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Advanced liquid rocketsA program to substitute iridium coated rhenium for silicide coated niobium in thrust chamber fabrications is reviewed. The life limiting phenomena in each of these material systems is also reviewed. Coating cracking and spalling is not a problem with iridium-coated rhenium as in silicide-coated niobium. Use of the new material system enables an 800 K increase in thruster operating temperature from around 1700 K for niobium to 2500 K for rhenium. Specific impulse iridium-coated rhenium rockets is nominally 20 seconds higher than comparable niobium rockets in the 22 N class and nominally 10 seconds higher in the 440 N class.
Document ID
19920015317
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schneider, Steven J. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
E-6976
NAS 1.15:105633
NASA-TM-105633
Report Number: E-6976
Report Number: NAS 1.15:105633
Report Number: NASA-TM-105633
Meeting Information
Meeting: JANNAF Propulsion Meeting
Location: Indianapolis, IN
Country: United States
Start Date: February 24, 1992
End Date: February 27, 1992
Accession Number
92N24560
Funding Number(s)
PROJECT: RTOP 506-42-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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