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Performance and heat transfer characteristics of the laser-heated rocket - A future space transportation systemThe application of advanced liquid-bipropellant rocket engine analysis techniques has been utilized for prediction of the potential delivered performance and the design of thruster wall cooling schemes for laser-heated rocket thrusters. Delivered specific impulse values greater than 1000 lbf-sec/lbm are potentially achievable based on calculations for thrusters designed for 10-kW and 5000-kW laser beam power levels. A thruster wall-cooling technique utilizing a combination of regenerative cooling and a carbon-seeded hydrogen boundary layer is presented. The flowing carbon-seeded hydrogen boundary layer provides radiation absorption of the heat radiated from the high-temperature plasma. Also described is a forced convection thruster wall cooling design for an experimental test thruster.
Document ID
19770032253
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shoji, J. M.
(Rockwell International Corp. Canoga Park, CA, United States)
Larson, V. R.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
November 1, 1976
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 76-1044
Meeting Information
Meeting: International Electric Propulsion Conference
Location: Key Biscayne, FL
Start Date: November 14, 1976
End Date: November 17, 1976
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
77A15105
Funding Number(s)
CONTRACT_GRANT: NAS3-19728
Distribution Limits
Public
Copyright
Other

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