Development and Testing of a Methane/Oxygen Catalytic Microtube Ignition System for Rocket Propulsion | Zendy

Matthew Deans | Zendy; Steven J. Schneider | Zendy

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Development and Testing of a Methane/Oxygen Catalytic Microtube Ignition System for Rocket Propulsion

Author(s) -

Matthew Deans,

Steven J. Schneider

Publication year - 2012

Publication title -

nasa sti repository (national aeronautics and space administration)

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.2012-4133

Subject(s) - ignition system , propulsion , methane , rocket (weapon) , aerospace engineering , oxygen , liquid oxygen , catalysis , spacecraft propulsion , environmental science , nuclear engineering , astrobiology , materials science , aeronautics , petroleum engineering , automotive engineering , engineering , chemistry , physics , organic chemistry , biochemistry

This 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.

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