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

Published online by Cambridge University Press:  16 December 2021

S. Gan Open the ORCID record for S. Gan [Opens in a new window] ,
X. Fang  and
X. Wei Open the ORCID record for X. Wei [Opens in a new window]
S. Gan
Affiliation:
State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, 210016, China
X. Fang
Affiliation:
State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, 210016, China
X. Wei*
Affiliation:
Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing, Jiangsu, 210016, China
*
*Corresponding author. Email: wei_xiaohui@nuaa.edu.cn
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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.

Keywords

Lattice Boltzmann methodOleo-pneumaticLanding gearOptimisation designResponse surface method
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1300 , June 2022 , pp. 973 - 992
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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