Nonlinear Flight Control System Design Including Handling Qualities Evaluation

Abstract

Progress in aircraft designs heavily depend on automatic flight control system. Modern aircraft have a wide flight envelope (linear and nonlinear) region. This study considers the design of stability and control augmentation system (SCAS) in high angle of attack region for a modern type aircraft via back stepping method. Because of highly nonlinear phenomena in aerodynamic parameters, a locally valid linear in the parameters nonlinear aircraft model is defined, of which the unknown parameters are approximated by Lyapunov base update laws. The numerical simulations show that the controller is capable of control aircraft based on conventional handling qualities and has a better time response than the classical PI.

Design and Simulation of Pitch Optimizer and Stall Protection for a Typical UAV

“…Most essential among these rotations is the pitch which can be controlled by the elevator. Pitch angle is controlled by the angle and lift force of the elevator [3]. Most UAVs employ PID controllers for adequate control, this means that a well-tuned PID to acceptable extent can be applied to control UAVs [4].Several works have been done in the field of optimizing pitch systems to prevent a stall.…”