PROPERTIES OF PLASMAS AS THEY PERTAIN TO THERMAL ARC-JETS

Abstract

Information is presented which will aid in selecting propellants for use in electro thermal engines. Several potential propellants were examined. These include hydrogen, ammonia, helium lithium hydride, nitrogen, methane, air, ARGON AND LITHIUM. Discussions of important propellant properties and their effect on engine performance and life are included. The effect of the propellant choice on the operation of the arc-jet is considered. This includes examining theoretical thruster efficiency, engine life and the effect of the engine's mission. Experiments were performed for eight propellants using Plasmadyne's one-kilowatt engine. The results of these tests are discussed.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1962
Accession Number
AD0292001

Entities

People

  • C. J. Chen
  • R. Greco

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Arc Jet Engines
  • Chemical Reactions
  • Electrical Conductivity
  • Energy
  • Energy Transfer
  • Heat Capacity
  • Heat Energy
  • Heat Loss
  • Heat Transfer
  • Ionization
  • Kinetic Energy
  • Latent Heat
  • Materials
  • Materials Laboratories
  • Phase Transformations
  • Test And Evaluation
  • Thermal Conductivity

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Electrochemical Engineering/ Fuel Cell Technologies
  • Theoretical Analysis.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster