• New & Renewable Energy
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• v.2 no.4 s.8
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• pp.102-106
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• 2006

에탄올은 금속, 고무 수지를 부식시키고 열화시키기 때문에 FFV 등 알코올 대응차량이 아닌 경우 에탄올 허용도가 제한되고 있으며, 물과의 상호용해성과 흡습성으로 수분혼입에 의한 상분리가 발생하여 혼합가솔린의 유통에서의 취급에 어려움이 야기되고 있다. 또한, 에탄올은 가솔린과 혼합되면 공비현상으로 인하여 50% 유출온도가 크게 떨어지고 증기압이 7kPa 정도 상승을 초래하는 점도 간과하지 않을 수 없다. 따라서, 자동차용휘발유에 에탄올을 혼입하여 사용할 경우, 가솔린기재를 적절히 선택하여 적정품질을 유지하여야 하며 무엇보다도 에탄을 혼입농도에 따른 저장탱크와 주유기 등의 부품에의 영향과 저장시의 상분리 문제를 충분히 규명하여 유통인프라에서의 적절한 대응책이 마련되어져야 한다. 유통 인프라 대응을 위해서는 우선 생산단계에서 수분 혼입을 최소화하기 위하여 저유소의 출하지점에서 서브옥탄가솔린과 에탄올을 라인브랜딩에 의해 제조하는 방법이 가장 타당하며, 수송부문에서는 탱크로리 등의 공급라인인 파이프와 실링 재질 등에 대해서 면밀한 검토가 필요하다고 할 수 있다. 주유소에서의 대응은 에탄을 혼합연료와 직접 접촉하는 연료계 등 부품재질을 내부식성의 재질로 변환시켜야 하며, 수분혼입을 최소화하기 위한 이중탱크 설치, 지하탱크 환기구내의 대기벨브 설치 등이 필요하며, 기타, 품질 및 수분관리 대책 등도 마련되어야 할 것이다.

• Corrugated packaging logistics
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• s.91
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• pp.78-96
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• 2010

열설비에서 회수되는 고온의 응축수를 고온수용 급수펌프를 이용하여 직접 급수시키므로 응축수탱크 및 보충수탱크에서 발생되는 재증발 증기를 Steam ejector를 이용, 흡입하여 중압으로 열사용처로 다시보내 15%이상의 에너지 절감효과 및 연료절감 효과를 볼수 있도록 하는 설비를 개발하여 소개하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.4
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• pp.98-106
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• 2000

A conceptual design of propulsion system for a geosynchronous communication satellite with 12 years design life is presented in this paper. Propellant mass budget for the design life is calculated using total velocity increment ($\Delta$V) flowed-down from mission requirement analysis. Sizes of the fuel and oxidizer tank are derived based on the calculated propellant mass budget, and mass of the pressurant as well as the size and Pressure of pressurant tank are calculated too. Thruster positioning, number of rocket engines, and position of tank are determined through trade-off study with Structure & Mechanical Subsystem. Propulsion system configuration and its schematics are presented finally.

• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.16-23
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• 2023

The aircraft fuel system performs a number of functions such as supplying fuel, transferring fuel between fuel tanks, and measuring the amount of residual fuel in each fuel tank. Since it is a direct cause of fire hazard in crash incident, it is a must to improve survivability of crew members by designing the airframe to tolerate expected crash impact. The civil aviation authority requires intensive verification of the fuel system design to determine precise application of the airworthiness requirement. Research activity on airworthiness certification criteria and verification scheme is still insufficient, although it has a significant importance. In this paper, as part of a study to improve flight safety by developing guidelines for demonstrating fuel system crash resistance, analysis results of fuel system crash-related airworthiness certification standards, verification scheme, and cases study applicable to military rotorcraft have been reviewed.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2007.05a
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• pp.356-360
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• 2007

Fuel sloshing in a vehicle fuel tank generates a reluctant low frequency noise, called slosh noise. To reduce slosh noise, whilst many approaches have used the Computational Fluid Dynamics method to first identify fuel behavior in a fuel tank, this paper applies the Transfer Path Analysis method. It is to find contribution of each transfer path from noise transfer function, vibration transfer function and acceleration. Then the final goal is to attenuate slosh noise by controlling them. To this aim, two types of models are studied. One is the decoupled model in which some of connection points of the fuel tank with the vehicle underbody are separated. The other is the modified model which is created by changing noise transfer function and acceleration from the original model. The analysis and validation test results show that the transfer path analysis can be an approach to enhancing slosh noise.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.17 no.8
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• pp.766-770
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• 2007

Fuel sloshing in a vehicle fuel tank generates a reluctant low frequency noise, called slosh noise. To reduce slosh noise, whilst many approaches have used the Computational Fluid Dynamics method to first identify fuel behavior in a fuel tank, this paper applies the Transfer Path Analysis method. It is to find contribution of each transfer path from noise transfer function, vibration transfer function and acceleration. Then the final goal is to attenuate slosh noise by controlling them. To this aim, two types of models are studied. One is the decoupled model in which some of connection points of the fuel tank with the vehicle underbody are separated. The other is the modified model which is created by changing noise transfer function and acceleration from the original model. The analysis and validation test results show that the transfer path analysis can be an approach to enhancing slosh noise.

• Journal of the Korean Society of Mechanical Technology
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• v.13 no.4
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• pp.15-21
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• 2011

The safety at this study is investigated by flow or stress analyses due to configuration or installation direction of fuel tank in the existing CNG bus. In case of the lower ceiling with sharp type, the equivalent stress due to the explosion of fuel tank is less than the type of flat or arc. it becomes safer on passenger. In case of the installation direction of fuel tank in the existing CNG bus, the stress applied on the lower ceiling at transverse direction becomes less than at longitudinal direction. It is more stable on the safety of passenger. The harm on the explosion accident can be prevented by use of the analysis result at this study.

• Journal of Auto-vehicle Safety Association
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• v.13 no.4
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• pp.73-80
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• 2021

Recently, Korea has established a plan for the supply of hydrogen vehicles and is promoting the expansion of the supply. Risk factors for hydrogen vehicles are hydrogen leakage, jet fire, and explosion. Therefore Safety measures are necessary for this hazard. In addition, risks in semi-closed spaces such as tunnels, underground roads, and underground parking lots should be analyzed. In this study, an explosion experiment was conducted on a hydrogen tank used in a hydrogen vehicle to analyze the risk of a hydrogen vehicle explosion accident that may occur in a semi-closed space. As results, the effect on the structure and the human body was analyzed using the overpressure and impulse values for each distance generated during the explosion.

• Journal of Aerospace System Engineering
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• v.15 no.1
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• pp.80-85
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• 2021

In this study, for conducting a static load test of an external fuel tank used for an aircraft, the flight load acting on the external fuel tank was converted to the test load and the suitability of the converted test loads was confirmed. In order to calculate the test load from the flight load, the external fuel tank was divided into several sections. Shear load, moment by unit shear load, and unit moment were calculated for each section. Test loads for each section were then calculated by computing the shear load, the moment of each section, and flight load condition. In actual static load tests, it might not be possible to impose the test load in the calculated position due to physical constraints. Therefore, after determining positions in which the load could be imposed in the actual test, the test load calculated for each section was redistributed to selected positions. Finally, a test load plan was established by applying a whiffle tree to enhance the efficiency of the test performance while making it easier to operate the actuator. The reliability of the test load plan was verified by comparing it with flight load conditions.

• Journal of Aerospace System Engineering
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• v.16 no.3
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• pp.99-104
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• 2022

Aircraft pylon connects the engine or external stores to the main wing, and transfers the load acting on the pylon to the main structure of the aircraft. In particular, it should perform the function of separating the external store mounted on the pylon in case of emergency or mission performance. At this time, if the separation of the external store is not performed properly due to peripheral air flow or functional problems during the separation process of the external store, it may seriously impact the survivability of the aircraft. For this reason, to apply an external attachment to an aircraft, it is necessary to prove the stability of the external attachment in the separation situation in advance. In this paper, we present the result of the ground separation test performed to confirm that the external fuel tank, which is an external attachment, can be safely separated from the pylon. As a result of the test, the separation movement of the external fuel tank was measured with a high-speed camera, and the stability of the separation of the external fuel tank from the pylon were confirmed through the ground separation test. Additionally, the test result provides basic data for the stability evaluation of the separation of external attachments in actual aircraft.