Observer Based Optimal Vibration Control of a Full Aircraft System Having Active Landing Gears and Biodynamic Pilot Model

Abstract

This paper deals with the design of an observed based optimal state feedback controller having pole location constraints for an active vibration mitigation problem of an aircraft system. An eleven-degree-of-freedom detailed full aircraft mathematical model having active landing gears and a seated pilot body is developed to control and analyze aircraft vibrations caused by runway excitation, when the aircraft is taxiing. Ground induced vibration can contribute to the reduction of pilot’s capability to control the aircraft and cause the safety problem before take-off and after landing. Since the state variables of the pilot body are not available for measurement in practice, an observed based optimal controller is designed via Linear Matrix Inequalities (LMIs) approach. In addition, classical LQR controller is designed to investigate effectiveness of the proposed controller. The system is then simulated against the bump and random runway excitation. The simulation results demonstrate that the proposed controller provides significant improvements in reducing vibration amplitudes of aircraft fuselage and pilot’s head and maintains the safety requirements in terms of suspension stroke and tire deflection.

Active control of a non-linear landing gear system having oleo pneumatic shock absorber using robust linear quadratic regulator approach

“…21 Active landing gear design by an optimal observerbased controller is studied by Yazici and Sever. 10 In order to design an active landing gear system with robust LQR controller, in the following sequel, theorem of a robust LQR controller design having pole location constraints is given. 17…”

A Static Output Feedback Controller Design for Reducing Vertical Acceleration of a Passenger Ship

“…Fakat, statik çıkış geri-beslemeli kontrolörlerin, kolayca ölçülebilen sinyalleri geri-besleyebilme özellikleri ile pratikte uygulanabilirlikleri yüksektir. Bununla birlikte dinamik çıkış geri-beslemeli kontrolörlere göre daha ucuz maliyetleri ile bozucu bastırama problemleri için büyük bir potansiyele sahiptirler [14,15]. Bu nedenle, bu çalışmada, bozucu dalga etkisindeki bir geminin düşey ivmelerinin azaltılması için LME tabanlı statik çıkış geri beslemeli kontrolör tasarımı gerçekleştirilmiştir.…”

“…Burada π = (A T P + PA + C y T K T B u T P + PB u KC y ) dır. Kararlılık koşullarına, performans indeksi, γ>0 olmak üzere z T (t)z(t) -γ 2 w T (t)w(t) şeklinde eklenmesi ile kapalı çevrim sistemin kararlılık ve performans kısıtları (15) şeklinde elde edilir. (15) Eşitsizliğinden, eğer Ψ<0 ise, V(x(t)) + z T (t)z(t) -γ 2 w T (t)w(t) < 0 olur ve sistemin bozucu girişlerinden performans çıkışlarına olan L 2 kazancı, x(0)=0 başlangıç koşulu için, ||T zw || ∞ < γ olur.…”

Free vibration analysis of a discretized aircraft with an integrated biodynamic pilot model – modal approach

“…Suggestion is made to extend the scope of work in including seated-human model in vehicle suspension systems and studying dynamic characteristics. Yazici and Sever [6] used Linear Matrix Inequalities (LMI) approach to design an observer based optimal state feedback controller for active vibration attenuation. An eleven DOF mathematical model of an aircraft with included biodynamic pilot model under runway disturbances during taxiing is considered for the study.…”