Experimental investigation of the burning rate of solid propellant rocket motors

Document Type : Original Article

Authors

1 Aerospace Engineering Department, Military Technical College, Cairo, Egypt.

2 Chemical Engineering Department, Military Technical College, Cairo, Egypt.

10.1088/1742-6596/3070/1/012018

Abstract

The burning rate of solid propellant is a critical parameter influencing the performance and stability of rocket motors. This study experimentally investigates the burning rate of composite solid propellant used in dual-thrust rocket motors through both static firing tests and acoustic emission strand burner tests. A standard sub-scale 2-inch motor is employed to measure dynamic burning rate under varying combustion chamber pressure, while strand burner tests provide static burning rate measurements. The experimental results reveal a deviation between static and dynamic burning rates, attributed to erosive burning effects. Additionally, an internal ballistics prediction module (IBPM) is validated by comparing its outputs with static firing test data, demonstrating its applicability for performance prediction. The findings provide essential insights into the influence of combustion conditions on burning rate characteristics, targeting improved modelling and optimization of dual-thrust solid rocket motors (DTRMs).

Keywords

International Conference on Aerospace Sciences and Aviation Technology
Volume 21, Issue 21
21st International Conference on Aerospace Sciences & Aviation Technology, ASAT 21, 2025.
September 2025
Pages 1-11

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