Numerical Simulation of Sloshing Test for Fuel Tank of Rotorcraft

회전익항공기용 연료탱크 슬로싱 시험 수치해석

  • Received : 2016.05.09
  • Accepted : 2016.07.07
  • Published : 2016.07.31


The rapid turning and acceleration movement of a rotorcraft leads to a sloshing phenomenon in the fuel tank. Sloshing caused by rapid movement can affect the internal components by creating an excessive load. In severe situations, the resulting damage to the internal components and pipes can also lead to the tearing of the fuel tank itself. Therefore, to improve the survivability of the crew, the internal components of the fuel tank must be designed to retain their structural soundness during the sloshing phenomenon. In order to accomplish this, the sloshing load acting on the components first needs to be determined. This paper investigates the sloshing load applied to the internal components by performing numerical analysis for rotary-wing aircraft fuel tanks in the sloshing test. Fluid-Structural Interaction (FSI) analysis based on smoothed particle hydrodynamics (SPH) is conducted and the conditions specified in the US military standard (MIL-DTL-27422D) are employed for the numerical simulation. Based on this numerical simulation, by analyzing the load applied to the internal components of the fuel tank due to the sloshing phenomenon, the possibility of obtaining the design data by numerical analysis is examined.


Grant : 내추락성 및 2.75%(MIL-G-26988 Class II) 측정정확도를 가진 헬기용 연료량 측정장치 기술개발

Supported by : 산업통상자원부


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