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Radiative properties of advanced spacecraft heat shield materialsExperimental results are presented to show the effects of simulated reentry exposure by convective heating and by radiant heating on spectral and total emittance of statically oxidized Inconel 617 and Haynes HS188 superalloys to 1260 K and a silicide coatea (R512E) columbium 752 alloy to 1590 K. Convective heating exposures were conducted in a supersonic arc plasma wind tunnel using a wedge-shaped specimen configuration. Radiant tests were conducted at a pressure of .003 atmospheres of dry air at a flow velocity of several meters per second. Convective heating specimens were subjected to 8, 20, and 38 15-min heating cycles, and radiant heating specimens were tested for 10, 20, 50, and 100 30-min heating cycles. Changes in radiative properties are explained in terms of changes in composition resulting from simulated reentry tests. The methods used to evaluate morphological, compositional and crystallographic changes include: Auger electron spectroscopy; scanning electron microscopy; X-ray diffraction analysis; and electron microprobe analysis.
Document ID
19840003190
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Cunnington, G. R. (Lockheed Missiles and Space Co. Palo Alto, CA, United States)
Funai, A. I. (Lockheed Missiles and Space Co. Palo Alto, CA, United States)
Mcnab, T. K. (Lockheed Missiles and Space Co. Palo Alto, CA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1983
Publication Information
Publisher: NASA
Subject Category
Metallic Materials
Report/Patent Number
NASA-CR-3740
NAS 1.26:3740
Accession Number
84N11258
Funding Number(s)
CONTRACT_GRANT: NAS1-16423
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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