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Rocket nozzle expansion ratio analysis for dual-fuel earth-to-orbit vehiclesResults are reported from a recent study of the effects of Space Shuttle Main Engine expansion ratio modifications, in the cases of both single-stage and two-stage systems. Two-position nozzles were employed; after varying the lower expansion ratio while the higher was held constant at 120, the lower expansion ratio was held constant at 40 or 60 while the higher expansion ratio was varied. The expansion ratios for minimum vehicle dry mass are different for single-stage and two-stage systems. For two-stage systems, a single expansion ratio of 77.5 provides a lower dry mass than any two-position nozzle.
Document ID
19890051789
Document Type
Reprint (Version printed in journal)
Authors
Martin, James A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1989
Publication Information
Publication: Journal of Spacecraft and Rockets
Volume: 26
ISSN: 0022-4650
Subject Category
LAUNCH VEHICLES AND SPACE VEHICLES
Distribution Limits
Public
Copyright
Other