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.