• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2012.06a
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• pp.282-283
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• 2012

국제표준규격(ISO 12215-5) 및 국내 플레저보트 검사지침의 개정에 따라 길이 6미터 미만의 플레저보트의 낙하시험에 의한 강도시험기준을 적용 가능하게 되었다. 하지만 현재 낙하시험은 자유낙하 시 내력 및 외력에 의한 선체 내부의 찌그러짐, 크랙, 박리, 파손 등을 육안으로 검사하는 방법으로 시험결과의 정량적인 판단이 이루어지지 않고 있다. 따라서 본 연구에서는 레저선박의 낙하시험을 위한 시스템 및 운용프로그램을 개발하여 플레저보트의 구조안전성의 정량적 평가가 가능한 시스템을 개발하고 다단 롤포밍 기법을 적용한 5m급 알루미늄레저보트에 적용하여 시스템의 성능을 검증하였다.

• Proceedings of the KAIS Fall Conference
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• 2011.12b
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• pp.631-634
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• 2011

항공기용 착륙장치의 완충기 충격흡수 성능은 해석 과정을 거쳐 예측한 값과 낙하시험을 수행하여 그 성능을 입증하여야 한다. 이는 미 연방 항공 규정에서 요구하고 있는 사항이다. 본 논문에서는 착륙장치 낙하시험을 위한 설비, 시험절차 및 시험방법과 낙하시험 수행 결과를 제시한다.

• Proceedings of the KAIS Fall Conference
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• 2011.12b
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• pp.635-638
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• 2011

항공기 착륙 시 발생되는 높은 충격하중에서 승무원 및 기체를 보호하기 위해 높은 충격흡수율이 요구된다. 따라서 착륙 시 발생하는 충격을 효과적으로 흡수할 수 있는 착륙장치는 항공기 핵심 구성요소이다. 다양한 종류의 완충장치가 존재하나, 소형항공기 주착륙장치에는 판스프링 방식을 이용하여 충격에너지를 흡수할 수 있다. 착륙장치의 완충 성능은 반드시 낙하시험을 통해 입증하여야 하며, 이는 미 연방 항공 규정에서 요구하고 있는 사항이다. 이 논문에서는 소형항공기 낙하시험을 위한 설비, 시험 절차 및 낙하시험 수행 결과를 제시한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.11
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• pp.1130-1135
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• 2010

The main function of a landing gear is to absorb the impact energy during touchdown. Most landing gear use an oleo-pneumatic shock absorber which essentially consists of an oil damper and a gas spring. The performance of a shock absorber can be estimated by analysis but it should be verified by drop test, which is required by MIL Spec. and FAR. In the drop test, various data such as ground loads, shock absorber pressure, stroke and mass travel are analyzed to validate the shock absorbing efficiency and the mathematical model for analysis. This paper presents the introduction of drop test facility, the test procedure and data evaluation method with real drop test example.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.8
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• pp.681-688
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• 2021

This paper considers the trajectory and impact point dispersion analysis of the test launch vehicle (TLV). The analysis, which performed before and after its flight test on November 28, 2018, is described and verified by comparing with the flight test results. The six degree-offreedom (DOF) simulation is used to compute the dispersion of the trajectory, attitude, and impact point, where the launch vehicle performance variations and wind effects during the atmospheric phase are included. The impact area to guarantee the flight safety is determined using the results of the dispersion analysis. The flight test results confirm that the safe flight of TLV is performed within the predicted dispersion boundary.

• Transactions of the Korean Society of Pressure Vessels and Piping
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• v.12 no.1
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• pp.134-140
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• 2016

The Control Rod Assembly (CRA) controls the reactor power by adjusting its position in the reactor core during normal operation and should be quickly inserted into the reactor core by free drop under scram condition to shut down chain reactions. Therefore, the drop time of the CRA is one of important factors for the safety of the nuclear reactor and must be experimentally verified. This study presents the drop performance test of the CRA which has been conceptually designed for the Proto-type Generation IV Sodium-cooled Fast Reactor. During the test, the CRA was free dropped from a height of 1 m under different flow rate conditions and its drop time was measured. The results showed that the drop time of the CRA increased as the flow rate increased; the average drop times of the CRA were approximately 1.527 seconds, 1.599 seconds and 1.676 seconds at 0%, 100% and 200% of design flow rates, respectively.

• Journal of Nuclear Fuel Cycle and Waste Technology(JNFCWT)
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• v.10 no.2
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• pp.105-115
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• 2012

Necessity of demonstration test to evaluate the structural integrity of a basket for accident conditions arose during license approval procedure for the WSPP's dry storage facility named MACSTOR/KN-400. A drop test facility for demonstration was constructed in KAERI site and demonstration tests for basket drop were conducted. As the upper welding region of a loaded basket was collided with a dropped basket during the drop test, the welding in this region was fractured and leakage happened after the drop test. The enhancement of basket design was needed since the existing basket design was not able to satisfy the performance requirement. The directions for design modification were determined and six enhanced designs were derived based on these directions. Structural analyses and specimen tests for each enhanced design were conducted. By evaluating structural analysis results and test results, one among six enhanced designs was decided as a final design for revision. The final design was the one to reduce the height of central post of a basket and to decrease the impact velocity with a dropped basket. Test basket models were fabricated with accordance with the final enhanced design. Additional demonstration test was performed for this test model and all the performance requirements were satisfied.

• Proceedings of the Korean Nuclear Society Conference
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• 2001.05a
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• pp.489-489
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• 2001

• Proceedings of the Safety Management and Science Conference
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• 2011.11a
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• pp.93-99
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• 2011

안전모는 낙하, 비례물에 대한 두부를 보호하는 보호구로 낙하물의 충격을 일부 흡수하여 완화시켜주는 기능을 하고 있다. 안전모 충격 흡수 성능으로 최고전달충격력이 있으나 낮을수록 성능이 좋은 것으로 나타나지만 안전모 제조과정에서 얼마 만큼의 충격이 흡수되는지는 알 수 없었다. 이로 인하여 성능 향상을 위한 충격력의 명확한 제어 가능한 성능 향상의 기준을 잡는데 어려움이 있었다. 본 연구에서는 충격량과 연관된 반발계수로 충격흡수 성능의 정도를 찾고자 하였다. 연구 대상은 시중에서 주로 착용되고 있는 ABS 재질의 안전인증 합격품을 대상으로 선정 하였다. 연구 방법으로는 운동량과 충격량의 이론으로 안전모 충격흡수성능 시험장치를 활용하여 인두에 전달된 충격량을 활용하여 충격흡수시의 반발계수를 구하고, 충격을 흡수치 않을 때를 가정하여 추정 충격력 곡선을 유도하고 충격흡수 전의 추정 최고 전달충격력과 반발계수를 구하여 충격흡수의 성능을 나타내었다. 연구결과 국내 안전인증 H사의 안전모의 최고전달충격력은 4100 N 이였고, 충격흡수 성능은 400 N 으로 약 9 %를 흡수되는 것으로 나타났다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.7
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• pp.601-607
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• 2012

The main function of a landing gear is to absorb the impact energy during touchdown. It it occasionally required for landing gear to have crashworthiness for improving survivability and safety in case of emergency landing. This paper introduces the design concept, performance analysis and drop test procedures for the development of the crashworthy landing gear. The shock absorbing ability and the crash behavior are proved by analyzing various sensor data and video clips from high speed camera recording during drop tests.