Evaluation System for Ablative Material in a High-Temperature Torch

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Ablative thermal protection system (TPS) has been used to protect a vehicle from the heat load experienced during hypersonic or re-entry flights. Typical materials for ablative TPS are carbon-carbon (C/C) composites and carbon-phenolic composites, which have generally been used at working temperatures that are not very high due to surface oxidation. From a material science perspective, modification with ultra-high-temperature ceramic (UHTC) materials or coating with UHTC materials have been undertaken in an attempt to enhance the performance of ablative TPSs for high-temperature applications. As no single facility can reproduce all the aspects of the harsh environments that a vehicle would experience in hypersonic flight, a facility appropriate for the environment of interest is selectively adopted to assess TPS materials. In this study, an evaluation system for ablative material in a high-temperature torch has been developed. As part of the development, cost-effective experiments were conducted using an oxy-kerosene torch. Performance of the C/C test sample was measured, and the flowfield was diagnosed. Numerical simulation of the oxy-kerosene flowfield and the one-dimensional material response have been performed and compared with the test data.
Publisher
SPRINGER
Issue Date
2019-09
Language
English
Article Type
Article
Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, v.20, no.3, pp.620 - 635

ISSN
2093-274X
DOI
10.1007/s42405-019-00185-2
URI
http://hdl.handle.net/10203/267392
Appears in Collection
AE-Journal Papers(저널논문)
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