Hardware Design of Flight Control System and Flight Experiments of Small-Scale Unmanned Aerial Vehicle

Abstract

In view of the strict requirements of small-scale unmanned aerial vehicle on the performance, volume and weight of flight control system, this paper presents a hardware design of flight control system based on STM32F103RCT6 microcontroller. In accordance with the system function and interface characteristics, the flight control system is divided into power module, main control module, sensor module and interface drive module, which meet the technical requirements of high integration, low coupling and expansibility of the flight control system. According to the characteristics of different types of sensor units integrated in the system, we design the interface circuit of inertial sensor, barometer and geomagnetic sensor based on I2C bus and GPS interface circuit based on UART. The flight experiments are carried out on the small-scale quadcopter platform. The results show that the flight control system designed in this paper has good practicability and high reliability, and meets the requirements of the small-scale unmanned aerial vehicle for the function and performance of the flight control system.