The Design Of Sting System In Wind Tunnels And Active Control Of Vibration

During the research process of the aircraft,a large number of wind tunnel tests are needed to obtain the flight data of the aircraft.The tail support sting system is frequently adopted in transonic wind-tunnel test.The tail support model support system has a low stiffness,therefore,the support system is easily subjected to the wind tunnel load to generate large amplitude and low frequency vibration,which seriously affects the accuracy of the wind tunnel test data and restricts the research and development of a new generation of aircraft to some extent.Aiming at this problem,an active vibration control system with stacked piezoelectric actuator is designed.In this paper,based on the analysis of the vibration principle of the model support system,a set of embedded structural vibration suppressor is designed,and a real-time active control system is built,and the performance of the active vibration suppression system is investigated experimentally.(1)Firstly,the characteristics of wind tunnel and the reason of model vibration are analyzed,and the principle of vibration suppression of actuator based on piezoelectric actuator is described.Then,combining the actual demand of vibration suppression in wind tunnel and the output characteristics of stacked piezoelectric ceramic actuator,selects the piezoelectric ceramic actuator suitable for vibration suppression.A closed-loop feedback control system is designed,adopted PD control algorithm.(2)According to the actual load of a wind tunnel test,a set of built-in damper structure is designed.Based on output characteristics of piezoelectric ceramic and the deformation characteristics of sting,studies the optimal installation location of the vibration damper.Then the static load and dynamic load of the vibration suppressor structure are checked.Finally,modal analysis is carried out on the model-sting system with vibration damper.(3)In order to explore the vibration suppression performance of the vibration damper,a rigid flexible coupling model is established in the simulation software ADAMS.The output performance of the vibration damper is investigated by applying shock load and sine excitation to the model.Then,a set of vibration active control system is built in the laboratory,and the vibration suppression performance is analyzed in the laboratory.Finally,in a transonic wind tunnel of China Aerodynamics Research Institute,under the conditions that wind speed is 0.6 Mach and 0.8 Mach,the performance of the vibration damper is investigated in the test that the angle of attack is a ladder change on a model.