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http://dx.doi.org/10.6108/KSPE.2017.21.6.064

Prediction of Preliminary Pogo Instability on a Space Launch Vehicle  

Lee, SangGu (Department of Mechanical and Aerospace Engineering, Seoul National University)
Sim, JiSoo (Department of Mechanical and Aerospace Engineering, Seoul National University)
Shin, SangJoon (Department of Mechanical and Aerospace Engineering, Seoul National University)
Seo, Yongjun (Department of Mechanical and Aerospace Engineering, Seoul National University)
Ann, Sungjun (Department of Mechanical and Aerospace Engineering, Seoul National University)
Song, Huiseong (Department of Mechanical and Aerospace Engineering, Seoul National University)
Kim, Youdan (Department of Mechanical and Aerospace Engineering, Seoul National University)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.21, no.6, 2017 , pp. 64-72 More about this Journal
Abstract
The longitudinal dynamic instability which can occur in the fueling process of a space launch vehicle is called pogo. It is caused by coupling between the fuselage and propulsion system and they would be formed as a closed-loop system. so that the amplitude of the response may increase or decrease. In this paper, a mathematical model which is applicable to the systematic pogo analysis of a general launch vehicle is developed for an example of space shuttle. The formulations are composed of the linearized second-order differential equation for the propulsion system, and of the pressure, weight displacement, and generalized displacement. Those are important parameters for pogo analysis, are derived through eigenvalue analysis. By the formulation suggested in this paper, it is expected that mathematical modeling method of the pogo system can be obtained and systematic pogo stability analysis for any launch vehicle will be enabled.
Keywords
Pogo Phenomenon; Pogo System Formulation; Space Shuttle;
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  • Reference
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