Multidisciplinary Optimal Design of an Active Control System and State Estimator for an Aircraft Wing

A multidisciplinary and multi-objective optimization approach that integrates the design of control surfaces’ sizes, active system, estimator for an aircraft’s wing with three surfaces is developed in this paper. Four objectives are considered: minimizing impacts external gust loads, maximizing stability robustness, reducing energy consumption, Frobenius norm gains. For simulation purposes, a mathematical model flexible having ailerons used. The system observer designed simultaneously. problem formulated solved by NSGA-II (non-dominated sorting genetic algorithm II). solution called Pareto set corresponding function evaluations front. properties front; sensitives dominant poles open-loop closed-loop to airspeed; responses controlled, uncontrolled, models at selected objective values obtained. results shows simultaneous algorithms, geometry settings very effective, can suppress flutter stabilize converges quickly always stable regardless air stream velocity.