Enhancement of a Flapping Wing Using Path and Dynamic Topology Optimization

Abstract

The flapping wing of a micro air vehicle is optimized to enhance performance while some rigidity is kept with a specific mass. A work flow for the design of the flapping wing is defined. The performances to be enhanced are thrust coefficient and propulsive efficiency. The flapping kinematics of the flapping wing is determined by solving a path optimization problem that maximizes the performances. The optimization process is carried out based on a well-defined surrogate model. The surrogate model is made from the results of two-dimensional fluid dynamic analysis. The kriging method is employed to establish the surrogate model and a genetic algorithm is used for the multi. objective function problem. Dynamic topology optimization is performed to find the distribution of reinforcement. Certain rigidity can be kept by the results of topology optimization. A dynamic topology optimization method is developed by modification of the equivalent static loads method for nonlinear static response structural optimization. Three-dimensional computational fluid dynamic analysis is performed based on the optimum values of the path optimization to evaluate the external loads for the topology optimization process. The process of the defined work flow is materialized by interfacing various software systems.