MENUFACTURING METHOD OF INTEGRAL NOZZLE FOR ROCKET MOTOR WITH INTEGRALLY MOLDED NOZZLE INSULATION AND INTEGRAL NOZZLE FOR ROCKET MOTOR MENUFACTURED BY THEREOF

摘要

The present invention relates to a method for manufacturing an integrated nozzle for a rocket propulsion engine in which a nozzle heat-resistant material including a phenol compound material is integrally molded, and to an integrated nozzle manufactured thereby. More specifically, the method comprises: a raw material mixing step of mixing a raw material of a nozzle heat-resistant material including 20 to 25 wt% of a phenol resin, 10 to 30 wt% of a glass fiber, 2 to 5 wt% of graphite powder, 10 to 15 wt% of mica, 15 to 8 wt% of silicon carbide, and 15 to 10 wt% of a hardening agent; a mold preparation step of preparing a mold by preheating the mold at a predetermined temperature; a step of arranging a nozzle outer cover in a molding space of the preheated mold, and inputting the mixture in a predetermined amount; an integral nozzle molding step of integrally forming a nozzle heat-resistant material on the outer surface of the nozzle outer cover by applying heat and pressure to the mold; and a removing step of removing the molded integrated nozzle from the mold. The method of the present invention can manufacture a nozzle having a simple manufacturing process, inexpensive costs, and excellent heat resistance and mechanical strength compared to a general composite material-type nozzle material in a conventional solid rocket propulsion engine.