Design Of Small And High-precision Missile-borne Actuator System

The actuator system is the core part of the flight missile,which determines the hit precision of the missile.At present,the commonly used missile-borne actuator system can be divided into the hydraulic actuator system,pneumatic actuator system and electric actuator system.The hydraulic actuator system has the features of complex structure,high environmental requirements and high accuracy in fabrication;the pneumatic actuator system requires a specific air source and poor maintenance;The electric actuator control system has the feature of high adaptable to the environmental,small size and high reliability.To meet the requirements of small,high precision and digitalization.This article takes the electric actuator system as the research object,the actuator body structure and circuit module integration are designed.The main research contents are as follows:Firstly,the overall scheme of missile-borne actuator system is designed,which consists of the servo system drive part and the actuator body.The servo system drive part mainly consists of the STM32H7 main control chip of ARM series Cortex-M7,servo system drive chip L6205,and isolation circuits,etc.The actuator body is composed of four actuators,and each includes a DC motor,reduction device and potentiometer.In order to meet the design requirements of smaller,the deceleration device uses a secondary transmission consisting of conical gear and harmonic gears.Secondly,the mathematical model of the missile-borne actuator system is established,and the control technology is studied.In this paper,PID control algorithm is adopted,and its simulation analysis and engineering realization are processed,and all the indicators meet the requirements of system design,while leaving a certain margin.The control algorithm adopts sliding mode variable structure control to improve the performance parameters of the system.The simulation results that the system has no overshoot and the time to reach the stable value is reduced by about 0.15 s.The tracking performance of the system is more stable,and the performance parameters are improved.Finally,the integrated modules are used to design the hardware circuit of the missile-borne actuator system,and the experimental test platform of the missile actuator system is setup,and the test software of the missile-borne actuator system is developed simultaneously.The missile-borne actuator system is tested and optimized in low temperature(-40℃),normal temperature and high temperature(+60℃)environment,all the test indicators meet the design requirements and the system performance is stable,it proves the feasibility of the design scheme and has good engineering practicability.