Assume the stress history shown represent the bending stress on the main rotor s

Question

Assume the stress history shown represent the bending stress on the main rotor shaft of a helicopter. The shaft is made of the alloy Ti-6AI-4V and no yielding occurs even locally at a notch where fatigue cracking is a possibility. The stress in the notch is approximately uniaxial, and with the stress concentration factor of the notch included, one stress unit is equivalent to 100 MPa. How many rotor revolutions can he applied before fatigue failure is expected? What is the estimated life in hours of flight if each rotor revolution requires 0.3 seconds? Material Properties: sigmax = 1233 MPa. C = 10(1889) & b = -0.104

Explanation / Answer

A) It would be the 6 rotor revolution due to the crest and trough. B) It would be around 200 estimated life in hours

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