Hybrid Electric Chemical Propulsion,

Abstract

A spacecraft propulsion concept that uses a combination of electrical energy and chemical energy for thrust is explored using thermodynamic modeling calculations. The essence of this concept consists of adding a carefully chosen amount of O2 or F2 oxidizer to the propellant flow of a conventional H2 electrothermal thruster. A general method is given for selecting the Fuel: oxidizer ratio so as to optimize the thruster performance for any set of mission constraints. Auxiliary propulsion, Chemically augmented electrothermal thrusters, Electric propulsion, Spacecraft propulsion. (mjm)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1989
Accession Number
ADA207584

Entities

People

  • James E. Pollard
  • Ronald B. Cohen

Organizations

  • The Aerospace Corporation

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Chemical Composition
  • Chemical Reaction Properties
  • Chemical Reactions
  • Classification
  • Combustion
  • Combustion Chambers
  • Electric Power
  • Electric Propulsion
  • Flow Rate
  • Hybrid Propulsion
  • Mass Flow
  • Payload
  • Propellants
  • Propulsion Systems
  • Security
  • Space Systems
  • Specific Impulse

Fields of Study

  • Physics

Readers

  • Aerospace Propulsion Engineering.
  • Combustion science or combustion engineering.
  • Computational Modeling and Simulation

Technology Areas

  • Space
  • Space - Hall-Effect Thruster