This paper presents the application of nonlinear H∞ state feedback theory to flight control. We divide the flight control into attitude control and velocity control which are different to the conventional longitudinal and lateral control. The new control framework which is based on nonlinear H∞ state feedback theory solves the 6 D aircraft governing equations directly without linearization. This new flight control methodology has the separation property where we can design the attitude controller and the velocity controller independently. Moreover, it can be shown that controller design can be done before parameter identifications of the aircraft.
|Number of pages||5|
|Journal||Proceedings of the American Control Conference|
|Publication status||Published - 1997|
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering