公开(公告)号：EP3597534B1

公开(公告)日：2023-02-22

申请号：EP19196564.9

申请日：2013-03-27

发明人： ROMAN, Dino L. ,  VASSBERG, John Charles ,  FRIEDMAN, Douglas M. ,  MALACHOWSKI, Adam P. ,  VEGTER, Christopher A.

IPC分类号： B64C23/06 ,  B64C5/10 ,  B64C3/58

公开(公告)号：EP3782911B1

公开(公告)日：2022-12-14

申请号：EP20190666.6

申请日：2020-08-12

发明人： SNYDER, Timothy S. ,  ZYSMAN, Steven H.

IPC分类号： B64C5/10 ,  B64C7/00 ,  B64D27/18 ,  B64D29/00 ,  F02C7/00 ,  F02C7/04 ,  F02C7/20 ,  F02K1/82 ,  F02K3/06 ,  F02K1/00

公开(公告)号：EP4043339A1

公开(公告)日：2022-08-17

申请号：EP21204668.4

申请日：2021-10-26

申请人： The Boeing Company

发明人： Vance, Jonathan B. ,  Martignoni, Andrew J. III

IPC分类号： B64C5/10 ,  B64C5/16 ,  B64C13/16 ,  B64C13/50 ,  B64C11/30 ,  B64C11/44

摘要： A calibration system (200) for aircraft control surface actuation includes an inclinometer (204) coupleable to an aircraft control surface. The inclinometer is configured to provide measurement data of an inclination value corresponding to an angle at which the surface is deflected. The system includes an adapter (214) with a wireless transmitter module (216) and an interface connector (218) connected to the inclinometer. The adapter is configured to receive and wirelessly transmit the measurement data. The system includes a wireless receiver device (220) and a computing device (202) connected thereto to receive the measurement data. The computing device is configured to determine if the inclination value differs by more than a predetermined amount from a directed deflection angle for the surface. The computing device is also configured to communicate an adjustment amount to a controller (226) configured to direct deflection of the surface, based on the difference between the measured inclination value and the directed deflection angle.

公开(公告)号：EP3388333B1

公开(公告)日：2020-08-19

申请号：EP18166816.1

申请日：2018-04-11

申请人： Airbus (Beijing) Engineering Centre Company Limited

发明人： SUN, Yumin

IPC分类号： B64C9/16 ,  B64C9/22 ,  B64C9/32 ,  B64C9/34 ,  B64C5/10 ,  B64C3/38

公开(公告)号：EP3668786A1

公开(公告)日：2020-06-24

申请号：EP18749483.6

申请日：2018-08-06

申请人： BAE Systems PLC

发明人： WHITE, Andrew Charles

IPC分类号： B64C5/02 ,  B64C5/10 ,  B64C15/02

公开(公告)号：EP2407376A4

公开(公告)日：2014-06-11

申请号：EP10750404

申请日：2010-03-11

申请人： AIRBUS OPERATIONS SL

发明人： VELA ORGE PILAR ,  NAMER ARNAUD ,  PASCUAL FUERTES ANGEL ,  SIMÓN CALERO FRANCISCO JAVIER

IPC分类号： B64C9/10 ,  B64C5/10 ,  B64C13/28

CPC分类号： B64C9/10 ,  B64C5/02 ,  Y02T50/32 ,  Y02T50/44

摘要： The system includes deflection transmission means (16) to provide a deflection position of the high-lift device (8) for each setting angle position of an adjustable HTP (2). Preferably, the deflection transmission means (18,20,23) comprise essentially of a mechanical linkage connected between the high-lift device (8) and the aircraft (1).

公开(公告)号：EP2595879A1

公开(公告)日：2013-05-29

申请号：EP11741666.9

申请日：2011-07-13

申请人： Airbus Operations SAS

发明人： GALL, Pierre-Emmanuel ,  CROS, Christophe ,  LALLEMAND, Mickaël

IPC分类号： B64C5/10

CPC分类号： B64C5/10 ,  B64C5/06 ,  B64C11/00

摘要： The stabilizing device (1) comprises auxiliary stabilizers (6) which are mounted on the horizontal tailplane (2) of the aircraft and which generate a lateral stabilizing effect when brought into a deployed position.

公开(公告)号：EP2346734A4

公开(公告)日：2013-01-02

申请号：EP10821429

申请日：2010-11-12

申请人： TAMARACK AEROSPACE GROUP INC

发明人： GUIDA NICHOLAS R

IPC分类号： B64C23/06 ,  B64C3/56 ,  B64C5/10 ,  B64C13/16

CPC分类号： B64C23/065 ,  B64C13/16 ,  B64C23/076 ,  Y02T50/164

摘要： An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing, and an angled portion that projects at an upward angle from the body portion. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and increase efficiency.

公开(公告)号：EP2407376A1

公开(公告)日：2012-01-18

申请号：EP10750404.5

申请日：2010-03-11

申请人： Airbus Operations S.L.

发明人： VELA ORGE, Pilar ,  NAMER, Arnaud ,  PASCUAL FUERTES, Angel ,  SIMÓN CALERO, Francisco Javier

IPC分类号： B64C9/10 ,  B64C5/10 ,  B64C13/28

CPC分类号： B64C9/10 ,  B64C5/02 ,  Y02T50/32 ,  Y02T50/44

摘要： The system includes deflection transmission means (16) to provide a deflection position of the high-lift device (8) for each setting angle position of an adjustable HTP (2). Preferably, the deflection transmission means (18,20,23) comprise essentially of a mechanical linkage connected between the high-lift device (8) and the aircraft (1).

摘要翻译： 系统包括偏转传动装置（16），用于为可调HTP（2）的每个设定角度位置提供高升程装置（8）的偏转位置。 优选地，偏转传动装置（18,20,23）基本上包括连接在高升降装置（8）和飞行器（1）之间的机械联动装置。

公开(公告)号：EP2038171B1

公开(公告)日：2011-09-07

申请号：EP07787319.8

申请日：2007-07-10

申请人： Airbus Operations GmbH

发明人： KONECZNY, Manfred

IPC分类号： B64C3/44 ,  B64C5/10

CPC分类号： B64C5/02 ,  B64C3/44 ,  B64C5/10 ,  B64C9/08

摘要： A trimmable horizontal stabilizer, which is provided adjacent to the fuselage (10) of an aircraft and has a predetermined aerodynamic profile, and adjacent to which a movable elevator (21) is arranged. The horizontal stabilizer (20) has a load-bearing structure (22) which extends in the span direction and is firmly connected to the fuselage of the aircraft, and movable areas (23, 24) which are connected to the load-bearing structure (22) such that they can move and can be moved independently of the elevator (21) in order to trim the horizontal stabilizer (20) by varying the aerodynamic profile.