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    NOSE CONE STRUCTURE FOR PYLON OF AIRCRAFT WITH WING-HUNG LAYOUT
    3.
    发明公开
    NOSE CONE STRUCTURE FOR PYLON OF AIRCRAFT WITH WING-HUNG LAYOUT 审中-公开
    翼虹布局的飞机的鼻翼的鼻锥体结构

    公开(公告)号：EP2987721A1

    公开(公告)日：2016-02-24

    申请号：EP14855047.8

    申请日：2014-08-28

    申请人： Commercial Aircraft Corporation Of China Ltd ,  Commercial Aircraft Corporation Of China Ltd Shanghai Aircraft Design and Research Institute

    发明人： CHEN, Yingchun ,  ZHANG, Miao ,  YU, Zhehui ,  ZHANG, Meihong ,  XUE, Fei ,  LIU, Tiejun ,  ZHANG, Dongyun ,  ZHOU, Feng ,  MA, Tuliang ,  ZHAO, Binbin

    IPC分类号： B64C7/02 ,  B64D29/02

    CPC分类号： B64D29/02 ,  B64C1/40 ,  B64C7/02 ,  B64C23/00 ,  B64D27/00 ,  Y02T50/44

    摘要： The present invention provides a nose cone structure for a pylon (20) of an aircraft with a wing-mounted layout. The nose cone comprises a front nose cone (21) located in front of a wing leading edge (31) and a rear nose cone (22) located behind the wing leading edge (31). The nose cone is characterized in that at least a part of the rear nose cone (22) is modeled and shaped by cross section control segments and comprises at least one group of latitudinal position control segments (P01, P02, P03, P04) and at least a group of longitudinal position control segments (S01, S02, S03, S04, S05). The rear nose cone of the pylon is shaped by latitudinal position control segments. The pylon design of the present application optimizes the passageway area of the space between the pylon/wing/engine nacelle by controlling the rear nose cone curvature of the pylon without deflection of the rear portion of the pylon.

    摘要翻译： 本发明提供了一种用于具有翼式布局的飞行器的吊架（20）的鼻锥结构。 鼻锥包括位于机翼前缘（31）前方的前鼻锥（21）和位于机翼前缘（31）后方的后鼻锥（22）。 鼻锥的特征在于，后鼻锥（22）的至少一部分由横截面控制段建模和成形并且包括至少一组经度位置控制段（P01，P02，P03，P04）和 至少一组纵向位置控制段（S01，S02，S03，S04，S05）。 塔架的后部鼻锥由纬度位置控制部分形成。 本申请的塔架设计通过控制塔架的后部鼻锥曲率而不使塔架的后部偏转来优化塔架/机翼/发动机机舱之间的空间的通道区域。

    AIRPLANE SUSPENSION COWLING STRUCTURE WITH WING-MOUNTED ARRANGEMENT
    4.
    发明公开
    AIRPLANE SUSPENSION COWLING STRUCTURE WITH WING-MOUNTED ARRANGEMENT 审中-公开
    FLUGZEUGAUFHÄNGUNGSVERKLEIDUNGSSTRUKTURMITFLÜGELMONTIERTERANORDNUNG

    公开(公告)号：EP2987728A1

    公开(公告)日：2016-02-24

    申请号：EP14855661.6

    申请日：2014-08-28

    申请人： Commercial Aircraft Corporation Of China Ltd ,  Commercial Aircraft Corporation Of China Ltd Shanghai Aircraft Design and Research Institute

    发明人： YU, Zhehui ,  ZHANG, Miao ,  ZHANG, Meihong ,  XUE, Fei ,  LIU, Tiejun ,  ZHANG, Dongyun ,  WANG, Junhong ,  CHENG, Pan ,  LU, Yong ,  LIU, Xiaoyan

    IPC分类号： B64D29/02

    CPC分类号： B64D29/02 ,  B64C7/02 ,  B64D2027/264

    摘要： Provided is an airplane suspension (20) fairing structure with a wing-mounted arrangement, the fairing structure comprising a front fairing located in front of the leading edge (31) of a wing and a rear fairing located at the back of the leading edge (31) of the wing; the vertical section line (G) of the front fairing is curved, ascending along air flow direction from a start point (p) of an engine nacelle (10) to the maximum height position and then descending and extending below the lower surface (32) of the wing. In the present invention, due to the curved vertical section line of the front fairing of the suspension, inner space of the suspension is met only in the position requiring greater inner space, thus enabling the engine to be mounted close to the wing without additional devices; and the fairing aerodynamic surface of the suspension will not extend to the upper surface of the wing, avoiding interference of the suspension with the wing during cruising.

    摘要翻译： 本发明提供一种具有机翼安装装置的飞机悬架（20）整流罩结构，整流罩结构包括位于机翼前缘（31）前方的前整流罩和位于前缘后部 31） 前整流罩的垂直剖面线（G）弯曲，沿着空气流动方向从发动机舱（10）的起始点（p）上升到最大高度位置，然后在下表面（32）的下方下降并延伸， 的翅膀。 在本发明中，由于悬架的前整流罩的弯曲的垂直截面线，悬架的内部空间仅在需要更大的内部空间的位置中被满足，从而能够使发动机安装在机翼附近而不需要额外的装置 ; 并且悬架的整流罩空气动力学表面将不会延伸到机翼的上表面，避免在巡航期间悬架与机翼的干扰。

    AIRPLANE WINGTIP DEVICE
    5.
    发明公开
    AIRPLANE WINGTIP DEVICE 审中-公开
    FLUGZEUGFLÜGELSPITZEN-VORRICHTUNG

    公开(公告)号：EP2684797A1

    公开(公告)日：2014-01-15

    申请号：EP12757583.5

    申请日：2012-03-12

    申请人： Commercial Aircraft Corporation Of China Ltd ,  Commercial Aircraft Corporation Of China Ltd Shanghai Aircraft Design and Research Institute

    发明人： CHEN, Yingchun ,  ZHANG, Miao ,  LIU, Tiejun ,  ZHANG, Meihong ,  WANG, Junhong ,  MA, Tuliang ,  YU, Zhehui ,  ZHOU, Feng ,  ZHANG, Dongyun

    IPC分类号： B64C3/10 ,  B64C3/36 ,  B64C23/06

    CPC分类号： B64C23/069 ,  Y02T50/164

    摘要： An aircraft wingtip device, comprising a transition part (1) and a wingtip part (2); the inner end of the transition part (1) is connected to the far end of an aircraft wing, and the outer end of the transition part is connected to the wingtip part (2); the wingtip part comprises a plurality of wingtip sections (3 n ), and each wingtip section (3 n ) comprises a wingtip (4 n ) and a wing root (5 n ) respectively; the wing root (5 1 ) of the first wingtip section (3 1 ) is connected to the outer end of the transition part (1), the wing root (5 n+1 ) of the n+1 wingtip section (3 n+1 ) is located on the wingtip (4 n ) of the n wingtip section (3 n ), and the chord length of the wing root (5 n+1 ) of the n+1 wingtip section (3 n+1 ) is smaller than or equal to the chord length of the wingtip (4 n ) of the nth wingtip section (3 n ), where n > 0. Because the wingtip device of the present invention is disposed in a stepped fashion, more than one discontinuity surface is added to the wingtip thereof, so that the wingtip vortices induced by the wingtip suppress each other, thereby reducing the strength of the vortices, and thus achieving drag reduction effect. In addition, the wing root of the present invention has a smaller bending moment increment, thus reducing the structural weight of the airplane and having less effect on the flutter properties.

    摘要翻译： 一种飞机翼尖装置，包括过渡部分（1）和翼尖部分（2）; 过渡部分（1）的内端连接到飞机机翼的远端，过渡部分的外端连接到翼尖部分（2）; 所述翼尖部分包括多个翼尖部分（3n），并且每个翼尖部分（3n）分别包括翼尖（4n）和翼根（5n） 第一翼尖部分（31）的翼根（51）连接到过渡部分（1）的外端，n + 1翼尖部分（3n + 1）的翼根（5 n + 1） 1）位于n翼尖部分（3n）的翼尖（4n）上，并且n + 1翼尖部分（3n + 1）的翼根（5n + 1）的弦长较小 大于或等于第n个翼尖部分（3 n）的翼尖（4 n）的弦长，其中n> 0。由于本发明的翼尖装置以阶梯形式设置，所以多于一个不连续表面是 加上翼尖，使得翼尖引起的翼尖涡流相互抑制，从而降低涡流的强度，从而实现减阻效果。 此外，本发明的翼根具有较小的弯矩增量，因此降低了飞机的结构重量并且对颤振特性的影响较小。