Parallel evolutionary optimized pitching motion control for F-16 aircraft

In this paper, the Stability Augmentation System (SAS) is designed to improve the stability while Parallel Evolutionary Optimization based on Lagrangian II (PEvolian II) is successfully applied to satisfy several constraints and to minimize the rising time. A controller to stabilize F-16 aircraft flying with a steady state around the altitude of 25,000ft is described. The nonlinear pitching motion model of F-16 is linearized in the range of the flight envelope of velocity vs. altitude. Then the statically unstable system is stabilized by applying feedback linearization. As the gain-scheduling method is introduced at various operating points within the flight envelope, the optimized controller is designed all over the envelope. Parallel Evolutionary Optimization based on Lagrangian II is used to optimize the proportional and integral gains of the controller, satisfying complex nonlinear constraints.