Preliminary Design Evaluation of Solid-Propellant Rocket Engines

Purpose. This article raises the issue of the necessity to develop methods for automated design evaluation of solid-propellant rocket engines at the early stages of missile development. Design / Method / Approach. The study is based on analytical models and empirical data derived from the development of numerous SREs by design bureaus, particularly Yuzhnoye State Design Office. It uses parametric analysis and optimization techniques, supported by statistical correction and verification against real-world motor data Findings. The article identifies critical parameters that influence solid-propellant rocket engines (SRE) efficiency and offers a computational framework for optimizing these parameters. The methodology significantly reduces the time required for preliminary assessments and allows for automated exploration of design alternatives. Theoretical Implications. This study contributes to the theoretical understanding of SRE performance modeling and optimization during conceptual design. It outlines how analytical dependencies can be constructed and refined based on engineering theory and empirical calibration. Practical Implications. The developed approach enables engineers to quickly generate and evaluate multiple engine design scenarios, improving the quality and speed of early decision-making in missile system development. Originality / Value. The work offers a practical and validated methodology for automated design evaluation of SREs, filling a gap in the early-stage engineering workflow. It is valuable to aerospace engineers, defense researchers, and developers of propulsion systems. Research Limitations / Future Research. The methodology focuses on typical SRE configurations and assumes statistical consistency across historical data. Future research may expand the models to incorporate novel materials, 3D-printed components, and adaptive control systems. Article Type. Methodological paper.