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Integrated Preparation and Protection Method of Propellant Grain for Solid Rocket Motors Based on Functional Sacrificial Core Model

PendingCN122077840ARealize constant temperature and continuous heatingAvoid constant heatingHeater elementsRocket engine plantsCombustion chamberAdhesive
This application relates to the field of solid rocket motor technology, and particularly to a method for integrated preparation and protection of solid rocket motor propellant grains based on a functional sacrificial core mold. The method includes: designing a high-burning-rate core mold assembly and an electrothermal heating assembly according to the propellant grain structural parameters; when the propellant grain length does not exceed a preset length threshold, the core mold is integrally formed using a mold method; otherwise, it is prepared in segments and connected via flanges; the electrothermal heating assembly is attached to the outer surface of the core mold using a high-temperature resistant adhesive, and a temperature sensor is fixed thereon, then the entire assembly is installed into the combustion chamber shell; an aluminum foil gasbag is placed inside the core mold cavity and filled with inert gas to ensure it adheres to the inner wall of the core mold; fluid propellant is injected into the cavity between the core mold and the shell through an injection port, followed by electrothermal heating to achieve isothermal curing; during storage and transportation, heating is continuously controlled to maintain the propellant grain temperature and prevent performance degradation. This method achieves integrated propellant grain forming and temperature-controlled protection, effectively improving process accuracy and storage reliability.
Owner:XIDIAN UNIV