L_2 GAIN VIBRATION CONTROL of AIRCRAFT LANDING GEAR HAVING INPUT DELAY

Abstract

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.   

Keywords

• aircraft landing gear,vibration,input delay

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