DURABILITY TEST OF THE LAUNCH ENGINE CASING OF THE 9M14M ROCKET USING SIEMENS NX SOFTWARE

Abstract

The article presents a method for calculating the structural integrity of a rocket engine casing using finite element method on Siemens NX software. This software is specialized for the calculation and design of weaponry. The propulsion motor of the 9M14M guided missile was used to construct the model and calculate the casing's structural integrity under the firing load conditions. The simulation results indicate that the motor casing is ensured durability during firing. The findings obtained from this research can be used to analyze, evaluate, and select optimal structural parameters as well as manufacturing materials for solid-propellant rocket engines.