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Development of thermoplastic composite aircraft structuresEfforts focused on the use of thermoplastic composite materials in the development of structural details associated with an advanced fighter fuselage section with applicability to transport design. In support of these designs, mechanics developments were conducted in two areas. First, a dissipative strain energy approach to material characterization and failure prediction, developed at the Naval Research Laboratory, was evaluated as a design/analysis tool. Second, a finite element formulation for thick composites was developed and incorporated into a lug analysis method which incorporates pin bending effects. Manufacturing concepts were developed for an upper fuel cell cover. A detailed trade study produced two promising concepts: fiber placement and single-step diaphragm forming. Based on the innovative design/manufacturing concepts for the fuselage section primary structure, elements were designed, fabricated, and structurally tested. These elements focused on key issues such as thick composite lugs and low cost forming of fastenerless, stiffener/moldine concepts. Manufacturing techniques included autoclave consolidation, single diaphragm consolidation (SDCC) and roll-forming.
Document ID
19940028354
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Renieri, Michael P. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Burpo, Steven J. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Roundy, Lance M. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Todd, Stephanie A. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Kim, H. J. (McDonnell Aircraft Co. Saint Louis, MO, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1992
Subject Category
Composite Materials
Report/Patent Number
NASA-CR-189593
NAS 1.26:189593
Accession Number
94N32860
Funding Number(s)
CONTRACT_GRANT: NAS1-18862
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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