A Vehicular Missile Launch Servo Control System Design

Vehicle missile launch platform is composed of optical, mechanical, electronic, computer hardware and software components of the system, can be achieved for space target detection, tracking, recognition and destruction.Based on a practical project as the background, in view of the two axis gyro stabilized platform space coupling relations, stability control algorithm and how to specifically implement the stable platform function and key technology used in the theoretical study and experimental verification.The main function of the design of the vehicle stabilized platform servo control system is to isolate the body in the azimuth and elevation on the two channel angular perturbations, so that the optical axis of the system in a geographic coordinate system remained stable, in order to eliminate the phase shift induced by the body, to realize stable tracking. Consequently, this system is a typical position servo system. To achieve high reliability control and high accuracy, control system employs two axes and four loop control scheme, namely the azimuth and elevation direction respectively by the analog current loop, analog speed loop, digital velocity loop, digital position loop, which will form a closed loop system.This master’s thesis focuses on the design of hardware and software of the servo system. Hardware design is based on the design of the main control DSP core, including designs of sensor signals collection, the data output channel and CAN communication module realizing the information exchange between the control system and the order-sender computer. Software design mainly includes the overall design of the servo control system, the software design of control algorithms and the design of test software. The intelligent PID algorithm commonly used in engineering is selected, which has been proved in practice to be able to obtain satisfactory control effect.