Multi-Fidelity Modeling of Thermal Stratification and Slosh Dynamics in Cryogenic Rocket Tanks for Spacecraft Propulsion Systems

Volume 4, Issue 1, February 2026     |     PP. 1-34      |     PDF (1759 K)    |     Pub. Date: June 11, 2026
DOI: 10.54647/aa590070    17 Downloads     90 Views  

Author(s)

Godfrey Benjamin Zulu, Department of Electrical and Electronics Engineering, School of Engineering and Technology, Mulungushi University, Kabwe, Zambia
Sam Sichilalu, Department of Mechanical Engineering, School of Engineering, University of Zambia, Lusaka, Zambia
Alvin Kabemba, Department of Mechanical Engineering, School of Engineering, Mulungushi University, Kabwe, Zambia
Arpachshad Zulu, Department of Electrical and Electronics Engineering, School of Engineering, Ural Federal University, Yekaterinburg, Russia
Eunice Mfula, Department of Radiology, School of Health Sciences, Evelyn Hone College, Lusaka, Zambia

Abstract
The performance and reliability of liquid rocket propulsion systems are significantly influenced by the thermo-fluid behavior of cryogenic propellants within storage tanks. This study presents an integrated multi-physics model for analyzing the coupled effects of thermal stratification and liquid slosh dynamics under dynamic flight conditions. The thermodynamic behavior is modeled using a lumped parameter approach that divides the tank into ullage gas, stratified liquid, bulk liquid, and tank wall thermal nodes, with governing mass and energy conservation equations used to simulate heat transfer, evaporation, condensation, and self-pressurization. Slosh dynamics are represented using reduced-order mechanical analog models, including pendulum and spring–mass–damper systems. The coupling between thermal and fluid motion is modeled through time-varying ullage volume, interfacial heat transfer, and fluid mixing. The integrated model is implemented in MATLAB/Simulink, while CFD simulations are used to analyze slosh behavior and baffle performance, and rocket flight simulations evaluate the impact on vehicle performance. Results show that sloshing disrupts thermal stratification, increases ullage pressure fluctuations, and reduces Net Positive Suction Head, potentially causing turbopump cavitation. Baffle installation significantly reduces slosh amplitude and improves propulsion system stability and reliability.

Keywords
Cryogenic propellant tanks, Thermal stratification, Slosh dynamics, Ullage pressure, Rocket propulsion systems, Lumped parameter modeling, CFD simulation, MATLAB/Simulink, Propellant feed systems, Turbopump cavitation, Spacecraft propulsion, Thermo-fluid dynamics, Baffle design, Rocket stability

Cite this paper
Godfrey Benjamin Zulu, Sam Sichilalu, Alvin Kabemba, Arpachshad Zulu, Eunice Mfula, Multi-Fidelity Modeling of Thermal Stratification and Slosh Dynamics in Cryogenic Rocket Tanks for Spacecraft Propulsion Systems , SCIREA Journal of Aviation & Aerospace. Volume 4, Issue 1, February 2026 | PP. 1-34. 10.54647/aa590070

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