System, designed for fight testing of electrical propulsion system in Space Electric Rocket Test (SERT) program, was tested at NASA Lewis Research Center in 1962 at environmental pressure of 8×10-5 mm of mercury; current, voltage, propellant flow rate, thrust, chamber pressure, and body temperatures were measured continuously; engine efficiencies (10-30%) and specific impulses (600-1400 sec) were deduced from data, but reliability of thrust measurements was poor; exhaust plume was photographed to reveal size, turning angle, and shape of wavelength regions.
1-kw arcjet-engine system-performance test
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 1 , n 3
1964
6 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
1-kw arcjet-engine system-performance test
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