This paper mainly describes the method of designing a aircraft control system based on the classical control theory after creating the aircraft movement models. The control system's performance is also simulated with the effects of some nonlinear elements such as saturation and transport delay. From the results we can see that the structure and parameters are reasonable, the performance can meet the need of the task. At the same time, it can offer more creditable data and diagram for the hardware-in-the-loop simulation and the flight experiment.