Actions for Medium power hydrogen arcjet performance

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Medium power hydrogen arcjet performance

Author
Sankovic, John M.
Published
JAN 1, 1991.
Physical Description
1 electronic document
Additional Creators
Haag, Thomas W., Curran, Francis M., Bullock, S. Ray, and Sarmiento, Charles J.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
An experimental investigation was performed to evaluate hydrogen arcjet operating characteristics in the range of 1 to 4 kW. A series of nozzles were operated in modular laboratory thrusters to examine the effects of geometric parameters such as constrictor diameter and nozzle divergence angle. Each nozzle was tested over a range of current and mass flow rates to explore stability and performance. In the range of mass flow rates and power levels tested, specific impulse values between 650 and 1250 sec were obtained at efficiencies between 30 and 40 percent. The performance of the two larger half angle (20, 15 deg) nozzles was similar for each of the two constrictor diameters tested. The nozzles with the smallest half angle (10 deg) were difiicult to operate. A restrike mode of operation was identified and described. Damage in the form of melting was observed in the constrictor region of all the nozzle inserts tested. Arcjet ignition was also difficult in many tests and a glow discharge mode that prevents starting was identified.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19910021902.
Accession ID: 91N31216.
NAS 1.15:104533.
NASA-TM-104533.
E-6409.
AIAA PAPER 91-2227.
Joint Propulsion Converence; 24-27 Jun. 1991; Sacramento, CA; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15679474