Abstract
The objective of the study is to determine an optimal flap damping configuration and flapping hinge location to achieve minimum hub and fuselage vibration levels simultaneously. An aeroelastic analysis of two soft in-plane two-bladed rotor is performed in conjunction with optimal control. A multi-objective bat algorithm (MOBA) approach was used to obtain the optimal design point. Under constraint conditions of meeting flight performance requirements, calculating the general parameters makes the objective function optimal. Objective functions include hub and fuselage vibration levels. It was found that MOBA inspired Pareto optimal flapping hinges design reduces hub vibration levels by 63% and fuselage vibration levels by 57% in comparison with the baseline design. The result was validated on an F300 Coaxial helicopter at the Beihang University.
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