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摘要:
为降低旋翼前飞状态的桨毂振动载荷水平，应用主动扭转旋翼技术，开展最优控制方案研究。建立基于中等变形梁理论的旋翼气动弹性动力学模型，以预测稳态飞行的桨毂振动载荷。使用UH-60A直升机旋翼算例验证所建模型准确性并作为研究基准。通过谐波相位及幅值变参分析，研究单谐波扭转控制对振动载荷的影响。构建基于遗传算法的主动扭转旋翼控制参数优化框架，开展展向一致多谐波扭转控制参数优化与分段多谐波扭转控制方案优化。结果表明：优化的多谐波扭转控制相比单谐波主动扭转控制可起到更好的桨毂振动载荷减缓效果。而以桨叶中点为分段点的最优2段扭转控制方案，通过对内外段桨叶施加不同的扭转控制规律，进一步降低了六方向的振动载荷水平。
Abstract: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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Key words:
- helicopter /
- rotor /
- active control /
- vibration reduction /
- optimization
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图 9 1Ω扭转控制在不同相位角下所获得的振动载荷降低率
Figure 9. Effects of 1Ω torsional control obtains vibration load reduction rate at different phase angles
图 10 2Ω扭转控制在不同相位角下所获得的振动载荷降低率
Figure 10. Effects of 2Ω torsional control obtains vibration load reduction rate at different phase angles
图 11 3Ω扭转控制在不同相位角下所获得的振动载荷降低率
Figure 11. Effects of 3Ω torsional control obtains vibration load reduction rate at different phase angles
图 12 4Ω扭转控制在不同相位角下所获得的振动载荷降低率
Figure 12. Effects of 4Ω torsional control obtains vibration load reduction rate at different phase angles
图 13 5Ω扭转控制在不同相位角下所获得的振动载荷降低率
Figure 13. Effects of 5Ω torsional control obtains vibration load reduction rate at different phase angles
图 14 1Ω扭转控制在不同扭转率幅值下所获得的振动载荷降低率
Figure 14. Effects of 1Ω torsional control obtains vibration load reduction rate at different torsion rate amplitudes
图 15 2Ω扭转控制在不同扭转率幅值下所获得的振动载荷降低率
Figure 15. Effects of 2Ω torsional control obtains vibration load reduction rate at different torsion rate amplitudes
图 16 3Ω扭转控制在不同扭转率幅值下所获得的振动载荷降低率
Figure 16. Effects of 3Ω torsional control obtains vibration load reduction rate at different torsion rate amplitudes
图 17 4Ω扭转控制在不同扭转率幅值下所获得的振动载荷降低率
Figure 17. Effects of 4Ω torsional control obtains vibration load reduction rate at different torsion rate amplitudes
图 18 5Ω扭转控制在不同扭转率幅值下所获得的振动载荷降低率
Figure 18. Effects of 5Ω torsional control obtains vibration load reduction rate at different torsion rate amplitudes
图 19 0Ω扭转控制在不同扭转率幅值下所获得的振动载荷降低率
Figure 19. Effects of 0Ω torsional control obtains vibration load reduction rate at different torsion rate amplitudes
图 20 不同谐波幅值可获得的振动载荷指数降低率
Figure 20. Effects of harmonic amplitude on vibration Index reduction
图 21 主动扭转旋翼控制参数优化框架
Figure 21. Optimization framework for active twist rotor control parameters
图 22 最优展向一致多谐波扭转控制的谐波分量的幅值
Figure 22. Amplitudes of harmonic components for optimal multi-harmonic twist control
图 23 最优多谐波控制和最优$ 2\varOmega $控制的波形
Figure 23. Waveform of optimized multi-harmonic twist control and optimized 2Ω twist control
图 26 最优2段多谐波控制的谐波分量的幅值
Figure 26. Amplitudes of harmonic components for optimal-2-sey twist control
图 29 3种主动扭转控制的振动载荷指数降低率
Figure 29. Reduction of vibration index using three active twist control approaches
表 1 UH-60A直升机旋翼主要参数
Table 1. Rotor main parameters of UH-60A helicopter
参数 数值 旋翼半径/m 8.1788 桨叶弦长/m 0.5273 挥舞摆振铰外伸量/m 0.381 桨叶线密度/(kg·m−1) 13.92 旋翼转速/(rad·s−1) 27.0 桨叶片数 4 
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