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公开(公告)号：EP1735211B1
公开(公告)日：2009-09-09
申请号：EP05733257.9
申请日：2005-04-18
发明人： MÄNZ, Christian
摘要： The invention relates to nose parts of the fairing of vertical and horizontal tails and wings of an aircraft with a skin and a support structure, the skin (2) being disposed on the support structure (4, 6). The support structure is provided with a plurality of ribs (6) and a plurality of stringers (4), the plurality of stringers being arranged on the plurality of ribs to support the skin. Advantageously, an improved deformation behavior can be obtained, e.g. in the event of an impact of a bird, while the weight and cost are minimized by providing the stringers.
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2.发明公开Method and apparatus for actuating movable components, including canards, over multiple ranges 审中-公开用于在多个调整的致动的可调节元件的方法和装置
公开(公告)号：EP1413516A1
公开(公告)日：2004-04-28
申请号：EP03078276.7
申请日：2003-10-16
申请人： The Boeing Company
发明人： Jones, Kelly T.
CPC分类号： F16C19/50 , B64C1/26 , B64C3/38 , B64C3/385 , B64C5/04 , B64C5/16 , B64C9/02 , B64C13/30 , B64C13/32 , B64C39/12 , F16C2326/43 , Y02T50/44 , Y10T29/49545 , Y10T29/49638 , Y10T29/49643 , Y10T29/4973
摘要： Methods and apparatuses for installing and actuating movable components (140), including canards, over multiple ranges. An apparatus in accordance with one embodiment of the invention includes a canard (140) coupled to multiple actuators (161,665), one of which moves the canard over a first range of motion and the other of which moves the canard over a second, extended range of motion. A lockout device (690) can prevent actuation over the second range of motion except when selected conditions are met.
摘要翻译： 该组件（60）具有与在锚定端（94）枢转地联接到可延伸的致动器（24）的一个端部（30）枢转地联接到的一个部分（78）的反应链路（90）和一驱动端（92） 驱动构件（74）。 可伸展致动器具有到致动器轴（25）那样不与飞机控制组件（22）的旋转轴线相交。 因此独立权利要求中包括了以下内容：（a）一种鸭翼组件; （B）在飞机; 和（c）到飞机控制部件致动方法。
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3.发明授权Efficient wing tip devices and methods for incorporating such devices into existing wing designs 有权有效翼尖装置和用于将这样的设备到现有机翼的方法
公开(公告)号：EP1493660B2
公开(公告)日：2012-10-24
申请号：EP04076872.3
申请日：2004-06-29
申请人： The Boeing Company
发明人： McLean, James D.
CPC分类号： B64C3/10 , B64C5/04 , B64C23/069 , Y02T50/12 , Y02T50/164
摘要： Efficient wing tip devices for use with aircraft wings. In one embodiment, an aircraft wing/winglet combination includes a wing having a wing root portion and a wing tip portion spaced apart from the wing root portion. The wing tip portion can have a wash-out twist relative to the wing root portion. The aircraft wing/winglet combination can further include a winglet extending from the wing tip portion of the wing. The winglet can be swept at least generally forward relative to the wing to favorably change the lift distribution on the wing and in turn reduce the induced drag on the wing.
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公开(公告)号：EP1735211A1
公开(公告)日：2006-12-27
申请号：EP05733257.9
申请日：2005-04-18
发明人： MÄNZ, Christian
摘要： The invention relates to nose parts of the fairing of vertical and horizontal tails and wings of an aircraft with a skin and a support structure, the skin (2) being disposed on the support structure (4, 6). The support structure is provided with a plurality of ribs (6) and a plurality of stringers (4), the plurality of stringers being arranged on the plurality of ribs to support the skin. Advantageously, an improved deformation behavior can be obtained, e.g. in the event of an impact of a bird, while the weight and cost are minimized by providing the stringers.
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5.发明公开Method and apparatus for rotatably supporting movable components, including canards 有权Verfahren und Vorrichtung zur Lagerung drehbarer Teile
公开(公告)号：EP1413782A1
公开(公告)日：2004-04-28
申请号：EP03078323.7
申请日：2003-10-21
申请人： The Boeing Company
CPC分类号： F16C19/50 , B64C1/26 , B64C3/38 , B64C3/385 , B64C5/04 , B64C5/16 , B64C9/02 , B64C13/30 , B64C13/32 , B64C39/12 , F16C2326/43 , Y02T50/44 , Y10T29/49545 , Y10T29/49638 , Y10T29/49643 , Y10T29/4973
摘要： Methods and apparatuses for rotatably supporting movable components (140), including canards. An apparatus in accordance with one embodiment of the invention includes an airfoil configured positioned external to an aircraft fuselage.
A connecting portion (140) can depend from the airfoil portion and can have an attachment portion configured to attach to an aircraft, internal to the aircraft fuselage. Rollers (1080) carried by one of the connecting portion and the fuselage can rotatably contact a track (1070a) carried by the other of the connecting portion and the fuselage.摘要翻译： 组件（60）具有反作用连杆（90），其中可枢转地联接到可延伸致动器（24）的一端（30）的枢轴端（94）和枢转地联接到可伸缩致动器（24）的一部分（78）的驱动端 驱动构件（74）。 可延伸致动器具有不与飞行器控制部件（22）的旋转轴线相交的致动器轴线（25）。 还包括以下独立权利要求：（a）一个鸭子装配; （b）飞机; 和（c）飞机控制部件致动方法。
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公开(公告)号：EP2961652B1
公开(公告)日：2017-01-04
申请号：EP14709508.7
申请日：2014-02-25
摘要： An aircraft includes a fuselage, a main wing pivotally coupled to an aft portion of the fuselage, and a canard coupled to a forward portion of fuselage, wherein the main wing and the canard are configured to be connected together for supersonic flight and disconnected from each other for subsonic flight.
摘要翻译： 飞机包括机身，枢转地联接到机身的后部的主翼，以及耦合到机身的前部的鸭舌，其中主翼和鸭被构造成连接在一起用于超音速飞行并且与每个机身断开连接 其他为亚音速飞行。
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公开(公告)号：EP2499042A2
公开(公告)日：2012-09-19
申请号：EP10788157.5
申请日：2010-11-05
申请人： Marganski, Edward
发明人： Marganski, Edward
IPC分类号： B64C5/04
摘要： The object of the invention is an aircraft provided with a device for creating a constant moment in relation to the axis of rotation of an additional control surface placed at the front of the aircraft at an as large as possible distance from the centre of gravity of the aircraft. The aircraft is characterised in that the control of the aerodynamic vertical force (7) is effected by deflecting control elements (3) pivotably mounted on the rotation axis (4), the deflection of said control elements causing rotation of a balance and control surface (1) mounted rotatably on axis (2), wherein the axis (2) is mounted perpendicularly to the plane of symmetry (5) of aircraft (6) forward of the resultant aerodynamic vertical force (7) generated by the balance and control surface (1).
摘要翻译： 本发明的目的是提供一种飞行器，该飞行器用于相对于放置在飞机前部的附加控制表面的旋转轴线产生恒定的力矩，该力矩与飞行器的重心距离尽可能大 飞机。 该飞行器的特征在于，通过偏转枢转地安装在旋转轴线（4）上的控制元件（3）来实现气动垂直力（7）的控制，所述控制元件的偏转导致平衡和控制表面（ 其中轴（2）垂直于飞机（6）的对称面（5）安装在由平衡和控制表面（7）产生的合成气动垂直力（7） 1）。
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8.发明授权Efficient wing tip devices and methods for incorporating such devices into existing wing designs 有权有效翼尖装置和用于将这样的设备到现有机翼的方法
公开(公告)号：EP1493660B1
公开(公告)日：2007-12-26
申请号：EP04076872.3
申请日：2004-06-29
申请人： The Boeing Company
发明人： McLean, James D.
CPC分类号： B64C3/10 , B64C5/04 , B64C23/069 , Y02T50/12 , Y02T50/164
摘要： Efficient wing tip devices for use with aircraft wings. In one embodiment, an aircraft wing/winglet combination includes a wing having a wing root portion and a wing tip portion spaced apart from the wing root portion. The wing tip portion can have a wash-out twist relative to the wing root portion. The aircraft wing/winglet combination can further include a winglet extending from the wing tip portion of the wing. The winglet can be swept at least generally forward relative to the wing to favorably change the lift distribution on the wing and in turn reduce the induced drag on the wing.
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公开(公告)号：EP0388068A3
公开(公告)日：1991-02-06
申请号：EP90302407.3
申请日：1990-03-07
摘要： A flight vehicle includes a fuselage 10 having a consumable fuel supply 18,12, main wings 12 each with an elevon 14 and a pair of jettisonable foreplanes 16. The foreplanes provide lift at take-off and during transonic flight and, at higher supersonic speeds they are jettisoned.
摘要翻译： 飞行器包括机身10，机身10具有消耗性燃料供应18,12，主翼12，每个主翼12具有升降机14和一对可抛弃的前机16.前机在起飞和跨音速飞行期间提供升力，并且在更高的超音速 他们被抛弃。
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