Electrolytic Ignition System for a Millipound Thruster

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.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1972
Accession Number
AD0745993

Entities

People

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

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Chemical Reactions
  • Combustion
  • Contracts
  • Decomposition
  • Detectors
  • Electrical Conductivity
  • Electrolytic Processes
  • Fabrication
  • Ignition
  • Ignition Systems
  • Material Degradation Processes
  • Materials
  • Materials Laboratories
  • Materials Processing
  • Measurement
  • Rocket Oxidizers

Readers

  • Aerospace Propulsion Engineering.
  • Rocket Propulsion.
  • Surface Engineering/Surface Coating Technology.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster