Robust Flight Vehicle Controller Design with Roll Dynamics

Abstract

This paper focuses on a design of nonlinear robust control system to invert a high performance fighter aircraft. Control system is developed based on the application of 1) a conditional integrator based continuous sliding mode control (SMC) design for robust control of slow dynamic part of aircraft system, and 2) dynamic inversion (DI) control as an inner-loop controller to maintain the stability of fast dynamics system. The robustness property of integrated conditional integral SMC and dynamic inversion controller is ensured to solving a tracking problem without adaptation of unknown lateral-directional aerodynamic parameters. The efficacy of the proposed robust nonlinear control system has been shown through the numerical simulations of a high performance fighter aircraft. Transient and steady state performance of a control system is also ensured without suffering from the drawback of control chattering.