基于CFD/CSD耦合的全动平尾气动弹性特性研究  

Aeroelastic Characteristic Research of Fully Moving Horizontal Tail Based on CFD/CSD Coupling Method

作　　者：罗文莉[1] 陆琪 LUO Wenli;LU Qi(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《机械制造与自动化》2020年第5期150-153,168,共5页Machine Building & Automation

摘　　要：针对飞行器全动平尾的流固耦合现象,基于CFD/CSD耦合的方法建立了气动力和结构模型,给出了平尾的气动力和结构响应曲线。分别在不同迎角下针对流场的压力分布响应和结构的应力响应进行了详细研究,解释了现象产生的原因。结果表明,考虑弹性后0°迎角下平尾迅速收敛至平衡位置,大迎角时的气动力和结构响应曲线均出现波动,随时间变化逐渐衰减至平衡位置。迎角越大,初始振幅越大,气动力减小越明显,结构应力越大,但随时间衰减得越快。结构变形导致下表面压力分布发生变化,对于平尾前缘、靠近翼根部分上偏压力增大,靠近翼尖部分下偏压力减小。平尾后缘均上偏压力减少,使得平尾整体压力减小、升力系数降低。靠近翼轴处应力较为集中,而翼轴上的应力较小。平尾上存在弯曲/扭转耦合现象,且迎角越大耦合越明显。For the fluid-structure coupling phenomenon of fully moving horizontal tail of aircraft,the aerodynamic and structural model is established based on CFD/CSD coupling method,and the response curve of the tail is calculated.The aerodynamic pressure distribution and structural stress response at different angle of attack(AOA)are researched on in detail and the causes of its phenomenon are explained.The result shows that the horizontal tail converges rapidly to the equilibrium position at 0-degree AOA after considering elasticity.The aerodynamic and structural response curve fluctuate and gradually attenuate to the equilibrium position at high AOA.When the AOA is higher,with both the initial amplitude and structure stress large,the aerodynamic force decreases more obviously,but the response curve attenuates faster.The structure deformation results in the change of pressure distribution on the lower surface,which causes the overall pressure and lift coefficient of the tail decreases.Stress is more concentrated near the rotation axis while stress at the axis itself is lower.The bending and torsion coupling phenomenon exists on the tail and turns more obvious with AOA higher.

关 键 词：CFD CSD 飞行器 水平尾翼 气动弹性 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]