Arcjet component conditions through a multistart test

Conference · Thu Jan 01 04:00:00 EST 1987

OSTI ID:6184405

Curran, F M; Haag, T W

A low power, dc arcjet thruster was tested for starting reliability using hydrogen-nitrogen mixtures simulating the decomposition products of hydrazine. More than 300 starts were accumulated in phases with extended burn-in periods interlaced. A high degree of flow stabilization was built into the arcjet and the power supply incorporated both rapid current regulation and a high voltage, pulsed starting circuit. A nominal current level of 10 A was maintained throughout the test. Photomicrographs of the cathode tip showed a rapid recession to a steady-state operating geometry. A target of 300 starts was selected, as this represents significantly more than anticipated (150 to 240), in missions of 10 yr or less duration. Weighings showed no apparent mass loss. Some anode erosion was observed, particularly at the entrance to the constrictor. This was attributed to the brief period during startup the arc mode attachment point spends in the high pressure region upstream of the nozzle. Based on the results obtained, startup does not appear to be performance or life limiting for the number of starts typical of operational satellite applications.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
• OSTI ID: 6184405
• Report Number(s): N-87-20382; NASA-TM-89857; E-3525; NAS-1.15:89857; AIAA-87-1060; CONF-870558-3
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330000* -- Advanced Propulsion Systems
CURRENTS
DIRECT CURRENT
ELECTRIC CURRENTS
ELEMENTS
FUELS
HYDRAZINE
HYDROGEN FUELS
ION PROPULSION
ION THRUSTERS
NITROGEN
NITROGEN COMPOUNDS
NONMETALS
PERFORMANCE TESTING
PROPULSION
SYNTHETIC FUELS
TESTING
THRUSTERS