Automated model based conceptual design approach for composite helicopter rotor blades

Abstract

In this paper, an automated conceptual structural design methodology of composite helicopter rotor blades is described. Furthermore, design outputs such as blade weights of commercial aircraft blades are compared with the outputs of the tool using this methodology. The methodology applied targets to find optimum internal structure which can compensate outcomes of major rotor design parameters which are chord length, rotor radius and rotor frequency. Minimum blade weight is objected while searching necessary internal structure. Structural integrity and cross-sectional center positions affecting dynamic responses are constrained while searching for the necessary internal structure. The method applied differs from traditional blade optimization studies with the solution time and maximum parametrization of blade structural configuration. Hence, method does not target to optimize a blade structure having a detailed initial design. It aims to find a feasible design from sweep models of blade configurations with necessary mass attachments.