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 design the nonlinear H∞ controller using the 6 D aircraft governing equations directly. Linear models are not necessary. This new flight control methodology has the separation property which we can design the attitude controller and the velocity controller independently. Moreover, it can be shown that controller can be designed before parameter identification of the aircraft. On the other hand, the solutions of the nonlinear H∞ controllers are sets. Hence we can find a controller from the solution sets to satisfy the performance specifications. The time responses, control energies and robustness by different controllers and different output weights will be discussed in this paper.
|Number of pages||12|
|Journal||Transactions of the Aeronautical and Astronautical Society of the Republic of China|
|Publication status||Published - 1997 Sep 1|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering