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    YAW CONTROL IN AN AIRCRAFT
    3.
    发明公开
    YAW CONTROL IN AN AIRCRAFT 审中-公开
    YAW在飞机上的控制

    公开(公告)号：EP3248866A1

    公开(公告)日：2017-11-29

    申请号：EP17172520.3

    申请日：2017-05-23

    申请人： Lockheed Martin Corporation

    发明人： DORSETT, Kenneth Merle ,  STORRIE, Robert Carl

    IPC分类号： B64C5/08 ,  B64C5/10 ,  B64C9/12 ,  B64C9/32

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

    摘要： A first deflector (250) configured to couple to a shaft of a wing (120) of an aircraft (100) and form part of a top surface (242) of the wing (120) when in a first closed position, and a second deflector (260) configured to couple to the shaft (310) and form part of a bottom surface (244) of the wing (120) when in a second closed position. The first deflector (250) and the second deflector (260) may be configured to be positioned proximate to the tip (220) of the wing (120). The first deflector (250) and the second deflector (260) may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft (310).

    摘要翻译： 第一偏转器（250），其被配置成在处于第一关闭位置时联接到飞行器（100）的机翼（120）的轴并形成机翼（120）的顶表面（242）的一部分;以及第二偏转器 偏转器260构造成在处于第二关闭位置时联接到轴310并且形成机翼120的底表面244的一部分。 第一偏转器（250）和第二偏转器（260）可以被配置成靠近机翼（120）的尖端（220）定位。 第一偏转器（250）和第二偏转器（260）可构造成在轴（310）致动时从闭合位置同时枢转到相应的第一打开位置和第二打开位置。

    PERFORMANCE-ENHANCING WINGLET SYSTEM AND METHOD
    4.
    发明授权
    PERFORMANCE-ENHANCING WINGLET SYSTEM AND METHOD 有权
    提高性能的WingLET系统和方法

    公开(公告)号：EP2644498B1

    公开(公告)日：2017-05-31

    申请号：EP13161307.7

    申请日：2013-03-27

    申请人： The Boeing Company

    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

    CPC分类号： B64C5/10 ,  B64C5/08 ,  B64C23/069 ,  Y02T50/164

    摘要： A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to a ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move from the static position to an in-flight position and resulting in a relative span increase of the wing.

    摘要翻译： 用于飞机机翼（50）的小翼系统（98）可以包括安装到机翼尖端（56）的上部小翼（100）和下部小翼（200）。 当机翼（50）经受地面静态负载时，下部小翼（200）可以具有静态位置。 下部小翼（200）可以构造成使得在大约1g的飞行载荷下向下偏转翼部（50）导致下部小翼（200）从静止位置移动到飞行位置并且导致 （50）的相对跨度增加。

    TAIL SPAR SPRING
    9.
    发明授权
    TAIL SPAR SPRING 有权
    尾羽HOLM

    公开(公告)号：EP2982597B1

    公开(公告)日：2017-01-25

    申请号：EP15177693.7

    申请日：2015-07-21

    申请人： Bell Helicopter Textron Inc.

    发明人： Van Buskirk, Matthew Carl ,  Seifert, Michael Scott ,  Burnett, Michael Christopher ,  Isaac, Mark Loring

    IPC分类号： B64C1/26 ,  B64C5/00 ,  B64C29/00

    CPC分类号： B64C5/02 ,  B64C1/26 ,  B64C5/10 ,  B64C29/0033

    摘要： According to one embodiment, an empennage attachment system features an aft attachment mechanism (164) and a forward attachment system (200). The aft attachment mechanism (164) is configured to be coupled to a tail section of a body of an aircraft (100) and to an empennage (160) proximate to an aft spar (162) of the empennage (160). The aft attachment mechanism (164) defines a pitch axis (165) such that the aft attachment mechanism (164) allows the empennage (160) to rotate about the pitch axis (165). The forward attachment system (200) is configured to be coupled to the tail section of the body and to the empennage (160) proximate to a forward spar (166) of the empennage (160). The forward attachment system (200) is configured to restrict rotation of the empennage (160) about the pitch axis (165) to an allowable range of motion.

    Upper attachment for trimmable horizontal stabiliser actuator
    10.
    发明公开
    Upper attachment for trimmable horizontal stabiliser actuator 有权
    用于可调水平稳定器执行器的上部附件

    公开(公告)号：EP3072808A1

    公开(公告)日：2016-09-28

    申请号：EP15305440.8

    申请日：2015-03-26

    申请人： Goodrich Actuation Systems SAS

    发明人： Medina, Raphael ,  Abdul-Bari, Anh-Vu

    IPC分类号： B64C13/28 ,  F16H25/20

    CPC分类号： B64C5/10 ,  B64C5/02 ,  B64C9/02 ,  B64C13/28 ,  F16H25/20 ,  F16H25/2204 ,  F16H25/2209 ,  F16H25/2454 ,  F16H35/18

    摘要： An upper attachment system for a trimmable horizontal stabiliser actuator (THSA) comprises: a housing 11 holding a yoke 2 and a ballscrew 3; a nut 4 coupled to the housing 11 and cooperating with the ballscrew 3 such that rotation of the ballscrew 3 relative to the nut4 results in linear motion of the ballscrew 3; a recess formed between the yoke 2 and the ballscrew 3 and arranged to receive, in use, an upper part 27 of a tie bar 29 of the secondary load path of the actuator; and a biasing mechanism 6, 7, 8 arranged such that, in use, when no axial load is applied to the tie bar 29, the yoke 2 and the ballscrew 3 are held by balanced forces from the biasing mechanism 6, 7, 8 in a position within the recess, and such that when, in use, an axial load is applied to the yoke 2 by the upper part 27 of the tie bar 29, the balanced forces from the biasing mechanism 7, 8, 9 are overcome and the axial load along with the biasing mechanism 7, 8, 9 results in linear motion of the ballscrew 3 in a first axial direction relative to the nut 4, wherein the linear motion moves the ballscrew 3 toward the yoke 2 and closes the recess around the upper part 27 of the tie bar 29.

    摘要翻译： 用于可修整水平稳定器致动器（THSA）的上部附接系统包括：壳体11，其保持轭2和滚珠丝杠3; 联接到壳体11并与滚珠丝杠3配合的​​螺母4，使得滚珠丝杠3相对于螺母4的旋转导致滚珠丝杠3的线性运动; 在轭2和滚珠丝杠3之间形成并设置成在使用中接收致动器的辅助负载路径的连杆29的上部27的凹部; 以及偏置机构6,7,8，该偏置机构被布置成使得在使用中，当没有轴向载荷施加到连杆29时，轭2和滚珠丝杠3被来自偏置机构6,7,8的平衡力保持在 在凹槽内的位置，并且使得当在使用中由连杆29的上部部分27向轭2施加轴向载荷时，来自偏置机构7,8,9的平衡力被克服，并且 轴向载荷与偏置机构7,8,9一起导致滚珠丝杠3相对于螺母4沿第一轴向方向线性运动，其中直线运动使滚珠丝杠3朝向轭2移动并且闭合围绕鞋帮的凹部 系杆29的部分27。