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Study of solid rocket motors for a space shuttle booster. Volume 1: Executive summaryThe factors affecting the choice of the 156 inch diameter, parallel burn, solid propellant rocket engine for use with the space shuttle booster are presented. Primary considerations leading to the selection are: (1) low booster vehicle cost, (2) the largest proven transportable system, (3) a demonstrated design, (4) recovery/reuse is feasible, (5) abort can be easily accomplished, and (6) ecological effects are minor.
Document ID
19720015124
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Vonderesch, A. H. (Lockheed Propulsion Co. Redlands, CA, United States)
Date Acquired
September 2, 2013
Publication Date
March 15, 1972
Subject Category
Propulsion Systems
Report/Patent Number
LPC-629-6-VOL-1
NASA-CR-123614
Accession Number
72N22774
Funding Number(s)
CONTRACT_GRANT: NAS8-28429
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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