Identification and reconfigurable control of multivariable aircraft

This paper presents the conceptual development of advanced flight control systems (flight management systems), where the objective is to attain real-time identification, design, and controller reconfiguration. The identification and control methods developed use a complete nonlinear aircraft model derived from the Lagrange equations of motion. The generalized performance functional is employed. Using the Hamilton-Jacobi theory, bounded controllers are designed applying the first- and second-order necessary criteria for optimality. The sufficient conditions are studied to analyze stability of the closed-loop systems with bounded control. In particular, the admissibility concept, which is based on the Lyapunov stability theory, is used. It is shown that innovative procedures guarantee real-time identification, constrained optimization, and controller reconfiguration. The concept reported can be applied to advanced highly maneuverable aircraft, as well as to agile missiles and interceptors