Japan Aerospace Exploration Agency

Subaru Corporation

Kawada Industries, Inc.

Yasutada Tanabe

Noboru Kobiki

Hirotaka Hayashi

Wataru Kobayashi

Mizuki Nakamura

Masafumi Sasaki

Takeshi Akasaka

Takashi Aoyama

Shigeru Saito

Chiharu Totsuka

Masato Okamoto

Masahiko Sugiura

Hideaki Sugawara

Provided is a flight efficiency improving system for a compound helicopter with a rotor and fixed wings. In forward flight of the compound helicopter, the flight efficiency improving system does not perform a cyclic pitch control of the rotor so as to allow a difference in lift generated by the rotor between an advancing side and a retreating side of the rotor, or the flight efficiency improving system performs the cyclic pitch control to an extent that does not completely eliminate the difference. The fixed wings are provided respectively on left and right sides of a body and are asymmetric to each other so that influence of an aerodynamic interference between the rotor and the fixed wings is reduced.

Flight efficiency improving system for compound helicopter

Provided is a vibration control system for a compound helicopter with a rotor and a fixed wing. The fixed wing includes a movable flap that is mounted on a rear edge of the fixed wing. The vibration control system periodically moves the movable flap so as to periodically change lift of the fixed wing such that vibration aerodynamically generated by the fixed wing is in anti-phase with vibration caused by rotation of the rotor.

Vibration control system for compound helicopter

A main rotor blade, which is the main rotor bladefor a high-velocity helicopter, includes: a blade root parthaving a length of 30% or more of a rotor radius R; and a blade main bodycontinuous with the blade root part. Preferably, a cross-sectional shape of the blade root partsatisfies (x/a)+(y/b)=1 and a&#x3e;b, where m: arbitrary number, x: chord length direction, and y: blade thickness direction.

Main rotor blade and helicopter

A small unmanned airplane includes; a main wing having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers placed at blade tips of left and right of the main wing; and two propellers installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

Small unmanned aircraft

In a blade vortex interaction (BVI) noise reduction system for a helicopter a rotor blade, a tab is movable via an actuator from a first position, wherein the tab is within the blade, to a second position, wherein the tab extends outwardly from a trailing edge of the rotor blade. The actuator is operated so that the tab advances and retreats in response to rotating timing of the rotor blade, to reduce the BVI noise of the rotor blade.

Helicopter blade vortex interaction noise reducing method and device

Growing community of inventors

Tokyo, Japan

Yasutada Tanabe