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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    Title :

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


    Contributors:

    Conference:

    AIAA Joint Propulsion Conference ; 2012 ; Atlanta, GA, United States


    Publication date :

    2012-07-11


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English