Investigation of Pulsed Performance of an Electrothermal Hydrazine Thruster, Using a Special See-Through Thruster.

Abstract

A special see-through thruster was developed to investigate the pulse performance of a prototype 0.2N electrothermal hydrazine thruster (EHT), designed for spacecraft attitude control applications. Results from tests were recorded by high-speed cine photography, synchronized with analogue data records. These showed that the poor response of a prototype EHT was related mainly to the injection and vaporization characteristics of the propellant in the thrust chamber. Various phenomena are described and an indication is given to the interaction between these events during repeated pulsed operation. Conclusions are reached regarding design changes necessary to improve performance. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1983
Accession Number
ADA137408

Entities

People

  • S. P. Field
  • W. G. Grenham

Organizations

  • Royal Aircraft Establishment

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Boiling
  • Boiling Point
  • Chambers
  • Conduction (Heat Transfer)
  • Energy
  • Film Boiling
  • Flow
  • Flow Rate
  • Heat Transfer
  • Hypervelocity Flow
  • Liquid Propellants
  • Photography
  • Propellants
  • Propulsion Systems
  • Test Facilities
  • Thrust Chambers
  • Vacuum Chambers

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Image Processing and Computer Vision.
  • Regression Analysis.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster