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Laminar flow control perforated wing panel developmentMany structural concepts for a wing leading edge laminar flow control hybrid panel were analytically investigated. After many small, medium, and large tests, the selected design was verified. New analytic methods were developed to combine porous titanium sheet bonded to a substructure of fiberglass and carbon/epoxy cloth. At -65 and +160 F test conditions, the critical bond of the porous titanium to the composite failed at lower than anticipated test loads. New cure cycles, design improvements, and test improvements significantly improved the strength and reduced the deflections from thermal and lateral loadings. The wave tolerance limits for turbulence were not exceeded. Consideration of the beam column midbay deflections from the combinations of the axial and lateral loadings and thermal bowing at -65 F, room temperature, and +160 F were included. Many lap shear tests were performed at several cure cycles. Results indicate that sufficient verification was obtained to fabricate a demonstration vehicle.
Document ID
19900000871
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Fischler, J. E. (McDonnell-Douglas Corp. Long Beach, CA, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1986
Subject Category
Composite Materials
Report/Patent Number
NASA-CR-178166
NAS 1.26:178166
Accession Number
90N10187
Funding Number(s)
CONTRACT_GRANT: NAS1-17506
PROJECT: RTOP 505-60-31-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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