An Investigation of Thermal Protection System of a Jupiter-Entry Capsule by Using Ablation

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(a)Shock layer around a Jupiter-entry vehicle with carbon ablator has been calculated, taking into account three-temperature model and nonequilibrium chemical reaction of an ablator air.(b)Nonequilibrium viscous-shock-layer calculation was performed for hypersonic H2 flow with ablation.(c)An investigation of the effect of the ablation gas for thermal protection system was performed as well as a prediction of the entry conditions. In particular, it has been elucidated that the effect of thermal nonequilibrium is stronger than what was expected.(d)Spallation particles emitted from an ablating test model mounted in a supersonic arc-heated air flow were experimentally and computationally investigated. Emission spectra resulted from the spallation particles which are CN violet band and C2 swan band can identified not only inside the shock layer of the ablator but also outside of it.(e)Experimental investigations of particle distributions were tested through a wave filter suitable for species in an ablation plume by using a high-quality CCD camera with high-speed gate.(f)For the development of an analysis of unsteady hypersonic turbulent flows around a Jupiter-entry vehicle, a new LES/RANS turbulence model has been investigated and proposed.