飞机着陆条件下机翼油箱垂荡问题研究

Zhen Dai, Fei Xu, Yabin Yan, Jiancheng Yao, Dongliang Chen

科研成果: 期刊稿件文章同行评审

1 引用 (Scopus)

摘要

In this article, the influence of the fuel sloshing on the tank under the landing condition is investigated to explain the skin deformation of wing tank. Based on the SPH method, a simplified fuel tank model of gas-liquid-solid three-phase is established. NanoFluidX, a fluid dynamics simulation tool, is used to calculate fuel sloshing through a given load and the pressure on the tank. The pressure on the lower wall of tank is then imported into the ABAQUS to calculate the stress distribution on the skin. A measured acceleration curve within 0.56s is used as the moving boundary condition of the fuel tank. It is found through simulation that the air has less influence on the pressure on the lower wall during the aircraft landing. By changing the liquid filling rate, the differences of the pressure on the lower wall are compared. Based on the above research, an empirical relationship among the wall pressure, the external load and the liquid filling rate is obtained.

投稿的翻译标题Fuel Tank Vertical Sloshing during Aircraft Landing
源语言繁体中文
页(从-至)288-294
页数7
期刊Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University
38
2
DOI
出版状态已出版 - 1 4月 2020

关键词

  • Landing
  • NanoFluidX
  • Simulation
  • Skin deformation
  • Sloshing
  • SPH
  • Wing fuel tank

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