Document Type : Original Article
Authors
1 Faculty of Engineering, Islamic Azad University, Science and Research Branch, Tehran, Iran
2 Faculty of Engineering, Islamic Azad University, Science and Research Branch, Tehran, Iran.
3 Department of Aerospace Engineering, K. N. Toosi University of Technology, Tehran, Iran.
Abstract
airplane in presence of asymmetric left-wing damaged. Variations of the aerodynamic parameters, mass and moments of inertia, and the center of gravity due to damage are all considered in the nonlinear mathematical modeling. The proposed discrete-time nonlinear MRAC algorithm applies the recursive least square (RLS) algorithm as a parameter estimator as well as the error between the real damaged dynamics and a model of nominal undamaged aircraft to generate the desired control commands. The discrete-time adaptive control algorithm is augmented with a Nonlinear Dynamic Inversion (NDI) control strategy and is implemented on the NASA generic transport model (GTM) airplane while considering the effect of wing damage and un-modeled actuator dynamics. The stability of the proposed nonlinear adaptive controller is demonstrated through Popov’s hyperstability theory. Simulation results of the introduced controller are compared with the classical discrete-time adaptive control strategy. The results demonstrate the effective performance of the proposed algorithm in controlling the airplane in presence of abrupt asymmetric damage.
Keywords
Main Subjects
Article Title [فارسی]
On the Design of Nonlinear Discrete-Time Adaptive Controller for damaged Airplane
Authors [فارسی]
- Karim Dastgerdi 1
- Farshad Pazooki 2
- Jafar Dr. Roshanian 3
1 Faculty of Engineering, Islamic Azad University, Science and Research Branch, Tehran, Iran
2 Faculty of Engineering, Islamic Azad University, Science and Research Branch, Tehran, Iran.
3 Department of Aerospace Engineering, K. N. Toosi University of Technology, Tehran, Iran.
Abstract [فارسی]
airplane in presence of asymmetric left-wing damaged. Variations of the aerodynamic parameters, mass and moments of inertia, and the center of gravity due to damage are all considered in the nonlinear mathematical modeling. The proposed discrete-time nonlinear MRAC algorithm applies the recursive least square (RLS) algorithm as a parameter estimator as well as the error between the real damaged dynamics and a model of nominal undamaged aircraft to generate the desired control commands. The discrete-time adaptive control algorithm is augmented with a Nonlinear Dynamic Inversion (NDI) control strategy and is implemented on the NASA generic transport model (GTM) airplane while considering the effect of wing damage and un-modeled actuator dynamics. The stability of the proposed nonlinear adaptive controller is demonstrated through Popov’s hyperstability theory. Simulation results of the introduced controller are compared with the classical discrete-time adaptive control strategy. The results demonstrate the effective performance of the proposed algorithm in controlling the airplane in presence of abrupt asymmetric damage.
Keywords [فارسی]
- flight dynamics
- nonlinear dynamic inversion
- tip-wing losing-
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