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    High-lift device, wing, and noise reduction structure for high-lift device
    3.
    发明授权
    High-lift device, wing, and noise reduction structure for high-lift device 有权
    高升力装置，机翼和降噪结构的提升设备

    公开(公告)号：EP2520488B1

    公开(公告)日：2013-12-18

    申请号：EP12178247.8

    申请日：2008-05-20

    申请人： MITSUBISHI HEAVY INDUSTRIES, Ltd.

    发明人： Hirai, Makoto ,  Maeda, Ichiro

    IPC分类号： B64C9/24

    CPC分类号： B64C9/24 ,  B64C2009/143

    摘要： The present invention provides a high-lift device (3), a wing (1), and a noise reduction structure for high-lift devices capable of suppressing the occurrence of aerodynamic noise while restricting an increase in airframe weight. A high-lift device (3) comprises a slat main body (4) that is disposed so as to be able to extend from and retract into a main wing (2), a concave part (5) that is formed on the slat main body (4) at a location that faces the main wing (2), so as to be able to accommodate at least a part of a leading edge of the main wing (2), and a lower-surface plate (7) that is a plate-like member extending toward the main wing (2) from an edge line at which the lower surface of the slat main body (4) and the concave part (5) meet, and whose angle with respect to the central axis can be deflected, wherein at the trailing edge of the lower-surface plate (7), serrations are provided along the longitudinal direction of the lower-surface plate (7).

    Rotary actuated high lift gapped aileron
    4.
    发明公开
    Rotary actuated high lift gapped aileron 有权
    可旋转的操作，高扬程的差距副翼

    公开(公告)号：EP2669190A1

    公开(公告)日：2013-12-04

    申请号：EP13167503.5

    申请日：2013-05-10

    申请人： The Boeing Company

    发明人： Kordel, Jan A. ,  Sakurai, Seiya

    IPC分类号： B64C9/14 ,  B64C9/18

    CPC分类号： B64C1/10 ,  B64C9/16 ,  B64C9/18 ,  B64C2009/143

    摘要： A rotary actuated high lift gapped aileron linkage (304) is presented. A high lift gapped aileron (306) couples to an airfoil at a hinge line (418) and changes a camber of the airfoil. A rotary actuator (312) coupled to the high lift gapped aileron produces a rotary motion of the high lift gapped aileron in response to an actuation command. A droop panel (308) positioned over the hinge line enhances lift of the high lift gapped aileron. A cove lip door (310) positioned under the hinge line provides an airflow over the high lift gapped aileron. The deployment linkage mechanism coupled to the high lift gapped aileron positions the droop panel and the cove lip door in response to the rotary motion.

    TRANSLATING FLAP DRIVE DOOR
    6.
    发明授权
    TRANSLATING FLAP DRIVE DOOR 有权
    滑门板DRIVE

    公开(公告)号：EP2178747B1

    公开(公告)日：2012-04-18

    申请号：EP08771511.6

    申请日：2008-06-19

    申请人： The Boeing Company

    发明人： COUGHLIN, Ray F.

    IPC分类号： B64C9/16 ,  B64C9/14 ,  B64C21/02

    CPC分类号： B64C9/16 ,  B64C2009/143 ,  Y02T50/32

    摘要： In one embodiment, an apparatus is provided for covering and uncovering a flap opening (14) in an aircraft. The apparatus comprises a door member (22), a torque tube roller member (26), at least one roller member (28), and a biasing member (30). The door member may be adapted to cover and uncover a flap opening. The torque tube roller member may be attached with the door member, and may be adapted to be pushed by a torque tube member (18) attached with a flap (16) of an aircraft. The door member may be adapted to be driven from a closed position covering a flap opening into an open position uncovering a flap opening. The roller member may be attached with the door member and may be adapted to follow at least one track member (20). The biasing member may be attached with the door member for biasing the door member towards a closed position covering a flap opening.

    ACTUATION SYSTEM FOR LEADING EDGE HIGH-LIFT DEVICE
    7.
    发明授权
    ACTUATION SYSTEM FOR LEADING EDGE HIGH-LIFT DEVICE 有权
    控制系统的前缘高升力装置

    公开(公告)号：EP2214959B1

    公开(公告)日：2011-09-14

    申请号：EP08806803.6

    申请日：2008-10-27

    申请人： Airbus Operations Limited

    发明人： CATHELAIN, Francois ,  KAY, Edmund

    IPC分类号： B64C9/24

    CPC分类号： B64C9/24 ,  B64C2009/143 ,  Y02T50/32

    摘要： An actuation system configured to deploy a high-lift device on a leading edge of an aircraft wing. The system comprises: a link pivotally connected to the wing at a first pivot point and to the high-lift device at a second pivot point; a first actuation mechanism configured to rotate the high-lift device about the first pivot point; and a second actuation mechanism configured to rotate the high-lift device about the second pivot point. The second actuation mechanism is operable independently of the first actuation mechanism, and can be operated in order to generate a sealing force between the high-lift device and the leading edge of the aircraft wing.

    AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM
    9.
    发明授权
    AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM 有权

    公开(公告)号：EP3208189B1

    公开(公告)日：2018-12-12

    申请号：EP17156712.6

    申请日：2017-02-17

    申请人： Hamilton Sundstrand Corporation

    发明人： BAINES, Andrew N. ,  CRANDALL-SIEBERT, Cory M. ,  BARGER, Victor ,  LEDEN, William E. ,  BOE, David K.

    IPC分类号： B64C9/16 ,  B64C13/00 ,  B64D45/00

    CPC分类号： B64D45/0005 ,  B64C9/02 ,  B64C9/16 ,  B64C9/18 ,  B64C13/00 ,  B64C13/28 ,  B64C13/40 ,  B64C2009/143 ,  B64D2045/001 ,  Y02T50/44

    摘要： An actuator system (100) for controlling a flight surface (24, 26) of an aircraft (10) includes a first actuator (200; 300) having a first actuator input (204; 310) and a first linear translation element (208; 304) that moves based on rotational motion received at the first actuator input (204; 310) and a first sensor (212; 308) coupled to the first linear translation element (208; 304) that generates a first output based on a displacement of the first linear translation element (208; 304). The system also includes a second actuator (202; 300) having a second actuator input (206; 310) and a second linear translation element (210; 304) that moves based on rotational motion received at the second actuator input (206; 310) and a second sensor (214; 308) coupled to the second linear translation element (210; 304) that generates a second output based on a displacement of the second linear translation element (210; 304). The system also includes a control unit (102) that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.