FLIGHT CONTROL SYSTEM DESIGN USING ROBUST CONTROL TECHNIQUE

Abstract

This project deals with the modeling of, and design I validation of controllers for high performance aircraft. The .work starts with the building of the non-linear model described by non-linear differential equation with highly non-linear coefficients which are calculated based on [oak up tables. The look up tables are real wind tunnel and engine test bed data for the F-16 aircraft. The data set available is, however, sparse and is valid for a restricted range of flight conditions. As, one of the objectives of the project was to attempt all stages of controller design with geometric, wind tunnel and test bed data of the fighter aircraft as a base line, a sparse data set was not considered to be a significant restriction. As a part of this project, software tools for numerically trimming the aircraft and numerically linearizing the non-linear model were developed from standard numerical algorithms. Controller have been designed using the H_ robust control technique using normalized coprime.factor of the weighted plant at linearized points on the flight envelop. The controller so designed have been shown to function within a restricted range of flight conditions with both scheduled and switching of the controller designed at various linearized design points