Vibration control system for compound helicopter
AssigneesSubaru Corporation, Japan Aerospace Exploration Agency
InventorsWataru Kobayashi, Hirotaka Hayashi, Mizuki Nakamura, Masafumi Sasaki, Yasutada Tanabe, Noboru Kobiki, Hideaki Sugawara
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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.
Claims18
A vibration control system for a compound helicopter with a rotor and a fixed wing,
- wherein the fixed wing includes a movable flap that is mounted on a rear edge of the fixed wing, and
- wherein a relationship of anti-phase between vibration aerodynamically generated by the fixed wing and vibration caused by rotation of the rotor is maintained by the vibration control system periodically moving the movable flap to change lift of the fixed wing.
Dependencies are inferred from the claim text.