| Summary: | A multidisciplinary rotor blade design approach, which is suitable for conceptual design, sizing and evaluation of helicopters is presented. Blade outer surface and structural geometry is represented by a geometrical model in which chord, thickness ratio, camber ratio and twist distributions along the blade radial stations can be defined as linear or nonlinear functions. Distribution of the number of laminas for both skin and spar were also defined in the presented model parametrically. Low level fidelity analysis methods were chosen to reduce the computing time. Performance analysis and sizing of the vehicle are performed by an in-house developed code named as ROTAP based on BEMT. Airfoil aerodynamic characteristics are calculated by Xfoil, a well-known panel method software. Structural analyses are performed by 1D finite element method approach. Cross-sectional properties of the composite beam are calculated by VABS software and displacements under the loads are calculated by the GEBT. All these programs are modified and embedded into the developed code and a single program with user friendly interface emerged. Developed algorithm and tool can be used for performance and structural strength calculations during the rotor design optimization studies at the conceptual design stage.
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