Plasma Acceleration Analysis for Advanced Propulsion Engine Design.

Abstract

The report describes the work performed for the evaluation of losses in plasma jet engines and the examination of possible ways of reducing these losses. Improved space simulation was accomplished by using consumable electrodes while the study of loss mechanism focussed on the investigation of a pure magnetic nozzle. Stable operation of the jet has been found difficult to achieve in a hard vacuum without some type of an enclosure for the arc chamger. The evaporation rate of the cathode has been found to be independent of the electrode diameter while the anode consumption depends on the electrode size. Resistive losses of the consumable electrodes have important influence on thruster performance. Some progress has been made in concentrating the cathode spot. (Author Modified Abstract)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1973
Accession Number
AD0759272

Entities

People

  • Adriano C. Ducati

Tags

DTIC Thesaurus Topics

  • Abstracts
  • Diameters
  • Electrodes
  • Engines
  • Evaporation
  • Jet Engines
  • Plasma Accelerators
  • Plasma Jets
  • Simulations
  • Test And Evaluation
  • Thrusters

Readers

  • Aerospace Propulsion Engineering.
  • Electrical Engineering
  • Theoretical Analysis.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster