Electrolytic Ignition System for a Millipound Thruster
Final rept. 15 Jul 1970-15 Jun 1972
UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CT
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The research had as its objective the development of an electrolytic ignition system for monopropellant-fueled millipound thrusters. The report describes the electrochemical decomposition of hydrazine-based monopropellants which was studied as a function of propellant composition and electrode materials. It was found that a 77 hydrazine-23 hydrazine azide composition yielded the highest heat output with the lowest power input provided platinum was used as an anode. Performance data was obtained on prototype engines incorporating the electrolytic ignition concept.
- Solid Propellant Rocket Engines