Reliability Analysis of Rotorcraft Composite Structures
Publication: Journal of Aerospace Engineering
Volume 14, Issue 4
Abstract
This paper develops a probabilistic analysis framework to predict the fatigue reliability of laminated composites and applies it to tapered composites used in rotorcraft structures. The method combines finite-element analysis, composite laminate analysis, fatigue failure modeling, and first-order reliability analysis to achieve this objective. This methodology is demonstrated on a composite helicopter rotor hub test specimen with thick, thin, and tapered regions. The specimen is subjected to centrifugal and oscillatory bending loads. The failure mechanism observed for this type of fatigue loading is an initial tension crack followed by internal delamination at the thick-to-taper transition, where internal ply drop-offs occur. The proposed method predicts the probability of delamination initiation for such rotor hubs. The method is validated using full-scale test results.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 14 • Issue 4 • October 2001
Pages: 140 - 146
History
Received: May 29, 2001
Published online: Oct 1, 2001
Published in print: Oct 2001
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