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NASA NTRS · Other - NASA Tech Brief

Heat Flux In A Dual-Throat Rocket Engine

Published 2019-07-11 From Legacy CDMS 2 authors
View on NASA NTRS ↗

Attribution

This is the abstract and citation. Full text lives at NASA NTRS — we link out rather than host. All credit to the authors and Legacy CDMS.

Abstract

Verbatim from NASA NTRS. Not paraphrased, not summarized.

Report describes tests of dual-throat rocket engine burning hydrogen in oxygen. In tests, heat-flux profiles measured in inner nozzle and outer chamber. Dual-throat engine being considered for advanced space transportation. Consisting of two combustion chambers in series operating separately or together, engine makes it possible to change mode of operation in flight to obtain performance in most advantageous regime. Produces high thrust at sea level or low thrust with higher performance at high altitudes or in space.

Authors

  • Ewen, R. L. Aerojet TechSystems Co.
  • Obrien, C. J. Aerojet TechSystems Co.

Citation: Ewen, R. L., Obrien, C. J. (2019). Heat Flux In A Dual-Throat Rocket Engine. Legacy CDMS. NASA NTRS ID 19890000203. https://ntrs.nasa.gov/citations/19890000203 ↗