Abstract
A technique is described which can be used for design of feedback controllers for high-performance aircraft operating in flight conditions in which nonlinearities significantly affect performance. Designs are performed on a mathematical model of the longitudinal dynamics of a hypothetical aircraft similar to proposed supermaneuverable flight test vehicles. Nonlinear controller designs are performed using truncated solutions of the Hamilton-Jacobi-Bellman equation. Preliminary results show that the method yields promising results.
| Original language | English (US) |
|---|---|
| Title of host publication | Proc 1989 Am Control Conf |
| Editors | Anon |
| Publisher | Publ by IEEE |
| Pages | 142-147 |
| Number of pages | 6 |
| State | Published - Dec 1 1989 |
| Event | Proceedings of the 1989 American Control Conference - Pittsburgh, PA, USA Duration: Jun 21 1989 → Jun 23 1989 |
Other
| Other | Proceedings of the 1989 American Control Conference |
|---|---|
| City | Pittsburgh, PA, USA |
| Period | 6/21/89 → 6/23/89 |