Robust vibration suppression control of helicopter trailing-edge flaps in dynamic flight scenarios

Abstract:

To address the vibration control problem in helicopter dynamic flight scenarios with continuously varying advance ratios (variable-speed forward flight), a robust vibration control method based on a linear parameter varying (LPV) model was proposed using active trailing-edge flaps. First, a linear time-invariant (LTI) model of the helicopter vibration response was identified using CAMRAD II simulation data, which served as the foundation for developing an LPV model representing the dynamic flight process. Based on this LPV model, an integral sliding mode robust control algorithm was designed. The stability of the control system was proved using a parameter-dependent Lyapunov function. Two distinct helicopter dynamic flight scenarios were designed to simulate and verify the proposed algorithm, which was also compared with the traditional H∞control method commonly used in helicopter vibration suppression. Furthermore, to validate the effectiveness of the proposed algorithm, it was implemented on a semi-physical simulation platform based on LabVIEW. Simulation results demonstrated that the designed integral sliding mode robust control algorithm could suppress vertical vibratory loads on the rotor hub by more than 95% within 2.5 seconds under steady-state conditions and by more than 90% under external disturbances and uncertainties in the process of varying advance ratios. This indicates the algorithm’s ability to effectively suppress rotor hub vertical vibration loads in dynamic flight scenarios.