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首页> 外文会议>AIAA Dynamics Specialists Conference, Apr 21-22, 1994, Hilton Head, SC >AEROELASTIC STABILITY ANALYSIS OF DAMAGED HELICOPTER ROTOR SYSTEM
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AEROELASTIC STABILITY ANALYSIS OF DAMAGED HELICOPTER ROTOR SYSTEM

机译：受损直升机转子系统的气动弹性稳定性分析

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摘要

The effects of rotor blade ballistic damages on helicopter airworthiness and blade and hub conditions are investigated using a UMARC helicopter aeroelas-tic analysis code. A finite element formulation based on Hamilton's principle is used for structural analysis, and aerodynamic loads are calculated using qua-sisteady aerodynamic theory. Each blade is treated as being composed of elastic beams undergoing flap bending, lag bending, elastic twist, and axial deflections. Dynamic responses of multi-bladed rotor systems are calculated from nonlinear periodic normal mode equations using a finite element in time scheme. Results are calculated for a soft in-plane articulated rotor helicopter for both undamaged and damaged blade configurations. Blade damage effects are determined in terms of blade mode shapes and frequencies, aeroelastic response and rotor hub loads. Blade dissimilarity due to ballistic damage can induce a large 1/rev vibratory component on the rotor hub.
机译：使用UMARC直升机航空弹力分析规范，研究了旋翼叶片弹道损坏对直升机适航性以及叶片和轮毂状况的影响。使用基于汉密尔顿原理的有限元公式进行结构分析，并使用准稳态气动理论计算气动载荷。每个叶片都被视为由经受横梁弯曲，滞后弯曲，弹性扭曲和轴向挠曲的弹性梁组成。使用时间方案中的有限元，从非线性周期正态方程中计算出多叶片转子系统的动力响应。针对未损坏和损坏的桨叶构型，计算了一个软平面铰接式旋翼直升机的结果。叶片损坏的影响取决于叶片模式的形状和频率，气动弹性响应和转子轮毂负载。由于弹道损坏而导致的叶片不相似会在转子轮毂上引起较大的1 / rev振动分量。

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