In this paper a state feedback delay
dependent
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 delay-dependent criteria is
developed for a stabilizing
gain controller synthesis involving a matrix
inequality. Bilinear Matrix 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.
Konular | Mühendislik |
---|---|
Bölüm | Araştırma Makalesi |
Yazarlar | |
Yayımlanma Tarihi | 31 Ekim 2017 |
Yayımlandığı Sayı | Yıl 2017 Cilt: 18 Sayı: 4 |