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Development and Testing of a Methane/Oxygen Catalytic Microtube Ignition System for Rocket PropulsionThis study sought to develop a catalytic ignition advanced torch system with a unique catalyst microtube design that could serve as a low energy alternative or redundant system for the ignition of methane and oxygen rockets. Development and testing of iterations of hardware was carried out to create a system that could operate at altitude and produce a torch. A unique design was created that initiated ignition via the catalyst and then propagated into external staged ignition. This system was able to meet the goals of operating across a range of atmospheric and altitude conditions with power inputs on the order of 20 to 30 watts with chamber pressures and mass flow rates typical of comparable ignition systems for a 100 Ibf engine.
Document ID
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Deans, Matthew C.
(Case Western Reserve Univ. Cleveland, OH, United States)
Schneider, Steven J.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 27, 2013
Publication Date
July 11, 2012
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
Meeting Information
Meeting: AIAA Joint Propulsion Conference
Location: Atlanta, GA
Country: United States
Start Date: July 30, 2012
End Date: August 1, 2012
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public Use Permitted.
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