公开(公告)号：US20170341731A1

公开(公告)日：2017-11-30

申请号：US15166369

申请日：2016-05-27

申请人： Lockheed Martin Corporation

发明人： Kenneth Merle Dorsett ,  Robert Carl Storrie

IPC分类号： B64C9/34 ,  B64C13/28 ,  B64C9/02

CPC分类号： B64C9/34 ,  B64C5/08 ,  B64C5/10 ,  B64C9/02 ,  B64C9/12 ,  B64C9/323 ,  B64C13/28 ,  B64C13/30 ,  Y02T50/44

摘要： In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

公开(公告)号：US20160318601A1

公开(公告)日：2016-11-03

申请号：US14677512

申请日：2015-04-02

申请人： Marc Arnold

发明人： Marc Arnold

IPC分类号： B64C13/28 ,  B64C13/04 ,  B64C9/20 ,  B64C9/18 ,  B64C39/02 ,  G05D1/06 ,  B64C13/16 ,  B64C9/10

CPC分类号： B64C13/28 ,  B64C9/10 ,  B64C9/12 ,  B64C9/18 ,  B64C9/20 ,  B64C13/04 ,  B64C13/16 ,  B64C19/02 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/141 ,  G05D1/0661 ,  G05D1/0676 ,  Y02T50/32 ,  Y02T50/44

摘要： A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor with memory containing firmware configured to: when the mode switch is in manual mode, drive both spoiler servos to a symmetrical position according to the spoiler control; when the mode switch is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting.

摘要翻译： 用于高宽比飞行器的控制增强系统具有副翼/襟翼和节气门位置传感器; 扰流板和挡板控制; 具有手动和着陆模式的模式切换; 所述控制器包括至少一个处理器，所述处理器具有包含固件的存储器，所述固件被配置为：当所述模式切换器处于手动模式时，根据所述扰流器控制将所述扰流器伺服驱动到对称位置; 当模式切换器处于着陆模式时，将左侧扰流板驱动到依赖于副翼和节气门位置的位置，而将右侧扰流板驱动到依赖于副翼和节气门位置的位置，当副翼不对中时，左侧和右侧扰流板位置不同， 当节气门位置处于低功率设置时，与节气门位置处于高功率设置时相比，平均的扰流器位置被更充分地部署。

公开(公告)号：US09272770B2

公开(公告)日：2016-03-01

申请号：US13790286

申请日：2013-03-08

申请人： AIRBUS OPERATIONS (SAS)

发明人： Benoit Joalland ,  Martin Delporte

IPC分类号： B64C13/16 ,  B64C9/12 ,  G05D1/00 ,  B64C9/32

CPC分类号： B64C13/16 ,  B64C9/12 ,  B64C9/323 ,  G05D1/0083 ,  Y02T50/32

摘要： A method and apparatus for carrying out a symmetric deflection of the spoilers so as to reduce the lift of the aircraft during a takeoff roll thereby improving lateral and directional control on the ground.

摘要翻译： 一种用于执行扰流板的对称偏转的方法和装置，以便在起飞辊期间减小飞行器的升力，从而改善地面上的横向和方向控制。

公开(公告)号：US07641152B2

公开(公告)日：2010-01-05

申请号：US11734842

申请日：2007-04-13

申请人： Dan Onu ,  John D. Winter ,  Candy L. Carr ,  Paul M. Vijgen ,  Gary A. Emch ,  Michael E. Renzelmann

发明人： Dan Onu ,  John D. Winter ,  Candy L. Carr ,  Paul M. Vijgen ,  Gary A. Emch ,  Michael E. Renzelmann

IPC分类号： G05D1/00

CPC分类号： B64C9/12 ,  Y02T50/32 ,  Y02T50/44

摘要： The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

摘要翻译： 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用改变飞行器条件的输入，如高度，马赫数，重量，重心，垂直速度和飞行阶段。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。

公开(公告)号：US20090283632A1

公开(公告)日：2009-11-19

申请号：US12507573

申请日：2009-07-22

申请人： Brian Herman Morgan ,  David LeRoy Hagen

发明人： Brian Herman Morgan ,  David LeRoy Hagen

IPC分类号： B64C9/00

CPC分类号： B64C9/06 ,  B64C5/02 ,  B64C5/06 ,  B64C9/12 ,  Y02T50/32

摘要： An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a plurality of thrusters mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface.

摘要翻译： 飞机姿态控制配置使得控制面能够在悬停或低空气速度条件下为飞行器提供姿态控制。 飞行器姿态控制结构包括安装在飞行器上用于推动空气的多个推进器，第一控制表面，其在第一推进器下游的位置处运动学地联接到飞行器，以使第一矢量力由推动的一部分产生 来自第一控制表面上的第一推进器的空气和在第二推进器下游的位置处运动学地联接到飞行器的第二控制表面，第一和第二控制表面在飞行器的纵向轴线的相对侧对称移位 所述第二控制表面被配置为相对于所述第一控制表面独立且可差分移动，以使第二向量力由所述第二控制表面上的来自所述第二推进器的被推动空气的一部分产生。

公开(公告)号：US20090250551A1

公开(公告)日：2009-10-08

申请号：US11720818

申请日：2005-12-05

申请人： Frederic Sauvinet

发明人： Frederic Sauvinet

IPC分类号： B64C9/00

CPC分类号： B64C9/12

摘要： The invention concerns a method which consists in subdividing the direction of the control surface into at least two elements (6I, 6S) and, during a roll control using the ailerons (5G, 5D), steering the upper element (6S) in the roll direction and the lower element (6I) in the opposite direction.

摘要翻译： 本发明涉及一种方法，该方法包括将控制表面的方向细分成至少两个元件（6I，6S），并且在使用副翼（5G，5D）进行滚动控制期间，将滚轮中的上部元件（6S） 方向和下部元件（6I）在相反方向。

公开(公告)号：US20060038086A1

公开(公告)日：2006-02-23

申请号：US11206313

申请日：2005-08-17

申请人： Daniel Reckzeh

发明人： Daniel Reckzeh

IPC分类号： B64C3/00

CPC分类号： B64C3/50 ,  B64C3/10 ,  B64C9/12 ,  B64C9/18 ,  B64C13/16 ,  B64C13/24 ,  Y02T50/12 ,  Y02T50/14

摘要： A system for setting a span load distribution of a wing of an aircraft with a base flap system comprises at least one inboard flap element and one outboard flap element, which elements in the direction of the span are arranged on the trailing edge of the wing, and can be positioned relative to the span direction of the wing. The flap elements are not mechanically coupled with each other and are controlled independently of each other for the purpose of setting the span load distribution.

公开(公告)号：US06641086B2

公开(公告)日：2003-11-04

申请号：US09930339

申请日：2001-08-14

申请人： Walter D. Clark

发明人： Walter D. Clark

IPC分类号： B64C1300

CPC分类号： B64C9/12 ,  B64C39/10 ,  G05D1/0841 ,  Y02T50/12 ,  Y02T50/32

摘要： A system for controlling an aircraft includes an airframe, a first airfoil, and a second airfoil. At least a portion of the first airfoil and the second airfoil are controllably deflectable so that, during a roll maneuver, the first airfoil generates increased lift and a consequent increased drag, and the second airfoil generates negative lift and a consequent increased drag, the increased lift and the decreased lift generating a roll moment, and the increased drag of the second airfoil producing a yaw moment that counteracts the yaw moment produced by the increased drag of the first airfoil such that no substantial change in aircraft yaw moment occurs. The drag on the down-going wing may counteract the drag on the up-going wing by having a reduced area providing the down-going force so that it has to deflect to the point that it is producing not only less, but actually negative lift.

摘要翻译： 用于控制飞行器的系统包括机身，第一翼型件和第二翼型件。 第一翼型件和第二翼型件的至少一部分是可控地偏转的，使得在滚动机动过程中，第一翼型件产生增加的升力和随之而来的增加的阻力，并且第二翼型件产生负提升并随之产生增加的阻力，增加 并且减小的升力产生滚动力矩，并且第二翼型件的增加的阻力产生横摆力矩，其抵消由第一翼型件的增加的阻力产生的横摆力矩，从而不会发生飞行器横摆力矩的实质变化。 下行翼上的阻力可能会通过减小面积来提供下降的力量来抵消上升机翼上的阻力，使其必须偏转到不仅产生较小的但实际上为负的升力 。

公开(公告)号：US20030122038A1

公开(公告)日：2003-07-03

申请号：US10026881

申请日：2001-12-27

申请人： TOYOTA JIDOSHA KABUSHIKI KAISHA

发明人： Yoshiki Fukada

IPC分类号： B64C013/16

CPC分类号： B64C9/12 ,  Y02T50/32

摘要： The present invention is structured such that lift control apparatus such as flaps and flaperons operate in association with elevator operation performed by a pilot. Lift control conforming to elevator operation by the pilot is performed.

摘要翻译： 本发明的结构使得诸如襟翼和襟副翼的升降机控制装置与由飞行员执行的电梯操作相关联地操作。 执行与飞行员的电梯操作一致的升降控制。

公开(公告)号：US20030034421A1

公开(公告)日：2003-02-20

申请号：US09930339

申请日：2001-08-14

申请人： Northrop Grumman Corporation

发明人： Walter D. Clark

IPC分类号： B64C005/00 ,  B64C009/00 ,  B64C013/00

CPC分类号： B64C9/12 ,  B64C39/10 ,  G05D1/0841 ,  Y02T50/12 ,  Y02T50/32

摘要： A system for controlling an aircraft includes an airframe, a first airfoil, and a second airfoil. At least a portion of the first airfoil and the second airfoil are controllably deflectable so that, during a roll maneuver, the first airfoil generates increased lift and a consequent increased drag, and the second airfoil generates negative lift and a consequent increased drag, the increased lift and the decreased lift generating a roll moment, and the increased drag of the second airfoil producing a yaw moment that counteracts the yaw moment produced by the increased drag of the first airfoil such that no substantial change in aircraft yaw moment occurs. The drag on the down-going wing may counteract the drag on the up-going wing by having a reduced area providing the down-going force so that it has to deflect to the point that it is producing not only less, but actually negative lift.