Research On Follow-up Control Based On Corps Launch Weapon System

Portable air defense missile is a powerful weapon to intercept low-altitude and ultra-lowaltitude fighters,bombers and helicopters.However,due to its single shoulder combat method,such problems as short detection distance,high energy consumption of shooters and short combat duty time,it can be loaded on the launcher to form the tripod-launched missile system,which can effectively improve its combat effectiveness.In this paper,the design and implementation of the servo control system,which is the core part of the system,is studied.The main contents of this paper include:Firstly,based on the operational requirements of the tripod-launched missile system and the performance index of the servo system,the overall scheme design of the servo system is completed.the hardware circuit of the servo system core processing unit is designed based on TMS320F28335 DSP,the communication mode of CAN bus is established,and the corresponding driver development is completed.Secondly,according to the requirements of the overall indicators,a servo control strategy based on the combination of zonal PID control and feedforward control is designed.The least squares method is used to extrapolate the fire control command in one step,and to compensate the delay of photoelectric tracking error.The position protection strategy is designed to ensure the safe operation of the servo system in azimuth and pitch directions.Then,a software framework with soft time series is designed.The control strategy mentioned above is realized by planning the timing and determining the control rhythm.The functional modules of the servo software are developed and the software and hardware of the system are debugged.Finally,a series of experimental tests are carried out,including the response test of typical input signal,the following flight experiment of civil airliner in a certain base,the following flight experiment of the drone aircraft in the joint exercise of the large combat system,and the experimental results are analyzed.The experimental results fully show that the servo subsystem designed in this paper meets the performance indicators and the operational requirements of the tripod-launched missile system.