Application of L1 Adaptive Control for Helicopter Vibration

Abstract

Recently, handling of vibration in helicopters becomes special attention in aerospace field. The vibration may take effect in pilot and passenger comfortable, it may also cause structure damage at fuselage if the generated frequency of the vibration is large. This paper presents the use of adaptive control for reducing the vibration in helicopter. The system is modeled using 3 DOF movement, including blades, rotor mount, and fuselage which connecting spring and damper. We modified the system using nonlinear semiactive damper which damper parameter is controlled variable. The simulation shows that use of nonlinear semi-active damper gives results a response with the amplitude and acceleration of fuselage closed to zero. This is better than if we use the passive damper. The results is satisfy the minimum requirement of helicopter vibration by NASA.