Variable structure robust flight control system for the F-14

摘要

A flight control law for a simplified F-14 aircraft model is designed, based on variable structure control (VSC) theory. For m-input, q-output linear uncertain systems q>m, a VSC law is derived. For the derivation of the control law, a choice of a sliding surface is made so that the zero dynamics of the system are stable. Application of variable structure system theory to the control of lateral dynamics is presented. A control law is derived for the control of roll angle, lateral velocity and yaw rate. Simulation results are presented to show that in the closed-loop system, precise bank angle trajectory tracking and regulation of lateral velocity and yaw rate can be accomplished in spite of the aerodynamic parameter uncertainty.