Realization of the missile servo system based on the application of microcontroller and contactless rotary position sensor of the missile wings

Abstract

This paper describes the procedure for the realization of servo systems for the guided missiles. The realized servo system consists of four servo units for driving the missile wings. The servo units are independent of the each other and they are controlled by a 32-bit microcontroller STM32F407. Contactless high resolution magnetic encoders are used as the position sensors of the missile wings. The communication between the microcontroller and the magnetic encoders is realized via the serial port using the SPI protocol. DC motors are used as actuators. The actuator's energy converters are realized in a Hbridge configuration. These converters are controlled by the corresponding pulse width modulation (PWM) signal from the microcontroller. This servo system with four independents servo units makes possible to rotate the missile wings according to the guidance algorithm and at the same time according to the algorithm for the missile rolling control. The steering structures of the servo units are based on the application of the PI controllers.