| 简化碰撞模型对直升机桨叶扬起下坠动响应影响 |
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| 引用本文： | 吴世杰,韩东.简化碰撞模型对直升机桨叶扬起下坠动响应影响[J].南京航空航天大学学报,2016,48(2):256-260. |
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| 作者姓名： | 吴世杰 韩东 |
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| 作者单位： | 南京航空航天大学直升机旋翼动力学国家级重点实验室,南京,210016 |
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| 摘 要： | 采用含阻尼项的简化碰撞模型模拟铰接式旋翼桨叶与限动块之间碰撞时的碰撞力变化，并研究了桨叶扬起下坠动响应过程。运用Hamilton原理建立桨叶扬起下坠动力学方程，并采用Newmark积分法求解桨叶下坠过程的动响应。分析扭转弹簧刚度、阻尼比和积分步长对挥舞铰处碰撞力矩的影响，计算结果表明：扭转弹簧刚度增大1 000倍时，碰撞力矩的峰值相应增大22.0倍；阻尼比从0增大到0.05时，碰撞力矩的峰值增加10.4%；积分步长变小时，计算的精度有所提高，但计算效率却有所降低。
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| 关 键 词： | 直升机 桨叶 扬起下坠 碰撞模型 动响应 |
Influence of Simplified Impact Model Between Blade and Droop Stop on Dynamic Response of Blade Droop Stop |
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| Wu Shijie,Han Dong.Influence of Simplified Impact Model Between Blade and Droop Stop on Dynamic Response of Blade Droop Stop[J].Journal of Nanjing University of Aeronautics & Astronautics,2016,48(2):256-260. |
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| Authors: | Wu Shijie Han Dong |
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| Institution: | National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics,
Nanjing University of Aeronautics & Astronautics, Nanjing, 210016, China |
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| Abstract: | A simplified impact model including a damping term is used to predict the transient contact force, and the dynamic response of blade droop stop impact is studied. The Hamilton principle is used to derive the dynamics equations during blade droop stop, and the Newmark integration method is used to solve the equations. The influences of hinge spring stiffness, damping ratio and integration step on the contact moment are analyzed. The results show that the peak impact moment increase by 22.0 times, when the spring stiffness is increased by 1000 times. The peak impact moment is increased by 10.4%, when the damping ratio changes from 0 to 0.05. The accuracy of calculation increases with smaller time integral step, but the efficiency decreases. |
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| Keywords: | helicopter blade droop stop impact model dynamic response |
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