DocumentCode
2433523
Title
Conceptual design and performancenumerical modeling of hybrid propulsion motor
Author
Tahmasebi, Ehsan A. ; Karimi, H. ; Ebrahimi, R.
Author_Institution
Aerosp. Eng. Dept., K.N. Toosi Univ. of Technol., Tehran, Iran
fYear
2009
fDate
11-13 June 2009
Firstpage
204
Lastpage
208
Abstract
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.
Keywords
aerospace propulsion; numerical analysis; rocket engines; chemical propulsion systems; hybrid chemical rocket propulsion; hybrid propulsion motor; hybrid rocket motor; liquid oxidizer; numerical modeling; solid fuel; Chemical technology; Combustion; Costs; Fuels; Propellants; Propulsion; Rockets; Safety; Solids; Temperature; conceptual design; experimental test; hybrid propulsion; liquid oxidizer; numerical modeling; solid fuel;
fLanguage
English
Publisher
ieee
Conference_Titel
Recent Advances in Space Technologies, 2009. RAST '09. 4th International Conference on
Conference_Location
Istanbul
Print_ISBN
978-1-4244-3627-9
Electronic_ISBN
978-1-4244-3628-6
Type
conf
DOI
10.1109/RAST.2009.5158198
Filename
5158198
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