Fuel Tank Vertical Sloshing during Aircraft Landing

飞机着陆条件下机翼油箱垂荡问题研究

¹ School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
² AVIC XAC Commercial Aircraft Co., Ltd., Xi'an 710089, China

Received: 17 June 2019

Abstract

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.

摘要

针对飞机机翼油箱下蒙皮处出现变形的工程现象，研究了飞机在降落条件下，机翼整体油箱垂荡导致的燃油晃荡对箱体产生的影响。采用SPH方法，建立了气液固三相的简化油箱模型。利用nanoFluidX流体动力学仿真工具，计算给定载荷下的燃油晃荡情况，以及油箱下壁板的压力值，然后在ABAQUS有限元软件中计算壁板的应力分布。将飞机降落时实测的0.56 s内的加速度曲线作为油箱的运动边界条件，通过改变箱内燃油的充液率，比较下壁板压力的变化，最终得出了下壁板压力值与外载荷及充液率之间的变化关系。