Time responses of system show that the controller guarantees stability of system with delay and has sufficient disturbance attenuation performance
📌 3 Key Takeaways
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Objective & Hypothesis:In this paper a state feedback delay dependent 2 gain controller is designed in order to control of aircraft landing gear vibration.
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Key Findings & Data:Based on the selection of suitable Lyapunov-Krasovskii (L-K) functional, first a Bounded Real Lemma (BRL) is obtained which enables defining stability criteria in terms of Linear Matrix Inequalities (LMIs).
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Conclusion & Impact:Time responses of system show that the controller guarantees stability of system with delay and has sufficient disturbance attenuation performance
🔬Design:Research Article
📍Scope:Comprehensive Sample
⚙️Variables:Domain Parameters
Abstract
In this paper a state feedback delay dependent 2 gain controller is designed in order to control of aircraft landing gear vibration. Based on the selection of suitable Lyapunov-Krasovskii (L-K) functional, first a Bounded Real Lemma (BRL) is obtained which enables defining stability criteria in terms of Linear Matrix Inequalities (LMIs). Extending BRL, sufficient delaydependent criteria is developed for a stabilizing Inequality (BMI) problem is solved by utilizing cone complementary algorithm. To show the effectiveness of proposed controller on aircraft landing gear vibration, simulation studies are given. Time responses of system show that the controller guarantees stability of system with delay and has sufficient disturbance attenuation performance
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Cite This Article
ÖZÜLKÜ, E., YAZICI, H. (2022). GAIN VIBRATION CONTROL of AIRCRAFT LANDING GEAR HAVING INPUT DELAY. Anadolu Üniversitesi Bilim ve Teknoloji Dergisi :A-Uygulamalı Bilimler ve Mühendislik, Cilt: 18 - Sayı: 4, 849–863. https://ajindex.com/articles/438300
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