Aeroassisted trajectories can be used to minimize spacecraft propellant requirements for near-Earth orbital operations. A review of spacecraft flight mechanics, aerothermodynamics, and energy balances relevant for near-term designs of reusable upper stages is presented. A reusable upper stage is modeled by a rigid tank containing liquid propellant with some propellant fraction undergoing phase change, while in an a planar aeroassist trajectory about an idealized Earth. Shortcomings of classical analyses are illustrated to motivate models with increased fidelity and complexity. A new method is proposed and models the material response of the spacecraft under aerothermal loading, that couples the simplicity of classical methods with a three-dimensional scheme that captures unsteady thermal gradients in the material. The new method is shown to provide similar solutions to a fully discrete case with a significant reduction in computational time.


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    Title :

    Unsteady Heat Transfer for Pressure Vessels in Atmospheric Flight at Orbital Velocities


    Contributors:

    Published in:

    Publication date :

    2019-07-19


    Size :

    18 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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