The design and technology development for A 150 mlb resistojet for H2 or NH3A 150 mlb thrust level hybrid resistojet which may operate on either H2 or NH3 is described whose design technique allows temperature distribution forecasting by means of a microcomputer-implemented mathematical model. The longer computer run times that accompany the exclusive use of BASIC, relative to assembled languages, are offset by the flexibility offered and the reduction of reprogramming and debugging efforts. The integration of a compact first-stage coiled heater with a concentric tubular gas heater offers direct matching of the 28 V terminal of the spacecraft system, while keeping maximum heater wall temperatures to less than 60 K over that of the gas temperature at the throat. Among the novel materials employed are grain-stabilized rhenium for heating elements and high purity aluminas for insulators.
Document ID
19830031288
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Page, R. J. (Page (R. J.) Co. Santa Ana, CA, United States)
Stoner, W. A. (R. J. Page Co. Santa Ana, CA, United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1982
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-1949
Meeting Information
Meeting: Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference