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Catalyzed Ignition of Bipropellants in MicrotubesThis paper addresses the need to understand the physics and chemistry involved in propellant combustion processes in micro-scale combustors for propulsion systems on micro-spacecraft. These spacecraft are planned to have a mass less than 50 kilograms with attitude control estimated to be in the 10 milli-Newton thrust class. These combustors are anticipated to be manufactured using Micro Electrical Mechanical Systems (MEMS) technology and are expected to have diameters approaching the quenching diameter of the propellants. Combustors of this size are expected to benefit significantly from surface catalysis processes. Miniature flame tube apparatus is chosen for this study because microtubes can be easily fabricated from known catalyst materials and their simplicity in geometry can be used in fundamental simulations to more carefully characterize the measured heat transfer and pressure losses for validation purposes. Experimentally, we investigate the role of catalytically active surfaces within 0.4 and 0.8 mm internal diameter micro-tubes, with special emphases on ignition and extinction processes in fuel rich gaseous hydrogen and gaseous oxygen. Flame thickness and reaction zone thickness calculations predict that the diameters of our test apparatus are below the quenching diameter of the propellants in sub-atmospheric tests. Temperature and pressure rises in resistively heated platinum and palladium micro-tubes are used as an indication of exothermic reactions. Specific data on mass flow versus preheat temperature required to achieve ignition are presented.
Document ID
20030022776
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Schneider, Steven J. (NASA Glenn Research Center Cleveland, OH, United States)
Boyarko, George A. (Case Western Reserve Univ. Cleveland, OH, United States)
Sung, Chih-Jen (Case Western Reserve Univ. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
February 1, 2003
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
E-13810
NAS 1.15:212206
NASA/TM-2003-212206
AIAA Paper 2003-0674
Meeting Information
Meeting: 41st Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 6, 2003
End Date: January 9, 2003
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS-22-755-04-08
Distribution Limits
Public
Copyright
Public Use Permitted.

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