Modeling and Additive Manufacturing of a Rocket Engine Nozzle for Micro-rocket Applications

Abstract

The paper presents the process of modeling a rocket engine nozzle and the manufacturing method of a nozzle intended for use in micro-rocket propulsion systems. The proposed design–technological solution enables the fabrication of a rocket engine component with reduced mass through the application of a structure that allows optimization of the cooling process during flight. Designs incorporating conformal cooling channels make it possible to reduce weight while maintaining high performance, equal to or at least comparable with that of conventionally used designs manufactured using traditional subtractive methods. The presented solution is based on additive manufacturing technologies.