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    Development Fatigue Testing of a Large Helicopter Rotor Blade

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    The laboratory development fatigue test program for a large pressure-jet rotor is described. In this program the objective was to establish a reliable unlimited-life blade for a 2-g level of load. The program includes testing in the design stage of components simulating suspected critical design details, and improving details where performance does not come up to expectations, with changes made to inexpensive small-element specimens in which relative improvements can be evaluated. Results of a program for improving bolted connections are presented. Final tests should be on a full-scale rotor, in which all loads significant to the fatigue strength are applied.

    Author Information:

    Lischer, Alan A.
    McDonnell Aircraft Corp., St. Louis, Mo.

    Committee/Subcommittee: E08.05

    DOI: 10.1520/STP45925S