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.
Development and Testing of a Methane/Oxygen Catalytic Microtube Ignition System for Rocket Propulsion
AIAA Joint Propulsion Conference ; 2012 ; Atlanta, GA, United States
2012-07-11
Conference paper
No indication
English
Catalytic Microtube Rocket Igniter
Online Contents | 2011
Catalyzed Ignition of Using Methane-Hydrogen Fuel in a Microtube for Microthruster Applications
Online Contents | 2009
|HYDROGEN-OXYGEN FOR ROCKET PROPULSION
AIAA | 1963
|Hydrogen-oxygen for rocket propulsion.
NTRS | 1964
|