Discharge ignition behavior of the Space Station plasma contactor-Reference-Cited by-同舟云学术

Discharge ignition behavior of the Space Station plasma contactor

Published:1994-06-27 Issue: Volume: Page:
ISSN:
Container-title:30th Joint Propulsion Conference and Exhibit
language:
Short-container-title:

Author:

Sarver-Verhey Timothy¹,Hamley John²

Affiliation:

1. NYMA, Inc., Brook Park, OH

2. NASA, Lewis Research Center, Cleveland, OH

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1994-3311

Reference21 articles.

1. demonstrated over 11,600 ignitions. For this test program, a test profile was developed to allow accelerated cyclic testing at projected operating conditions. To datc, two HCAs have successfully demonstrated multiple ignitions at conditions similar to those expected on-orbit. A prototype HCA has achieved 3598 successful ignitions. Nominal operating conditions were 18.0 v and 8.82pa.Lls for anode voltage and xenon flow rate, respectively. The anode voltage from an initial value of 12.8V,i the ignition testing, several parameters were investigated, of which the heater power and pre-heat time were the sept,1993,

2. AIAA Paper 94-3312, June 1994,

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3. Integration testing of the Space Station Plasma contactor power electronics unit;30th Joint Propulsion Conference and Exhibit;1994-06-27