公开(公告)号：EP4400415A1

公开(公告)日：2024-07-17

申请号：EP24151062.7

申请日：2024-01-09

申请人： Bombardier Inc.

发明人： SERMEUS, Kurt

IPC分类号： B64C3/50 ,  B64C13/02 ,  B64C9/12 ,  B64C9/20 ,  B64C9/00

CPC分类号： B64C3/50 ,  B64C13/0425 ,  B64C9/12 ,  B64C2009/00520130101 ,  B64C9/20

摘要： The disclosed systems and methods for for controlling a variable camber (VC) flight control system (200) of an aircraft (10) in a cruise flight phase, comprising: i) in response to a first input from a user, operating the VC flight control system (200) in a first mode, the first mode configured to operate the aircraft (10) according to a passenger comfort goal, by maintaining a deck angle of the aircraft (10) at a low and substantially constant value; and ii) in response to a second input from the user, operating the VC flight control system (200) in a second mode, the second mode configured to operate the aircraft (10) according to an efficiency goal.

公开(公告)号：EP2974955B1

公开(公告)日：2020-03-11

申请号：EP15170142.2

申请日：2015-06-01

申请人： The Boeing Company

发明人： PACHIKARA, Abraham J. ,  MOSER, Matthew A. ,  CARPENTER, Paul H. ,  FINN, Michael R. ,  KOCH, Thomas S. ,  BIENIAWSKI, Stefan R. ,  WHITEHEAD, Brian T.

IPC分类号： B64C13/16 ,  B64C9/12 ,  G05D1/00 ,  B64D45/00 ,  G05D1/08 ,  B64C9/00 ,  B64C3/44

公开(公告)号：EP3323713A1

公开(公告)日：2018-05-23

申请号：EP16199342.3

申请日：2016-11-17

申请人： Airbus Operations S.L.

发明人： López López, Ladislao

IPC分类号： B64C9/32 ,  B64C9/12 ,  B64C5/02 ,  B64C5/06 ,  B64C9/00

CPC分类号： B64C9/12 ,  B64C9/00 ,  B64C9/16 ,  B64C9/32 ,  B64C9/323 ,  B64C13/16 ,  Y02T50/32

摘要： The object of this invention is relative to an air brake system for aircraft able to use a set of control surfaces 42, 43, 44, 45, 46, 52, 53, 54, 55, 56, such as:
- slats 45, 46, 55, 56, mounted on leading edge 47, 57 of each wing 40, 50 of the aircraft 10, able to extent to the front of the wings 40, 50, in order to reduce the stall speed by altering the air flow over the wings 40, 50;
- flaps 44, 54, mounted on the trailing edge 48, 58 of each wing 40, 50 of the aircraft , able to extent to the rear of the wings 40, 50, in order to reduce the stall speed by altering the air flow over the wings 40, 50;
- spoilers 42, 43, 52, 53, located over each wings 40, 50 of the aircraft 10, able to disrupt airflow over the wings 40, 50 and greatly reduce lift;
characterized in that, said air brake system comprise additionally,
- aircraft stabilizers 60, 70, comprising movable control surfaces 61, 62, 71 such as said control surfaces 61, 62, 71 are respectively split in the spanwise direction in at least two parts 61 a, 61 b, 62a, 62b, 71 a, 71 b, configured to be deployed desynchronously when the aircraft touches down.

公开(公告)号：EP2212193A1

公开(公告)日：2010-08-04

申请号：EP08840878.6

申请日：2008-10-16

申请人： AIRBUS OPERATIONS (SAS)

发明人： Journade, Jérôme

IPC分类号： B64C9/12 ,  B64C13/16 ,  B64C23/06

CPC分类号： B64C23/06 ,  B64C9/12 ,  B64C13/16 ,  Y02T50/162

摘要： The invention relates to a method and a device for creating a continuous protected space along the path of an aircraft (1), in which protected space a maximum induced speed Vtc in a vortex (3) of radius Rtc in the wake of an aircraft (1) is decreased by increasing the radius Rtc. The method comprises - a preliminary step of identifying changes in the aerodynamic configurations of the aircraft (1) liable to initiate disruptions in the wake that will have the effect of increasing the radius Rtc, - for each change in configuration determining beforehand the characteristics of propagation of the wake disturbances in the vortex (3), - carrying out, along the course of the aircraft (1), at least two configuration changes separated by a distance such that spaces, in which the effects of the wake disturbances resulting from each of the configuration changes propagated for a predetermined length of time, forms a substantially continuous protected space

公开(公告)号：EP0887256A2

公开(公告)日：1998-12-30

申请号：EP98202168.5

申请日：1998-06-29

申请人： McDonnell Douglas Corporation

发明人： Khavari, Kourosh

IPC分类号： B64C9/12 ,  B64C13/16 ,  G05D1/02

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

摘要： A vertical stabilizer fin and rudder assembly (10) for use on an aircraft including a stabilizer fin (26) with airfoil surfaces and a rudder (18) with a forward margin pivotally mounted on the trailing edge of the stabilizer fin (20). The assembly is subjected to Bernoulli forces as a relatively moving airstream passes over it in a chordal direction. A fin spoiler (26) is pivotally mounted on each fin surface at a forward chordal location on the assembly (10) whereby the effective sideslip capability for the fin surfaces, when the aircraft is operated in a crosswind, is substantially increased.

摘要翻译： 一种在飞行器上使用的垂直稳定翼和方向舵组件（10），包括具有翼型表面的稳定翼（26）和具有可枢转地安装在稳定翼（20）的后缘上的前翼缘的舵（18）。 组装受到伯努利部队的影响，因为一个相对移动的气流在弦方向上传播。 翅片扰流器（26）在组件（10）上的前弦位置处枢转地安装在每个翅片表面上，由此当飞机在侧风中操作时翅片表面的有效侧滑能力大大增加。

公开(公告)号：EP3825227A1

公开(公告)日：2021-05-26

申请号：EP20209049.4

申请日：2020-11-20

申请人： The Boeing Company

发明人： VIJGEN, Paul M. ,  MALACHOWSKI, Adam P. ,  KONINGS, Christopher A. ,  GEPPERT, Brian E.

IPC分类号： B64C9/00 ,  B64C9/04 ,  B64C9/10 ,  B64C9/12 ,  B64C9/32

摘要： Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings are described. An example aircraft includes a wing (800), a lateral-control surface in the form of an aileron (132), a flaperon or a spoiler, as well as a mini-spoiler (808). The lateral-control surface is movably coupled to the wing. The lateral-control surface is movable between a neutral position, a first upward deflected position, and a second upward deflected position extending beyond the first upward deflected position. The mini-spoiler is located on or forward of the lateral-control surface. The mini-spoiler is movable between a retracted position and a deployed position. The mini-spoiler is configured to be moved from the retracted position to the deployed position based on the lateral-control surface being moved from the neutral position to or toward the first upward deflected position.

公开(公告)号：EP3472045A1

公开(公告)日：2019-04-24

申请号：EP17734835.6

申请日：2017-06-16

申请人： C Series Aircraft Limited Partnership

发明人： MCCLEMENTS, Arthur ,  KROESE, Paul

IPC分类号： B64C9/12 ,  B64C13/16 ,  B64C13/50

公开(公告)号：EP3034393A1

公开(公告)日：2016-06-22

申请号：EP15199859.8

申请日：2015-12-14

申请人： The Boeing Company

发明人： Fevergeon, Matthew D M ,  Kordel, Jan A.

IPC分类号： B64C9/16 ,  B64C9/02 ,  B64C9/04 ,  B64C9/12 ,  B64C9/10 ,  B64C9/32

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 150 is configured to at least indirectly link any movement of an aircraft wing spoiler-like hinge panel to the movement of an aircraft wing 110 trailing edge flight control device 124. 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： 双臂曲柄机构150构造成至少间接地将飞机机翼扰流板状铰接面板的任何运动与飞机机翼110后缘飞行控制装置124的运动联系起来。飞机机翼被配置为固定到并延伸 从飞机机身看，机翼包括前缘和后缘。 飞行控制装置连接到后缘，并且控制装置的任何移动都直接受到飞机输入控制器的影响。 可移动的空气动力学铰链面板位于控制装置的近侧，并且铰链面板分别附接到后缘。 如所配置的，钟形曲柄机构确保以旨在优化空气动力学性能和效率的方式将任何铰链面板运动从属于控制装置。

公开(公告)号：EP2930102A1

公开(公告)日：2015-10-14

申请号：EP15162566.2

申请日：2015-04-07

申请人： Arnold, Marc

发明人： Arnold, Marc

IPC分类号： B64C9/12 ,  B64C13/16 ,  B64C19/02 ,  G05D1/00

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 (200) for high aspect ratio aircraft has aileron/ flaperon and throttle position sensors (208, 210, 212, 214); spoiler and flap controls (219, 222); a mode switch (224) with manual, and landing modes; and a controller (202) driving left and right spoiler and flap servos (230, 232, 234), the controller (202) including at least one processor (240) with memory (242) containing firmware configured to: when the mode switch (224) is in manual mode, drive both spoiler servos (230, 232) to a symmetrical position according to the spoiler control (219); when the mode switch (224) 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 (104) 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： 的控制增强系统（200），用于高纵横比飞行器具有副翼/襟副翼和节流位置传感器（208，210，212，214）; 扰流片和对照组（219，222）; 模式开关（224）具有手动和着陆模式; 和控制器（202）驱动左和右阻流板和襟翼伺服（230，232，234），所述控制器（202）包括至少一个处理器（240）与存储器（242）包含固件被配置为：当模式开关（ 224）处于手动模式时，驱动这两个伺服系统的扰流板（230，232），以对称的位置gemäß在扰流板控制（219）; 当模式开关（224）是（在着陆模式，驱动左扰流到依赖于副翼和节气门位置，和右阻流板的位置依赖于副翼和油门位置的位置，左和右阻流板的位置不同每当副翼 104）不集中，并且平均扰流板的位置更完全展开当节气门位置是在低功率设定比当节气门位置是在高功率设置。

公开(公告)号：EP1631493A2

公开(公告)日：2006-03-08

申请号：EP04809418.9

申请日：2004-05-26

申请人： NORTHROP GRUMMAN CORPORATION

发明人： CLARK, Walter, D.

IPC分类号： B64C1/00 ,  B64C5/08 ,  B64C9/12 ,  B64C9/32 ,  B64C9/34 ,  B64C39/02

CPC分类号： B64C1/0009 ,  B64C5/08 ,  B64C9/12 ,  B64C9/32 ,  B64C9/323 ,  B64C9/34 ,  B64C39/024 ,  B64C2001/0045 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/22 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44

摘要： An aircraft (10) with swept back wings (16, 18) and spoilers (30,32) inlaid into the top surface (36) near the tips of the wings. The aircraft also includes an elevator (34) formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings.