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Manufacturing scale-up of composite fuselage crown panels

Author
Brown, T.
Published
Jan 1, 1993.
Physical Description
1 electronic document
Additional Creators
Gessel, M., Willden, Kurtis, and Grant, Carroll G.
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
The goal of the Boeing effort under the NASA ACT program is to reduce manufacturing costs of composite fuselage structure. Materials, fabrication of complex subcomponents and assembly issues are expected to drive the costs of composite fuselage structure. Several manufacturing concepts for the crown section of the fuselage were evaluated through the efforts of a Design Build Team (DBT). A skin-stringer-frame intricate bond design that required no fasteners for the panel assembly was selected for further manufacturing demonstrations. The manufacturing processes selected for the intricate bond design include Advanced Tow Placement (ATP) for multiple skin fabrication, resin transfer molding (RTM) of fuselage frames, innovative cure tooling, and utilization of low-cost material forms. Optimization of these processes for final design/manufacturing configuration was evaluated through the fabrication of several intricate bond panels. Panels up to 7 ft. by 10 ft. in size were fabricated to simulate half scale production parts. The qualitative and quantitative results of these manufacturing demonstrations were used to assess manufacturing risks and technology readiness for production.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19950022414.
Accession ID: 95N28835.
NASA. Langley Research Center, Third NASA Advanced Composites Technology Conference, Volume 1, Part 2; p 689-704.
Terms of Use and Reproduction
No Copyright.
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