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
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;
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
DOI :
10.1109/RAST.2009.5158198
