Publication Date:
2019-07-13
Description:
The effect of nozzle configuration on the operating characteristics of a low power dc arcjet thruster was determined. A conical nozzle with a 30 deg converging angle, a 20 deg diverging angle, and an area ratio of 225 served as the baseline case. Variations on the geometry included bell-shaped contours both up and downstream, and a downstream trumpet-shaped contour. The nozzles were operated over a range of specific power near that anticipated for on-orbit operation. Mass flow rate, thrust, current, and voltage were monitored to provide accurate comparisons between nozzles. The upstream contour was found to have minimal effect on arcjet operation. It was determined that the contour of the divergent section of the nozzle, that serves as the anode, was very important in determining the location of arc attachment, and thus had a significant impact on arcjet performance. The conical nozzle was judged to have the optimal current/voltage characteristics and produced the best performance of the nozzles tested.
Keywords:
SPACECRAFT PROPULSION AND POWER
Type:
NASA-TM-102050
,
E-4802
,
NAS 1.15:102050
,
1989 JANNAF Propulsion Meeting; May 23, 1989 - May 25, 1989; Cleveland OH; United States
Format:
application/pdf
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