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High temperature oxidation-resistant thruster researchA program was conducted for NASA-LeRC by Aerojet Propulsion Division to establish the technology base for a new class of long-life, high-performance, radiation-cooled bipropellant thrusters capable of operation at temperatures over 2200 C (4000 F). The results of a systematic, multi-year program are described starting with the preliminary screening tests which lead to the final material selection. Life greater than 15 hours was demonstrated on a workhorse iridium-lined rhenium chamber at chamber temperatures between 2000 and 2300 C (3700 and 4200 F). The chamber was fabricated by the Chemical Vapor Deposition at Ultramet. The program culminated in the design, fabrication, and hot-fire test of an NTO/MMH 22-N (5-lbF) class thruster containing a thin wall iridium-lined rhenium thrust chamber with a 150:1 area ratio nozzle. A specific impulse of 310 seconds was measured and front-end thermal management was achieved for steady state and several pulsing duty cycles. The resulting design represents a 20 second specific impulse improvement over conventional designs in which the use of disilicide coated columbium chambers limit operation to 1300 C (2400 F).
Document ID
19910006750
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Wooten, John R. (Aerojet TechSystems Co. Sacramento, CA, United States)
Lansaw, P. Tina (Aerojet TechSystems Co. Sacramento, CA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-185233
AD-A231532
NAS 1.26:185233
Accession Number
91N16063
Funding Number(s)
CONTRACT_GRANT: NAS3-24643
PROJECT: RTOP 506-42-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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