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首页> 外文会议>American Helicopter Society International annual forum >Rotor Structural Loads Analysis Using Coupled Computational Fluid Dynamics/Computational Structural Dynamics
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Rotor Structural Loads Analysis Using Coupled Computational Fluid Dynamics/Computational Structural Dynamics

机译：耦合计算流体动力学/计算结构动力学的转子结构载荷分析

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Coupled CFD/CSD (RCAS/Helios and CAMRAD Ⅱ/Helios) analyses are performed and the calculated rotor structural loads are compared with the flight test data obtained from the NASA/Army UH-60A Airloads Program. Three challenging level flight conditions are investigated: 1) high speed with advancing blade negative lift, 2) low speed with blade-wake interaction, and 3) high thrust with dynamic stall. The predicted flap bending and torsion moments, pitch link and lag damper loads, in general, show reasonably good correlation with the test data. A nonlinear lag damper model is essential for the accurate prediction of root chord bending moment and lag damper load. Both analyses, however, significantly underpredict the chord bending moments, especially the 4/rev harmonic amplitude. Parametric study shows that blade stiffness variations have only a small influence on the loads calculations. However, modal damping in the first flap mode has a significant influence on the flap bending moments. Inclusion of a simple one degree-of-freedom drivetrain model shows the potential importance of high frequency drivetrain modes for the accurate prediction of the 4/rev chord bending moments and a need to develop a realistic drivetrain model.
机译：进行了CFD / CSD耦合分析（RCAS / Helios和CAMRADⅡ/ Helios），并将计算出的转子结构载荷与从NASA /陆军UH-60A空载计划获得的飞行测试数据进行了比较。研究了三种具有挑战性的水平飞行条件：1）前进的叶片负向提升时的高速; 2）叶片与尾翼相互作用的低速;以及3）动态失速的高推力。通常，预测的襟翼弯曲和扭转力矩，节距连杆和滞后阻尼器载荷与测试数据显示出合理的良好相关性。非线性滞后阻尼器模型对于准确预测根弦弯矩和滞后阻尼器载荷至关重要。但是，两种分析都大大低估了弦弯矩，特别是4 / rev谐波幅度。参数研究表明，叶片刚度变化对载荷计算影响很小。然而，在第一襟翼模式中的模态阻尼对襟翼弯曲力矩具有显着影响。包含一个简单的一自由度传动系统模型就表明了高频传动系统模式对于准确预测4 / rev弦弯矩的潜在重要性，并且需要开发一个现实的传动系统模型。

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