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

Abstract

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. Additional informationNotes on contributorsBING-YU ZHANG Institute for Mathematics and Its Applications, University of Minnesota, Mineapolis, MN-55455, U.S.A.