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公开(公告)号：EP2669189A1
公开(公告)日：2013-12-04
申请号：EP13167354.3
申请日：2013-05-10
申请人： The Boeing Company
发明人： Kordel, Jan A. , Sakurai, Seiya
CPC分类号： B64C1/10 , B64C9/16 , B64C9/18 , B64C2009/143
摘要： A rotary actuated high lift gapped aileron system and method are presented. A high lift gapped aileron (306) couples to an airfoil at a hinge line (418) and changes a camber of the airfoil. A rotary actuator (312) coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel (308) positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door (310) positioned under the hinge line provides an airflow over the high lift gapped aileron. A deployment linkage mechanism (504,506,510,512,514) coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.
摘要翻译： 介绍了一种旋转驱动的高升隙气动副翼系统和方法。 高升力有间隙的副翼（306）在铰接线（418）处耦合到翼型并且改变翼型的外倾角。 耦合到高升力有间隙副翼的旋转致动器（312）响应于致动命令产生高升力有间隙副翼的旋转运动。 定位在铰接线上的下垂面板（308）增强了高升力有间隙的副翼的升力。 位于铰接线下方的海湾边门（310）在高升力有间隙的副翼上提供气流。 联接到高升力有间隙的副翼的展开联动机构（504,506,510,512,514）响应于旋转运动而定位下垂板和凹进唇缘门。
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公开(公告)号：EP2509857A1
公开(公告)日：2012-10-17
申请号：EP10788395.1
申请日：2010-12-06
发明人： WILDMAN, Eric
CPC分类号： B64C13/28 , B64C9/20 , B64C9/323 , B64C2009/143 , Y10T29/49815
摘要： An aerodynamic control surface assembly comprising: an aerodynamic control surface (4); an actuator (10) for controlling deployment of the control surface; and a locking mechanism (30) moveable from a locked to an unlocked position. When the locking mechanism is set to the locked position, the actuator is operatively coupled to the control surface and the control surface can move in dependently of the actuator when the locking mechanism is set to the unlocked position. Such an assembly may be used in an aircraft to prevent clashing between a deployed flap (16) and a drooped spoiler (4) in the event of an actuator control systems failure.
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公开(公告)号：EP2268540B1
公开(公告)日：2011-08-24
申请号：EP09724701.9
申请日：2009-03-12
发明人： MANN, Alan
IPC分类号： B64C9/22
CPC分类号： B64C9/22 , B64C2009/143
摘要： An aircraft slat deployment mechanism comprising: a first drive member (4) coupled to the slat at a first pivot point (5); and a second drive member (6) coupled to the slat at a second pivot point (7) which is offset from the first pivot point. A first rack is provided on the first drive member, and a first pinion (11) is carried by the drive shaft (10). The first pinion (11) is arranged to transmit mechanical power from the drive shaft (10) to the first drive member (4) via the first rack. A second rack is provided on the second drive member (6), and a second pinion (12) is carried by the drive shaft (10). The second pinion has a different radius to the first pinion. The second pinion is arranged to transmit mechanical power from the drive shaft to the second drive member via the second rack, such that the second drive member moves at a different speed to the first drive member.
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公开(公告)号：EP2268540A2
公开(公告)日：2011-01-05
申请号：EP09724701.9
申请日：2009-03-12
发明人： MANN, Alan
IPC分类号： B64C9/22
CPC分类号： B64C9/22 , B64C2009/143
摘要： An aircraft slat deployment mechanism comprising: a first drive member (4) coupled to the slat at a first pivot point (5); and a second drive member (6) coupled to the slat at a second pivot point (7) which is offset from the first pivot point. A first rack is provided on the first drive member, and a first pinion (11) is carried by the drive shaft (10). The first pinion (11) is arranged to transmit mechanical power from the drive shaft (10) to the first drive member (4) via the first rack. A second rack is provided on the second drive member (6), and a second pinion (12) is carried by the drive shaft (10). The second pinion has a different radius to the first pinion. The second pinion is arranged to transmit mechanical power from the drive shaft to the second drive member via the second rack, such that the second drive member moves at a different speed to the first drive member.
摘要翻译： 一种飞行器板条展开机构，包括：第一驱动部件（4），其在第一枢轴点（5）处连接到所述板条; 以及第二驱动构件（6），所述第二驱动构件在与所述第一枢转点偏移的第二枢转点（7）处联接至所述缝翼。 第一齿条设置在第一驱动构件上，并且第一小齿轮（11）由驱动轴（10）承载。 第一小齿轮（11）布置成经由第一齿条将驱动轴（10）的机械动力传递至第一驱动构件（4）。 第二齿条设置在第二驱动构件（6）上，并且第二小齿轮（12）由驱动轴（10）承载。 第二小齿轮具有与第一小齿轮不同的半径。 第二小齿轮布置成将机械动力从驱动轴经由第二齿条传递至第二驱动构件，使得第二驱动构件以不同于第一驱动构件的速度移动。
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公开(公告)号：EP2125510B1
公开(公告)日：2010-09-22
申请号：EP08716024.8
申请日：2008-02-25
发明人： VOSS, Timo , LOERKE, Joachim
IPC分类号： B64C9/32
CPC分类号： B64C9/32 , B64C9/18 , B64C9/323 , B64C2009/143
摘要： The invention pertains to a spoiler (5) for an aerodynamically active surface of an aircraft (1), particularly for an airfoil of an aircraft, wherein said spoiler is supported on the aerodynamically active surface such that it is articulated about an axis (11) extending transverse to the air flow direction and can be adjusted relative to the air flow. According to the invention, the spoiler features two or more segments (6, 7) that are arranged behind one another referred to the air flow direction and extend transverse to the air flow direction, wherein said segments are connected to one another in an articulated fashion and can be adjusted to different angles referred to the air flow. The successively arranged segments of the spoiler (5) can be actuated, in particular, by means of an actuating device (8,9,10) in such a way that the rear segment (7) is adjusted relative to the air flow by a greater angle than the front segment (6).
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66.发明授权SEAL ASSEMBLIES FOR USE WITH DROOPED SPOILERS AND OTHER CONTROL SURFACES ON AIRCRAFT 有权密封结构为使用规则破坏者差异和其他控制区的飞机上
公开(公告)号：EP1940680B1
公开(公告)日：2010-07-14
申请号：EP06851632.7
申请日：2006-08-29
申请人： The Boeing Company
CPC分类号： B64C7/00 , B64C9/18 , B64C2009/143 , Y02T50/32 , Y10S277/916
摘要： Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.
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公开(公告)号：EP2125510A1
公开(公告)日：2009-12-02
申请号：EP08716024.8
申请日：2008-02-25
发明人： VOSS, Timo , LOERKE, Joachim
IPC分类号： B64C9/32
CPC分类号： B64C9/32 , B64C9/18 , B64C9/323 , B64C2009/143
摘要： The invention pertains to a spoiler (5) for an aerodynamically active surface of an aircraft (1), particularly for an airfoil of an aircraft, wherein said spoiler is supported on the aerodynamically active surface such that it is articulated about an axis (11) extending transverse to the air flow direction and can be adjusted relative to the air flow. According to the invention, the spoiler features two or more segments (6, 7) that are arranged behind one another referred to the air flow direction and extend transverse to the air flow direction, wherein said segments are connected to one another in an articulated fashion and can be adjusted to different angles referred to the air flow. The successively arranged segments of the spoiler (5) can be actuated, in particular, by means of an actuating device (8,9,10) in such a way that the rear segment (7) is adjusted relative to the air flow by a greater angle than the front segment (6).
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68.发明公开AIRCRAFT TRAILING EDGE DEVICES, INCLUDING DEVICES WITH NON-PARALLEL MOTION PATHS, AND ASSOCIATED METHODS 有权后端设备对于飞机包括与非平行运动CARS设备和相关方法
公开(公告)号：EP1963179A1
公开(公告)日：2008-09-03
申请号：EP06844458.7
申请日：2006-11-20
申请人： THE BOEING COMPANY
发明人： LACY, Douglas, S. , BEYER, Kevin, W. , BROWN, Stephen, T. , DEES, Paul, W. , HUYNH, Neal, V. , KORDEL, Jan, A. , PROW, Clayton, A. , SAKURAI, Seiya
IPC分类号： B64C9/16
CPC分类号： B64C9/16 , B64C2009/143
摘要： Aircraft trailing edge devices (230) , including devices with non-parallel motion paths (241, 242, 243) , and associated methods are disclosed. A device in accordance with one embodiment includes a wing (220) and an inboard trailing edge (231) device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path (241) . An outboard trailing edge (232) device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path (242) that is non-parallel to the first motion path. An intermediate trailing edge device (260) can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path (243) that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.
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69.发明公开SEAL ASSEMBLIES FOR USE WITH DROOPED SPOILERS AND OTHER CONTROL SURFACES ON AIRCRAFT 有权密封结构为使用规则破坏者差异和其他控制区的飞机上
公开(公告)号：EP1940680A2
公开(公告)日：2008-07-09
申请号：EP06851632.7
申请日：2006-08-29
申请人： The Boeing Company
IPC分类号： B64C9/02
CPC分类号： B64C7/00 , B64C9/18 , B64C2009/143 , Y02T50/32 , Y10S277/916
摘要： Aerodynamic seals (140) for use with control surfaces (114a) on aircraft (100) are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member (342) and a second seal member (352). The first seal member has a first proximal portion (344) configured to be attached to a fixed airfoil portion (108) of the aircraft, and a first distal portion (346) configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion (356) configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.
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70.发明公开AEROSPACE VEHICLE LEADING EDGE SLAT DEVICES AND CORRESPONDING METHODS 有权TRAGFLÄCHENKLAPPUNGSVORRICHTUNGEN用于飞机及相关手续
公开(公告)号：EP1843942A1
公开(公告)日：2007-10-17
申请号：EP06733722.0
申请日：2006-01-17
申请人： The Boeing Company
CPC分类号： B64C9/26 , B64C3/50 , B64C9/22 , B64C2003/146 , B64C2009/143 , B64C2230/06 , Y02T50/166
摘要： Aerospace vehicle leading edge slat devices and corresponding methods are generally disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes an airfoil (102a, 102b) having a leading edge (110a, 110b). The system further includes a first flow body (120) fixedly coupled to the airfoil to form at least one gap (114, 115) between the leading edge of the airfoil and the first blow body (120). A second flow body (130) can be coupled to the airfoil and can be movable between at least a retracted position where the second flow body (130) is positioned to at least approximately aerodynamically seal the at least one gap (14, 15), and an extended position where the second flow body (130) is positioned to allow fluid flow through the at least one gap (114, 115).
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