Name
Abstract | ||
|---|---|---|
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 L2-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 |
Year | DOI | Venue |
|---|---|---|
2005 | 10.1109/CDC.2005.1582232 | conference on decision and control |
Keywords | DocType | ISBN |
control systems,degree of freedom,asymptotic stability,nonlinear equations,aerodynamics,exact solution,nonlinear equation | Conference | 0-7803-9567-0 |
Citations | PageRank | References |
0 | 0.34 | 2 |
Authors | ||
4 | ||
Name | Order | Citations | PageRank |
|---|---|---|---|
| Chien-Chun Kung | 1 | 2 | 0.80 |
| Ciann-Dong Yang | 2 | 1 | 1.10 |
| Jyh-Woei Hwang | 3 | 0 | 0.34 |
| Chi-Yu Wu | 4 | 0 | 0.34 |