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Conceptual design and performancenumerical modeling of hybrid propulsion motor

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3 Author(s)
Tahmasebi, E.A. ; Aerosp. Eng. Dept., K.N. Toosi Univ. of Technol., Tehran, Iran ; Karimi, H. ; Ebrahimi, R.

Conceptual design algorithm of hybrid rocket motor with solid fuel and liquid oxidizer is investigated in this study. Hybrid chemical rocket propulsion is presently of interest due to reduced system complexity compared to classical chemical propulsion systems. A computational code for conceptual design and performance modeling of hybrid propulsion motor developed. Results are validating with experimental test results.

Published in:

Recent Advances in Space Technologies, 2009. RAST '09. 4th International Conference on

Date of Conference:

11-13 June 2009