ABSTRACT
Crossover probability and mutation probability is calculated as follows.
P
k f f f f
f f
k f f c avg
=
<
⎧ ⎨⎪ ⎩⎪
)− ,max max (1)
1 INTRODUCTION
For the classic flight controller design method, firstly, we have to select a series of trim points within the flight envelope, then the nonlinear dynamic model of the aircraft must be linearized on the trim point [1]. And the Flight controller is designed based on the linearized model in the end. The most important part of the work is the choice of the controller parameters. For the classic flight controller design method, the trial and error method is often used to enable the control system to achieve the appropriate targets. This control system design methods are inefficient, and mostly depends on the engineering experience of designer. Although the designed control system can be achieved in engineering, it is not necessarily the optimal result. With the improved performance of aircraft, flight control systems are complex more and more.
