Saturation Effects On Stagnation Radiative Heating For The Jupiter Probe
The equations for nonequilibrium radiation transport in the stagnation ablation layer for conditions typical of entry of spacecraft into the atmosphere of a major planet are developed. The equations are simplified and shown to contain two parameters which are used to classify the radiation transfer as equilibrium or nonequilibrium. The parameter ω represents the ratio of the radiative de-excitation rate to the sum of the radiative de-excitation rate plus the collisional excitation rate. The second parameter is ω′ and it represents the ratio of the radiative excitation rate, due to external radiation, to the sum of the radiative de-excitation rate plus the collisional excitation rate. Both parameters vary between zero and unity. It is shown that the population ratio of the two electronic states of a molecular band approaches its equilibrium value as ω approaches zero. When ω and ω′ are greater than zero the population ratio becomes greater than its equilibrium value. An order of magnitude analysis is undertaken for conditions expected in the shock layer near the maximum heating point in the entry trajectory of the Jupiter Probe. It shows that saturation effects are likely to occur in the ablation layer. © 1980 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
H. F. Nelson, "Saturation Effects On Stagnation Radiative Heating For The Jupiter Probe," AIAA Journal, vol. 18, no. 9, pp. 1133 - 1140, American Institute of Aeronautics and Astronautics, Jan 1980.
The definitive version is available at https://doi.org/10.2514/3.7712
Mechanical and Aerospace Engineering
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01 Jan 1980