Resumo

MALDONADO VILLA, Jorge et al. Evaluation of the thermal performance of polymer matrix composites in nozzle prototypes for low orbit rockets. Rev. Cient. Gen. José María Córdova [online]. 2014, vol.12, n.13, pp.275-290. ISSN 1900-6586.

A method of manufacturing of nozzle prototypes was consolidated for low orbit rockets, composed of two polymer (thermoset and elastoplastic) matrix zones, reinforced according to its consolidated performance: a thermal zone (TZ) with ablative properties, that was hardened by dispersion with type I or II ceramic powder, and a structural zone (EZ) with characteristics of mechanical resistance, with hybrid fiber-reinforcement and carbon, glass and slates fibers. Ablative structural strength and nozzle 12 prototypes in different configuration requirements are studied through the flight time (90 through 120 seconds), that is, differences in temperature and weight loss and thickness of the prototypes. Additionally, the performance was evaluated by simulating actual operating conditions in tensile and impact of oxy-fuel flame to determine weight loss, thickness, temperature differential and changing mechanical properties, etc., leading to find a positive behavior system. The matrix which showed the best thermal performance was the elastoplastic, hardened by dispersion with type II ceramic powder; however, the best structural performance was offered by prototype 9, which also has a polymer matrix.

Palavras-chave : Ablative material; composite materials; impact test flame; nozzles.

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