Published: Jan 1971
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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.
aircraft, helicopters, damage, rotary wings, components, cracking (fracturing), crack propagation, loads (forces), cyclic loads, residual stress, plastic properties, fracture properties
Chief, Sikorsky Aircraft, Division of United Aircraft Corp., Stratford, Conn.
Paper ID: STP26681S