Versatile Absolute Nodal Coordinate Formulation Model for Dynamic Folding Wing Deployment and Flutter Analyses
Versatile Absolute Nodal Coordinate Formulation Model for Dynamic Folding Wing Deployment and Flutter Analyses
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DOI：
10.1115/1.4041022
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发表时间：
2018-09
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影响因子：
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通讯作者：
Keisuke Otsuka;Yinan Wang;Kanjuro Makihara
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文献类型：
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作者：
Keisuke Otsuka;Yinan Wang;Kanjuro Makihara
使用变形机翼技术可以提高飞机性能，其中机翼可以在飞行条件下展开和折叠，提供宽的飞行包线，良好的燃油效率，并减少存储飞机所需的空间。由于机翼的展开是一个包含大刚体运动和大弹性变形的非线性耦合运动，因此需要非线性折叠机翼模型进行必要的时域展开仿真，而线性模型则需要进行频域颤振分析。本文的目的是提出一个通用的模型，可应用于时域和频域分析的折叠翼，基于柔性多体动力学（MBD），使用绝对节点坐标公式（ANCF）和非定常空气动力学。这种新的通用模型扩展了在时域仿真中使用ANCF的柔性MBD的应用范围，使其能够表达下一代飞机中出现的极大弹性变形和大刚体运动的耦合运动。使用该模型进行的时域部署仿真是有用的参数化部署系统的设计，因为该模型具有改善的计算时间。在折叠翼的频域颤振分析中，由该模型得到的颤振速度与实验结果一致，误差为4.0%，显示出应用于下一代飞机设计的前景。
Aircraft performance can be improved using morphing wing technologies, in which the wing can be deployed and folded under flight conditions, providing a wide flight envelope, good fuel efficiency, and reducing the space required to store the aircraft. Because the deployment of the wing is a nonlinear-coupled motion comprising large rigid body motion and large elastic deformation, a nonlinear folding-wing model is required to perform the necessary time-domain deployment simulation, while a linear model is required to perform the frequency-domain flutter analysis. The objective of this paper is to propose a versatile model that can be applied to both the time-domain and frequency-domain analyses of a folding wing, based on flexible multibody dynamics (MBD) using absolute nodal coordinate formulation (ANCF) and unsteady aerodynamics. This new versatile model expands the application range of the flexible MBD using ANCF in time-domain simulation, allowing it to express the coupled motion of extremely large elastic deformations and large rigid body motions that arise in next-generation aircraft. The time-domain deployment simulation conducted using the proposed model is useful for parametric deployment-system design because the model has improved calculation time. In the frequency-domain flutter analysis of a folding wing, the flutter speed obtained from the proposed model agrees with that obtained from an experiment, with an error of 4.0%, showing promise for application in next-generation aircraft design.