• Proceedings of the Korean Fiber Society Conference
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• 1995.10a
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• pp.40-40
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• 1995

• 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.

• Proceedings of the Korea Water Resources Association Conference
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• 2017.05a
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• pp.512-512
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• 2017

날로 심각해지는 해수 오염, 유류사고, 해파리에 의한 인명피해 및 발전소의 경제적 피해사고, 해양 쓰레기 등과 같은 해양 환경 문제가 발생하고 있다. 이러한 해양환경문제를 해결하기위해 생물학적 방법과 물리적 방법이 있으나 생물학적 방법은 개체군과 종류의 변화로 그 적용이 어려운 실정이고, 물리적 방법은 지속적인 제거를 위한 비용적인 문제와 인부 및 자원봉사자의 안전문제가 발생한다. 따라서 에어버블을 이용한 각종 친환경적 방법이 주목받고 있다. 본 연구에서는 에어버블 차단막의 차단율을 증가시키기 위해 현장조건 내에서 에어버블의 거동특성에 대한 실험을 하였다. 실험을 위해 회류식 개수로 에어버블 거동실험장치를 제작하였다. 실험장치는 길이 8.1m, 높이 1.2m, 폭 0.7m이며, 두께 10mm의 투명 아크릴를 사용하여 에어버블의 거동을 관찰 할 수 있게하였다. 대형펌프를 사용하여 물이 회류함을 통해 흐름유속을 만들어 현장조건을 고려하였다. 에어버블을 분사하기 위해 압축공기 저장탱크와 연결된 분사구가 있으며, 노즐의 크기(0.5mm~1.0mm)로 분사량을 조절하고 분사압은 별도의 조절장치를 이용하여 0~5bar 범위의 분사압 조절을 가능하게 하였다. 초고속 카메라와 3축유속계를 사용하여 에어버블의 이동경로, 유속 및 에어버블의 거동을 측정하였다. 실험을 통한 구간별 에어버블의 거동 분석 결과, 상승속도는 분사구에서 분출되는 구간인 0~0.8m 에서는 상승속도가 증가하고, 0.8~1.2m구간에서는 속도가 다시 상승하는 경향을 확인하였다. 이는 수표면에 가까워질수록 수압이 작아져서 에어버블의 크기가 커짐에 따라 부력이 커짐으로 판단된다. 같은 이유로 분사량이 많을수록 상승속도도 같이 증가되는 것으로 나타났다. 유속에 따른 거동은 유속을 0.1m/s~0.5m/s로 조정하여 유속별 에어버블이 수표면까지 도달하는 거리, 속도 및 이동경로를 분석하였다. 유속과 에어버블이 수표면까지 도달하는 거리는 비례하여 증가하는 것을 확인하였다. 실험결과를 바탕으로 조건에 따른 에어버블 거동 경험식을 도출하였다. 본 실험은 회류식 개수로 에어버블 거동실험장치를 활용하여 에어버블 거동 경험식을 제시하였으며, 이를 바탕으로 에어버블 차단막 기술 개발을 위한 기초자료로 이용될 수 있을 것이다.

• Journal of Aerospace System Engineering
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• v.16 no.4
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• pp.88-94
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• 2022

The vibration mode measurement test measures the natural vibration characteristics of the target specimen. The measured natural mode characteristics are compared with the numerical analysis result to verify the reliability of the numerical analysis. If necessary, it is used to supplement the numerical analysis model of the specimen used for the dynamic characteristic analysis. In this paper, the natural frequency and natural mode of the external fuel tank are respectively obtained through the vibration mode measurement test and the numerical analysis, using the finite element model. The results are compared to verify the reliability of the numerical analysis model of the external fuel tank to apply to the entire aircraft model. To measure the vibration mode of the test specimen, a bungee cord was used, to simulate the free boundary condition for the test specimen. And, 3-axis accelerometers were installed on the test specimen. The response characteristics of the test specimen were measured, by excitation with an impact hammer. As a result of the test, after performing the frequency response analysis on the response acceleration, the natural frequency of the test specimen and its vibration mode were confirmed. The reliability of the numerical analysis model was verified by comparing the frequency and vibration mode, obtained through the test and the numerical analysis.

• 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.

• Journal of Aerospace System Engineering
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• v.18 no.1
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• pp.64-71
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• 2024

The external fuel tank of an aircraft is a main component that can increase the cruising range of the aircraft. It must be able to be stably separated from the pylon in an emergency situation. At this time, a separation load is applied to the fin and the pivot of the external fuel tank. To stably separate the external fuel tank, the structural soundness of the fin and the pivot must be confirmed. In this study, structural tests were conducted to verify the structural integrity of the external fuel tank pin and pivot when the external fuel tank was separated from the aircraft. Results are then presented. In this paper, a test configuration diagram consisting of the hydraulic and load control equipment, data acquisition system, and pneumatic supply unit used in the structural test was explained. Test installation and test load application plan for each test condition were provided. As results of the structural test, it was found that test load and internal pressure of the test specimen were properly controlled within the allowable range in each test. It was confirmed that serious structural defects in the test specimen did not occur under required load conditions. In conclusion, through structural test for design limit load and design ultimate load, it was proven that the fin and pivot of the external fuel tank for aircraft covered in this study had sufficient structural strength.

• Journal of Aerospace System Engineering
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• v.13 no.4
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• pp.60-65
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• 2019

This study did a structural design of a fuel system of auxiliary fuel tank applied to aircraft then analyzed it. The safety of the structural design result was investigated. Aluminum alloy metal structure was applied to the fuel system structure. The structural analysis was conducted using commercial finite element software. The design requirement was maximum accelerate condition of the structure. Therefore, structural design was done considering the maximum accelerate condition.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.274-279
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• 2010

The present work is to analyze the longitudinal static stability and the drop trajectory of fighter aircraft's external fuel tank, of which horizontal fin is modified as the 20% scale down size compared with the original one. The analytical results to the pitching stability of external fuel tank using a thin airfoil's aerodynamic force data show the corresponding tendency to results of wind tunnel experiment. Results of trajectory simulation by the 6 degree of freedom equations of motion, comparing with drop trajectories of wind tunnel experiment, are shown that aircraft's attitude affects strongly on horizontal movement but not on the vertical movement. Those results give the reliability to aircraft safety when the external fuel tank with the 20% reduced horizontal fins is released from aircraft based on the flight manual.

• Journal of the KSME
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• v.35 no.1
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• pp.36-45
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• 1995

주노즐내의 공기제트의 효율을 높이기 위해, 주노즐 제트 속도는 높을수록 높은 마찰력을 초래 하여 위사의 속도를 증가시킨다. 가속관의 길이가 증가하면 노즐출구에서의 공기의 속도와 난 류가 감소하며; 가속관의 직경이 증가할 때에는 공기속도가 감소하며 난류는 증가한다. 탱크압력, 가속관의 길이 등 유동조건에 따라 유동은 니들 끝과 가속관 출구에서 이중 초크(M=1)가 발 생할 수 있다. 에어가이드 직경과 노즐직경의 그 비율이 클수록 제트에 의한 유동의 비말동 반(entrainment)이 크게 된다. 실제 노즐직기내의 유동은 위사를 동반한 유동이므로 위와 같은 정성적인 설명에 위사의 물성치에 따른 고려를 반드시 하여야만 한다. 현장에서의 노즐설계는 노즐형상 자체의 영향은 물론 각종 위사의 물성치에 맞는 압축공기 압력 최적조건이 무엇인가를 찾는 일도 매우 중요하다.

• Korean Journal of Fisheries and Aquatic Sciences
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• v.25 no.6
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• pp.529-537
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• 1992

Airlift pumps were tested to evaluate their pumping and aeration capacities. The pumps were 34.5 inch long made of 2, 3, 4 and 6 inch nominal diameter PVC pipes. An one hp air blower was used to supply the air. The air-flow rate was measured by an anemometer type air-flow meter and air pressure was level changes in a water tank from which water was pumped. Aeration by the pumps was tested by the standard aeration test method with the center of pump outlet positioned 3 inches above water surface. Oxygen concentrations in water were measured to determine aeration rate. As pumping head increased by water level draw-down in the tank water flow decreased while air flow increased. The reduction rate of water flow was higher with 4 and 6-inch pumps. Small pumps showed very minor changes in the reduction. Aeration rates were similar among 3, 4, and 6 inch pumps. With one hp air blower 6-inch pump at the minimum pumping head achieved the best performance in terms of water circulation.