Software Design For An Aircraft Attitude Control System Based Upon DSP

Guided weapons generally consists of three parts, they are respectively named warhead, flight control system, propulsion system. The flight control system including the guidance system and control system. Due to its internal aircraft attitude control system, guided aircraft can make its flights according to the desired trajectory. This topic is committed to research and design a set of an aircraft attitude control system based upon TMS320F28335. The control system is mainly used to set and control an aircraft flight attitude and trajectory.This paper first briefly introduces the research background and significance, as well as domestic and foreign research status about the guidance technology. Then flight attitude control system is introduced the basic working principle, hardware composition and its functional requirements in detail, and make the general design for the software part of aircraft attitude control system. Afterwards, the paper particularly introduces the design process for each function module of the aircraft attitude control system, which mainly is an attitude trajectory control method with the high precision DSP TMS320F28335as the control core. The paper studies the INS and GPS combined guidance technology, analyzes the characteristics of the strapdown inertial navigation system, and compares it with the platform inertial navigation system. After in research guidance technology, the paper continues to study the relationship between the attitude angle of aircraft and the four steering rudder surface position and the actuator control algorithm which is suitable for high speed flight state. And according to the specific project requirements, make the software design and function implementation to the aircraft attitude control system. Navigation uses the attitude and heading reference system which is composed of MEMS as aircraft attitude information feedback device, through the data processing then output control signals by a combined PID control algorithm. This topic is mainly to design the software part of the aircraft attitude control system, which is adopted the C language and assembly language mix programming, and design the self-test module, communication module, the drift correction module and steering gear control module, also adds the software anti-interference technology.In the end, it is the aircraft attitude control system for debugging, including the debugging of each function module, software and hardware joint debugging. According to the result of debugging to improve and optimize the control system. The paper concludes with a further modify and some suggestions for the future.