MATEC Web Conf.
Volume 153, 2018The 4th International Conference on Mechatronics and Mechanical Engineering (ICMME 2017)
|Number of page(s)||5|
|Section||Power Machinery and Transmission|
|Published online||26 February 2018|
Parameters Affecting the Erosive Burning of Solid Rocket Motor
Beihang University (BUAA), Aerospace Department, 100191 Beijing, China
2 Militery Technical College (MTC), Rocket Department, Cairo, Egypt
Increasing the velocity of gases inside solid rocket motors with low port-to-throat area ratios, leading to increased occurrence and severity of burning rate augmentation due to flow of propellant products across burning propellant surfaces (erosive burning), erosive burning of high energy composite propellant was investigated to supply rocket motor design criteria and to supplement knowledge of combustion phenomena, pressure, burning rate and high velocity of gases all of these are parameters affect on erosive burning. Investigate the phenomena of the erosive burning by using the 2’inch rocket motor and modified one. Different tests applied to fulfil all the parameters that calculated out from the experiments and by studying the pressure time curve and erosive burning phenomena.
© The Authors, published by EDP Sciences, 2018
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (http://creativecommons.org/licenses/by/4.0/).
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