Flame Deflector Ablation Analysis based on Artemis 1 Launch Environment

William M Dziedzic

NASA NTRS · 20230007918

Flame Deflector Ablation Analysis based on Artemis 1 Launch Environment

Abstract

This paper presents the updated ablative analysis methods used to determine Artemis 1 launch load environment on the flame deflector for the design based on Artemis I Assessments. The flame trench under Pad 39B at Kennedy Space Center contains a flame deflector to safely divert the exhaust plume from the SLS rocket during launch. During launch of Artemis I the refurbished flame trench and the new flame deflector experienced peak temperatures of over 2,000 degrees Fahrenheit (over 1,000 degrees Celsius) for several seconds. These extreme conditions caused ablation (material removal) from the steel plates. This paper contains flame deflector heat flux values for design based on Artemis I assessment. Post flight images of the flame deflector are shown along with “Pre vs Post” Flame Deflector scan image to measure the post flight deviations. Using COMSOL, a method to calculate a heat flux value due to measured deviations in the deflector plates caused by ablation is shown.

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William M Dziedzic. Flame Deflector Ablation Analysis based on Artemis 1 Launch Environment. https://ntrs.nasa.gov/citations/20230007918

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