Abstract
A global stability result is presented for nonlinear aircraft pitch-axis models with dynamic inversion control laws. The result is applied to the F-14 aircraft model. Using this result, we are able to sketch a stability region of the F-14 model in terms of the engine thrust and the selected pitch attitude.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1-25 |
| Number of pages | 25 |
| Journal | International Journal of Control |
| Volume | 63 |
| Issue number | 1 |
| DOIs | |
| State | Published - Jan 1 1996 |
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