Aeronautics and astronautics – Aircraft structure – Details
Patent
1984-06-07
1990-10-16
Nelson, Peter A.
Aeronautics and astronautics
Aircraft structure
Details
244123, 244132, 244133, B64C 106
Patent
active
049629042
ABSTRACT:
A transition fitting (16) for a high strength composite article (10) comprised of a matrixed skin (12) supported by and bonded to a core (14) to locate the same in an intended structural disposition subjecting the composite and fitting at or about a juncture thereof to bending and/or shear loads, comprising a profiled web (22) disposed within the composite article and a shank for fixturing the article, wherein the web includes a longitudinal aspect projecting into the core from the juncture to a tip of the web (26), a lateral aspect projecting across the core bounding the juncture, and a transverse aspect extending through the core; wherein the transverse aspect of the web tapers inwardly along the longitudinal direction of the web toward the tip and is dimensioned to provide load distribution to transfer structural loads from the composite to the fitting along a longitudinal force gradient having a minimum force value at the tip and a maximum force value at the shank, and yet further wherein the lateral aspect is dimensioned to yield a web surface area selected to provide force balancing for maintaining loads transferred to the web along the gradient below the interfacial shear limits at the junctures of the fitting, the core and the skin.
REFERENCES:
patent: 3328229 (1967-06-01), Windecker
patent: 4113910 (1978-09-01), Loyd
patent: 4213587 (1980-07-01), Roeseler et al.
patent: 4253378 (1981-03-01), Donovan
patent: 4390153 (1983-06-01), Wuermseer
patent: 4411940 (1983-10-01), Derkacs et al.
patent: 4448372 (1984-05-01), Larson
Perry John S.
Stowe Harold A.
Neary J. Michael
Nelson Peter A.
The Boeing Company
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