直升机旋翼桨叶鸟撞动态响应计算

林长亮 王益锋 王浩文 陈仁良尚晓冬

振动与冲击 ›› 2013, Vol. 32 ›› Issue (10) : 62-68.

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PDF(2124 KB)
振动与冲击 ›› 2013, Vol. 32 ›› Issue (10) : 62-68.
论文

直升机旋翼桨叶鸟撞动态响应计算

  • 林长亮1 王益锋2 王浩文 3陈仁良1尚晓冬4
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COMPUTATION OF DYNAMIC RESPONSE FOR THE BIRD IMPACT ON HELICOPTER BLADE

  • LIN Chang-liang1 WANG Yi-feng2 WANG Hao-wen3 CHEN Ren-liang1 SHANG Xiao-dong4
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摘要

基于旋翼综合气弹分析程序,求解出直升机旋翼桨叶在飞行过程中的稳态响应。以此作为鸟体撞击桨叶的初始状态,采用非线性流-固耦合算法,建立了直升机旋翼桨叶鸟撞动力学方程,利用直接数值积分方法求解桨叶的动态响应。并讨论了鸟体速度,质量,撞击位置、桨叶根部约束、离心力等参数对桨叶动态响应的影响,从而为直升机桨叶抗鸟撞设计提供一些理论依据。

Abstract

The steady-state response of the helicopter rotor in flight is solved by using its comprehensive aeroelastic analysis program. The result is then used for the initial state of bird impact on the blade. The bird impact dynamic equation of helicopter rotor blade is established by adopting non-linear fluid-solid coupling algorithm. Finally the dynamic response of blades is solved by using direct numerical integration method.To provide some theoretical basis for the anti-bird impact on helicopter blade design, the system parameters such as bird speed、bird quality、impact position、blade root constraint and rotation speed were discussed in the paper.

关键词

直升机 / 鸟撞 / 桨叶 / 动态响应 / 流-固耦合

Key words

helicopter / bird impact / blade / dynamic response / fluid-structure coupling

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林长亮 王益锋 王浩文 陈仁良尚晓冬. 直升机旋翼桨叶鸟撞动态响应计算[J]. 振动与冲击, 2013, 32(10): 62-68
LIN Chang-liang WANG Yi-feng WANG Hao-wen CHEN Ren-liang SHANG Xiao-dong. COMPUTATION OF DYNAMIC RESPONSE FOR THE BIRD IMPACT ON HELICOPTER BLADE[J]. Journal of Vibration and Shock, 2013, 32(10): 62-68

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