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http://dx.doi.org/10.6108/KSPE.2017.21.6.001

Performance Prediction and Analysis of a MEMS Solid Propellant Thruster  

Jung, Juyeong (ICT-Railroad Convergence Research Team, Korea Railroad Research Institute)
Lee, Jongkwang (Department of Mechanical Engineering, Hanbat National University)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.21, no.6, 2017 , pp. 1-7 More about this Journal
Abstract
The performance of a MEMS solid propellant thruster was predicted and analyzed through internal ballistics model and CFD analysis. The nozzle throat was $416{\mu}m$, and the area ratio of the nozzle was 1.85. As a result of the internal ballistics model, chamber pressure increased up to 197 bar and the maximum thrust was 3,836 mN. In CFD analysis, the chamber pressure of the internal ballistics model was applied as the operating pressure, and the CFD model was divided into an adiabatic and a heat loss model. As a result, the maximum thrust of the adiabatic model was 14.92% lower than that of the internal ballistics model, and the effect of heat loss was insignificant.
Keywords
Micro Thruster; Micro Nozzle; MEMS; CFD; Micro Satellite;
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