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Minimize Propellant Slosh During Moon Landing

Hamming, Maarten (2024) Minimize Propellant Slosh During Moon Landing. Bachelor's Thesis, Mathematics.


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This research delves into the intricate dynamics of propellant sloshing during spacecraft lunar landing manoeuvres, aiming to minimize its effects through various approaches. Using the ComFLOW software, the study examines the impact of different fuel tank shapes, fuel types, and landing manoeuvre strategies. Investigation through comparing cylindrical and spherical fuel containers shows negligible differences, but the ellipsoidal design exhibits reduced slosh-induced forces. The research also explores the effects of using different propellant types with varying physical properties. Lower density fuels, such as liquid hydrogen, results in lower average and peak forces compared to denser fluids like RP-1, and ethanol. Additionally, alternative landing maneuver strategies are evaluated, focusing on timing and coordination. Simultaneous rotation and deceleration with extended rotation duration shows promise in minimizing slosh-induced disturbances. The findings underscore the importance of fuel tank design, fuel type selection, and maneuver coordination in optimizing spacecraft stability during critical landing phases.

Item Type: Thesis (Bachelor's Thesis)
Supervisor name: Luppes, R. and Sterk, A.E.
Degree programme: Mathematics
Thesis type: Bachelor's Thesis
Language: English
Date Deposited: 10 May 2024 11:41
Last Modified: 10 May 2024 11:41

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