Abstract
Multicomponent wing load and corresponding derived internal stress time histories are evaluated considering load transfer through mechanically fastened joints. These time histories are from both analytically derived and dynamic response test measured data considering flights through continuous turbulence of a heavy logistics aircraft. This evaluation is used as a basis to develop a rational fastener load transfer fatigue analysis methodology that includes gust loads in the power spectral density form. The technique developed includes the establishment of a matrix of axial-shear stress phasing relationships based on variations in operational flight parameters. The results of a durability assessment, utilizing the developed procedure, of specific structural joints subjected to two different load spectra are presented. Significant elements of this procedure are the aforementioned stress phasing relationships, joint geometric configuration data, fastener characteristics, and built-up S-N data. The results are compared to a fatigue assessment based on a uniaxial-stress fatigue analysis procedure. The potential applications of the developed load transfer analysis technique include structural joint design optimization and the durability evaluations of structural joints that have operating loads different from their design loads.
Published Version
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