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Integrated one-dimensional dynamic analysis methodology for space launch vehicles reflecting liquid components

Published online by Cambridge University Press:  11 July 2017

J.B. Kim ,
J.S. Sim ,
S.G. Lee ,
S.J. Shin ,
J.H. Park  and
Y. Kim
J.B. Kim
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
J.S. Sim*
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
S.G. Lee
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
S.J. Shin
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
J.H. Park
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
Y. Kim
Affiliation:
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul, Republic of Korea
*
[email protected]
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Abstract

In this paper, structural modelling and dynamic analysis methods reflecting the characteristics of a liquid propellant were developed for a pogo analysis. The pogo phenomenon results from the complex interaction between the vehicle structural vibration in the longitudinal direction and the propulsion system. Thus, for an accurate vibration analysis of a liquid propellant launch vehicle, both the consumption of the liquid propellant and the change in the stiffness reflecting the nonlinear hydroelastic effect were simultaneously considered. A complete vehicle structure, including the liquid propellant tanks, was analytically modelled while focusing on pogo. In addition, a feasible liquid propellant tank modelling method was established to obtain an one-dimensional complete vehicle model. With these methods, comparative studies of the hydroelastic effect were conducted. Evaluations of the dynamic analysis of a reference vehicle were also conducted during the first burning stage. The numerical results obtained with the present orthotropic model and the dynamic analysis method were found to be in good agreement with the natural vibration characteristics according to previous analyses and experiments. Additionally, the reference vehicle showed the estimated occurrence of pogo in the first structural mode when compared with the frequencies of the propellant feeding system. In conclusion, the present structural modelling and modal analysis procedures can be effectively used to analyse dynamic characteristics of liquid propellant launch vehicles. These techniques are also capable of identifying the occurrence of pogo and providing design criteria related to pogo instability.

Keywords

Rocket enginesspacestructural dynamicslaunch vehiclesstructural dynamicspogohydroelasticliquid propellantspring-masslongitudinal responseSaturn Vfluid structure interactionliquid propulsion
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1243 , September 2017 , pp. 1217 - 1238
Copyright
Copyright © Royal Aeronautical Society 2017 

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