MULTI-DIMENSIONAL VIBRATION CONTROL METHOD FOR STING-MOUNTED AIRCRAFT MODEL

The invention belongs to the field of active vibration control, and relates to a multi-dimensional vibration control method based on piezoelectric ceramic actuator applied to wind tunnel test of aircraft model. In this method, the pitch and yaw acceleration sensors arranged on the center of mass of the aircraft model are used to measure the two components of the main vibration acceleration of the aircraft model, and the main vibration vector of the aircraft model is obtained and the real-time vibration plane of the strut is determined. Inertia is introduced to solve the dynamic bending moment on the active section of the multi-dimensional vibration damper, and then the stress distribution on the active section is obtained. The multi-dimensional active vibration control system is adopted to improve the stability and reliability of the active vibration control system of wind tunnel model, extend the service life of piezoelectric ceramic actuator, and ensure the quality of wind tunnel test data and the safety of wind tunnel test.