AVCOAT 5026-39 is a low density epoxy novolac resin impregnated with fiberglass in an aluminum honeycomb, a material that NASA used on the Apollo Command Module and will use on the Orion Command Module as an ablative heat shield. The process of ablation allows the material to withstand extremely high temperatures, such as those experienced during atmospheric re-entry or during operation of rocket engines, in order to protect against structural failure. The purpose of this study was to characterize the ablation and thermal properties of AVCOAT using the oxyacetylene test bed (OTB) in conjunction with an in-situ ablation and thermal sensor to measure in-depth temperatures and recession rate of the ablative during testing. This in-situ ablation and thermal sensing technique has been successfully demonstrated on carbon/carbon composites (density of 1.8 g/cc) and carbon-phenolic ablatives (density of 1.42 g/cc). This is the first time extending this sensing technique to a low density ablator, such as AVCOAT (density of 0.53 g/cc), which was provided by NASA to our research group. This sensing technique will enable a qualitative analysis when comparing the ablative performance of any two materials.
In-situ ablation and thermal sensing of avcoat 5O26-39
2014
10 Seiten, Bilder, Tabellen, 5 Quellen
(nicht paginiert)
Aufsatz (Konferenz)
Datenträger
Englisch
MODELING OF THE CRACK GROWTH IN THE AVCOAT HEAT SHIELD
British Library Conference Proceedings | 2011
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