Computer Design Technology of the Small Thrust Rocket Engines Using CAE / CAD Systems

Abstract

The paper presents an algorithm for designing liquid small thrust rocket engine, the process of which consists of five aggregated stages with feedback. Three stages of the algorithm provide engineering support for design, and two stages - the actual engine design. A distinctive feature of the proposed approach is a deep study of the main technical solutions at the stage of engineering analysis and interaction with the created knowledge (data) base, which accelerates the process and provides enhanced design quality. The using multifunctional graphic package Siemens NX allows to obtain the final product –rocket engine and a set of design documentation in a fairly short time; the engine design does not require a long experimental development.