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dc.contributor.authorSundaresan, N K-
dc.contributor.authorAmbirajan, A-
dc.contributor.authorRamasamy, A-
dc.contributor.authorGupta, P P-
dc.contributor.authorBhandari, D R-
dc.identifier.issn0975-1041 (Online); 0019-5596 (Print)-
dc.description.abstractAblatives are very often used in the Thermal Protection System of re-entry spacecraft. Their thermal conductivity will play an important role in determining the temperatures of components and payloads during the on-orbit and re-entry phases on the mission. A series of calorimetric tests were conducted on these materials to ascertain their thermal conductivity. A description of the experiments and the results of analyses of the experimental temperature data from the ablatives are presented in this paper. Three-dimensional mathematical model of the experiment was developed and analysed. The thermal conductivity of two ablative samples is determined by manually minimising the root sum of squares error (RSSE) between experimental and numerical data. The results obtained using this technique are compared with the results of a one-dimensional analysis.en_US
dc.sourceIJPAP Vol.44(10) [October 2006]en_US
dc.subjectThermal conductivityen_US
dc.subjectAblative materialen_US
dc.subjectRe-entry spacecraften_US
dc.titleEvaluation of thermal conductivity of ablative materialen_US
Appears in Collections:IJPAP Vol.44(10) [October 2006]

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