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| 1 | 结构参数对机翼非线性颤振系统混沌运动特性的影响显示文摘机翼非线性颤振系统中的混沌运动是一种复杂的非线性动力学现象,研究结构参数对机翼非线性颤振系统混沌运动特性的影响,对非线性动力学系统的混沌运动控制具有重要意义。建立具有立方型非线性操纵刚度的带操纵面二元机翼的颤振方程,采用数值积分方法分别获得该非线性颤振系统在不同阻尼水平和不同操纵刚度下的分岔特性图。对分岔特性图进行对比分析结果表明:操纵面的操纵刚度并不影响系统的混沌运动特性,而操纵面偏转自由度或机翼俯仰自由度上的阻尼将会影响系统混沌颤振区域内的周期窗口,进而影响系统的混沌运动特性,特别是两自由度中任意一个的阻尼水平减小到一定程度时,系统混沌颤振区域内的周期窗口都将会消失;但是,单一的减小某个自由度上的阻尼水平,会使机翼非线性颤振系统的颤振临界速度降低。为了使得该系统在混沌颤振区域内不产生周期窗口又不降低其颤振临界速度,可采用在减小俯仰自由度阻尼的同时增大操纵面偏转自由度阻尼的方法。 | 张惠 杨智春 张新平 周建 谷迎松 | 2013 | 振动与冲击2013，32，12： | 5 |
| 2 | Flutter analysis of an airfoil with nonlinear damping using equivalent linearization显示文摘The equivalent linearization method(ELM) is modified to investigate the nonlinear flutter system of an airfoil with a cubic damping. After obtaining the linearization quantity of the cubic nonlinearity by the ELM,an equivalent system can be deduced and then investigated by linear flutter analysis methods. Different from the routine procedures of the ELM,the frequency rather than the amplitude of limit cycle oscillation(LCO) is chosen as an active increment to produce bifurcation charts. Numerical examples show that this modification makes the ELM much more efficient.Meanwhile,the LCOs obtained by the ELM are in good agreement with numerical solutions. The nonlinear damping can delay the occurrence of secondary bifurcation. On the other hand,it has marginal influence on bifurcation characteristics or LCOs. | Chen Feixin Liu Jike Chen Yanmao | 2014 | Chinese Journal of Aeronautics2014，27，1： | 4 |
| 3 | 风力机叶片及翼型变形分析显示文摘在以往有关风力机叶片变形的研究中,主要关注挥舞、扭转变形。但事实上,由翼型自身的柔性变形所引起的翼型弯度、厚度变化对气动性能也有较大的影响。文章以NERL某5 MW风力机为例,利用Bladed软件计算风力机叶片载荷,并将载荷通过MPC多点约束的方式加载到ANSYS有限元模型中,研究柔性叶片翼型截面的变形情况。研究表明,翼型横截面扭转变形不是整体的挥舞、扭转变形,从腹板到尾缘段的扭转幅度比腹板到前缘段的幅度要大,翼型截面自身也会发生形变进而影响叶片的气动性能。 | 邓勇 钟铭 刘乐 陈严 罗振 | 2017 | 可再生能源2017，35，5： | 4 |
| 4 | Aeroelastic analysis and flutter control of wings and panels:A review显示文摘Flutter is a self‐excited vibration under the interaction of the inertial force,aero-dynamic force,and elastic force of the structure.After the flutter occurs,the aircraft structures will exhibit limit cycle oscillation,which will cause catastrophic accidents or fatigue damage to the structures.Therefore,it is of great theoretical and practical significance to study the aeroelastic characteristics and flutter control for improving the aeroelastic stability of aircraft structures.This paper reviews the recent advances in aeroelastic analysis and flutter control of wings and panel structures.The me-chanism of aeroelastic flutter of wings and panels is presented.The research methods of aeroelastic flutter for different structures developed in recent years are briefly summarized.Various control strategies including the linear and nonlinear control algorithms as well as the active flutter control results of wings and panels are presented.Finally,the paper ends with conclusions,which highlight challenges of the development in aeroelastic analysis and flutter control,and provide a brief outlook on the future investigations.This study aims to present a comprehensive under-standing of aeroelastic analysis and flutter control.It can also provide guidance on the design of new wings and panel structures for improving their aeroelastic stability. | Yuyang Chai Wei Gao Benjamin Ankay Fengming Li Chuanzeng Zhang | 2021 | International Journal of Mechanical System Dynamics2021，1，1： | 0 |
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