An analysis of stability margin for altitude control of aircraft based on overload control

In this paper, for the overload control system of aircraft pitching channel, using the internal and external loops nested each other, the dual PID mode height loop is designed, and Matlab software is used to solve the transfer function of its linearized model, and the Bode diagram is summarized to analyze its stability margin, and finally the rationality of the designed height loop is verified by digital simulation analysis. Thus provides a whole set of engineering practical aircraft altitude loop design and analysis methods, with high engineering practical value.