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.
| Original language | English |
|---|---|
| Pages (from-to) | 485-497 |
| Number of pages | 13 |
| Journal | International Journal of Aeronautical and Space Sciences |
| Volume | 18 |
| Issue number | 3 |
| DOIs | |
| Publication status | Published - 2017 Sept |
Bibliographical note
Funding Information:This work was supported by the Advanced Research Center Program (NRF-2013R1A5A1073861) through a grant from the National Research Foundation of Korea (NRF) funded by the Korean government (MSIP) through a contract with the Advanced Space Propulsion Research Center at Seoul National University.
Publisher Copyright:
© The Korean Society for Aeronautical & Space Sciences.
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering
- Materials Science(all)
- Aerospace Engineering
- Electrical and Electronic Engineering