Stability Control of Flight Attitude Angle for Four Rotor Aircraft

In the four-rotor aircraft control system, the stability control of the attitude angle is the key to the stable flight of the four-rotor aircraft. Maintaining the stability of the attitude angle can ensure its safety, have better flight experience and accomplish specific tasks. Nonlinear, multivariable, and susceptible to external disturbances make attitude angle control difficult. Hence, a differential prior PID control algorithm is proposed to stabilize the attitude angle of a quadrotor. The algorithm improves the stability of the attitude angle and the anti-interference ability of the system under high frequency interference and frequent lifting. In order to study the performance of this algorithm, the dynamic model of the four rotor aircraft was established, simulated and compared with the conventional PID control algorithm. The simulation results show that the differential PID controller has a faster response speed, less overshoot and stronger anti-interference ability than the conventional PID controller in high frequency interference and frequent lifting environment, which effectively improves the stability control of the attitude range of the quadrotor.