Vibration reduction optimization design for parameterized composite blade

For blade dynamics optimization design, a parametrization model of composite multi-cell C-type blade section was estabished for engineering design. The parameterized design of aerodynamic shape of the blade section, the internal structure of components and composite material layer was implemented, and a parameterized method capable of maintaining a constant C-type beam fiber area was presented. Then in combination with the composite blade parameterization model and aero-elastic analysis model, the optimal parameters of blade sections could be obtained to reduce the hub vibration via the optimal process based on multi-population genetic algorithm(MPGA). The "Dolphin" helicopter's blade profile modeling and performance calculation contrasts were given, with total error less than 3%. With use of the blade parameterization model of blade for rotor dynamic optimization, the results show that the rotor's weighted optimizaton vibration load coefficient decreases by 4.15%, and the balance weight of blade is more smooth after optimization, helping to ease the blade internal stress/strain mutation; some balance weight assigned to the blade tip can increase the rotation inertia of the rotor, and improve the safety for autorotative glide.