目的 探究不同充液率下,油液晃动特性及其对机身结构应力应变的影响。方法 采用STAR-CCM+与ABAQUS联合仿真技术,基于流体体积法（VOF）建立燃油晃动模型,通过单向流固耦合模拟俯仰过载下油箱晃动工况,并对比油箱区和非油箱区的应力应变值。结果 结构应力应变分布呈现明显的区域化特征。油箱区域作为主要承力部位,其应力水平显著高于其他区域,最大等效应力达到154.9 MPa,非油箱区域的应力水平相对较低（约为油箱区的48.4%）。油箱区最大拉伸应变为725.5με,非油箱区最大拉伸应变为油箱区的81.1%。结论 针对流体域的分析表明,油箱壁板压力主要受过载及液面高度影响,油箱壁板力传递到固体域模型后,非油箱区的响应特性揭示了载荷在机体结构中的传递规律。在俯仰工况下,油箱晃动导致非油箱区的应力应变应予以关注。
Abstract
The work aims to investigate the effects of fuel sloshing characteristics under different liquid filling ratios on the stress-strain distribution of aircraft fuselage structures. A coupled STAR-CCM+ and ABAQUS simulation approach was employed to develop a fuel sloshing model based on the Volume of Fluid (VOF) method. A one-way fluid-structure coupling analysis was conducted to simulate the fuel tank behavior under pitch overload conditions, and stress-strain responses between tank and non-tank regions were compared. Stress-strain distribution exhibited distinct regional characteristics. The tank region, as the primary load-bearing area, showed significantly higher stress levels, with a maximum vonMises stress of 154.9 MPa. Non-tank regions displayed relatively lower stress concentrations (about 48.4% of the tank region's maximum). Maximum tensile strain in the tank region reached 725.5με, while non-tank regions measured 81.1% of the tank region's strain. Fluid domain analysis confirms that tank wall pressure is predominantly governed by overload conditions and fuel surface height. After the tank wall pressure is transmitted to the solid domain model, the response characteristics of the non-tank region reveal the transmission law of the load in the aircraft structure. Under pitch maneuver conditions, attention should be paid to the stress and strain in the non-tank region caused by the fuel tank sloshing.
关键词
油箱 /
晃动冲击 /
过载 /
流固耦合 /
应力应变 /
充液率
Key words
fuel tank /
sloshing impact /
overload /
fluid structure coupling /
stress and strain /
liquid filling ratio
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