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Sliding Mode Differentiator Based Tracking Control of Uncertain Nonlinear Systems with Application to Hypersonic Flight
Author(s) -
An Hao,
Fidan Baris,
Wu Qianqian,
Wang Changhong,
Cao Xibin
Publication year - 2019
Publication title -
asian journal of control
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.769
H-Index - 53
eISSN - 1934-6093
pISSN - 1561-8625
DOI - 10.1002/asjc.1932
Subject(s) - differentiator , control theory (sociology) , nonlinear system , hypersonic flight , hypersonic speed , sliding mode control , tracking error , range (aeronautics) , trajectory , convergence (economics) , variable structure control , computer science , signal (programming language) , engineering , control (management) , aerospace engineering , physics , artificial intelligence , computer network , bandwidth (computing) , quantum mechanics , astronomy , economic growth , economics , programming language
This paper presents a performance‐guaranteed adaptive back‐stepping design for a class of nonlinear systems with uncertainties and disturbances. To circumvent the increasing complexity caused by the repeated analytic differentiations in back‐stepping, sliding mode differentiation technique is employed to estimate the derivative of the virtual control. Compared with the well‐known command filtered back‐stepping, no compensating signal is required. Besides, time‐varying parameters, system uncertainties and external disturbances are compensated using nonlinear damping technique, while the output tracking error is regulated in the prescribed range with the adjustable convergence speed and steady‐state error. As a verification example, this method is applied to the longitudinal control of an air‐breathing hypersonic vehicle configured with the variable geometry inlet.