• Composites Research
• /
• v.12 no.2
• /
• pp.26-35
• /
• 1999

This paper presents the vibration damping characteristic of a single lap joint beam with partial dampers analyzed using the model strain energy method and the harmonic response analysis which were based on a finite element model. The two finite element analysis methods exhibited very similar results of the resonant frequency and system loss factor which were comparable to those by the theoretical analysis. Effects of the location of partial dampers and elastic moduli and thickness of their layers on the system loss factor were studied. The damping effects due to changes of modules and loss factor of the viscoelastic layer in lap joint and partial dampers were also studied. Consequently, the geometrical and material conditions at maximizing the system loss factor were suggested.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 2010.10a
• /
• pp.397-398
• /
• 2010

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2003.10a
• /
• pp.160-160
• /
• 2003

• Proceedings of the Optical Society of Korea Conference
• /
• 2007.02a
• /
• pp.173-174
• /
• 2007

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2009.10a
• /
• pp.593-594
• /
• 2009

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.12 no.1
• /
• pp.1-6
• /
• 2011

The accurate results of finite element analysis are directly related to reliability FE model which is exactly describing dynamic characteristics of target structure. So, a model updating is necessary to establish reliable FE(Finite Element) model with a lot of experience and effort using modal testing. A large structure is too difficult to obtain the dynamic characteristics owing to its weight and size. In this work, using main gun firing test, modal testing was performed to obtain dynamic characteristics of large naval vessel, which is difficult to tap the general modal testing method. The result of experiment was considered its possibility and future plans.

• Journal of Aerospace System Engineering
• /
• v.12 no.3
• /
• pp.26-37
• /
• 2018

The Korea Aerospace Research Institute has developed a 6U HiREV Nano-satellite for the observation of the earth using high resolution videos and images. Since the 6U Nano-satellite is bulky compared to the 1U/3U Nano-satellite, the first natural frequency is relatively low. Large equivalent stress and total deformation, due to structural load, can be generated. In this paper, the design of the 6U HiREV Nano-satellite is described and structure analysis, such as acceleration load analysis, modal analysis, and random vibration analysis are carried out. It is proven that the structural design of the 6U HiREV is stable. These results will be useful as reference materials for the development of additional 6U Nano-satellites, which will be applied to various future missions in KOREA.

• Proceedings of the KAIS Fall Conference
• /
• 2005.05a
• /
• pp.71-74
• /
• 2005

본 논문에서는 폐목재의 재활용을 위한 1차 파쇄기의 다음 공정인 2차 파쇄기에 대해 경계조건과 하중조건을 적응하여 유한요소법에 의한 ANSYS로 구조해석과 모달해석을 수행하여 응력(stress), 변형률(strain)을 구하고 구조적 타당성을 검토하였다. 이는 안전성을 고려한 설계의 기초 자료가 되며 고유진동수(natural frequency)를 구하여 모터의 회전을 제어함으로서 공진(resonance) 현상을 피하는데 있다.

• Proceedings of the KAIS Fall Conference
• /
• 2004.11a
• /
• pp.66-69
• /
• 2004

본 논문에서는 트레드밀의 풀리 벨트를 통해 회전하는 앞 롤러와 러닝 벨트를 통해 회전하는 뒤 롤러의 경계조건과 하중조건을 적용하여 ANSYS로 구조해석을 수행하여, 변위(displacement), 응력 (stress), 변형률(strain)을 구하여 구조적 타당성을 검토하는데 있으며, 각각의 롤러를 모달해석을 통해 고유진동수(natural frequency)를 알아보고 얻어진 데이터 값을 통해 진동 발생 요소인 모터의 회전을 제어함으로서 공진(resonance) 현상을 피하는데 있다.

• Proceedings of the KAIS Fall Conference
• /
• 2004.11a
• /
• pp.80-82
• /
• 2004

본 논문에서는 폐목재의 재활용을 위한 파쇄기의 경계조건과 하중조건을 적용하여 유한요소법에 의한 ANSYS로 구조해석과 모달해석을 수행하여 변위(displacement), 응력(stress), 변형률(strain)을 구하고 구조적 타당성을 검토하였다. 이는 안전성을 고려한 설계의 기초자료가 되며 고유진동수(natural frequency)를 구하여 모터의 회전을 제어함으로서 공진(resonance) 현상을 피하는데 있다.