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.
| Translated title of the contribution | Fuel Tank Vertical Sloshing during Aircraft Landing |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 288-294 |
| Number of pages | 7 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 38 |
| Issue number | 2 |
| DOIs | |
| State | Published - 1 Apr 2020 |