公开(公告)号：US20210094681A1

公开(公告)日：2021-04-01

申请号：US16608403

申请日：2018-02-07

Applicant: JAPAN AEROSPACE EXPLORATION AGENCY

Inventor： Masahiko SUGIURA ,  Yasutada TANABE ,  Noboru KOBIKI ,  Takashi AOYAMA

IPC: B64C27/46 ,  B64C27/467 ,  B64C27/473 ,  B64C27/04 ,  F01D5/14 ,  F01D5/30

Abstract: [Object] To provide a main rotor blade for a helicopter such as a main blade type helicopter, which may reduce a drag coefficient during high-velocity forward flight and which provides easy control. It is an object of the present invention to provide a helicopter including such a main rotor blade.
[Solving Means] A main rotor blade 1, which is the main rotor blade 1 for a high-velocity helicopter, includes: a blade root part 10 having a length of 30% or more of a rotor radius R; and a blade main body 20 continuous with the blade root part 10. Preferably, a cross-sectional shape of the blade root part 10 satisfies (x/a)m+(y/b)m=1 and a>b, where m: arbitrary number, x: chord length direction, and y: blade thickness direction.

公开(公告)号：US20210371092A1

公开(公告)日：2021-12-02

申请号：US17334311

申请日：2021-05-28

Applicant: SUBARU CORPORATION ,  Japan Aerospace Exploration Agency

Inventor： Wataru KOBAYASHI ,  Hirotaka HAYASHI ,  Mizuki NAKAMURA ,  Masafumi SASAKI ,  Yasutada TANABE ,  Noboru KOBIKI ,  Hideaki SUGAWARA

IPC: B64C27/26 ,  B64C27/00

Abstract: 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.