Investigation of Dual-Thrust Rocket Motor with Sonic Flow through an Intermediate Nozzle | ||||
International Conference on Aerospace Sciences and Aviation Technology | ||||
Article 17, Volume 16, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015, May 2015, Page 1-14 PDF (754.32 K) | ||||
Document Type: Original Article | ||||
DOI: 10.21608/asat.2015.22903 | ||||
View on SCiNiTO | ||||
Authors | ||||
Amr M. El-Nady1; Ahmed M. Sarhan2; Mohamed A. Al-Sanabawy1; Mahmoud Y. Mohamed1 | ||||
1Egyptian Armed Forces. | ||||
2Modern Academy at Maadi, Cairo, Egypt. | ||||
Abstract | ||||
The Dual-Thrust Rocket Motors (DTRMs) are the most widely used solid propulsion system for anti-tank guided missiles. DTRM with intermediate nozzle is a special type of this system. Depending on the internal conditions, the flow through the intermediate nozzle can be sonic, subsonic or reversed. The objective of this paper is to understand the internal ballistics (IB) and phenomena of DTRM with sonic intermediate nozzle. In this study, a mathematical model describing the performance of this DTRM is derived from the main governing equations of internal ballistics. Also, a set of experiments is conducted using a developed test motor to inspect the physics of DTRM with sonic intermediate nozzle and assess the mathematical model validity. Results of the mathematical model have shown a good agreement compared with those from the experimental studies. | ||||
Keywords | ||||
Internal Ballistics; Solid propulsion; Dual Thrust Rocket Motor; Test Rocket Motor | ||||
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