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
28.02.2023
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |