Prospects for mjcronave heatfd propulsion

Michael M. Micci

Research output: Contribution to conferencePaperpeer-review

Abstract

The utilization of microwave energy in an electrothermal thruster scheme to heat gases to high temperatures followed by a nozzle expansion was examined. Hydrogen is the propellant of choice since it produces the highest exhaust velocity for a given chamber temperature, however, hydrogen does suffer frozen flow losses which are discussed. Five schemes for the absorption of microwave radiation in a high pressure gas are identified with two schemes being capable of isolating the high temperature gas region away from material walls. Experimental evidence exists showing almost complete microwave absorption by the gas as well as hydrogen gas temperatures up to 9000 K equating to a specific impulse of 2000 seconds including frozen flow losses. The generation of microwave energy can be accomplished with electrical efficiencies approaching 85%, making the on-board generation of the microwaver power feasible.

Original languageEnglish (US)
StatePublished - Jan 1 1984
EventAIAA//SAE/ASEE 20th Joint Propulsion Conference, 1984 - Cincinnati, United States
Duration: Jun 11 1984Jun 13 1984

Other

OtherAIAA//SAE/ASEE 20th Joint Propulsion Conference, 1984
CountryUnited States
CityCincinnati
Period6/11/846/13/84

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering
  • Aerospace Engineering
  • Energy Engineering and Power Technology
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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