The effect of propellant sloshing upon the stability of a liquid-propelled space vehicle has been studied extensively. For a typical space vehicle with thrust vector control and a single slosh tank, the slosh danger zone is located between the vehicle center of mass and the center of percussion. If the slosh mass is located between these two locations, baffles may be required to provide additional damping for stability. In this work, the methodology behind the classic single tank solution analytical is extended to a tandem tank configuration where the tanks are located along the vehicle centerline or symmetrically offset from the centerline. Secondly, the slosh stability boundary for a vehicle with pairs of outboard reaction jets, rather than thrust vectoring, for attitude control is studied. Finally, the impact of aerodynamics and vehicle axial acceleration on the classic danger zone solution are analyzed.


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    Title :

    Analytical Investigation of Propellant Slosh Stability Boundary on a Space Vehicle


    Contributors:
    Jing Pei (author)

    Conference:

    AIAA SciTech Forum ; 2021 ; Nashville, US


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English