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公开(公告)号：EP3301015A1
公开(公告)日：2018-04-04
申请号：EP17194415.0
申请日：2013-06-21
申请人： Bombardier Inc. , Learjet Inc.
CPC分类号： B64C3/38 , B64C3/385 , B64C3/40 , B64C3/44 , B64C3/52 , B64C3/54 , B64C2003/445 , B64C2003/543 , Y02T50/14
摘要： A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration.
摘要翻译： 飞机的变形机翼包括顶面，底面，前缘，后缘，尖端和根部。 多个结构肋设置在根部和尖端之间，使得它们在顶部表面和底部表面之间延伸并且与其横向轴线相交。 至少一个活动构件沿着或者相对于横向轴线以第一角度连接在两个相邻的结构肋之间。 活动构件可主动调整。 至少一个被动构件沿着或者相对于横向轴线以第二角度连接在两个相邻结构肋之间。 被动部件被动调节。 至少一个主动构件的调节使相邻的结构肋相对于彼此移动，由此使机翼从第一构型变形为第二构型。
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公开(公告)号：EP3301015B1
公开(公告)日：2019-05-22
申请号：EP17194415.0
申请日：2013-06-21
申请人： Bombardier Inc. , Learjet Inc.
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公开(公告)号：EP2864195A1
公开(公告)日：2015-04-29
申请号：EP13735135.9
申请日：2013-06-21
申请人： Bombardier Inc. , Learjet Inc.
CPC分类号： B64C3/38 , B64C3/385 , B64C3/40 , B64C3/44 , B64C3/52 , B64C3/54 , B64C2003/445 , B64C2003/543 , Y02T50/14
摘要： A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration.
摘要翻译： 用于飞行器的变形翼包括顶表面，底表面，前缘，后缘，尖端和根部。 多个结构肋设置在根部和尖端之间，使得它们在顶表面和底表面之间延伸并且与其横向轴线相交。 至少一个有源构件沿着或相对于横向轴线以第一角度连接在两个相邻结构肋之间。 活动构件可以主动调节。 至少一个被动构件沿着或相对于横向轴线的第二角度在两个相邻的结构肋之间连接。 被动元件被动调节。 至少一个活动构件的调整使相邻的结构肋相对于彼此移动，从而使机翼从第一构型变形到第二构型。
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公开(公告)号：EP2864195B1
公开(公告)日：2017-11-01
申请号：EP13735135.9
申请日：2013-06-21
申请人： Bombardier Inc. , Learjet Inc.
CPC分类号： B64C3/38 , B64C3/385 , B64C3/40 , B64C3/44 , B64C3/52 , B64C3/54 , B64C2003/445 , B64C2003/543 , Y02T50/14
摘要： A morphing wing for an aircraft includes a top surface, a bottom surface, a leading edge, a trailing edge, a tip, and a root. A plurality of structural ribs is disposed between the root and tip so that they extend between the top surface and the bottom surface and intersect with a lateral axis thereof. At least one active member connects between two adjacent structural ribs along or at a first angle to the lateral axis. The active member is actively adjustable. At least one passive member connects between the two adjacent structural ribs along or at a second angle to the lateral axis. The passive member is passively adjustable. Adjustment of at least one active member moves the adjacent structural ribs with respect to one another, thereby morphing the wing from a first configuration to a second configuration.
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公开(公告)号：EP3699081A1
公开(公告)日：2020-08-26
申请号：EP20158984.3
申请日：2020-02-24
申请人： Bombardier Inc.
IPC分类号： B64C3/42
摘要： A wing having a main wing section (11) with a forward spar (14A) and an aft spar (14B) extending through an internal cavity. The forward and aft spars are spaced apart and delimiting a dry segment of the internal cavity (19). A winglet (20) is rotatably coupled to the main wing section (11) by a cant hinge (30) defining a cant axis (32) about which the winglet (20) rotates relative to the main wing section (11) between an extended position in which the winglet (20) is aligned with the main wing section (11), and a folded position in which the winglet (20) is rotated about the cant axis (32). A linkage assembly (40) disposed in the dry segment is pivotably mounted to one of the forward and aft spars (14A, 14B) and is coupled to the cant hinge (30). The linkage assembly (40) is displaceable to apply a force to move the winglet (20) between the extended position and the folded position during flight of the aircraft.
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公开(公告)号：EP4303121A1
公开(公告)日：2024-01-10
申请号：EP23183964.8
申请日：2023-07-06
申请人： Bombardier Inc.
发明人： XI, Fengfeng , MOOSAVIAN, Amin , KOJOVIC, Stefan , EPP, Jordan
摘要： Aircraft control surface includes a span-wise extending spar having at least one aperture. A displacement guide is adjacent to the aperture. A span-wise extending airfoil is mounted to the spar and extends chord-wise between leading and trailing edges. A resiliently deformable airfoil top skin is mounted to the spar via a leaf spring. The top skin is bendable relative to the spar and extends chord-wise from the spar to a top skin rear edge. A resiliently deformable airfoil bottom skin is disposed beneath the top skin. Part of the bottom skin is displaceable chord-wise through the aperture and is guidable therethrough by the displacement guide. The bottom skin extends chord-wise from the spar to a bottom skin rear edge joined to the top skin rear edge to form the airfoil trailing edge. An actuator is connected to and configured to displace the bottom skin chord-wise to displace the trailing edge.
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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
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。
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