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Upper-stage space shuttle propulsion by means of separate scramjet and rocket enginesA preliminary mission study of a reusable vehicle from staging to orbit indicates payload advantages for a dual-propulsion system consisting of separate scramjet and rocket engines. In the analysis the scramjet operated continuously and the initiation of rocket operation was varied. For a stage weight of 500,000 lb the payload was 10.4 percent of stage weight or 70 percent greater than that of a comparable all-rocket-powered stage. When compared with a reusable two-state rocket vehicle having 50,000 lb payload, the use of the dual propulsion system for the second stage resulted in significant decreases in lift-off weight and empty weight, indicating possible lower hardware costs.
Document ID
19720016189
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Franciscus, L. C. (NASA Lewis Research Center Cleveland, OH, United States)
Allen, J. L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
May 1, 1972
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TN-D-6762
E-6555
Accession Number
72N23839
Funding Number(s)
PROJECT: RTOP 139-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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