EFFECT OF UNSTEADINESS AND NOZZLE ASYMMETRY ON THRUST OF A MICROTHRUSTER

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Due to the small size and short propulsion pulses of solid propellant microthrusters, unsteady characteristics and/or fabrication errors may cause appreciable effects on the total thrust. The present work simulates a 2D planar and conical nozzle of 200 mu m throat diameter using the traditional momentum equations and turbulence closure model. Unsteady characteristics were found to be insensitive to the inlet mass flux but sensitive to the chamber size. The characteristic time of transient momentum variations in the nozzle was found to be on the order of 0.1 ms, and that for decay was smaller than that for development by about 25%. This work confirmed that the magnitude of thrust was not sensitive to distortions in the nozzle geometry. A mismatch of the nozzle throat changed the position of sonic plane, but its effect on thrust was almost negligible.
Publisher
TAYLOR & FRANCIS INC
Issue Date
2012
Language
English
Article Type
Article
Keywords

SPRAY PROCESS; DESIGN

Citation

NANOSCALE AND MICROSCALE THERMOPHYSICAL ENGINEERING, v.16, no.1, pp.50 - 63

ISSN
1556-7265
DOI
10.1080/15567265.2011.645997
URI
http://hdl.handle.net/10203/101723
Appears in Collection
AE-Journal Papers(저널논문)
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