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舰载直升机旋翼/机体耦合动力学稳定性

刘洋 向锦武

刘洋, 向锦武. 舰载直升机旋翼/机体耦合动力学稳定性[J]. 北京航空航天大学学报, 2013, 39(4): 442-446.
引用本文: 刘洋, 向锦武. 舰载直升机旋翼/机体耦合动力学稳定性[J]. 北京航空航天大学学报, 2013, 39(4): 442-446.
Liu Yang, Xiang Jinwu. Stability analysis of coupled rotor/fuselage system of shipboard helicopter[J]. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(4): 442-446. (in Chinese)
Citation: Liu Yang, Xiang Jinwu. Stability analysis of coupled rotor/fuselage system of shipboard helicopter[J]. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(4): 442-446. (in Chinese)

舰载直升机旋翼/机体耦合动力学稳定性

基金项目: 国家自然科学基金资助项目(10672011)
详细信息
  • 中图分类号: V 212.5; V 214.4+2

Stability analysis of coupled rotor/fuselage system of shipboard helicopter

  • 摘要: 建立了舰载直升机和舰船运动耦合动力学模型,考虑了舰载直升机起落架非线性和非对称的特点,并将舰船振动自由度与旋翼/机体系统相结合分析了直升机系统耦合动力学稳定性.舰载直升机采用无轴承旋翼,用中等变形梁理论建立桨叶、柔性梁和扭矩套的有限元模型,考虑桨叶多路传力特点和桨叶根部的摆振销与变距拉杆的约束.起落架包括液压作动器和橡胶轮胎,起落架系统具有非线性特点,在不同载荷下其刚度和阻尼都不同.采用所建立的动力学模型分析了舰载直升机的"舰面共振"动力学特性,首先通过算例中的无轴承旋翼直升机"地面共振"频率与阻尼曲线验证了旋翼机体耦合模型的正确性.其次发现舰船在横摇振动情况下,旋翼/机体耦合系统的旋翼不稳定转速区域会提前出现,如果鱼叉系留则会推迟不稳定转速,并且增加系统的阻尼.

     

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出版历程
  • 收稿日期:  2012-11-05
  • 网络出版日期:  2013-04-30

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