Variable Structure Robust Flight Control System for the F-14

Document Type



In this paper, 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. The linear lateral and longitudinal dynamics of the F-14 are decoupled. This allows design of lateral and longitudinal flight controllers separately. An application of variable structure system (VSS) theory to control of lateral dynamics is presented. A control law is derived for the control of roll angle, lateral velocity, and yaw rate. The chosen sliding surface for the controller design is a linear function of the tracking error, its derivative, and the integral of the tracking error. 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 aerodynamic parameter uncertainty.


Use Find in Your Library, contact the author, or use interlibrary loan to garner a copy of the article. Publisher copyright policy allows author to archive post-print (author’s final manuscript). When post-print is available or publisher policy changes, the article will be deposited