| Citation: | ZHANG X C，WAN Z Q，YAN D. Optimal active twist control for rotor vibration reduction[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（12）：3397-3408 （in Chinese） doi: 10.13700/j.bh.1001-5965.2022.0105
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The active twist control rotor is investigated to evaluate the effectiveness in rotor vibration reduction. A numerical model for predicting the isolated rotor vibration loads in steady level flight is deployed and validated by modeling a UH-60A rotor. A parametric sweep of the amplitude and phase angle for uniform single-harmonic active twist control is conducted to demonstrate the effects on rotor vibration loads. The optimal control schedule of the uniform multi-harmonic twist control for vibration reduction are obtained using an optimization framework based on genetic algorithm. The results indicate that the uniform multi harmonic twist control reduces the rotor vibration loads more than the uniform single-harmonic active twist control. An optimal 2 segment twist control layout with the segment point at the midpoint of the blade achieves further rotor vibration reduction by applying divergent control schedules to each segment.
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