تلخیص
The advent of MEMS has shifted the trend from
bulkier satellites to pico or nano satellites, owing to their low
manufacturing and launch cost. This project involves the
numerical modeling (CFD), simulation and performance
prediction of proposed micro-resistojet thruster configuration.
After the validation of our numerical CFD methods and results
with available numerical and experimental data, a parametric
study has been conducted. The effects of change of mass flow
rate of the working fluid (N2
gas in this case) and the heater
temperature on Thrust; Specific Impulse (Isp) and viscous
subsonic layer thickness has also been investigated. It has been
developed that optimum results are found for mass flow rate of
1.2 mg/s and at heater temperature of 500oC.
Syed Sheraz Ali, Dr. Nauman Qureshi, Captain Dr. Shafiq ur Rehman. (2017) Performance Prediction of Mems Based Resistojet Thruster Through CFD, Journal of Space Technology , Volume 7, Issue 1.
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