OPTIMUM NOZZLE ANGLE OF A MICRO SOLID-PROPELLANT THRUSTER

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The characteristics of supersonic flow field and thrust for a micronozzle used in a microthruster were analyzed numerically to determine the optimum nozzle geometry. Typical parameter values are 300 mu m throat diameter, 10 bar and 1000 K for stagnation conditions, and 1-100 ms for combustion completion. The effects of the boundary layer, heat loss, and unsteady stagnation conditions were considered. Thrust was much more dependent on the nozzle expansion angle than the area ratio or length. Optimum nozzle expansion angle for maximum thrust was close to 30 degrees for a planar 2D nozzle and 25 degrees for a 2D axisymmetric nozzle.
Publisher
TAYLOR FRANCIS INC
Issue Date
2011
Language
English
Article Type
Article
Keywords

SPRAY PROCESS; PERFORMANCE

Citation

NANOSCALE AND MICROSCALE THERMOPHYSICAL ENGINEERING, v.15, no.3, pp.165 - 178

ISSN
1556-7265
URI
http://hdl.handle.net/10203/93575
Appears in Collection
AE-Journal Papers(저널논문)
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