Analysis and optimisation design on damping orifice of oleo-pneumatic landing gear

2021 ◽  
pp. 1-20
Author(s):  
S. Gan ◽  
X. Fang ◽  
X. Wei
Keyword(s):  
Numerical Model ◽  
Response Surface ◽  
Maximum Error ◽  
Landing Gear ◽  
Drop Test ◽  
Damping Force ◽  
Mean Velocity ◽  
Aircraft Landing ◽  
Surface Method ◽  
Boltzmann Method

Abstract This paper investigates the feasibility of improving the aircraft landing performance by design the damping orifice parameters of the landing gear using lattice Boltzmann method coupled with the response surface method. The LBM is utilised to simulate characteristics of the damping orifice after model validation. The numerical model of the landing gear using simulated damping force is validated by single landing gear drop test. Based on the numerical model and the response surface functions, the sensitivity analysis and the optimisation design are performed. The maximum error of mean velocity simulated using LBM with experimental data is 7.07% for sharp-edged orifices. Moreover, the numerical model predicts the landing responses adequately, the maximum error with drop test data is 2.51%. The max overloading of the aircraft decreases by 5.44% after optimisation, which proves that this method is feasible to design the damping orifice for good landing performance.

scholarly journals Parametric Analysis on Landing Gear Strut Friction of Light Aircraft for Touchdown Performance

2021 ◽  
Vol 11 (12) ◽  
pp. 5445
Author(s):  
Shengyong Gan ◽  
Xingbo Fang ◽  
Xiaohui Wei
Keyword(s):  
Response Surface ◽  
Energy Absorption ◽  
Landing Gear ◽  
Surface Model ◽  
Absorption Properties ◽  
Surface Method ◽  
Design Variables ◽  
Landing Impact ◽  
Landing Response ◽  
Parametric Studies

The aim of this paper is to obtain the strut friction–touchdown performance relation for designing the parameters involving the strut friction of the landing gear in a light aircraft. The numerical model of the landing gear is validated by drop test of single half-axle landing gear, which is used to obtain the energy absorption properties of strut friction in the landing process. Parametric studies are conducted using the response surface method. Based on the design of the experiment results and response surface functions, the sensitivity analysis of the design variables is implemented. Furthermore, a multi-objective optimization is carried out for good touchdown performance. The results show that the proportion of energy absorption of friction load accounts for more than 35% of the total landing impact energy. The response surface model characterizes well for the landing response, with a minimum fitting accuracy of 99.52%. The most sensitive variables for the four landing responses are the lower bearing width and the wheel moment of inertia. Moreover, the max overloading of sprung mass in LC-1 decreases by 4.84% after design optimization, which illustrates that the method of analysis and optimization on the strut friction of landing gear is efficient for improving the aircraft touchdown performance.

Parametric design and analysis on the landing gear of a planet lander using the response surface method

2018 ◽  
Vol 148 ◽  
pp. 225-234 ◽  
Author(s):  
Guang Zheng ◽  
Hong Nie ◽  
Min Luo ◽  
Jinbao Chen ◽  
Jianfeng Man ◽  
...  
Keyword(s):  
Response Surface ◽  
Response Surface Method ◽  
Parametric Design ◽  
Landing Gear ◽  
Surface Method

Oil damping energy loss analysis of landing gear shock absorber

2018 ◽  
Vol 233 (8) ◽  
pp. 3096-3106
Author(s):  
Fujun Jiao
Keyword(s):  
Energy Loss ◽  
Theoretical Calculation ◽  
Shock Absorber ◽  
Volume Flow Rate ◽  
Landing Gear ◽  
Drop Test ◽  
Damping Force ◽  
Flow Process ◽  
Ansys Fluent ◽  
Loss Analysis

It is seen that previous research on falling vibration of landing gear only provides work–stroke diagram and damping force value. Nevertheless, the change process of buffering medium at a micro-level is yet to be analyzed. The velocity, pressure, and their change over time of fluid particle are rarely researched in reality. To improve the intuitive, concreteness, and accuracy of the falling vibration analysis, this paper uses theoretical calculation and simulation to analyze oil damping energy loss of shock absorber. On the basis of theoretical calculation, the paper provides a feasible solution for calculating oil damping energy loss in the drop test of landing gear. Based on the classical fluid mechanics, the research builds a series-parallel model for calculating oil damping coefficient, and the oil damping energy loss values are calculated. To the flow passage type with one inlet and two outlets, the best solution of volume flow rate weighting of two outlets is determined. With regard to simulation, ANSYS FLUENT is used to show the dynamic flow process of oil in damping orifice. Damping energy loss values are calculated by total pressure difference. By comparison, the results of the theoretical calculation, the simulation, and the drop test achieve a good consistency.

scholarly journals Multibody rigid models and 3D FE models in numerical analysis of transport aircraft main landing gear

2015 ◽  
Vol 63 (3) ◽  
pp. 745-757 ◽  
Author(s):  
W. Krason ◽  
J. Malachowski
Keyword(s):  
Numerical Model ◽  
Contact Problems ◽  
3D Models ◽  
Landing Gear ◽  
Fe Model ◽  
Transport Aircraft ◽  
Aircraft Landing ◽  
Aircraft Landing Gear ◽  
Drop Tests ◽  
3D Numerical Model

Abstract Dynamic analyses of a transport aircraft landing gear are conducted to determine the effort of such a complex system and provide capabilities to predict their behaviour under hazardous conditions. This kind of investigation with the use of numerical methods implementation is much easier and less expensive than stand tests. Various 3D models of the landing gear part are defined for the multistage static FE analysis. A complete system of the main landing gear was mapped as a deformable 3D numerical model for dynamic analysis with the use of LS-Dyna code. In this 3D deformable FE model, developed in a drop test simulation, the following matters were taken into consideration: contact problems between collaborating elements, the phenomena of energy absorption by a gas-liquid damper placed in the landing gear and the response of the landing gear during the touchdown of a flexible wheel with the ground. The results of numerical analyses for the selected drop tests and the results from the experiments carried out on a real landing gear were used for verification of FE models and a methodology of the landing gear dynamics analysis. The results obtained from the various simulations of the touchdown have proved the effectiveness of the 3D numerical model and how many problems can be solved in the course of only one numerical run, e.g. geometric and material nonlinearities, a question of contact between the mating components, investigation of the landing gear kinematics, investigation of the energy dissipation problem in the whole system and the stresses influence on the structure behaviour, which can appear in some elements due to overload.

Evaluation of the Aircraft Landing Gear Crashworthiness by Crash Drop Test

2020 ◽  
Vol 44 (5) ◽  
pp. 377-382
Author(s):  
Tae-Uk Kim ◽  
Seunggyu Lee ◽  
Donggeon Lee ◽  
JeongJun Jo ◽  
SeokNam Shin
Keyword(s):  
Landing Gear ◽  
Drop Test ◽  
Aircraft Landing ◽  
Aircraft Landing Gear

scholarly journals Experimental Research on Aircraft Landing Gear Drop Test Based on MRF Damper

2011 ◽  
Vol 15 ◽  
pp. 4712-4717 ◽  
Author(s):  
Zhu Shixing ◽  
Wang Peng ◽  
Tian Jing
Keyword(s):  
Experimental Research ◽  
Landing Gear ◽  
Drop Test ◽  
Aircraft Landing ◽  
Aircraft Landing Gear

Effects of magnetic core parameters on landing stability and efficiency of magnetorheological damper-based landing gear system

2019 ◽  
Vol 31 (2) ◽  
pp. 198-208 ◽  
Author(s):  
Chulhee Han ◽  
Bo-Gyu Kim ◽  
Byung-Hyuk Kang ◽  
Seung-Bok Choi
Keyword(s):  
Equations Of Motion ◽  
Magnetic Core ◽  
Landing Gear ◽  
Gear System ◽  
Magnetorheological Damper ◽  
Design Parameters ◽  
Damping Force ◽  
Magnetic Circuits ◽  
Aircraft Landing ◽  
New Type

In this research, a new type of magnetorheological damper for a small-sized aircraft landing gear system is proposed and its performance is evaluated with respect to design parameters of the magnetic core. As a first step, a new configuration of magnetorheological damper for the landing gear system, which consists of orifices, recoil valve, and magnetic circuits, is introduced with working principles. After formulating the governing equations of motion, six different models of magnetorheological damper featuring different number of magnetic core and different pole length are chosen to investigate both the landing stability and the efficiency. Subsequently, the distribution of the magnetic field intensity of each model is analyzed through the finite element method, followed by the calculation of the field-dependent damping force to be used for the landing simulation, which is undertaken by adopting the dynamic model of a half airplane landing gear system. In order to identify the significance of the magnetic core parameters, the landing stability is judged from the sign of the minimum force and the landing efficiency is determined from the energy dissipation during the vertical drop motion.

Aircraft Landing Gear of a Dynamic Research and Computer Simulation

2011 ◽  
Vol 383-390 ◽  
pp. 2426-2429 ◽  
Author(s):  
Shen Shou Li ◽  
Xiao Ming Liu ◽  
Zhong Gan Zhu ◽  
Fang Yang
Keyword(s):  
Landing Gear ◽  
Structural Constraints ◽  
Test Results ◽  
Dynamics Model ◽  
Damping Force ◽  
Aircraft Landing ◽  
Aircraft Landing Gear ◽  
Spring Force ◽  
Adams Software ◽  
Software Modules

by the MSC Adams / Aircraft software features, setting pillar-type landing gear as the prototype, and using ADAMS software modules prior to the establishment of a certain type of aircraft landing gear model, then calculate the air buffer spring force oil, damping force and the structural constraints force curve based on dynamics model, At the end of paper we will analyze the model drop-test results. The results proved that we used this method was feasible.

scholarly journals Intelligent Control Based on a Neural Network for Aircraft Landing Gear with a Magnetorheological Damper in Different Landing Scenarios

2020 ◽  
Vol 10 (17) ◽  
pp. 5962 ◽  
Author(s):  
Quoc Viet Luong ◽  
Dae-Sung Jang ◽  
Jai-Hyuk Hwang
Keyword(s):  
Neural Network ◽  
Mr Damper ◽  
Landing Gear ◽  
Magnetorheological Damper ◽  
Damping Force ◽  
Hybrid Controller ◽  
Aircraft Landing ◽  
Neural Network Controller ◽  
Passive Damper ◽  
Aircraft Landing Gear

A typical oleo-pneumatic shock-absorbing strut (classic traditional passive damper) in aircraft landing gear has a metering pin extending through the orifice, which can vary the orifice area with the compression and extension of the damper strut. Because the metering pin is designed in a single landing condition, the traditional passive damper cannot adjust its damping force in multiple landing conditions. Magnetorheological (MR) dampers have been receiving significant attention as an alternative to traditional passive dampers. An MR damper, which is a typical semi-active suspension system, can control the damping force created by MR fluid under the magnetic field. Thus, it can be controlled by electric current. This paper adopts a neural network controller trained by two different methods, which are genetic algorithm and policy gradient estimation, for aircraft landing gear with an MR damper that considers different landing scenarios. The controller learns from a large number of trials, and accordingly, the main advantage is that it runs autonomously without requiring system knowledge. Moreover, comparative numerical simulations are executed with a passive damper and adaptive hybrid controller under various aircraft masses and sink speeds for verifying the effectiveness of the proposed controller. The main simulation results show that the proposed controller exhibits comparable performance to the adaptive hybrid controller without any needs for the online estimation of landing conditions.

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