Nonlinear Control of Aircraft Flight Dynamics Using Integrator-Backstepping Design Method
Publication: Journal of Aerospace Engineering
Volume 35, Issue 2
Abstract
This paper investigated a nonlinear control algorithm for flight dynamics of aircraft using an integrator backstepping–based design. The paper focused on two points. Firstly, a systematic procedure was presented for formulating an integrator-backstepping law for a strict-feedback form of nonlinear dynamic system. In this approach, a set of coordinate transformations including a definition of modified tracking error and state feedback laws is provided to transform a strict-feedback model into a state-decoupled linear model. This process of control design is implemented using a backstepping recursive design in which a backstepping control law is formulated for further study. Secondly, successful applications of roll dynamics of L-59 aircraft model and longitudinal dynamics of F-16 aircraft model were restructured in a strict-feedback form of nonlinear dynamic system under a series of less restrictive assumptions. A direct applicability of the proposed control theoretic framework was used to derive backstepping control laws for the achieved models. To show advancement, improvement, and validation of the proposed control method, both simulation and experimental studies were implemented, which used the numerical simulation of the flight path angle control of the longitudinal motion of an F-16 aircraft model and an experimental study of roll angle control of an L-59 aircraft model to validate the proposed control approach.
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Data Availability Statement
Some or all data, models, or code that support the findings of this study are available from the corresponding author upon reasonable request.
Acknowledgments
This research is funded by Vietnamese-German University under Grant No. DTCS2020-003.
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Published In
Journal of Aerospace Engineering
Volume 35 • Issue 2 • March 2022
Copyright
© 2022 American Society of Civil Engineers.
History
Received: Feb 24, 2020
Accepted: Nov 10, 2021
Published online: Jan 5, 2022
Published in print: Mar 1, 2022
Discussion open until: Jun 5, 2022
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