Provided is a vibration control system for a compound helicopter (1) having a rotor (3) and a fixed wing (4). The fixed wing includes a movable flap (41) that is mounted on a rear edge of the fixed wing (4). The vibration control system periodically moves the movable flap (41) so as to periodically change lift of the fixed wing (4) such that vibration aerodynamically generated by the fixed wing (4) is in anti-phase with vibration caused by rotation of the rotor (3).
VIBRATION CONTROL SYSTEM FOR COMPOUND HELICOPTER
SCHWINGUNGSSTEUERUNGSSYSTEM FÜR EINEN ZUSAMMENGESETZTEN HUBSCHRAUBER
SYSTÈME DE COMMANDE DE VIBRATION POUR HÉLICOPTÈRE COMBINÉ
2023-11-01
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |