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Abstract
High-temperature-resistant engines are typically propulsion engines, such as solid-fuel rocket engines. This study focuses on the fabrication of a thermal protection base for engines operating under high-temperature and high-pressure conditions of combustible gases, with an extremely short working duration measured in seconds. The engine base, particularly at the connection point with the nozzle, endures the harshest conditions and requires robust thermal protection. Carbon fabric-reinforced composite with a phenolic resin matrix has been established as an advantageous thermal protection material due to its superior heat resistance and erosion resistance, attributed to its high coke content and the stability of the protective layer configuration. To address the requirements for designing and manufacturing the thermal protection base, the authors aim to resolve the technological challenges of fabricating a heat-resistant engine base using composite materials based on phenolic resin matrix reinforced with carbon fabric. The hot-pressing method is employed, and experiments are conducted to determine technological parameters, analyze defects, and provide recommendations for achieving optimal processing conditions to enhance product quality. The research results propose the following technological parameters for hot-pressing the thermal protection base:Pressing temperature: approximately 160°C,Pressing pressure: 25 Mpa, Pressing duration: 30 minutes will give good mechanical properties and ensure product quality.