International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Structural Dynamic Analysis of a Space Launch Vehicle using an Axisymmetric Two-dimensional Shell Element

  • Sim, JiSoo (Korea Aerospace Industries, LTD.) ;
  • Lee, SangGu (Department of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Kim, JunBeom (Republic of Korea Air Force) ;
  • Shin, SangJoon (Department of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Park, SeungSoo (Department of Mechanical Engineering, Yonsei University) ;
  • Ohm, WonSuk (Department of Mechanical Engineering, Yonsei University)
  • Received : 2017.05.12
  • Accepted : 2017.09.18
  • Published : 2017.09.30
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Abstract

The pogo phenomenon refers to a type of multidiscipline-related instability found in space launch vehicles. It is caused by coupling between the fuselage structure and other structural propulsion components. To predict the pogo phenomenon, it is essential to undertake adequate structural modeling and to understand the characteristics of the feedlines and the propulsion system. To do this, a modal analysis is conducted using axisymmetric two-dimensional shell elements. The analysis is validated using examples of existing launch vehicles. Other applications and further plans for pogo analyses are suggested. In addition, research on the pogo phenomenon of Saturn V and the space shuttle is conducted in order to constitute a pogo stability analysis using the results of the present modal analysis.

Keywords

Acknowledgement

Supported by : National Research Foundation of Korea (NRF)

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