Accession Number:

AD0745993

Title:

Electrolytic Ignition System for a Millipound Thruster

Descriptive Note:

Final rept. 15 Jul 1970-15 Jun 1972

Corporate Author:

UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CT

Personal Author(s):

• Brown, Charles T.
• McMahon, D. G.
• Russell, S.
• Fondrk, T.
• Reed, I.

Report Date:

1972-06-01

Pagination or Media Count:

190.0

Abstract:

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.

Descriptors:

• *HYDRAZINES
• *ELECTROLYSIS
• *IGNITION SYSTEMS
• *HYDRAZINE DERIVATIVES
• *ATTITUDE CONTROL SYSTEMS
• ELECTROLYTES
• SALTS
• ELECTROLYTIC CELLS
• MONOPROPELLANTS
• ELECTRODES
• ELECTRICAL CONDUCTIVITY
• ELECTROCHEMISTRY
• PRODUCTION
• POLARIZATION
• LIQUID PROPELLANT ROCKET ENGINES

Subject Categories:

• Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE