Abstract
Development and application of solid rockets have put forward new requirements for the combustion performance of AP/HTPB propellants. Herein, carbon-supported Ti/Co bimetallic oxide (MTiCo) nanocomposites with carbon skeleton and porous structure were proposed to use as catalysts for improving the combustion performance of AP/HTPB propellants. For AP decomposition, MTiCo-2 (2.0 wt%) reduced the AP HD temperature by 93.1 °C and enhanced heat release by about 356.3 %. Simultaneously, MTiCo-2 (2.0 wt%) significantly decreased Ea of AP HD stage by 51.4 %. MTiCo-2 (2.0 wt%) also reduced the ignition delay of AP/HTPB propellant by 78.3 % and enhanced combustion rate by 192.0 %. The synergistic effect of catalysis and combustion support of MTiCo-2 provided by the structure of carbon-supported Ti/Co bimetallic oxide was the main mechanism for improving the combustion performance of AP/HTPB propellants.
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