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Analysis of Crash Load in Crash Impact Test for Fuel Tank of Rotorcraft

항공기용 연료탱크 Phase I 충돌충격시험 충격하중 분석

  • Received : 2015.03.19
  • Accepted : 2015.06.11
  • Published : 2015.06.30

Abstract

Crash impact test is conducted to verify the crashworthiness of fuel tank. Success of the crash impact test means the improvement of survivability of crews by preventing post-crash fire. But, there is a big risk of failure due to huge external load in the crash impact test. The failure of crash impact test can result in serious delay of a entire rotorcraft development because of the design complement and re-production of the test specimens requiring a long-term preparation. Thus, the numerical simulations of the crash impact test has been required at the early design stage to minimize the possibility of trial-and-error in the real test. Present study conducts on the numerical simulation of phase I crash impact test using SPH supported by crash simulation software, LS-DYNA. Test condition of MIL-DTL-27422 is reflected on analysis and material data is acquired by specimen test of fuel cell material. As a result, the crash load on the skin material, overlap area and metal fitting is estimated to confirm the possibility of acquisition of the design load for the determination of the overlap area and adhesive strength.

Keywords

Fuel tank LS-DYNA;SPH(Smoothed Particle Hydrodynamic)

References

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Acknowledgement

Grant : Virtual Test 기반 항공기 내추락 설계/해석 기술개발사업

Supported by : 기초기술연구회