Robust Control of F16 Aircraft Short-Period Mode by Parametric Space Approach

Ahmet Doğancı

Electrical Engineering Department
Istanbul Technical University, Istanbul, Turkey
edoganci@dho.edu.tr

M. Turan Söylemez

Electrical Engineering Department
Istanbul Technical University, Istanbul, Turkey

Abstract

In this study the feedback gain matrix that provides robust stability of F16 aircraft short-period mode is obtained by using parameter space approach. The non-linear flight equation of F16 aircraft is linearized for 48 different flight conditions at the steady wings level flight of the speed-altitude envelope. The linear equation of 13000 feet, 500 feet/second is taken as the nominal flight condition. The other flight conditions are represented by uncertainties on the nominal flight equation. The uncertainty boxes are obtained by analyzing the variation of longitudinal motion coefficients. PARADISE toolbox is used to obtain feedback gain coefficients and the calculated coefficients are checked for all uncertainty parameter stability planes which are called stability analysis. The suggested feedback gain matrix moves the system eigenvalue spread into desired region in the complex plane and make the system satisfy desired performance requirements in spite of uncertain parameter variations.