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Structural design of an in-line bolted joint for the space shuttle solid rocket motor case segments

Author:
Stein, Peter A.
Published:
Mar 1, 1987.
Physical Description:
1 electronic document
Additional Creators:
Dorsey, John T. and Bush, Harold G.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary:
Results of a structural design study of an in-line bolted joint concept which can be used to assemble Space Shuttle Solid Rocket Motor (SRM) case segments are presented. Numerous parametric studies are performed to characterize the in-line bolted joint behavior as major design variables are altered, with the primary objective always being to keep the inside of the joint (where the O-rings are located) closed during the SRM firing. The resulting design has 180 1-inch studs, an eccentricity of -0.5 inch, a flange thickness of 3/4 inch, a bearing plate thickness of 1/4 inch, and the studs are subjected to a preload which is 70% of ultimate. The mass penalty per case segment joint for the in-line design is 346 lbm more than the weight penalty for the proposed capture tang fix.
Other Subject(s):
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19870010916.
Accession ID: 87N20349.
NAS 1.15:89027.
NASA-TM-89027.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15699791