L_2 GAIN VIBRATION CONTROL of AIRCRAFT LANDING GEAR HAVING INPUT DELAY

Year 2017, Volume: 18 Issue: 4, 849 - 863, 31.10.2017

Ezgi Özülkü , Hakan Yazıcı

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

References

• Howe D. Aircraft Loading and Structural Layout. London, UK: Professional Engineering Publishing, 2004.
• Currey NS. Aircraft Landing Gear Design: Principles and Practices. Washington D.C., USA: American Institute of Aeronautics and Astronautics Inc, 1988.
• Krüger W, Besselınk I, Cowlıng D. Doan DB, Kortüm W and Krabacher W. Aircraft landing gear dynamics. Simulation and Control, Vehicle System Dynamics 1997; 28:119-158.
• Howell WE, McGebee JR, Daugherty RH and Vogler WA. F-106B airplane active control landing gear drop test performance, Proceedings of the Landing Gear Design Loads Conference, 1991 California,USA.
• McGebee JR and Carden HD. Mathematical model of an active control landing gear for load control during impact and roll-out. NASA Technical Note D-8080,1976.
• Li Y, Gao B and Guan W. Fault-tolerant control for semi-autonomous damper. In: 25th Chinese Control and Decision Conference; 2013 Guiyang, China, pp.623 – 628.
• Zapateiro M, Pozo F, Rossell JM, Karimi HR, Luo N. Landing gear suspension control through adaptive backstepping techniques with H_∞ performance. In: 18th IFAC World Congress;2011 Milano, Italy pp.4809-4814.
• Hua-Lin L, Yong C, Qi H, Jian L. Fuzzy PID control for landing gear based on magneto-rheological (MR) damper. In: Int. Conf. on Apperceiving Computing and Intelligence Analysis, 2009 Chengdu; pp.22-25.
• Ghiringhelli LG and Gualdi S Evalution of landing gear semi-active control system for complete aircraft landing, Aerotechnica Missili e Spazio 2004;83:21-31.
• Sateesh B and Maiti DK. Vibration control of an aircraft nose landing gear due to ground-induced excitation, Proceedings of the Institution of Mechanical Engineers 2010;224: 245-258.
• Ross I and Edson R Application of active control landing gear technology to the A-10 aircraft, NASA CR-166104, 1993, USA.
• Yazici H and Sever M Active control of a non-linear landing gear system having oleo pneumatic shock absorber using robust LQR aproach. Shock and Vibration 2016;1-20.
• Li F, Wei G, Qi W and Xinhe X. Modeling and adaptive control of magneto-rheological buffer system for aircraft landing gear. Applied Mathematical Modelling 2015; 39: 2509-2517
• Toloei AR, Zarchi M and Attaran B. Application of active suspension system to reduce aircraft vibration using PID technique and Bees algorithm. Int J Comput Appl 2014; 98: 17–24.
• Yazici H and Sever M. Active control of a non-linear landing gear system having oleo pneumatic shock absorber using robust linear quadratic regulator approach. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 2017, https://doi.org/10.1177/0954410017713773.
• Sivakumar S and Haran AP. Aircraft random vibration analysis using active landing gears. Journal of Low Frequency Noise Vibration and Active Control 2015; 34: 307-322.
• Gu K, Kharitonov V and Chen J. Stability of Time Delay System. Bostan, USA: Birkhauser: Basel, 2003.
• Zhao Y, Sun W and Gao H. Robust control synthesis for seat suspension systems with actuator saturation and time-varying input delay. Journal of Sound and Vibration 2010; 329: 4335–4353.
• Du H and Zhang, N. H_∞ control of active vehicle suspensions with actuator time delay. Journal of Sound and Vibration 2007; 301: 236–252.
• Ghaoui L. E., Qustry F. and Ait Rami M. A Cone complementarity linearization algorithm for static output feedback and related problems. IEEE Transactions on Automatic Control 1997;42:1171-1176.
• Moon Y.S., Park P., Kwon H.W. and Lee Y.S. Delay-Dependent robust stabilization of uncertain state-delayed systems. International Journal of Control 2001;74:1447-1455
• Yazici H., Guclu R., Kucukdemiral I.B.,Parlakci MNA. Robust delay-dependent H control for uncertain structural systems with actuator delay. Journal of Dynamic Systems, Measurement and Control 2012;134:1-15
• Boyd S., Ghaoui L.E., Feron E., Balakrishnan V Linear Matrix Inequalities in System and Control Theory, Society for Industrial and Applied Mathematics, Philadelphia, USA, 1994.
• Löfberg J. Yalmip: A toolbox for modeling and optimzation in MATLAB, Proc. of the CACSD Conference, 2004, Taipei, Taiwan.
• Strum F, Using SeDuMi 1.02 a Matlab for optimization over symmetric cones, Optimization Methods and Software, 1999;11:625-653.