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

Yazıcı, Hakan; Sever, Mert

doi:10.1177/0954410017713773

Cited by 8 publications

(7 citation statements)

References 27 publications

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“…is obtained. The equation (17) can be easily derived by simply arranging the equation (22). This completes the proof.…”

Section: Lemma [21]mentioning

confidence: 59%

“…All the LQ type optimal control laws discussed above were designed with a solution of Algebraic Riccati Equations (AREs). However, Linear Matrix Inequalities (LMIs) based optimal controller design has received considerable attention in recent years [13], [14], [15], [16], [17]. An optimal LMI based active suspension controller, which is robust against parameter variations and having pole location constraints, has been proposed by Soliman and Bajabaa [18].…”

Section: Introductionmentioning

confidence: 99%

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Electro Hydraulic Suspension System Design With Optimal State Derivative Feedback Controller

Sever¹,

Şendur²,

Yazıcı³

et al. 2017

ANADOLU UNIVERSITY JOURNAL OF SCIENCE AND TECHNOLOGY a - Applied Sciences and Engineering

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This paper is concerned with a control design of an electro-hydraulic suspension system. In some practical problems, for instance in the active suspension design, the state derivative signals such as acceleration and velocity are easier to obtain rather than the state variables such as displacement and velocity, since the most commonly used sensors are the accelerometers. Hence, design of an optimal state derivative feedback controller is proposed by employing the linear matrix inequalities framework. In order to demonstrate the effectiveness of the proposed controller, a two-degree-of-freedom quarter vehicle suspension model equipped with an electro hydraulic actuator is preferred. Throughout the numerical simulation studies, bump type road irregularities at different vehicle forward velocities are applied to evaluate the performances of the controller in terms of ride comfort and safety.

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“…is obtained. The equation (17) can be easily derived by simply arranging the equation (22). This completes the proof.…”

Section: Lemma [21]mentioning

confidence: 59%

Section: Introductionmentioning

confidence: 99%

Electro Hydraulic Suspension System Design With Optimal State Derivative Feedback Controller

Sever¹,

Şendur²,

Yazıcı³

et al. 2017

ANADOLU UNIVERSITY JOURNAL OF SCIENCE AND TECHNOLOGY a - Applied Sciences and Engineering

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View full text Add to dashboard Cite

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“…The realistic and plausible goal is to reduce the acceleration of the helicopter at its center of gravity [20,21]. An exemplar time history of helicopter acceleration at the center of gravity is presented in Figure 6.…”

Section: Control Targetmentioning

confidence: 99%

Semi-Active Control for a Helicopter with Multiple Landing Gears Equipped with Magnetorheological Dampers

2021

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Due to their extensive use in various applications, helicopters need to be able to land in a variety of conditions. Typically, a helicopter landing gear system with skids or passive wheel-dampers is designed based on only one critical touchdown condition. Thus, this helicopter landing gear system may not perform well in different landing conditions. A landing gear system with magnetorheological (MR) dampers would be a promising candidate to solve this problem. However, a semi-active controller must be designed to determine the electrical current applied to the MR damper to directly manage the damping force. This paper presents a new skyhook controller, called the skyhook extended controller, for a helicopter with multiple landing gears equipped with MR dampers to reduce the helicopter’s acceleration at the center of gravity in off-normal landing attitude conditions. A 9-DOF simulation model of a helicopter with multiple MR landing gears was built using RECURDYN. To verify the effectiveness of the proposed controller, co-simulations were executed with RECURDYN and MATLAB in different initial pitch and roll angles at touchdown. The main simulation results show that the proposed controller can greatly decrease the peak and rms acceleration of the helicopter’s center of gravity compared to a traditional skyhook controller and passive damper.

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“…However, the current work of landing analysis compared with the results of taxiing analysis of same aircraft on random runways by the other authors. Hakan Yazici and Mert Sever [15] has obtained RMS values of a typical aircraft taxiing at a speed of 120 km/hr and 240 km/hr. The fuselage acceleration while taxiing on grade C, D, E random runway irregularities in the range of 0.112, 0.159 and 0.226 m/s² and for active landing gear using robust LQR controller is 0.038, 0.051 and 0.068 m/s² respectively.…”

Section: Non Stationary Random Response On Grade E Profilementioning

confidence: 99%

Investigation of random runway effect on landing of an aircraft with active landing gears using nonlinear mathematical model

Sivakumar¹,

Selvakumaran²,

Sanjay³

2021

J. vibroeng.

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Random runway roughness effect on the dynamic response of an aircraft with landing gears has been investigated using nine degree of freedom nonlinear mathematical model. The developed mathematical model incorporates nonlinear characteristics of air spring stiffness, landing gear damping, tire stiffness and damping of the oleo pneumatic main landing gears and nose gear. Equation of motion for aircraft and each landing gear have been written considering heave, pitch, roll of aircraft and three vertical motions of landing gears respectively for landing response analysis. The equations for longitudinal motion of each landing gear are also written from the mathematical model will be helpful for longitudinal dynamics. The aircraft touchdown and roll on with variable decent velocities on Grade E random runway represented by nonstationary random process. The excitation of different grades of random runway can be considered as stationary random process when the aircraft landing at constant sink velocity. This work mainly focused on finding the dynamic responses of the aircraft such as heave, pitch, roll acceleration, vertical forces and all the three landing gears vertical vibration levels while landing on random runways. The active landing gear system performance is compared with passive landing gear system by numerical simulation in MATLAB/SIMULINK. The investigation using nonlinear model predicted that the effect of active control landing gear provides significant reduction in vibration levels and vertical reactions during landing at various vertical velocities on random runways. To validate the above mathematical model a multi-body dynamics (MBD) model has been simulated in ABAQUS/CAE and the dynamic responses of landing gear forces are compared with those obtained from the nonlinear mathematical model. The nonlinear model responses are also compared with the results of other authors. This study is more useful to adopt active control landing gear in the aircraft to reduce the landing loads transmit on aircraft structure and landing gears due to landing impact. The reduction of vibration levels and vertical forces by the active system increase the fatigue life of landing gears and structural life of airframe.

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

Cited by 8 publications

References 27 publications

Electro Hydraulic Suspension System Design With Optimal State Derivative Feedback Controller

Electro Hydraulic Suspension System Design With Optimal State Derivative Feedback Controller

Semi-Active Control for a Helicopter with Multiple Landing Gears Equipped with Magnetorheological Dampers

Investigation of random runway effect on landing of an aircraft with active landing gears using nonlinear mathematical model

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