Performance of a Hydrogen Pulsed Electrothermal Thruster. Strategic Defense Initiative Organization Innovative Science and Technology. SBIR. Phase 1.

Abstract

This report describes effort to determine the technical feasibility of measuring the performance of a pulsed electrothermal thruster on liquid hydrogen propellant. The design of a 5 kW thruster is presented, including the capacitive pulse forming network, arc discharge characteristics, nozzle performance and predicted specific impulse and thrust. A thermal model is discussed which treats and solves the problem of liquid hydrogen it is concluded that a Phase II test should concentrate on water and/or hydrazine, and liquid hydrogen testing should be postponed to Phase III. Keywords: Electric propulsion, Pulsed electrothermal propulsion; Liquid hydrogen propellant.

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Document Details

Document Type
Technical Report
Publication Date
Sep 28, 1987
Accession Number
ADA191999

Entities

People

  • Rodney L. Burton
  • Shih-ying Wang
  • Shyke A. Goldstein

Tags

Communities of Interest

  • Energy and Power Technologies
  • Human Systems
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Artificial Satellites
  • Chemical Reactions
  • Electric Propulsion
  • Engineering
  • Engines
  • Liquid Hydrogen
  • Materials
  • Microsecond Time
  • Payload
  • Propellants
  • Propulsion Systems
  • Reconnaissance Satellites
  • Rocket Engines
  • Rockets
  • Thrusters

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Defense Technology Research and Development.
  • Electrical Engineering

Technology Areas

  • Space
  • Space - Hall-Effect Thruster