Study on Optimization Tool Development for Flight Control System Design

초록

In order to control an aircraft using a linear controller, it is necessary to calculate control gains at a sufficient number of design points due to the nonlinearity of the model. Performing this pas-sively requires a lot of time and effort by the designer, and the cost is high. In this paper, we describe the development of automatic optimization tool for flight control system to solve these problems. A linear model is derived by linearization of the nonlinear model. Then, a linear model is applied to the controller to calculate the control gain. As a result, the control gain is calculated for multiple design points through the linearization of the F-16 aircraft 6-DOF nonlinear model. Thereafter, a nonlinear model is applied to the controller to which the calculated control gain is applied for determine whether or not nonlinearity is assured.