YANG Min-bo, YANG Lei, KANG Chang-xi, WANG Rui-qi
In order to reduce the impact of the folded control surface of the missile when it is unfolded under severe wind load condition in hypersonic flight, it's necessary to design an active damping gas actuator and develop the principle prototype. Based on the introduction of actuator structure and working principle, the main parts of the actuator are designed, and analyed by finite element method. Then it gives the method of wind load simulation on the control surface, and also provides the ground simulation loading system. The mathematical model and simulation model of the working process of the actuator are established, and the main technical parameters of the actuator are obtained through the simulation analysis by MATLAB/Simulink. Finally, ground simulation loading experiment shows that under the condition of downwind load, the piston rod of the actuator firstly accelerates, then decelerates, and finally moves to the final position at a smaller speed, so the actuator has a good load adaptive ability. The result of the experiment is almost consistent with the result of the simulation analysis, so the result can be a reference for subsequent engineering application.