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Combustion interaction with radiation-cooled chambersOver 15 hours of thruster operation at temperatures between 1916 and 2246 C without failure or erosion has been demonstrated using iridium-coated rhenium chamber materials with nitrogen tetroxide/monomethylhydrazine propellants operating over a mixture ratio range of 1.60-2.05. Research is now under way to provide a basic understanding of the mechanisms which make high-temperature operation possible and to extend the capability to a wider range of conditions, including other propellant combinations and chamber materials. Techniques have been demonstrated for studying surface fracture phenomena. These include surface Raman and Auger for study of oxide formation, surface Raman and X-ray diffraction to determine the oxide phase, Auger to study oxide stoichiometry, and sputter Auger to study interdiffusion of alloy species.
Document ID
19900054975
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rosenberg, S. D.
(Aerojet Technical Systems Co. Sacramento, CA, United States)
Jassowski, D. M.
(Aerojet TechSystems Sacramento, CA, United States)
Barlow, R.
(Aerojet Technical Systems Co. Sacramento, CA, United States)
Lucht, R.
(Aerojet Technical Systems Co. Sacramento, CA, United States)
Mccarty, K.
(Sandia National Laboratories Livermore, CA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2121
Accession Number
90A42030
Funding Number(s)
CONTRACT_GRANT: NAS3-25646
Distribution Limits
Public
Copyright
Other

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