Abstract
This paper investigates the implementation of nonlinear H∞ control theory for F-16 flight control system. The complete six degree-of-freedom nonlinear equations of motion for F-16 are considered directly to design the nonlinear H∞ 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 H∞ controller with simple proportional feedback structure. Real aerodynamic data and engine data of F-16 are employed to determine the angles of control surface deflection from the nonlinear H∞ control command. Feasibility of tracking nonlinear H∞ control command by using F-16 actuator system is discussed in detail, and the guaranteed stability and robustness of nonlinear H∞ flight control system implemented by F-16 actuators are confirmed over large flight envelope in a six degree-of-freedom flight simulator.
| Original language | English |
|---|---|
| Pages (from-to) | 4480-4485 |
| Number of pages | 6 |
| Journal | Proceedings of the IEEE Conference on Decision and Control |
| Volume | 4 |
| Publication status | Published - 2002 Dec 1 |
| Event | 41st IEEE Conference on Decision and Control - Las Vegas, NV, United States Duration: 2002 Dec 10 → 2002 Dec 13 |
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering
- Modelling and Simulation
- Control and Optimization