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해저 배출관로 건설을 위한 토압식 쉴드TBM 커터헤드의 설계·제작 및 현장 굴진성능의 분석
배규진,장수호,박영택,최순욱,이규필,권준용,한경태,Bae, Gyu-Jin,Chang, Soo-Ho,Park, Young-Taek,Choi, Soon-Wook,Lee, Gyu-Phil,Kwon, Jun-Yong,Han, Kyoung-Tae 한국터널지하공간학회 2014 한국터널지하공간학회논문집 Vol.16 No.2
본 연구에서는 해저 배출관로 건설을 위한 직경 4.4 m 토압식 쉴드TBM을 설계 제작하였다. 압축강도가 가장 큰 구간을 대상으로 커터헤드를 설계하고 쉴드TBM의 핵심 사양을 검토하였다. 쉴드TBM의 최대 용량을 만족하기 위해서는 디스크커터의 관입깊이를 7 mm/rev 이하로 적용해야 하는 것으로 나타났다. 설계 제작된 재활용 쉴드TBM의 현장 굴진자료를 분석한 결과, 약 95%의 현장 관입깊이가 7 mm/rev이하였으며, 디스크커터와 TBM 최대 용량 이내로 굴진이 이루어졌음을 확인하였다. 또한 CSM모델에 의한 커터 작용력과 현장의 커터 작용력을 비교한 결과, CSM모델로 예측한 커터 적용력이 약 22~25% 크게 나타났으나 대체로 현장의 커터 작용력과 유사한 경향을 나타내었다. An earth pressure balanced shield TBM with the diameter of 4.4 m was designed and manufactured for a subsea discharge tunnel excavation. Its cutterhead was designed to be optimized for the strongest rock mass condition in the tunnel alignment, and then the applicability of the refurbished shield TBM was validated for its maximum capacity. Especially, the maximum cutter penetration depth for the strongest rock mass condition should be kept to be below 7 mm/rev in order to satisfy the allowable capacities of the shield TBM. From the analysis of TBM advance data, approximately 95% of field data showed the cutter penetration depth below 7 mm/rev. In addition, it was certified that the acting forces of every disc cutter, TBM thrust and torque during TBM driving were within the allowable capacities of the shield TBM and its disc cutters. When real acting forces of the disc cutters in the field were compared with those predicted by the CSM model, they showed the close relationships with each other even though the predictions by the CSM model were approximately 22~25% higher than field data.
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Accelerated Life Analysis and Endurance Verification of Electro-Mechanical Actuator
허석행(Seok Haeng Huh),이병호(Byung Ho Lee),설진운(Jin Woon Seol),백주현(Joo Hyun Baek),양명석(Myung Seok Yang),권준용(Jun Young Kwon) Korean Society for Precision Engineering 2016 한국정밀공학회지 Vol.33 No.10
Electro-Mechanical Actuator installed on the aircraft plays a key role in an aircraft’s flight control through flight control computer. Reliable prediction of the actuator is important for the aircraft. To estimate the lifetime of a product, it is necessary to test full target life. However, it is very difficult to perform it due to the long life time of actuator but short period of development time with increasing cost. Therefore, accelerated life test has been used to reduce the test time for various reasons such as reducing product’s development cycle and cost. In this paper, to predict the lifetime of the actuator, we analyzed the flight profile of aircraft and adapted the method of accelerated life test in order to accelerate failure modes that might occur under user conditions. We also set up an endurance test equipment for validating the demanded lifetime of an actuator and performed accelerated life test.
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