , B64C25/04 , B64C29/02 , B64C39/024 , B64C2201/028 , B64C2201/102 , B64C2201/108 , B64F1/007 , G05D1/0011
摘要： One example embodiment includes a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV). The VTOL UAV includes a flight control system configured to provide avionic control of the VTOL UAV in a hover mode and in a level-flight mode. The VTOL UAV also includes a body encapsulating an engine and the flight control system. The VTOL UAV further includes a propeller disk coupled to the engine and configured to provide vertical thrust in the hover mode and to provide horizontal thrust for flight during the level-flight mode.
摘要翻译： 一个示例性实施例包括垂直起飞和着陆（VTOL）无人机（UAV）。 VTOL无人机包括飞行控制系统，配置为以悬停模式和水平飞行模式提供垂直起降无人机的航空电子控制。 VTOL无人机还包括一个封装发动机和飞行控制系统的机身。 垂直起落架无人机还包括联接到发动机并被构造成在悬停模式下提供垂直推力并在水平飞行模式期间提供水平推力以用于飞行的螺旋桨盘。
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7.发明公开AN AIRCRAFT WING WITH A WING TIP DEVICE AND A STRUT 审中-公开FLUGZEUGFLÜGELMIT FLUGELSPITZENELEMENT UND STREBE
公开(公告)号：EP3126227A1
公开(公告)日：2017-02-08
申请号：EP15714913.9
申请日：2015-04-02
CPC分类号： B64C23/072 , B64C3/185 , B64C3/54 , B64C3/546 , B64C3/56 , Y02T50/14 , Y02T50/164
摘要： An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). An external strut (9) extends between the wing (1) and the wing tip device (3), the strut (9) being joined to the wing (1) at a second connection (13). The second connection (13) is inboard of the first connection, such that loadings on the wing tip device (3) generated during use, are transferred, via the strut (9), to a location on the wing (1) that is inboard of where the root (7) of the wing tip device (3) is joined to the tip of the wing.
摘要翻译： 飞机机翼（1）具有与其连接的翼尖装置（3）。 翼尖装置（3）的根部（7）在第一连接（11）处连接到机翼（1）的末端。 外部支柱（9）在机翼（1）和翼尖装置（3）之间延伸，支柱（9）在第二连接（13）处连接到机翼（1）。 第二连接件（13）在第一连接件的内侧，使得在使用过程中产生的翼尖装置（3）上的载荷经由支柱（9）传递到位于内侧的机翼（1）上的位置 其中翼尖装置（3）的根部（7）连接到机翼的尖端。
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公开(公告)号：EP3403922A1
公开(公告)日：2018-11-21
申请号：EP17171842.2
申请日：2017-05-18
IPC分类号： B64C3/56
摘要： The present invention relates to a wing arrangement for an aircraft, comprising a wing (9) having a base section (11) and a tip section (13) pivotably connected to base section (11) such that the tip section (13) is pivotable about a tip section pivot axis (17) between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement (21, 21') which includes an engagement portion (25) on one of the tip section (13) and the base section, a latching actuator (33, 33') selectively movable between a first actuator position and a second actuator position, an elastically deformable structure (37a, 25, 29), and a latching element (23, 23') which has a hook-shaped portion, is secured to the other one of the tip section (13) and the base section to be pivotable with respect thereto and is selectively movable between different positions by moving the latching actuator (33, 33').
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公开(公告)号：EP3395677A1
公开(公告)日：2018-10-31
申请号：EP18163340.5
申请日：2018-03-22
发明人： BRAKES, David
摘要： Disclosed is an aerodynamic structure for an aircraft, comprising a first region having a first magnetic sealing surface, movably connected to a second region having a second magnetic sealing surface. The structure is moveable between a first configuration in which the first sealing surface contacts the second sealing surface such that the first region and the second region form a continuous aerodynamic surface, and a second configuration in which a gap exists between the first and second magnetic sealing surfaces and. The magnetic sealing surfaces are configured such that an attractive magnetic force exists between the magnetic sealing surfaces in the first configuration. The aerodynamic structure is configured such that during movement between the first and second configurations, relative movement of the first and second regions occurs along a direction at an angle in the range 1-90° to the normal of the first sealing surface and/or the second sealing surface.
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