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Advanced manufacturing development of a composite empennage component for L-1011 aircraftWork continued toward the development of tooling and processing concepts required for a cocured hat/skin cover assembly. A plan was developed and implemented to develop the process for using preimpregnated T300/5208 with a resin content of 34 + or - 2 percent by weight. Use of this material results in a simplified laminating process because removal by bleeding or prebleeding is no longer required. The approach to this task basically consists of fabricating and testing flat laminated panels and simulated structural panels to verify known processing techniques relative to end-laminate quality. The flat panels were used to determine air bleeding arrangement and required cure cycle. Single and multihat-stiffened panels were fabricated using the established air bleeding arrangement and cure cycle with the resulting cured parts yielding excellent correlation of ply thickness with all surfaces clear of porosity and voids.
Document ID
19830017421
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Date Acquired
September 4, 2013
Publication Date
October 13, 1978
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
QTR-11
LR-28743
NAS 1.26:172658
DRL-003
NASA-CR-172658
Accession Number
83N25692
Funding Number(s)
CONTRACT_GRANT: NAS1-14000
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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