L_2 GAIN VIBRATION CONTROL of AIRCRAFT LANDING GEAR HAVING INPUT DELAY

Authors : Ezgi ÖZÜLKÜ, Hakan YAZICI

Pages : 849-863

Doi:10.18038/aubtda.340810

View : 19 | Download : 10

Publication Date : 2017-10-31

Article Type : Research Paper

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 insert ignore into journalissuearticles values(L-K); functional, first a Bounded Real Lemma insert ignore into journalissuearticles values(BRL); is obtained which enables defining stability criteria in terms of Linear Matrix Inequalities insert ignore into journalissuearticles values(LMIs);. Extending BRL, sufficient delay-dependent criteria is developed for a stabilizing   gain controller synthesis involving a matrix inequality. Bilinear Matrix Inequality insert ignore into journalissuearticles values(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