A fully integrated aerodynamic/dynamic optimization procedure is described for helicopter rotor blades. The procedure combines performance and dynamic analyses with a general purpose optimizer. The procedure minimizes a linear combination of power required (in hover, forward flight, and maneuver) and vibratory hub shear. The design variables include pretwist, taper initiation, taper ratio, root chord, blade stiffnesses, tuning masses, and tuning mass locations. Aerodynamic constraints consist of limits on power required in hover, forward flight and maneuvers; airfoil section stall; drag divergence Mach number; minimum tip chord; and trim. Dynamic constraints are on frequencies, minimum autorotational inertia, and maximum blade weight. The procedure is demonstrated for two cases. In the first case, the objective function involves power required (in hover, forward flight and maneuver) and dynamics. The second case involves only hover power and dynamics. The designs from the integrated procedure are compared with designs from a sequential optimization approach in which the blade is first optimized for performance and then for dynamics. In both cases, the integrated approach is superior.


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    Title :

    Fully integrated aerodynamic/dynamic optimization of helicopter rotor blades


    Contributors:

    Conference:

    AIAA, ASME, ASCE, AHS, and ASC Structures,Structural Dynamics and Materials Conference ; 1992 ; Dallas, TX, United States


    Publication date :

    1992-02-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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