This paper investigates the implementation of nonlinear Hinfinity control theory for F-16 flight control system. The complete six degree-of-freedom nonlinear equations of motion for F-16 are considered directly for the design of the nonlinear Hinfinity flight controller by treating the longitudinal and lateral motions as a whole. The associated Hamilton-Jacobi partial differential inequality is solved analytically, resulting in a nonlinear Hinfinity controller with simple proportional feedback structure. Real aerodynamic data and engine data of F-16 are employed to determine the angles of control surface deflection from the nonlinear Hinfinity control command. Feasibility of tracking nonlinear Hinfinity control command by using F-16 actuator system is discussed in detail and the guaranteed stability and robustness or nonlinear Hinfinity flight control system implemented by F-16 actuators are confirmed over large flight envelope in a six degree-of-freedom flight simulator.
F-16 nonlinear Hinfinity control
IEEE Conference on Decision and Control, 41 ; 4480-4485
2002
6 Seiten, 8 Quellen
Conference paper
English
Nonlinear Hinfinity control of active suspensions
Tema Archive | 2001
|Hinfinity design of future flight control systems
Tema Archive | 1990
|H2 and Hinfinity control for MagLev vehicles
Tema Archive | 1998
|Adaptive fuzzy mixed H2/Hinfinity attitude control of spacecraft
Tema Archive | 2000
|VSTOL first flight on an Hinfinity control law
Tema Archive | 1995
|