SOLID-PROPELLANT ROCKET ENGINE FOR JET PROJECTILE; METHOD OF PRODUCTION OF POLYMERIC COMPOSITE MATERIAL INSERTS FOR ROCKET ENGINE NOZZLE ASSEMBLY, MOULD FOR PRODUCTION OF POLYMERIC COMPOSITE MATERIAL INSERTS FOR ROCKET ENGINE NOZZLE ASSEMBLY

摘要

FIELD: military equipment, in particular, rocket engines for guided jet projectiles for salvo launching systems using composite solid propellant. SUBSTANCE: heat-insulating inserts of the nozzle assembly inlet and outlet cones in the rocket engine are mode of polymeric composite material based on silica glass fibre and phenolic polyamide binder with definite protected values. At manufacture of inserts for the rocket engine nozzle assembly their moulding is accomplished in three stages at protected values of pressure, temperature and time. The mould for production of inserts is made with a built-up punch and die consisting of two shells combined with a radial clearance, whose value is protected. EFFECT: facilitated procedure. 3 cl, 5 dwg, 1 tbl