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Transient Radiant Thermal Testing of Reusable Thermal Protection Systems and Insulation MaterialsA transient radiant thermal test setup used for high-temperature testing of reusable insulation material and thermal protection systems (TPS) subject to heating profiles simulating re-entry or hypersonic cruise flight conditions is described. The test setup can be used to evaluate the thermal performance of TPS and for validation of TPS thermal models. The test pressure can vary between 0.001 torr and 760 torr, and the sample hot-side temperature can vary between 20°C and 1600°C. The system is designed to have well-characterized and controlled thermal boundary conditions to enable accurate thermal testing and modeling of TPS. The thickness to planar dimensions of the test sample is selected to facilitate one-dimensional heat transfer. The test setup is described, some representative test data on a flexible alumina felt insulation is presented, and comparison of test data and thermal model predictions is provided.
Document ID
20250004276
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Kamran Daryabeigi
(Langley Research Center Hampton, United States)
Elora Kurz
(Langley Research Center Hampton, United States)
Date Acquired
April 29, 2025
Publication Date
May 1, 2025
Publication Information
Publisher: National Aeronautics and Space Administration
Subject Category
Spacecraft Design, Testing and Performance
Report/Patent Number
NASA/TM-20250004276
Funding Number(s)
WBS: 833011.02.07.89WO.25
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert
Keywords
Thermal Analysis
Thermal Protection Systems
Transient Thermal Testing
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