• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.2
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• pp.200-205
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• 2010

Heat-resistance of W/$Y_2O_3$ as throat insert material was evaluated to develop rocket motor keeping thrust uniformly under condition of high-temperature, high-pressure and long-burn time. Test was conducted with varying burn time, and test results were compared with CIT. Test showed that ablation rate was decreased according as burn time was increased, and that ablation rate of W/$Y_2O_3$ was about 55 % of CIT. Macro/micro structures of throat insert did not show a peculiar phenomenon by increased burn time. In addition, the vacuum heat treatment is effective for the prevention of crack in throat insert.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.67-71
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• 2008

Rocket nozzle components and thrusters for next-generation solid rocket with variable thrust, and small uncooled liquid rocket thrusters are required to withstand ultra-high temperature upto $2500^{\circ}C$. In this survey, the operationg environments are investigated with the suggeations of proper materials and their fabrication methods. Especially, It is suggested that Rhenium and other competative matrials are exploited to $2500^{\circ}C$ hot components, and thus needed to be developed.