Japan Aerospace Exploration Agency

Mitsubishi Heavy Industries Limited

Kawasaki Jukogyo Kabushiki Kaisha

Mitsubishi Aircraft Corporation

Mitsuhiro Murayama

Kazuomi Yamamoto

Yuzuru Yokokawa

Yasushi Ito

Kentaro Tanaka

Masataka Kohzai

Yosuke Ueno

Kensuke Hayashi

Tohru Hirai

Takehisa Takaishi

Kazuhide Isotani

Kenji Hayama

A leading-edge high-lift device according to an embodiment of the present invention is a leading-edge high-lift device that is deployable and retractable from/into a fixed leading edge of a main wing of an aircraft and includes: a leading edge portion; a trailing edge portion that forms a gap between a trailing edge portion and the main wing during deployment; a cusp portion formed at a lower edge of the leading edge portion; a lower surface portion formed between the cusp portion and the trailing edge portion; and a curved hump portion that is locally provided on a surface of the lower surface portion and protrudes toward the main wing in a cross-sectional shape perpendicular to a wing span direction of the main wing.

Leading-edge high-lift device, wing, and aircraft

A noise reduction apparatus, an aircraft, and a noise reduction method capable of increasing the amount of noise reduction are provided. The noise reduction apparatusincludes a porous platedisposed to face a fluid flow, the porous plateincluding a bend regionbent toward an upstream side of the fluid flow. The bend regionis provided at the end portionof the porous plate, and has a concave R-shape on an upstream side of the fluid flow.

Noise reduction apparatus, aircraft, and noise reduction method

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.

Flap and aircraft

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.

Wing, flap, and aircraft

Growing community of inventors

Tokyo, Japan

Mitsuhiro Murayama