Abstract: The four-axis aircraft attitude angle system is a nonlinear, strongly coupled and multi-variable complex system. The four-axis aircraft usually adopts PID control, but the PID control has the disadvantages of low precision and vulnerability to interference. To this end, a new four-axis aircraft attitude angle control method and simulation is introduced. Firstly, the mathematical modeling and analysis of the four-axis aircraft attitude angle system is carried out, and a simplified mathematical model is obtained. Then a new attitude angle control method is proposed and the attitude control effect and anti-interference performance of the new control system are obtained. Simulink modeling is carried out with the performance of the anti -control object. Finally, the simulated attitude angle Simulink simulation model is simulated. The simulation results show that the new attitude angle control method achieves stable and precise control of the attitude angle. The anti-interference is good. After the interference is removed, the attitude angle can quickly return to stability. When the control object changes, the attitude angle can still maintain a stable value; the system has certain reference and application value.

Key words: moment of inertia, PID, anti-interference, object change, Simulink simulation