This study explores the best vibration reduction method using a multicyclic controller with an individual blade control (IBC) actuation scheme for a lift-offset coaxial helicopter during high-speed flight. The rotorcraft dynamics model consists of coaxial three-bladed counter-rotating rotors and a finite element fuselage stick model constructed based on the measured data of the XH-59A helicopter. The two-way coupled rotor–body vibration analysis results exhibited excellent correlation with the test data for the rotor hub loads and airframe vibrations. The best actuation scenarios are sought for the minimum vibration of the vehicle using either an open- or closed-loop control scheme. IBC actuation is shown to effectively reduce the vibrations of the rotorcraft. Coreduction of the three per rotor revolution () and vibrations of the rotorcraft is achieved using multicyclic control with offline system identification. Multicyclic harmonic IBC actuation enables the suppression of rotorcraft vibration at the rotor hub and pilot seat by 81.4%, and cockpit vibration by 92% compared with the uncontrolled case, leading to a significantly reduced vibration level (below ) of the rotorcraft. The closed-loop multicyclic control using the identified system and aircraft model shows good correlation, ensuring the suitability of the present optimal control simulations.
Active Vibration Suppression of Lift-Offset Coaxial Rotorcraft Using Multicyclic Control
AIAA Journal ; 63 , 6 ; 2428-2442
01.06.2025
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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