Numerical Investigation and Dynamic Modelling of Sloshing in a Liquid Propellant Launch Vehicle

Date

2025-8-27

Author

Kalipcilar, Alp

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The complex dynamics of propellant sloshing in liquid propellant rocket engine tanks significantly affect the stability, control, and structural integrity of launch vehicles. To analyze and estimate the effects of lateral sloshing on a system, this thesis presents a dynamic model methodology for use in the early design phase. An experiment was conducted to validate the analytical approach, linear potential theory, which forms the basis of the dynamic model. Consistent results were obtained by comparing the natural frequency from the experiment with the analytical solution. A numerical approach using FLOW-3D was employed to analyze various parameters and validate the dynamic model. The comparison of slosh-induced lateral forces and moments shows that the dynamic model aligns well with the numerical results. The dynamic model was linked to a 3-DOF rocket dynamics model to study the effects of aerodynamic coefficients. It was found that sloshing forces and moments increased with higher lift coefficients and lower drag coefficients. The moment coefficient was analyzed in terms of amplitude and frequency, considering it as oscillatory. An increase in the moment coefficient amplitude led to greater sloshing effects. Additionally, the analysis of the moment frequency showed that sloshing intensified as the natural frequency approached. The critical case was examined with and without baffles.

Subject Keywords

Liquid Propellant Rocket Engine, Sloshing Dynamics, Equivalent Mechanical Model, Numerical Approach, Experimental Methods

URI

https://hdl.handle.net/11511/116048

Collections

Graduate School of Natural and Applied Sciences, Thesis