CALCULATION OF PRINCIPAL STRUCTURAL PARAMETERS OF A PULSE JET ENGINE INTEGRATED IN MISSILE SYSTEMS

Abstract

This study addresses the question of how to determine the principal structural parameters of pulsejet engines integrated into guided missile systems, given the current lack of comprehensive domestic research on this topic. The objective of the work is to develop an analytical model capable of providing reliable estimations of key structural characteristics to support the design and manufacturing of new-generation guided rocket munitions. An analytical method was employed to formulate the model based on predefined tactical and technical requirements, including thrust, operating time, chamber pressure, propellant mass, combustion chamber configuration, and nozzle geometry. Using these inputs, the structural parameters of the pulsejet engine were calculated and subsequently compared with publicly available technical data for the pulsejet engine used on the ERINT missile. The findings demonstrate a high level of consistency between the calculated results and reference data, with only minor deviations observed in total impulse, geometric dimensions, propellant mass, and maximum chamber pressure. The results confirm that the proposed model provides a practical and reliable tool for early-stage structural estimation of pulsejet engines. The study concludes that the developed model can be effectively applied in the preliminary design and modernization of guided rocket systems currently in operational use.