Damping of the limited perturbations in the system of the aircraft control when landing

Abstract

A linear model of the aircraft control system in the landing mode is consid- ered in the presence of limited external perturbations. The method of lin- ear matrix inequalities is implemented in the generalized H∞-optimization problem in order to evaluate and reduce the influence of external and ini- tial disturbances on qualitative characteristics of the system. In particular, influence of weight coefficients of the generalized quality criteria on the sta- bility factor and the transient process time of a closed system have been investigated.