TY - GEN
T1 - Nonlinear μ flight control and suboptimal exact solution on F-16 application
AU - Kung, Chien Chun
AU - Yang, Ciann Dong
AU - Hwang, Jyh Woei
AU - Wu, Chi Yu
PY - 2005
Y1 - 2005
N2 - This paper investigates the theory of nonlinear H∞ analysis to flight vehicles with varying real parameters which arise from the uncertain aerodynamic coefficients. It's so called nonlinear μ flight control. The difficult task involved in applying the nonlinear μ light control is to solve the associated Hamilton-Jacobi inequality for uncertain system. In this paper we derive the suboptimal condition to meet the L 2-gain of the nonlinear uncertain system less than a constant γ. The complete six degree-of-freedom nonlinear equations of motion for F-16 aircraft are considered directly to design the nonlinear μ 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 μ controller with simple proportional feedback structure. This paper verify that the derived nonlinear μ control law can ensure global flight envelop and asymptotical stability of the closed loop system with varying aerodynamic characteristics and have strong robustness against wind gusts with varying statistical characteristics.
AB - This paper investigates the theory of nonlinear H∞ analysis to flight vehicles with varying real parameters which arise from the uncertain aerodynamic coefficients. It's so called nonlinear μ flight control. The difficult task involved in applying the nonlinear μ light control is to solve the associated Hamilton-Jacobi inequality for uncertain system. In this paper we derive the suboptimal condition to meet the L 2-gain of the nonlinear uncertain system less than a constant γ. The complete six degree-of-freedom nonlinear equations of motion for F-16 aircraft are considered directly to design the nonlinear μ 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 μ controller with simple proportional feedback structure. This paper verify that the derived nonlinear μ control law can ensure global flight envelop and asymptotical stability of the closed loop system with varying aerodynamic characteristics and have strong robustness against wind gusts with varying statistical characteristics.
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U2 - 10.1109/CDC.2005.1582232
DO - 10.1109/CDC.2005.1582232
M3 - Conference contribution
AN - SCOPUS:33847211451
SN - 0780395689
SN - 9780780395688
T3 - Proceedings of the 44th IEEE Conference on Decision and Control, and the European Control Conference, CDC-ECC '05
SP - 666
EP - 671
BT - Proceedings of the 44th IEEE Conference on Decision and Control, and the European Control Conference, CDC-ECC '05
T2 - 44th IEEE Conference on Decision and Control, and the European Control Conference, CDC-ECC '05
Y2 - 12 December 2005 through 15 December 2005
ER -