Saturation Effects On Stagnation Radiative Heating For The Jupiter Probe

Abstract

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.

Department(s)

Mechanical and Aerospace Engineering

International Standard Serial Number (ISSN)

0001-1452

Document Type

Article - Journal

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 2023 American Institute of Aeronautics and Astronautics, All rights reserved.

Publication Date

01 Jan 1980

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