Numerical Investigations of Subscale Flexible High Aspect Ratio Aircraft on a Dynamic Wind Tunnel Rig
Numerical Investigations of Subscale Flexible High Aspect Ratio Aircraft on a Dynamic Wind Tunnel Rig
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DOI：
10.2514/6.2023-1559
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发表时间：
2023-01
期刊：
影响因子：
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通讯作者：
Punsara D. Banneheka Navaratna;Alessandro Pontillo;D. Rezgui;M. Lowenberg;S. Neild;J. Cooper
中科院分区：
文献类型：
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作者：
Punsara D. Banneheka Navaratna;Alessandro Pontillo;D. Rezgui;M. Lowenberg;S. Neild;J. Cooper
大展弦比机翼由于其能够提高现代飞机的气动效率而一直是研究的主要课题。许多数值研究表明，它们的柔性通过几何效应引起非线性，它们对内部载荷和动力学的影响，如降低颤振速度和与飞机机身耦合引起机身自由颤振。文献中已有验证悬臂机翼模型的实验工作，但只有少数在动态安装的全翼展飞机模型上进行了风洞试验。本文提出的工作是建立一个五自由度机动风洞试验平台的刚柔耦合数值模型。该模型用于仿真一个全翼展的柔性模型飞机的约束的钻机的调查之间的耦合的刚体和柔性模式以及几何非线性效应。机翼柔性的建模是基于与涡格气动力模型相联系的降阶几何精确结构方法。飞机的机身和尾翼，以及操纵装置，被建模为刚体。这项研究的结果将有助于未来的实验风洞探索。
High aspect ratio wings have been a major topic for research due to their capability to improve the aerodynamic efficiency of modern aircraft. Many numerical studies have shown their flexibility causing nonlinearity through geometric effects and their impact on internal loads and dynamics, such as reduced flutter speed and coupling with the aircraft body causing body freedom flutter. Experimental work is present in the literature for validation of cantilever wing models but only a few have implemented wind tunnel testing on dynamically-mounted full-span aircraft models. The work presented here develops a rigid-flexible coupled numerical model for a wind tunnel test platform known as the 5-degree-of-freedom manoeuvre rig. This model is used for the simulation of a full-span flexible model aircraft constrained by the rig for the investigation of the coupling between rigid body and flexible modes together with geometric nonlinear effects. The modeling of the wing flexibility is based on a reduced order geometrically exact structural method linked with a vortex lattice aerodynamic model. The aircraft fuselage and empennage, and the manoeuvre rig, are modelled as rigid bodies. The findings of the study will aid future experimental wind tunnel explorations.