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    HEAT REMOVAL STRUCTURE OF AIRCRAFT MAIN LANDING GEAR BAY
    41.
    发明申请
    HEAT REMOVAL STRUCTURE OF AIRCRAFT MAIN LANDING GEAR BAY 有权
    飞机主要起落架的散热结构

    公开(公告)号：US20160214720A1

    公开(公告)日：2016-07-28

    申请号：US14973098

    申请日：2015-12-17

    申请人： MITSUBISHI AIRCRAFT CORPORATION

    发明人： Nobuhide HARA ,  Tadahiko SUZUTA

    IPC分类号： B64D13/00 ,  B64C25/36 ,  B64C25/16

    CPC分类号： B64D13/006 ,  B60T5/00 ,  B64C1/14 ,  B64C7/00 ,  B64C25/001 ,  B64C25/12 ,  B64C25/16 ,  B64C25/34 ,  B64C25/36 ,  F16D65/847

    摘要： An aircraft includes: a fairing which covers a lower part of a fuselage having a main landing gear bay (MLG bay), and defines a ventilation cavity communicating with the MLG bay between the fairing and the fuselage; and a heat removal system which removes heat generated from the MLG inside the MLG bay to the outside of the MLG bay by suctioning/discharging air through an inlet port and an outlet port leading from the ventilation cavity or the MLG bay to external air. The fairing defines a wheel opening through which a wheel of the MLG enters and exits, and defines a ventilation port, which functions as one of the inlet and outlet ports, between the fairing and an outer peripheral part of the wheel exposed from the wheel opening to the lower side of the MLG bay when the MLG is retracted.

    摘要翻译： 飞机包括：整流罩，其覆盖具有主起落架舱（MLG舱）的机身的下部，并且限定了在整流罩和机身之间与MLG舱相通的通风腔; 以及散热系统，其通过从通风腔或MLG舱引导到外部空气的入口和出口吸入/排出空气，从而将MLG舱内的MLG产生的热量移动到MLG舱的外部。 整流罩定义了一个车轮开口，MLG的车轮通过该车轮开口进入和离开，并且限定了一个通风口，该通风口用作整流罩与从车轮开口露出的车轮外周部分之间的入口和出口之一 当MLG缩回时，到MLG托架的下侧。

    AIRCRAFT LANDING GEAR
    42.
    发明申请
    AIRCRAFT LANDING GEAR 有权
    飞机起落架

    公开(公告)号：US20160207611A1

    公开(公告)日：2016-07-21

    申请号：US14599705

    申请日：2015-01-19

    申请人： Bell Helicopter Textron Inc.

    发明人： Carlos A. Fenny ,  Brent C. Ross ,  Kevin Kell ,  Andrew Baines

    IPC分类号： B64C25/20

    CPC分类号： B64C25/20 ,  B64C25/12 ,  B64C25/18 ,  B64C25/60

    摘要： In some embodiments, an aircraft may include a retractable or extendable landing gear. The landing gear may include a wheel connected to an axle, a strut configured to resist longitudinal compression, and a linear actuator that is partially disposed within an opening of the strut.

    摘要翻译： 在一些实施例中，飞行器可以包括可伸缩或可延伸的起落架。 起落架可以包括连接到轴的轮，被构造成抵抗纵向压缩的支柱，以及部分地设置在支柱的开口内的线性致动器。

    Landing gear with composite leaf spring
    45.
    发明授权
    Landing gear with composite leaf spring 有权
    复合板簧起落架

    公开(公告)号：US08640988B2

    公开(公告)日：2014-02-04

    申请号：US12918492

    申请日：2009-02-24

    申请人： Robert Ian Thompson

    发明人： Robert Ian Thompson

    IPC分类号： B64C25/58 ,  B64C25/10

    CPC分类号： B64C25/62 ,  B64C25/12 ,  B64C25/14 ,  B64C25/18

    摘要： An aircraft landing gear comprising: an arm mounted to a pivot and carrying one or more wheel assemblies; and a composite leaf spring which is coupled to the arm and arranged to provide a resilient biasing force which opposes rotation of the arm about the pivot. The arm can be made relatively stiff in comparison with the leaf spring, so that load is transferred directly into the pivot without a large amount of bending of the leg. The leaf spring shock absorber typically has a reduced part count compared with a conventional oleo-pneumatic shock absorber. By forming the leaf spring from a composite material, its weight is significantly reduced in comparison with a conventional metal spring, making it suitable for use on a relatively large aircraft.

    摘要翻译： 一种飞机起落架，包括：安装到枢轴并承载一个或多个车轮组件的臂; 以及复合板簧，其联接到所述臂并布置成提供与所述臂围绕所述枢轴旋转的弹性偏压力。 与板簧相比，臂可以制成相对刚性，使得负载直接转移到枢轴中，而不会有大量的腿的弯曲。 与常规的油气减震器相比，板簧减震器通常具有减少的部件数量。 通过从复合材料形成板簧，与传统的金属弹簧相比，其重量显着降低，使其适用于较大的飞机。

    LANDING GEAR FOR AN AIRCRAFT
    46.
    发明申请
    LANDING GEAR FOR AN AIRCRAFT 审中-公开
    用于飞机的起落架

    公开(公告)号：US20130313360A1

    公开(公告)日：2013-11-28

    申请号：US13902010

    申请日：2013-05-24

    申请人： Airbus Operations Limited

    发明人： Leung Choi CHOW ,  Christopher Neil Wood ,  Philip Ian Campbell

    IPC分类号： B64C23/00 ,  B64C25/00

    CPC分类号： B64C23/00 ,  B64C25/001 ,  B64C25/12 ,  B64C25/20 ,  B64C25/26 ,  B64C2025/003

    摘要： The invention provides a landing gear 120 for an aircraft 110, the landing gear comprising a main strut 121 having a first upper end arranged to be moveably mounted to a structure of the aircraft, a landing gear wheel assembly 131, 132 connected to a second lower end of the main strut, the landing gear wheel assembly comprising at least one landing gear wheel arranged to roll in a fore-aft direction with respect to the main strut, and a stay 122 having a first upper end arranged to be connected to a structure of the aircraft, and a second lower end pivotally mounted to a mounting element 140 on the main strut, wherein the mounting element on the main strut is positioned substantially in line with the main strut in the fore-aft direction. The invention also provides a main strut, an aircraft and a kit of parts.

    摘要翻译： 本发明提供了一种用于飞行器110的起落架120，起落架包括主支柱121，主支柱121具有布置成可移动地安装到飞行器的结构的第一上端;连接到第二下部的起落架齿轮组件131,132 主支柱的端部，起落架轮组件包括布置成相对于主支柱在前后方向上滚动的至少一个起落架，以及具有布置成连接到主支柱的结构的第一上端的撑杆122 以及枢转地安装到主支柱上的安装元件140的第二下端，其中主支柱上的安装元件基本上与主支柱沿前后方向一致地定位。 本发明还提供主支柱，飞机和一套零件。

    Fuselage mounted landing gear
    47.
    发明授权
    Fuselage mounted landing gear 有权
    机身安装起落架

    公开(公告)号：US08523107B2

    公开(公告)日：2013-09-03

    申请号：US12722848

    申请日：2010-03-12

    申请人： James Jason Salmon ,  Sergey D. Barmichev ,  Michael Allan Long

    发明人： James Jason Salmon ,  Sergey D. Barmichev ,  Michael Allan Long

    IPC分类号： B64C25/10

    CPC分类号： B64C25/12 ,  B64C25/18 ,  B64C25/26 ,  B64C2025/125

    摘要： A landing gear for an aircraft. The landing gear may have a wheel/truck assembly, an oleo strut/support frame for supporting the wheel/truck assembly, and a retraction assembly attached to the oleo strut/support frame, the retraction assembly for moving the landing gear between a deployed position and a retracted position. The retraction assembly may have a pivoting trunnion brace attached to the oleo strut/support frame and to a fuselage of the aircraft for positioning the wheel/truck assembly, the oleo strut/support frame and the retraction assembly at least substantially fully within the fuselage of the aircraft in the retracted position.

    摘要翻译： 飞机起落架。 起落架可以具有轮/卡车组件，用于支撑车轮/卡车组件的油支架/支撑框架和连接到油支架/支撑框架的缩回组件，该缩回组件用于将起落架移动在展开位置 和缩回位置。 缩回组件可以具有连接到油支架/支撑框架和机身的机身的枢转耳轴支架，用于将车轮/卡车组件，油支架/支撑框架和缩回组件至少基本上完全地设置在机身内 飞机处于缩回位置。

    AIRCRAFT LANDING GEAR OF THE ROCKER-ARM AND DEFORMABLE-PARALLELOGRAM TYPE
    48.
    发明申请
    AIRCRAFT LANDING GEAR OF THE ROCKER-ARM AND DEFORMABLE-PARALLELOGRAM TYPE 有权
    摇臂式和可变平行机类型的飞机起落架

    公开(公告)号：US20130020436A1

    公开(公告)日：2013-01-24

    申请号：US13522782

    申请日：2011-01-19

    申请人： Dominique Ducos ,  Jean-François Locufier

    发明人： Dominique Ducos ,  Jean-François Locufier

    IPC分类号： B64C25/12

    CPC分类号： B64C25/12 ,  B64C2025/125

    摘要： The invention relates to an aircraft landing gear of deformable-parallelogram type, including: a leg including a casing (1) having a lower end on which a rocker arm (3) carrying at least one wheel is hinged by means of a pivot (2), a shock absorber (5) being connected between the rocker arm and the casing; two panels (10, 11) each hinged on the one hand on the structure of the aircraft and on the other hand on the leg, about parallel axes; According to the invention, one of the panels (11) is hinged on the leg whilst being connected to the casing by a pin on one end of the pivot (2) of the rocker arm.

    摘要翻译： 本发明涉及一种可变形 - 平行四边形类型的飞机起落架，包括：腿部，其包括具有下端的壳体（1），通过枢轴（2）铰接至少一个轮的摇臂（3） ），在所述摇臂和所述壳体之间连接的减震器（5） 两个面板（10,11）一方面铰接在飞行器的结构上，另一方面在腿上围绕平行的轴线铰接; 根据本发明，一个面板（11）铰接在腿上，同时通过在摇臂的枢轴（2）的一端上的销连接到壳体。

    SKID-TYPE LANDING GEAR FOR A HELICOPTER
    49.
    发明申请
    SKID-TYPE LANDING GEAR FOR A HELICOPTER 有权
    用于直升机的滑轨式起落架

    公开(公告)号：US20110233323A1

    公开(公告)日：2011-09-29

    申请号：US13071333

    申请日：2011-03-24

    申请人： Alexander Engleder ,  Stefan Görlich

    发明人： Alexander Engleder ,  Stefan Görlich

    IPC分类号： B64C25/52

    CPC分类号： B64C25/12 ,  B64C25/52 ,  B64C2025/325

    摘要： The invention relates to a skid-type landing gear (1) for a helicopter (2) comprising bow shaped crosstubes (10-13) directed symmetrically towards a left- and a right-hand side of a longitudinal mid axis (9) of the helicopter (2) with respective skids (14, 15) at outboard ends thereof and main beams (5-8) in a fuselage (4), the crosstubes (10-13) being connected to the main beams (5-8) via supports (16-23) fixed to the main beams (5-8). The skid-type landing gear (1) is retractable. A method for operating such a skid-type landing gear (1) for a helicopter (2) is provided.

    摘要翻译： 本发明涉及一种用于直升机（2）的滑行式起落架（1），该起落架起落架（2）包括弓形交叉管（10-13），其对称地朝着所述纵向中轴线（9）的左侧和右侧 直升机（2）在其外侧具有相应的滑板（14,15）和机身（4）中的主梁（5-8），所述交叉管（10-13）经由主梁（5-8）经由 支撑（16-23）固定在主梁（5-8）上。 防滑型起落架（1）可伸缩。 提供了一种用于操作这种用于直升机（2）的滑行式起落架（1）的方法。