Fluid-structure Interaction Dynamic Analysis Of Aircraft Fuel Tank Sloshing During Large Overload Maneuver

The fuel in the aircraft fuel tank sloshes under the movement of tank,and the sloshing fuel impacts the wall and makes it deform in return.This coupling problem between the wall and fuel is aircraft fuel tank sloshing,which is a typical fluid-structure interaction problem.The sloshing of aircraft fuel tank can have a great influence on the safety and driveability of plane.Large overload will be produced especially during the maneuver,and the sloshing problem is extremely complicated which leads to the research on aircraft fuel tank sloshing during maneuver significant when the tank is subjected to the impact of fuel and inertial force of overload.The tank's dynamic response is calculated when solving the fluid characteristics of sloshing in the tank sloshing problem which contains both fluid and solid,so the finite element method software ABAQUS and computational fluid dynamics software Star-CCM+are united to analysis the fluid-structure interaction dynamics of tank sloshing in the large overload maneuver process under considering the advantage of computational fluid dynamics in capturing fluid motion and superiority of finite element method in getting solid response.Taking the integral fuel tank of a certain aircraft as the research object,the sloshing of fuel and response of structure under two kinds of maneuvering flight,namely Split-S and normal hover,are studied correspondingly.It is proved that the method presented can be used to investigate the fluid-structure interaction problem of fuel tank sloshing,and the one-way method is more suitable through the verification and comparison of the methods.The results of Split-S show that the stress and strain of tank change with the overload,the influence of maneuver overload is greater than the sloshing on the dynamic response of the structure,the fuel gradually peaceful and concentrates in lower half of the tank and variations of component stress and strain tend to be stable with the change of overload,the forms of fuel impact on wall are different under different filling rate,the stress of components except upper skin goes up and the stable time of sloshing rises with the increase of filling rates.The results of normal hover indicate that the fluid characteristics and structural response first change with the tank roll,then overload,and dominated by the inertial force under full load.In the condition of non-full,the fuel in theentry stage sloshes violently and generates large impact pressure and the impact time is advanced with higher filling rate,the fuel gradually accumulates at the bottom of tank under the action of overload in the constant speed hovering stage,the higher the filling rate is,the faster the fuel stabilizes.When the filling rate is low,the roll has a greater influence on the component stress,while the filling rate is high,the effect of spiral overload is bigger.In the stage of large overload of Split-S and normal hover,though the sloshing slows down and tends to be stable,the fluid pressure,stress and strain of the tank are relatively large,which shows that the maneuver overload has a significant impact on the fluid-structure interaction effect of aircraft fuel tank sloshing.