Sliding mode control of directly excited structural dynamic model of twin-tailed fighter aircraft

DOI10.1016/J.JFRANKLIN.2021.10.017zbMath1480.93077OpenAlexW3209793576MaRDI QIDQ2068220

Ayman A. El-Badawy, Youssef Mahgoub

Publication date: 19 January 2022

Published in: Journal of the Franklin Institute (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1016/j.jfranklin.2021.10.017

zbMATH Keywords

frequency-response curvessliding mode controllerbuffeting loadtwin-tails of a fighter aircraft

Mathematics Subject Classification ID

Feedback control (93B52) Frequency-response methods in control theory (93C80) Variable structure systems (93B12)

Cites Work

• Unnamed Item
• Active control of an aircraft tail subject to harmonic excitation
• Nonlinear time delay saturation-based controller for suppression of nonlinear beam vibrations
• Buffeting analysis: a numerical study on the extraction of equivalent static wind loads
• Primary and secondary resonance analyses of a cantilever beam carrying an intermediate lumped mass with time-delay feedback
• Active vibration control of a dynamical system via negative linear velocity feedback
• Control of a directly excited structural dynamic model of an F-15 tail section

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