Electrolytic Ignition System for a Millipound Thruster
Special rept. 15 Jul-31 Dec 70 on Phase I,
UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CT
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The objective was the selection of an electrolyte and electrode materials for an electrolytic ignition system for millipound thrusters. This report describes the evaluation of electrode polarization effects, ohmic effects due to both electrolytes and electrodes, and possible catalytic effects on electrode surfaces. Electrical conductivity measurements indicate that hydrazine-based salts must be added to hydrazine in order to minimize ohmic effects and that the mixture of 77 hydrazine-23 hydrazine azide is the most promising electrolyte candidate. Polarization studies have shown that platinum or pyrolytic graphite should be the best anode material for the electrolytic cell and that AM350 or 304SS should be the best cathode material in terms of minimizing the power needs for the cell. These electrodes were also found to catalyze the propellant decomposition reaction in addition to providing simple electrolytic decomposition. This result indicates that the reaction will be self-propagating at power inputs considerably below theoretical.
- Electrical and Electronic Equipment
- Combustion and Ignition
- Liquid Propellant Rocket Engines