论文信息 - Stability of dynamic inversion control laws applied to nonlinear aircraft pitch-axis models

Stability of dynamic inversion control laws applied to nonlinear aircraft pitch-axis models

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.

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