METHOD FOR HYBRID SHELL OF INTEGRAL ROCKET ASSISTANCE PROPELLANT OF INCLUDING COMBUSTIBLE SEPARATOR AND HYBRID SHELL OF INTEGRAL ROCKET ASSISTANCE PROPELLANT OF INCLUDING COMBUSTIBLE SEPARATOR MANUFACTURED BY THE METHOD

摘要

The present invention relates to a manufacturing method of an integrated rocket assistance propellant for an extended range munition, including a combustible separating plate, and an integrated rocket assistance propellant for an extended range munition manufactured thereby. More specifically, the manufacturing method of an integrated rocket assistance propellant for an extended range munition comprises the following steps of: manufacturing and preparing a combustible separating plate consisting nitrocellulose, pulp, resin, stabilizer, solvent and strength increasing additive; combining the combustible separating plate with a mold for a propellant, filling a propellant therein, and curing the same; and combining the cured propellant with a mold for an inhibitor again, applying an inhibitor thereto in a vacuum atmosphere and curing the same to form an integrated rocket assistance propellant. According to the present invention, compared to the conventional rocket assistance propellant, the integrated rocket assistance propellant of the present invention includes a separating plate for separating each propellent grain segment, which is made of a material with high combustion properties and mechanical strength instead of polystyrene, and thus deformation of the separating plate due to a lack of mechanical strength, residue during combustion and the like are not generated, thereby having an effect that a nozzle of a rocket assistance propellant is not blocked.