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- W2151857997 abstract "A nonlinear approach to the automatic pitch attitude control problem for a generic fighter aircraft is presented. A nonlinear model describing the longitudinal equations of motion in strict feedback form is derived. Backstepping is utilized for the construction of a globally stabilizing controller with a number of free design parameters. Two tuning schemes are proposed based on the desired locally linear controller properties. The controller is evaluated using the HIRM fighter aircraft model." @default.
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- W2151857997 date "2000-01-01" @default.
- W2151857997 modified "2023-10-11" @default.
- W2151857997 title "Aircraft Pitch Attitude Control using Backstepping" @default.
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