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    HIGH-LIFT-GENERATING DEVICE, WING, AND NOISE-REDUCTION DEVICE FOR HIGH-LIFT-GENERATING DEVICE
    1.
    发明公开
    HIGH-LIFT-GENERATING DEVICE, WING, AND NOISE-REDUCTION DEVICE FOR HIGH-LIFT-GENERATING DEVICE 有权
    HOCHAUFTRIEBGENERATOR，FLÜGELUND RAUSCHVERRINGERUNGSSTRUKTURFÜRDEN HOCHAUFTRIEBGENERATOR

    公开(公告)号：EP2455282A1

    公开(公告)日：2012-05-23

    申请号：EP10799817.1

    申请日：2010-07-12

    申请人： Mitsubishi Heavy Industries, Ltd. ,  Japan Aerospace Exploration Agency

    发明人： HIRAI, Makoto ,  TAKENAKA, Keizo ,  IMAMURA, Taro ,  YAMAMOTO, Kazuomi ,  YOKOKAWA, Yuzuru

    IPC分类号： B64C9/16 ,  B64C3/50

    CPC分类号： B64C3/48 ,  B64C3/50

    摘要： In a high-lift-device, a wing, and noise reduction device for a high-lift-device that are capable of reducing noise generated when a flap is extended, preventing deterioration of aerodynamics characteristic when retracting the flap, and preventing an increase in weight, a flap main body (5) disposed so as to be extendable/retractable relative to a main wing and a protruding portion (6A-1) that smoothly protrudes at least at the vicinity of one end portion of a positive-pressure surface (PS) of the flap main body (5) in a direction away from the flap main body (5) are provided.

    摘要翻译： 在用于高升力装置的高升力装置，机翼和降噪装置中，能够减少当翼片延伸时产生的噪音，防止在缩回翼片时空气动力特性的劣化，并防止增加 重量，相对于主翼设置成能够伸缩的翼片主体（5）和至少在正压表面的一个端部附近平滑地突出的突出部分（6A-1） 提供了一种离开皮瓣主体（5）的方向上的皮瓣主体（5）的PS）。

    FLAP AND AIRCRAFT
    3.
    发明公开
    FLAP AND AIRCRAFT 审中-公开
    FLAP和飞机

    公开(公告)号：EP3305654A1

    公开(公告)日：2018-04-11

    申请号：EP16799510.9

    申请日：2016-04-14

    申请人： Mitsubishi Aircraft Corporation ,  Japan Aerospace Exploration Agency

    发明人： HAYASHI, Kensuke ,  MURAYAMA, Mitsuhiro ,  YAMAMOTO, Kazuomi

    IPC分类号： B64C3/50 ,  B64C9/18 ,  B64C23/06

    CPC分类号： B64C9/20 ,  B64C3/50 ,  B64C9/16 ,  B64C23/06 ,  B64C23/065 ,  B64C2230/14 ,  Y02T50/164 ,  Y02T50/44

    摘要： An aircraft flap 3 is equipped with: a flap body 8 which is provided so as to be deployable with respect to a main wing 2; and inclined portions 5 which are provided so as to protrude on the upper surface 301 of at least the end 40 on the outboard OTB side in the span direction D2 of the flap body 8, and are inclined to the aircraft axial direction D1; and a protruding portion 7 which protrudes smoothly from the lower surface 302 of at least the end 40 on the outboard side. The rear end 52 of each of the inclined portions 5 is located closer to the side end edge 301A of the end 40 in the span direction D2 of the flap body 8 than the virtual line VL that passes through the front end 51 of the inclined portion 5 and is parallel to the aircraft axis direction.

    摘要翻译： 飞机襟翼3配备有：襟翼主体8，该襟翼主体8被设置成可相对于主机翼2展开; 以及倾斜部5，其设置成在翼主体8的翼展方向D2上至少在外侧OTB侧的端部40的上表面301上突出并且相对于飞行器轴向D1倾斜; 以及从外侧的至少端部40的下表面302平滑地突出的突出部7。 每个倾斜部分5的后端52位于比翼片本体8的翼展方向D2上的端部40的侧端边缘301A更靠近通过倾斜部分的前端51的假想线VL的位置 5并且平行于飞机轴线方向。

    NOISE REDUCING DEVICE, AIRCRAFT, AND NOISE REDUCTION METHOD
    4.
    发明公开
    NOISE REDUCING DEVICE, AIRCRAFT, AND NOISE REDUCTION METHOD 审中-公开

    公开(公告)号：EP3760882A1

    公开(公告)日：2021-01-06

    申请号：EP19756790.2

    申请日：2019-01-23

    申请人： Japan Aerospace Exploration Agency

    发明人： HIRAI, Tohru ,  MURAYAMA, Mitsuhiro ,  YAMAMOTO, Kazuomi ,  ITO, Yasushi ,  TANAKA, Kentaro ,  TAKAISHI, Takehisa ,  YOKOKAWA, Yuzuru

    IPC分类号： F15D1/00 ,  B64C25/04

    摘要： [Object] To provide a noise reduction apparatus, an aircraft, and a noise reduction method capable of increasing the amount of noise reduction.
    [Solving Means] The noise reduction apparatus 1 includes a porous plate 2 disposed to face a fluid flow, the porous plate 2 including a bend region 5 bent toward an upstream side of the fluid flow. The bend region 5 is provided at the end portion 6 of the porous plate 2, and has a concave R-shape on an upstream side of the fluid flow. Although the direction of the fluid flow is typically deflected toward the outside from the center of the porous plate 2 due to the porous plate 2, the deflected fluid easily passes through the porous plate 2 since the porous plate has the bend region 5. Thus, the shear layer of the fluid flow is weakened, the noise induced by the vortex is reduced, and it is possible to increase the reduction amount of noise.

    WING, FLAP, AND AIRCRAFT
    5.
    发明公开
    WING, FLAP, AND AIRCRAFT 审中-公开
    WING，FLAP和AIRCRAFT

    公开(公告)号：EP3305656A1

    公开(公告)日：2018-04-11

    申请号：EP16799702.2

    申请日：2016-04-14

    申请人： Japan Aerospace Exploration Agency

    发明人： MURAYAMA, Mitsuhiro ,  YAMAMOTO, Kazuomi

    IPC分类号： B64C9/18 ,  B64C3/10 ,  B64C23/06

    CPC分类号： B64C9/20 ,  B64C3/10 ,  B64C9/18 ,  B64C23/06 ,  Y02T50/162

    摘要： [Object] To reduce noise resulting from a wing tip vortex of a wing such as a flap.
    [Solving Means] A flap 3 of an aircraft includes a flap main body 8 provided to a parent wing 2 in a deployable manner, and a vortex generation portion 50 including a protruding member 5, the protruding member 5 being provided to protrude from an upper surface 301 at least at an end 40 of the flap main body 8 on an outboard side OTB in a span direction D2 and forming a predetermined angle to an axial direction D1 of the aircraft. A rear end 52 of the protruding member 5 is located on the side adjacent to a side-end edge 301A at the end 40 of the flap main body 8 in the span direction D2 relative to a virtual line VL passing through a front end 51 of the protruding member 5 and being parallel to the axial direction D1.

    摘要翻译： [目的]减少机翼的翼尖涡流如翼片产生的噪音。 [解决手段]飞行器的翼3包括以可展开的方式设置于主翼2的翼主体8和包括突出构件5的涡流产生部50，突出构件5设置成从上部 至少在外侧OTB上的翼片主体8的端部40处在跨度方向D2上并且与飞行器的轴向方向D1形成预定角度。 突出构件5的后端52相对于通过前端51的假想线VL，位于翼片主体8的端部40处的翼端方向D2上的侧端缘301A侧 突出构件5并平行于轴向方向D1。