• Bulletin of the Korean Space Science Society
• /
• 2004.04a
• /
• pp.71-71
• /
• 2004

KSLV-I 추진기관 기체공급계는 상부의 산화제 탱크로부터 나온 산화제 주배관이 하부의 연료탱크를 관통하여 엔진공급계로 이어지도록 구성되어 있다. 연료탱크에는 산화제 배관의 관통을 위한 tunnel이 구성되어 있으며 배관과 tunnel은 일정한 간격을 유지하게 된다. 배관과 연료탱크 사이의 열전달을 줄이기 위하여 산화제 배관에 단열재를 적용할 수 있으나, 이 경우 배관의 운송, 조립시에 handling이 힘들게 되고, 특히 발사체에 조립된 후에 발생하는 단열재의 파손 및 성능감소에 대한 유지보수가 불가능하다. (중략)

• Aerospace Engineering and Technology
• /
• v.3 no.1
• /
• pp.272-276
• /
• 2004

Fuel tank design requires special care because tank explosion can cause critical event with high possibility and cause of recent explosion accidents haven't been found out definitely. In this study, cause of fuel tank explosion was reviewed and several design considerations to minimize explosion possibility were introduced.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.36 no.10
• /
• pp.1032-1037
• /
• 2008

The fuel tank systems of fixed wing and rotary wing aircrafts require the self-sealing and crash-worthiness for their survivability. For these requirements, the flexible composite fuel tank is generally used. In this study, the performance of the flexible composite fuel tank is investigated. The FE simulation includes the drop test of a fuel tank using MSC.DYTRAN. MSC.DYTRAN can provide the fluid-structure modeling of these test from Euler and Lagrange grids. Using MSC.DYTRAN, the finite element modeling of the test cube of the flexible fuel tank and its FE simulation are performed for various environments. The simulation results can show if the test cube satisfies the performance requirements of the fuel tank.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.18 no.7
• /
• pp.709-713
• /
• 2017

In urgent situations such as crashes, the integrity of an aircraft's fuel tank is directly related to the survivability of the crew. Thus, an external auxiliary fuel tank should be robust against bird strikes. In this study, a numerical analysis was carried out using impact analysis software to analyze the influence of bird strike on a composite container for an external auxiliary fuel tank. The structure was modeled as a shell element, and the fluid and bird were modeled by the particle method. The behavior of the internal fluid was also examined. The maximum stress, deformation, and strain of the composite container were also calculated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.713-716
• /
• 2010

Slosh and vibration effects of fuel inside of fuel tank can be occurred due to the acceleration and flight speed during the rotorcraft flight. It can lead to the failure of internal fuel component and fuel tank skin can be damaged. This is directly related to human survival. Military specification (MIL-DTL-27422D) specifies that stability of aircraft fuel tank and internal component against slosh &vibration load shall be verified through the qualification test procedures. This report shows the establishment of slosh and vibration test facility and KUH fuel tank qualification test result.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.38 no.8
• /
• pp.806-812
• /
• 2010

Fuel tanks for rotorcraft have a great influence on the survivability of crews. The philosophy of crashworthy rotorcraft design evolved from the long term effort of the US Army. US army established MIL-DTL-27422D for specifying detail requirements related to crash resistant fuel tank especially for military rotorcraft to prevent post crash fire which is the greatest threat to life in rotorcraft crash. Crashworthiness of the rotorcraft fuel tank could be guaranteed through the crash impact tests which are specified in the MIL-DTL-27422D. Fuel tanks for Korea Helicopter Program have been developed and tested according to MIL-DTL-27422D with minor modifications of flexible fittings. The present study shows some results of the mandatory crash impact tests of the fuel tanks to verify their performances.

• Journal of the Computational Structural Engineering Institute of Korea
• /
• v.16 no.1
• /
• pp.77-86
• /
• 2003

Dynamic response of baffled fuel-storage tank in turnaround motion is simulated using the ALE finite element method. Fuel-storage tank undergoes abrupt impact load caused by inertia force of internal fuel in turnaround motion. Also, large dynamic force and moment caused by this load influence structural stability and control system. In this paper, ring-type baffles are adopted to suppress the dynamic influence. Through the parametric analysis with respect to the baffle number and location, the effects of baffle on the dynamic response of baffled fuel-storage tank is analyzed. The ALE finite element method is adopted for the accurate and effective simulation of the hydrodynamic interaction between fluid and structure.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.15 no.3
• /
• pp.80-85
• /
• 2011

The air in the fuel tank could cause oxidation of fuel during storage, and it also reduced the fuel transfer performance. To find better procedure for refueling of aircraft fuel tank, the vacuum refueling process was proposed to reduce the air in the fuel tank. In this study, the vacuum refueling process was established and tested, it could be helpful to find out what happened during vacuum refueling. Also the revised vacuum refueling process was proposed to reduce the air and refueling time.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.04a
• /
• pp.385-390
• /
• 2011

The air remained in the fuel tank could cause oxidation of fuel during storage, and it also reduce the fuel transfer performance. To find better procedure for refueling of aircraft fuel tank, the vacuum refueling process was proposed to reduce air in the fuel tank. In this study, the vacuum refueling process established and tested, it could be helpful to find out what happened during vacuum refueling. Also the revised vacuum refueling processes were proposed to reduce the remained air and refueling time for aircraft fuel tank.

• Journal of the Computational Structural Engineering Institute of Korea
• /
• v.24 no.5
• /
• pp.521-530
• /
• 2011

Since aircraft fuel tanks have many interfaces connected to the airframe as well as the fuel system, they have been considered as one of the system-dependent critical components. Crashworthy fuel tanks have been widely implemented to rotorcraft and rendered a great contribution for improving the survivability of crews and passengers. Since the embryonic stage of military rotorcraft history began, the US army has developed and practised a detailed military specification documenting the unique crashworthiness requirements for rotorcraft fuel tanks to prevent most, hopefully all, fatality due to post-crash fire. The mandatory crash impact test required by the relevant specification, MIL-DTL-27422D, has been recognized as a non-trivial mission and caused inevitable delay of a number of noticeable rotorcraft development programs such as that of V-22. The crash impact test itself takes a long-term preparation efforts together with costly fuel tank specimens. Thus a series of numerical simulations of the crash impact test with digital mock-ups is necessary even at the early design stage to minimize the possibility of trial-and-error with full-scale fuel tanks. In the present study the crash impact simulation of a few fuel tank configurations is conducted with the commercial package, Autodyn, and the resulting equivalent stresses and internal pressures are evaluated in detail to suggest a design improvement for the fuel tank configuration.