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기영중(Youngjung Kee),김승호(Seung-Ho Kim),정재권(Jae-Kwon Jung),허장욱(Jang-Wook Heo) 대한기계학회 2010 대한기계학회 춘추학술대회 Vol.2010 No.11
Helicopter rotor systems are dynamically loaded structures with many composite components such as main and tail rotor blades. Fatigue properties of composite materials are extremely important to design durable and reliable helicopter rotor blades. The safe-life methodology has been generally used in the helicopter industry to substantiate dynamically loaded composite components. However, it is not available to evaluate the strength reducing effects of flaws and defects that may occur in manufacturing and operational usage. Damage tolerance methodology provides a proper means to overcome this shortcoming, but it is difficult to economically apply it to every composite components. Flaw tolerant methodology is an equivalent option to damage tolerance for civil and military rotorcraft. The flaw tolerant safe life evaluation is described and illustrated by means of successful application to substantiate the retirement time of composite blades.
인공신경망을 이용한 머신러닝 기반의 연료펌프 고장예지 연구
최홍(Hong Choi),김태경(Tae-Kyung Kim),허경린(Gyeong-Rin Heo),최성대(Sung-Dae, Choi),허장욱(Jang-Wook Hur) 한국기계가공학회 2019 한국기계가공학회지 Vol.18 No.9
The key technology of the fourth industrial revolution is artificial intelligence and machine learning. In this study, FMEA was performed on fuel pumps used as key items in most systems to identify major failure components, and artificial neural networks were built using big data. The main failure mode of the fuel pump identified by the test was coil damage due to overheating. Based on the artificial neural network built, machine learning was conducted to predict the failure and the mean error rate was 4.9% when the number of hidden nodes in the artificial neural network was three and the temperature increased to 140 °C rapidly.
기영중(Young-Jung Kee),김승호(Seung-Ho Kim),한정호(Jeong-Ho Han),정재권(Jae-Kwon Jung),허장욱(Jang-Wook Heo) 대한기계학회 2012 대한기계학회 춘추학술대회 Vol.2012 No.2
헬리콥터 로터 시스템은 동적인 하중이 가해지는 구조물로서 복합재로 제작된 주로터 및 꼬리로터 블레이드를 포함하고 있으며, 내구성과 신뢰성이 우수한 로터 블레이드를 설계하고 제작하기 위해서는 제작에 사용된 복합소재의 피로특성을 평가하는 것이 매우 중요하다. 최근까지 안전수명 개념을 기반으로 동적인 하중이 가해지는 복합재 구성품의 피로수명을 평가해왔으나, 제작공정 중 발생 가능한 결함과 운용 중 외부물체의 충돌로 인한 강도저하 현상을 적합하게 고려할 수 없는 단점이 있다. 이와 같은 단점들은 손상허용 개념을 통해 해결할 수 있으나, 효율적이며 결제적으로 적용할 수 있는 방법이 현재까지 제시되지 못하고 있다. 내결함 개념은 손상허용 개념과 마찬가지로 결함과 손상의 영향을 고려할 수 있으며, 민수 또는 군용헬기에 대해 적용이 가능하다. 따라서 본 논문에서는 결함과 손상이 적용된 복합재 로터 블레이드에 대해 내결함 개념을 이용하여 피로시험을 수행하는 절차와 시험데이트를 이용한 피로수명 평가 방안을 제시하였다. Helicopter rotor systems are dynamically loaded structures with many composite components such as main and tail rotor blades. Fatigue properties of composite materials are extremely important to design durable and reliable helicopter rotor blades. The safe life mathodology has been generally used in the helicopter industry to substantiate dynamically loaded composite components. However, it is not available to evaluate the strength reducing effects of flaws and defects that may occur in manufacturing and operational usage. Damage tolerance methodology provides a proper means to overcome this shortcoming, but it is difficult to economically apply it to every composite components. Flaw tolerant methodology is an equivalent option to damage tolerance for civil and military rotorcraft. In this study, the flaw tolerant safe life evaluation is described and illustrated by means of successful application to substantiate the retirement time of composite rotor blades.
기영중(Young-Jung Kee),김승호(Seung-Ho Kim),한정호(Jeong-Ho Han),정재권(Jae-Kwon Jung),허장욱(Jang-Wook Heo) 대한기계학회 2012 大韓機械學會論文集A Vol.36 No.10
헬리콥터 로터 시스템은 동적인 하중이 부가되는 구조물로서 복합재료로 제작된 주로터 및 꼬리로터 블레이드를 포함하고 있으며, 복합재료의 피로특성은 내구성과 신뢰성이 우수한 로터 블레이드를 설계하고 제작하기 위해 매우 중요한 요소라 할 수 있다. 최근까지 안전수명 개념을 기반으로 동적인 하중이 부가되는 복합재 구성품의 피로수명을 평가해왔으나, 제작공정 중 발생 가능한 결함과 운용 중 외부물체의 충돌로 인한 강도저하 현상을 적합하게 고려할 수 없는 단점이 있었다. 손상허용 개념을 통해 이와 같은 단점들은 극복할 수 있으나, 현재까지 효율적이며 경제적으로 적용할 수 있는 방법이 제시되지 못하고 있다. 내결함 안전수명 개념은 손상허용 개념과 마찬가지로 결함과 손상의 영향을 고려할 수 있으며, 민수 또는 군용헬기에 대해 적용이 가능하다. 따라서 본 논문에서는 결함과 손상이 적용된 복합재 로터 블레이드에 대해 내결함 안전수명 개념을 이용하여 피로시험을 수행하는 방법과 시험데이터를 이용한 피로수명 평가 절차를 제시하였다. Helicopter rotor systems are dynamically loaded structures with many composite components such as the main and the tail rotor blades. The fatigue properties of composite materials are extremely important to design durable and reliable helicopter rotor blades. The safe-life methodology has generally been used in the helicopter industry to substantiate dynamically loaded composite components. However, it cannot be used to evaluate the strength reducing effects of flaws and defects that may occur during manufacturing and operational usage. The damage tolerance methodology provides a proper means to overcome this shortcoming; however, it is difficult to economically apply it to every composite component. The flaw tolerant methodology is an equivalent option to the damage tolerance methodology for civil and military rotorcraft. In this study, the flaw tolerant safe-life evaluation is described and illustrated by means of successful application to substantiate the retirement time of composite rotor blades.
3D프린팅 덕트를 활용한 군용 전자장비 방열 설계 및 검증
진성은(Sung-Eun Jin),이승철(Seung-Cheol Lee),김현우(Hyeon-woo Kim),이공희(Gong-Hee Lee),윤의열(Eui-Yeol Yoon),허장욱(Jang-Wook Heo) 대한기계학회 2022 대한기계학회 춘추학술대회 Vol.2022 No.11
In this study, the heat dissipation structure of the high-heat electronic equipment system was improved by using the CFD analysis technique and 3D printing duct. By arranging the power supply in a separate space, the amount of cooling air flowing into the circuit card assembly was increased, and a geometric 3D printing duct was installed to concentrate cooling air into the high-heating circuit card assembly. Afterwards, an improved prototype was manufactured and operation tests were conducted in a high-temperature environment. As a result, it was confirmed that the electronic equipment was operated stably at high temperature and that the high-heat circuit card assembly had an average high-temperature margin of 17℃ based on the allowable temperature.
3D프린팅 덕트를 활용한 군용 전자장비 방열 설계 및 검증
진성은(Sung-Eun Jin),이승철(Seung-Cheol Lee),김현우(Hyeon-woo Kim),이공희(Gong-Hee Lee),윤의열(Eui-Yeol Yoon),허장욱(Jang-Wook Heo) 대한기계학회 2022 대한기계학회 춘추학술대회 Vol.2022 No.11
In this study, the heat dissipation structure of the high-heat electronic equipment system was improved by using the CFD analysis technique and 3D printing duct. By arranging the power supply in a separate space, the amount of cooling air flowing into the circuit card assembly was increased, and a geometric 3D printing duct was installed to concentrate cooling air into the high-heating circuit card assembly. Afterwards, an improved prototype was manufactured and operation tests were conducted in a high-temperature environment. As a result, it was confirmed that the electronic equipment was operated stably at high temperature and that the high-heat circuit card assembly had an average high-temperature margin of 17℃ based on the allowable temperature.