L_2 GAIN VIBRATION CONTROL of AIRCRAFT LANDING GEAR HAVING INPUT DELAY

Yıl 2017, Cilt: 18 Sayı: 4, 849 - 863, 31.10.2017

Ezgi Özülkü , Hakan Yazıcı

Öz

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.   

Anahtar Kelimeler

aircraft landing gear, vibration, input delay

Kaynakça

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