This paper investigates the application of nonlinear H∞ control theory to flight vehicles whose complete six degree-of-freedom nonlinear equations of motion are considered directly without linearization. Nonlinear flight control modes such as velocity control, body-rate control, attitude control, and hovering control are designed in a unified framework such that the derived nonlinear H∞ control law is valid for arbitrary flight vehicles. The most difficult and challenging task involved in applying the nonlinear H∞ control theory is to solve the associated Hamilton-Jacobi partial differential inequality (HJPDI). In this paper we show that the HJPDI of flight control problems can be solved analytically with simple manipulations. A closed-form expression for the nonlinear H∞ flight controller is derived from the solution of HJPDI and shown to be in the simple structure of proportional feedback. The numerical simulations show that the derived nonlinear H∞ control law can ensure global and asymptotical stability of the closed loop system and have strong robustness against wind gusts with varying statistical characteristics.
|Number of pages||5|
|Journal||Proceedings of the American Control Conference|
|Publication status||Published - 2000|
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering