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Design, Fabrication, and Test of a LOX/LCH4 RCS Igniter at NASAA workhorse liquid oxygen-liquid methane (LOX/LCH4) rocket igniter was recently tested at NASA Glenn Research Center s (GRC) Research Combustion Laboratory (RCL). These tests were conducted in support of the Reaction Control Engine (RCE) development task of the Propulsion and Cryogenics Advanced Development (PCAD) project. The igniter was a GRC in-house design used to evaluate the ignition processes for LOX/LCH4. The test matrix was developed to examine the flammability of LOX/LCH4 over a range of oxidizer-to-fuel mixture ratios, both in the core fuel flow and total flow. In addition, testing also examined the durability of the hardware by accumulating ignition pulses. Over the course of testing, a total of 1402 individual ignition pulses were successfully demonstrated over the range of mixture ratios. Testing was halted after the failure of the ceramic in the igniter spark plug.
Document ID
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Schneider, Steven J.
(NASA Glenn Research Center Cleveland, OH, United States)
John, Jeremy W.
(NASA Glenn Research Center Cleveland, OH, United States)
Zoeckler, Joseph G.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
November 1, 2007
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA Paper-2007-5442
Meeting Information
Meeting: 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Location: Cincinnati, OH
Country: United States
Start Date: July 8, 2007
End Date: July 11, 2007
Sponsors: American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc., American Society of Mechanical Engineers, American Society for Electrical Engineers
Distribution Limits
Work of the US Gov. Public Use Permitted.
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