Simple Guided Rockets Telescopic Electromagnetic Servo Technology Research

Telescopic electromagnetic actuator, designed for a certain model of simple guided rocket, is a2D trajectory correction implement mechanism, which can improve the impact accuracy and damage efficiency of projectile. Therefore, studying the telescopic electromagnetic actuator has high military application value.In order to improve the performance of telescopic electromagnetic actuator, the whole optimization plan of actuator is designed though applying the contradiction matrix in TRIZ. Furthermore, the simulation results by using ADAMS show that the optimal actuator has better performance than the original actuator.By comparing kinds of characteristics of vane, vane has been selected which can apply to simple guided rocket. And the shape parameters of vane are optimized by using GA. On the basis of theoretical analysis, the corrective force, which produced in the process of opening and retracting the vane, has been calculated by using the MATLAB software. It provides reference for formulating the corrective strategy of simple guided rocket.In order to reduce the response time of actuator, a two direction rotation angle electromagnet is designed which has high output torque. And its control circuit is designed. The simulation results through using Maxwell show:while the electromagnet operates at40°～140°, the output torque is more than0.3N·m, and changes relatively stable.The shielding case which is made of permeability alloy is designed in order to inhibiting the interference of the magnetic field environment of actuator and reduce the measuring errors of the magnetic module. Experiments have been performed to verify the shielding effect of shielding case. The experiment results show:while the actuator and magneto-device are located20cm, and using double-layer permeability alloy, the shielding effect of shielding case is the best.The results of wind tunnel test show that the telescopic electromagnetic actuator can act reliably, and its response time is less than50ms, when the flow velocity is between1.0and3.0mach. Therefore it can be applied to simple guided rocket with10r/s roll speed.