Abstract: This study describes designing process of rocket engine with thrust 25 N for system of orientation and starting of spacecraft instead of prototype with defect of burnout chamber which was not fixed during of development tests. The new version of the engine has been designed and additional research with CFD-modeling has been performed to completely exclude burnout possibility.
Vasiliy Zubanov, Vitaliy Egorychev and Leonid Shabliy, 2014. Hydrogen-Oxygen Rocket Engine Design Using CFD-Modeling. Research Journal of Applied Sciences, 9: 660-663.