On the approximate solution of aircraft landing gear under nonstationary random excitations

Hwang, Jai Hyuk; Kim, Jung Soo

doi:10.1007/bf03185799

Cited by 7 publications

(3 citation statements)

References 3 publications

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“…where, the flow quantity Q flow is calculated by (16) The servo valve displacement l(t) is controlled by the PID controller. Time delay is inevitable in the active control system because of the involved dynamics of servo actuators, filters and sensors, to generate active control force.…”

Section: Active Control Force and Controller Designmentioning

confidence: 99%

“…Tyan et al [15] studied shape filter method and sinusoidal approximation for generating one-dimensional random profiles. Hwang and Kim [16] reported that the response of aircraft landing gear over a random runway can be modelled by a non-classically damped system subject to nonstationary random excitations. Dynamic displacement and acceleration response of cars with uncertain parameters and random input excitations are investigated by Dai et al [17].…”

Section: Introductionmentioning

confidence: 99%

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Aircraft Random Vibration Analysis Using Active Landing Gears

Sivakumar

Haran

2015

Journal of Low Frequency Noise, Vibration and Active Control

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In this article, random vibration analysis of full aircraft with passive and active landing gears has been done by numerical simulations on random runway profile. The mathematical model of full aircraft with active landing gears and modelling of runway profiles have been developed for analysing the aircraft bounce, pitch, roll accelerations, displacement and shock strut travel while taxiing on random runways. The results show that vibration levels of the aircraft by the active landing gear system is less than the conventional landing gear system while taxiing on different grades of random runways. Comparison results also show that the active system improves the ride comfort and easiness of pilot handling and thus, increases the fatigue life of the aircraft. NOMENCLATURE MAircraft fuselage mass m 1Nose landing gear tire mass m 2 Rear left landing gear tire mass m 3 Rear right landing gear tire mass ks 1 Nose gear shock strut stiffness ks 2 Rear left gear shock strut stiffness ks 3 Rear right gear shock strut stiffness cs 1 Nose gear shock strut damping coefficient cs 2 Rear left gear shock strut damping coefficient cs 3 Rear right gear shock strut damping coefficient kt 1 Nose gear tire stiffness kt 2 Rear left gear tire stiffness kt 3 Rear right gear tire stiffness ct 1 Nose gear tire damping coefficient ct 2 Rear left gear tire damping coefficient ct 3 Rear right gear tire damping coefficient [M] Mass matrix [C] Damping INTRODUCTIONLanding gear is a critical component of the aircraft which transmits the ground loads to the aircraft structure. It provides ride comfort to the passengers during taxiing on the runways. It also improves the pilot's efficiency to control the aircraft and to read the instruments in the glass cockpits during ground manoeuvres. The landing gear fitted in the aircraft is not able to adjust the damping characteristics in real-time runway conditions. The focus on active landing gear system is essential to overcome the difficulties of passive landing gear. presented a PID controller tuned with Ziegler-Nichols rules for both robustness and vibration suppression performance aspects. The application of proportional controller to active vibration control incorporated with a passive vibration isolator to suppress the resonant oscillation at its natural frequency was studied by Liu [13]. The present study analysed random vibration of full aircraft model with active landing gears under normal landing condition and dynamic response on different grades of random runways. The designed PID controller generates the control force to reduce bounce, pitch, roll displacement and accelerations of fuselage body considerably. This article does not analyse the bank angle response by PID controller during flight. The PID controller requires the bank angle reference command to tackle the unknown banking for turn coordination. However, the bank angle reference is required by the PID controller during crosswind taxiing conditions. Runway roughness affects both the landing gear and the airframe. Nowada...

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Section: Active Control Force and Controller Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aircraft Random Vibration Analysis Using Active Landing Gears

Sivakumar

Haran

2015

Journal of Low Frequency Noise, Vibration and Active Control

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“…Drop simulation and testing play a key role in the design and evaluation of aerospace landing systems [1]. Accurately predicting the behavior of landing gear under various conditions is essential for ensuring the safety and reliability of aircraft operations [2]. Numerical modeling using computational tools has become an indispensable process in this domain, offering a cost-effective and efficient means of studying complex dynamic systems [3,4].…”

Section: Introductionmentioning

confidence: 99%

Linear and Nonlinear Models for Drop Simulation of an Aircraft Landing Gear System with MR Dampers

Kang

Kim

et al. 2023

Actuators

Self Cite

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In this study, our focus is on the drop test simulation of an MR (Magnetorheological) damper-based main landing gear (MRMLG), aiming to explore multi-degree-of-freedom (DOF) dynamic models during aircraft landing. Three different 6-DOF dynamic models are proposed in this work, and their drop performances are compared with results achieved by commercial software. The proposed models include a nonlinear aircraft model (NLAM); a linearized approximated aircraft model (LAAM) linearizing from the nonlinear equations of motion in NLAM; and a fully approximated aircraft model (FAAM) which linearizes the MRMLG’s strut force model. In order to evaluate the drop performance of the aircraft landing gear system with MR dampers, a 7-DOF aircraft model incorporating the nonlinear MRMLG was formulated using RecurDyn. The principal comparative parameters are the coefficient of determination (R2) for the system response of each model with the RecurDyn model and root mean square error (RMSE), which is the ensemble of CG displacement data for each model. In addition, the ensemble of time series data is created for diverse drop scenarios, providing valuable insights into the performance of the proposed drop test models of an aircraft landing gear system featuring MR dampers.

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Non-stationary Response of a Bridge Due to Moving Vehicle with Random Arrival Rate

Pillai,

Talukdar

2023

Mechanisms and Machine Science

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On the approximate solution of aircraft landing gear under nonstationary random excitations

Cited by 7 publications

References 3 publications

Aircraft Random Vibration Analysis Using Active Landing Gears

Aircraft Random Vibration Analysis Using Active Landing Gears

Linear and Nonlinear Models for Drop Simulation of an Aircraft Landing Gear System with MR Dampers

Non-stationary Response of a Bridge Due to Moving Vehicle with Random Arrival Rate

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