The RAE 10 cm Hollow Cathode Mercury Thruster.

Abstract

The performance of the RAE 10 cm electron bombardment mercury ion engine is discussed. Results are given which show how, at 80% utilisation efficiency, the discharge losses are reduced from 540 eV/ion to 260 eV/ion by increasing the grid open area ratio from 50% to 75%. The effect of mass flow rate and magnetic field strength on performance is also shown. Thermal time constants and the effect of hollow cathode flow rate on discharge potential are given and their implications are discussed in connection with engine control. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1971
Accession Number
AD0734316

Entities

People

  • B. P. Day
  • R. Hastings

Organizations

  • Royal Aircraft Establishment

Tags

DTIC Thesaurus Topics

  • Efficiency
  • Electric Vehicles
  • Electrons
  • Engines
  • Flow
  • Flow Rate
  • Ion Engines
  • Magnetic Fields
  • Mass
  • Mass Flow
  • Thrusters

Readers

  • Plasma Physics.
  • Systems Analysis and Design

Technology Areas

  • Microelectronics
  • Space
  • Space - Hall-Effect Thruster