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Phenomenology of Nonlinear Aeroelastic Responses of Highly Deformable Joined-wings Configurations

机译:高变形连接翼构型的非线性气动弹性响应现象学

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Dynamic aeroelastic behaviour of structurally nonlinear Joined Wings is presented. Three configurations, two characterized by a different location of the joint and one presenting a direct connection between the two wings (Sensorcraft-like layout) are investigated. As a first step, the snap-divergence is studied from a dynamic perspective in order to assess the real response of the configuration. Later on, the investigations focus on the nutter occurrence (critical state) and go further in analyzing postcritical phenomena: Limit Cycle Oscillations (LCOs) are observed followed by a lost of periodicity of the solution as speed is further increased. In some cases, it is also possible to ascertain the presence of period doubling (flip-) bifurcation. Differences between flutter (Hopf's bifurcation) speed evaluated with linear and nonlinear analyses are discussed in depth, in order to understand if a less computationally intense approach may be used with confidence. Both frequency and time-domain approaches are compared. Moreover, aerodynamic solvers based on the potential flow are critically examined and discussed. In particular, it is assessed in what measure the use of more sophisticated (and computationally more intensive) aerodynamic and interface models impacts the aeroelastic predictions. These differences range from the methods adopted for load transferring to the models employed to describe the wake. When the use of the tools gives different results, a physical interpretation of the leading mechanism generating the mismatch is provided. In particular, for PrandtlPlane-like configurations the aeroelastic response is very sensitive to the wake's shape. As a consequence, it is suggested that a more sophisticated modelling of the wake positively impacts the reliability of aerodynamic and aeroelastic analysis. For Sensorcraft-like configurations some LCOs are characterized by a non-synchronous motion of the inner and outer portion of the lower wing: the wings' tip exhibits a small oscillation during the descending or ascending phase, whereas the mid-span station describes a sinusoidal-like trajectory in the time domain.
机译:提出了结构非线性连接翼的动态气动弹性行为。研究了三种构型,两种构型的特征在于关节的位置不同,而另一种构型则表示两个机翼之间具有直接连接(类似传感器的布局)。第一步,从动态角度研究速散,以便评估配置的实际响应。后来,研究主要集中在小结的发生(临界状态)上,并进一步分析了临界后现象:观察到极限循环振荡(LCO),随后随着速度的进一步提高,解决方案的周期性丧失。在某些情况下,还可以确定周期倍增(翻转)分支的存在。深入讨论了通过线性和非线性分析评估的颤振(霍夫夫分叉)速度之间的差异,以便了解是否可以放心使用计算强度较小的方法。比较了频域和时域方法。此外,对基于势流的空气动力学求解器进行了严格的检查和讨论。特别要评估的是,采用哪种更为复杂(且计算强度更高)的空气动力学和界面模型以何种方式影响空气弹性预测。这些差异从用于负载转移的方法到用于描述尾流的模型不等。当使用这些工具得出不同的结果时,将提供对导致失配的主导机制的物理解释。特别是,对于类似PrandtlPlane的配置,气动弹性响应对尾流的形状非常敏感。因此,建议对尾流进行更复杂的建模会对空气动力学和空气弹性分析的可靠性产生积极影响。对于类似Sensorcraft的配置,某些LCO的特征在于下机翼内部和外部的不同步运动:机翼的尖端在下降或上升阶段表现出较小的振荡,而中跨测站则描述为正弦曲线时域中的类似轨迹。

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