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公开(公告)号：US20180155007A1
公开(公告)日：2018-06-07
申请号：US15577712
申请日：2016-04-14
CPC分类号： B64C9/20 , B64C3/50 , B64C9/16 , B64C23/06 , B64C23/065 , B64C2230/14 , Y02T50/164 , Y02T50/44
摘要： A flap of an aircraft includes a flap body that is provided deployably with respect to a main wing, an inclined portion that protrudes from an upper surface of a tip part on at least an outboard side in a span direction of the flap body and is inclined with respect to an aircraft axis direction, and a protruding portion that smoothly protrudes from a lower surface of the tip part on at least the outboard side. A rear end of the inclined portion is located closer to a side end edge of the tip part in the span direction of the flap body than a virtual line that passes through a front end of the inclined portion and is parallel to the aircraft axis direction.
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公开(公告)号：US11577823B2
公开(公告)日：2023-02-14
申请号：US16976020
申请日：2019-01-23
发明人： Tohru Hirai , Mitsuhiro Murayama , Kazuomi Yamamoto , Yasushi Ito , Kentaro Tanaka , Takehisa Takaishi , Yuzuru Yokokawa
摘要： A noise reduction apparatus, an aircraft, and a noise reduction method capable of increasing the amount of noise reduction are provided. 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.
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公开(公告)号：US10562606B2
公开(公告)日：2020-02-18
申请号：US15577055
申请日：2016-04-14
摘要： The present invention is directed to reducing noise resulting from a wing tip vortex of a wing such as a flap. A flap of an aircraft includes a flap main body provided to a parent wing in a deployable manner, and a vortex generation portion including a protruding member, the protruding member being provided to protrude from an upper surface at least at an end of the flap main body on an outboard side in a span direction and forming a predetermined angle to an axial direction of the aircraft. A rear end of the protruding member is located on the side adjacent to a side-end edge at the end of the flap main body in the span direction relative to a virtual line passing through a front end of the protruding member and being parallel to the axial direction.
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公开(公告)号：US20180170521A1
公开(公告)日：2018-06-21
申请号：US15577055
申请日：2016-04-14
CPC分类号： B64C9/20 , B64C3/10 , B64C9/18 , B64C23/06 , Y02T50/162
摘要： The present invention is directed to reducing noise resulting from a wing tip vortex of a wing such as a flap. A flap of an aircraft includes a flap main body provided to a parent wing in a deployable manner, and a vortex generation portion including a protruding member, the protruding member being provided to protrude from an upper surface at least at an end of the flap main body on an outboard side in a span direction and forming a predetermined angle to an axial direction of the aircraft. A rear end of the protruding member is located on the side adjacent to a side-end edge at the end of the flap main body in the span direction relative to a virtual line passing through a front end of the protruding member and being parallel to the axial direction.
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