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公开(公告)号：US20180088575A1
公开(公告)日：2018-03-29
申请号：US15816839
申请日：2017-11-17
申请人： LAM AVIATION, INC.
发明人： Michael LAM , Greg COLE
CPC分类号： G05D1/0083 , B64C9/04 , B64C9/20 , B64C13/38 , B64C2009/005 , G05D1/0816 , Y02T50/32
摘要： An aircraft includes a wing. The wing includes an aileron pivotally connected to a trailing edge of the wing, and a Lam aileron pivotally connected to the trailing edge of the wing. The aircraft includes a motor connected to the Lam aileron and configured to rotate the Lam aileron. The aircraft includes a controller configured to detect a deflection of the aileron from a neutral position, calculate a target deflection for the Lam aileron using the deflection of the aileron, and cause the motor to rotate the Lam aileron to the target deflection.
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公开(公告)号：US09840320B2
公开(公告)日：2017-12-12
申请号：US14577848
申请日：2014-12-19
申请人： The Boeing Company
CPC分类号： B64C9/04 , B64C9/02 , B64C9/10 , B64C9/16 , B64C9/18 , B64C9/323 , B64C13/28 , B64C2009/005 , Y02T50/32
摘要： A bell crank mechanism is configured to at least indirectly link movement of an aircraft wing spoiler-like hinge panel to the movement of a primary flight control device on an aircraft wing trailing edge. The aircraft wing is configured to be fixed to and to extend from an aircraft fuselage, the wing including a leading edge and a trailing edge. The primary flight control device is attached to the trailing edge, and any movement of the control device is directly subject to an aircraft input controller by a linear actuator. The moveable aerodynamic hinge panel, a secondary control device, is situated proximally to the primary flight control device, and the hinge panel is separately attached to the trailing edge. The bell crank mechanism slaves any hinge panel motion to movements of the primary control device.
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公开(公告)号：US09555875B2
公开(公告)日：2017-01-31
申请号：US14285712
申请日：2014-05-23
发明人： Alexander Burchard
CPC分类号： B64C9/18 , B64C9/04 , B64C9/16 , B64C13/38 , B64C2009/005 , Y02T50/32 , Y10T74/18216
摘要： The present disclosure pertains to an actuation mechanism for a flap with aileron functionality, including a crank having a crank axle, a crank arm and a crank pivot; a displacement shaft articulated to the crank pivot at an actuating end portion; and a rotatable linear-motion bearing in which the displacement shaft is slidably supported, wherein the displacement shaft is fixedly connectable to a flap body of the aircraft flap at a flap end portion of the displacement shaft opposite to the actuating end portion, and wherein the linear-motion bearing is rotatably attachable at a pivot point to an aircraft wing comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point. The present disclosure further pertains to an aircraft flap with such an actuation mechanism and an aircraft having an aircraft flap.
摘要翻译： 本公开涉及具有副翼功能的翼片的致动机构，包括具有曲柄轴，曲柄臂和曲柄枢轴的曲柄; 在致动端部处铰接到曲柄枢轴的位移轴; 以及可旋转的直线运动轴承，其中所述位移轴可滑动地支撑在所述可移动的直线运动轴承中，其中所述位移轴可固定地连接到所述飞行器翼片的翼片主体，所述翼片主体在所述移动轴的与所述致动端部相对的翼片端部处， 直线运动轴承可旋转地附接到包括飞行器翼片的飞行器机翼的枢转点处，使得位移轴能够绕着绕枢转点的飞行器翼展方向的轴线旋转。 本公开还涉及具有这种致动机构的飞机翼片和具有飞行器翼片的飞行器。
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公开(公告)号：US20160176507A1
公开(公告)日：2016-06-23
申请号：US14577848
申请日：2014-12-19
申请人： The Boeing Company
CPC分类号： B64C9/04 , B64C9/02 , B64C9/10 , B64C9/16 , B64C9/18 , B64C9/323 , B64C13/28 , B64C2009/005 , Y02T50/32
摘要： A bell crank mechanism is configured to at least indirectly link any movement of an aircraft wing spoiler-like hinge panel to the movement of an aircraft wing trailing edge flight control device. The aircraft wing is configured to be fixed to and to extend from an aircraft fuselage, the wing including a leading edge and a trailing edge. The flight control device is attached to the trailing edge, and any movement of the control device is directly subject to an aircraft input controller. The moveable aerodynamic hinge panel is situated proximally to the control device, and the hinge panel is separately attached to the trailing edge. As configured, the bell crank mechanism assures that any hinge panel motion is slaved to the control device in a manner intended to optimize aerodynamic performance and efficiency.
摘要翻译： 钟形曲柄机构构造成至少间接地将飞机机翼扰流板状铰链板的任何运动连接到飞机机翼后缘飞行控制装置的运动。 飞行器机翼被配置成固定到飞机机身并从飞机机身延伸，机翼包括前缘和后缘。 飞行控制装置附接到后缘，并且控制装置的任何运动都直接受飞机输入控制器的控制。 可移动空气动力学铰链板位于控制装置的近侧，并且铰链板分别附接到后缘。 如图所示，钟形曲柄机构确保任何铰链板运动以预定的优化空气动力学性能和效率的方式从属于控制装置。
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公开(公告)号：US20150321747A1
公开(公告)日：2015-11-12
申请号：US14699085
申请日：2015-04-29
发明人： Martin RECKSIEK
IPC分类号： B64C9/04
CPC分类号： B64C9/04 , B64C9/02 , B64C9/16 , B64C9/22 , B64D2045/001
摘要： An aircraft wing comprising a main wing, a high lift element, and at least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprises a track element provided on the main wing, and having a first support surface and a first track side wall, an actuator device, a drive rod, and a carriage device connected to the high lift element and having an engagement portion. The object is to provide an aircraft wing which is configured in such a manner that when the connecting system for connecting the high lift element to the main wing fails the high lift element can still be held in a possibly unskewed position.
摘要翻译： 一种飞机机翼，包括主翼，高升力元件和至少两个间隔开的连接系统，用于将高提升元件可移动地连接到主翼，其中每个连接系统包括设置在主翼上的轨道元件，并且具有第一 支撑表面和第一轨道侧壁，致动器装置，驱动杆和连接到高升力元件并具有接合部分的滑架装置。 本发明的目的是提供一种飞行器机翼，其结构使得当用于连接高升力元件与主机翼的连接系统故障时，高升降元件仍然可以保持在可能不偏好的位置。
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公开(公告)号：US20140288731A1
公开(公告)日：2014-09-25
申请号：US14275102
申请日：2014-05-12
IPC分类号： B64C19/00
摘要： A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.
摘要翻译： 公开了一种用于控制具有由手动控制的飞行控制表面和由计算装置控制的飞行器的系统和方法。 本发明通过减少机械飞行控制表面部件同时在机械或电力相关故障的情况下提供足够的后备控制能力来改进总体飞行控制操作。 通过本发明，自动反馈从机械飞行控制表面提供给操作者，该机械飞行控制表面独立于计算机辅助飞行控制表面操作。 此外，通过本发明，对从飞行员接收的力输入信号进行滤波，以改善计算机辅助飞行控制表面的操作。
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7.发明申请Flap System For An Aircraft, Method For Adjusting The Lift Of An Aircraft And Aircraft Comprising A Main Wing And At Least One Flap System 有权飞机翼片系统，用于调整包括主翼和至少一个翼片系统的飞机和飞机的升力的方法公开(公告)号：US20140166819A1
公开(公告)日：2014-06-19
申请号：US14134102
申请日：2013-12-19
IPC分类号： B64C9/18
摘要： A flap system for an aircraft includes a flow body, a trailing flap and a movement means. The flow body includes an upper surface and a lower surface, the lower surface having a recess. The movement means is attachable to the flow body and the trailing flap. The trailing flap includes a shape that corresponds to the recess in the lower surface. The movement means is adapted for conducting at least a chordwise movement of the trailing flap such that it is movable out of and into the recess of the flow body in absence of a gap between the leading edge of the trailing flap and the flow body. Thereby, a clear increase in a lift coefficient may be achieved, while at the same time maintaining a low complexity and a high reliability of the flap system.
摘要翻译： 用于飞行器的翼片系统包括流动体，尾翼和运动装置。 流动体包括上表面和下表面，下表面具有凹部。 运动装置可附接到流动体和尾翼。 尾翼包括对应于下表面中的凹部的形状。 移动装置适于进行尾翼的至少弦和弦运动，使得其在后挡板的前缘和流体之间没有间隙的情况下可移动到流体的凹部中并进入流体的凹部中。 因此，可以实现升力系数的明显增加，同时保持翼片系统的低复杂性和高可靠性。
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公开(公告)号：US07661630B2
公开(公告)日：2010-02-16
申请号：US12075718
申请日：2008-03-13
申请人： John Libby
发明人： John Libby
IPC分类号： B64C9/16
摘要： A bipartite, full span airplane flap system having an inboard flap portion and an outboard flap portion, wherein the outboard flap portion includes an integrated aileron mounted on its substantially equivalent spanwise length. The outboard flap portion is adapted to translate between a first and a second position to create a functional slot between a bottom surface of the flap member leading part and a bottom surface of the airfoil trailing part to draw a portion of higher pressure air from the bottom surface of the airfoil through the functional slot to distribute the higher pressure air over a top surface of the outboard flap portion.
摘要翻译： 具有内侧翼片部分和外侧翼片部分的二分，全跨度飞行器翼片系统，其中所述外侧翼片部分包括安装在其基本相当的翼展长度上的集成副翼。 外侧翼片部分适于在第一和第二位置之间平移以在挡板构件引导部分的底表面和翼型后部的底表面之间形成功能槽，以从底部抽出一部分较高压力的空气 翼面的表面通过功能槽将高压空气分配在外侧翼片部分的顶表面上。
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公开(公告)号：US07546984B2
公开(公告)日：2009-06-16
申请号：US11187334
申请日：2005-07-22
申请人： Bernd Poppe , Kurt Auhagen
发明人： Bernd Poppe , Kurt Auhagen
IPC分类号： B64C9/02
摘要： Described is an interconnection system, in particular for flaps which are located side-by-side, on an aircraft wing, for example landing flaps or high-lift flaps. The interconnection system is in particular characterised in that it comprises a correspondingly guided compensating profile for a gap between the flaps, which gap changes when the flaps are moved. Preferably, the interconnection system is combined with a failsafe device for adjacent flaps in the form of a longitudinally adjustable interconnection strut which is connected to the adjacent flaps by way of corresponding load introduction fittings. The interconnection system is in particular suitable for large aircraft in which the gap between adjacent flaps, due to the relatively large lateral movement of the flaps during retraction and extension, becomes relatively wide, and the forces acting on the flaps are relatively great.
摘要翻译： 描述了一种互连系统，特别是在飞机机翼上并排设置的襟翼，例如落地襟翼或高升襟翼。 互连系统的特征特征在于，其包括用于襟翼之间的间隙的相应引导的补偿轮廓，当襟翼移动时，该间隙变化。 优选地，互连系统与用于相邻翼片的故障保护装置组合，其形式为纵向可调节的互连支柱，其通过相应的负载引入配件连接到相邻的翼片。 互连系统特别适用于大型飞行器，其中相邻翼片之间的间隙由于在缩回和延伸期间襟翼的相对大的横向运动变得相对较宽，并且作用在翼片上的力相对较大。
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公开(公告)号：US20070271008A1
公开(公告)日：2007-11-22
申请号：US11383791
申请日：2006-05-17
IPC分类号： G01C23/00
CPC分类号： B64C13/04 , B64C9/04 , B64C9/10 , B64C13/38 , B64C13/503
摘要： A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces.
摘要翻译： 公开了一种用于控制具有由手动控制的飞行控制表面和由计算装置控制的飞行器的系统和方法。 本发明通过减少机械飞行控制表面部件同时在机械或电力相关故障的情况下提供足够的后备控制能力来改进总体飞行控制操作。 通过本发明，自动反馈从机械飞行控制表面提供给操作者，该机械飞行控制表面独立于计算机辅助飞行控制表面操作。
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