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Lower power dc arcjet operations with hydrogen hydrogen/nitrogen propellant mixtures

Author
Nakanishi, S.
Published
Jan 1, 1986.
Physical Description
1 electronic document
Additional Creators
Curran, F. M.
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
The arcjet assembly from a flight model system was modified with a new thoriated tungsten nozzle insert and has been tested with hydrogen-nitrogen mixtures simulating the decomposition products of ammonia and hydrazine. Arcjet power consumption ranged from 0.7 to 1.15 kW depending on low rate, input current, and mixture composition. At a nominal 1 kW power level the ammonia mixtures thrust efficiency was about 0.31 at specific impulse values ranging between 460 and 500 sec. Hydrazine mixtures gave similar thrust efficiencies at the same power level with specific impulse values between 395 and 430 sec. Large, spontaneous voltage mode changes were not observed once the thruster had passed a period of instability immediately following start up. This period of instability, and the startup at low pressure, were seen as major causes of constrictor damage during the tests.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19860015935.
Accession ID: 86N25407.
E-2982.
NASA-TM-87279.
NAS 1.15:87279.
Joint Propulsion Conference; 16-18 Jun. 1986; Huntsville, AL; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15702574