SYMPOSIA PAPER Published: 01 January 1971
STP26681S

Crack Propagation in Helicopter Rotor Blades

Source

Design criteria are presented for the residual strength and life of fatigue loaded helicopter structures. The crack propagation rate methods and data are reviewed, and a bilinear semilog method is shown to be most accurate for predicting residual life. The methods developed are compared with full scale rotor blade fatigue data. The good correlation with test data demonstrates the value of fracture mechanics analysis for fail-safe design.

Author Information

Rich, MJ
Sikorsky Aircraft, Division of United Aircraft Corp., Stratford, Conn.
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Details
Developed by Committee: E08
Pages: 243–251
DOI: 10.1520/STP26681S
ISBN-EB: 978-0-8031-4595-5
ISBN-13: 978-0-8031-0031-2