An integrated aerodynamic/dynamic optimization procedure is used to minimize blade weight and 4/rev vertical shear of a rotor blade in forward flight. Both single and multiple objective functions are used, with constraints imposed on the first four coupled natural frequencies (elastic modes only), the blade aerorotational inertia, and the centrifugal stress. The global criteria approach is used for the multiple objective formulation, and the results are compared with those obtained from single objective function formulations. Optimum designs are compared against a reference blade, and it is shown that optimum results can be obtained in 7-10 cycles.
Integrated aerodynamic/dynamic optimization of helicopter rotor blades
AIAA, ASME, ASCE, AHS, and ASC, Structures, Structural Dynamics and Materials Conference ; 1989 ; Mobile, AL, United States
1989-01-01
Conference paper
No indication
English
Fully integrated aerodynamic/dynamic optimization of helicopter rotor blades
Tema Archive | 1992
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