Multidisciplinary Conceptual Design Methodology and Design Tool for Rotor Blades of Advanced Helicopters
Keywords:
Rotor Blade, Conceptual Design Optimization, Performance, Structural StrengthAbstract
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, chamber ratio and twist distributions along the blade radial stations can be defined as linear or nonlinear functions. Distribution of the number of the 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 in-house developed by author BEMT based code called ROTAP. Airfoil aerodynamic characteristics are calculated by the panel method software Xfoil. Structural analyses are obtained 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 in to the code developed for present study as a single code with user friendly interface. 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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The manuscript with title and authors is being submitted for publication in Journal of Aeronautics and Space Technologies. This article or a major portion of it was not published, not accepted and not submitted for publication elsewhere. If accepted for publication, I hereby grant the unlimited and all copyright privileges to Journal of Aeronautics and Space Technologies.
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