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Insulated Engine, 100-Pound ThrustThe design and test results of an insulated, 100-pound thrust engine capable of delivering high performance, providing long, steady state and pulse mode endurance, and maintaining a low outside surface temperature of 4000 F, are presented. Included are descriptions of the injector designs and insulation materials investigated, plus a discussion of the thermal analysis and test results. Continuous operation in excess of 29 minutes, and start capability in excess of 4900 pulses, have been demonstrated. To allow the use of available chamber materials and coating systems under insulated conditions, the major challenge to the designer was to define an injector design that would provide gas temperatures and performance of a predetermined value. The solution was the development of an unbalanced, 8-element triplet injector having an unequal fuel distribution within each element, capable of providing a specific impulse in excess of 290 pounds at reduced wall temperatures. The design consists of a columbium chamber and nozzle utilizing a silicide coating, a columbium injector, a composite insulation system of aluminum oxide
Document ID
19990047396
Acquisition Source
Jet Propulsion Laboratory
Document Type
Reprint (Version printed in journal)
Authors
Roth, N. R.
(Textron Bell Aerospace Co. Buffalo, NY United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1966
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA Paper 66-591
Meeting Information
Meeting: Propulsion Joint Specialist
Location: Colorado Springs, CO
Country: United States
Start Date: June 13, 1966
End Date: June 17, 1966
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NAS7-305
Distribution Limits
Public
Copyright
Other

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