Design and simulation of aircraft pitch system based on PD control.

Nowadays, Automatic Flight Control System is more and more common in aircraft design and manufacturing. An automatic Flight Control System is essential for reducing the effort of pilots and ensuring flight security. The aircraft pitch system is implemented in the Automatic Flight Control System to control the pitch angle of the aircraft. However, traditional control methods are usually so slow that the aircraft tends to be unstable during the flight. In this paper, an improved PD controller is proposed. It has the advantages of high stability, fast response, and vibration suppression. The calculation result demonstrates the reliability and the feasibility of PD controller. The simulation results verify the effectiveness of the PD controller. The result also points out possible drawbacks of using a PD controller. This study also explores a more complex and stable model for aircraft pitch control. This study is of great significance for improving the performance of the aircraft pitch system. [ABSTRACT FROM AUTHOR]