季开云, 杨加明. 基于CFD/CSD大展弦比复合材料机翼的气动弹性分析[J]. 南昌航空大学学报(自然科学版), 2017, 31(2): 1-6. DOI: 10.3969/j.issn.1001-4926.2017.02.001
引用本文: 季开云, 杨加明. 基于CFD/CSD大展弦比复合材料机翼的气动弹性分析[J]. 南昌航空大学学报(自然科学版), 2017, 31(2): 1-6. DOI: 10.3969/j.issn.1001-4926.2017.02.001
JI Kai-yun, YANG Jia-ming. Aeroelastic Analysis of High-aspect Ratio Composite Wing Based on CFD/CSD[J]. Journal of nanchang hangkong university(Natural science edition), 2017, 31(2): 1-6. DOI: 10.3969/j.issn.1001-4926.2017.02.001
Citation: JI Kai-yun, YANG Jia-ming. Aeroelastic Analysis of High-aspect Ratio Composite Wing Based on CFD/CSD[J]. Journal of nanchang hangkong university(Natural science edition), 2017, 31(2): 1-6. DOI: 10.3969/j.issn.1001-4926.2017.02.001

基于CFD/CSD大展弦比复合材料机翼的气动弹性分析

Aeroelastic Analysis of High-aspect Ratio Composite Wing Based on CFD/CSD

  • 摘要: 高空长航时无人机在飞行过程中受气动力的影响,机翼产生弯曲和扭转变形,这种弹性变形将严重影响飞机的飞行性能和飞行安全,不能将这种飞机机翼当作传统的刚性机翼进行气动分析。针对一大展弦比复合材料机翼,采用气动/结构耦合的分析方法,利用计算流体力学(CFD)软件FLUENT和计算结构动力学(CSD) ABAQUS联合求解,研究了大展弦比复合材料机翼在不同攻角下和复合材料的各向异性对机翼气动特性的影响。结果表明,大展弦比复合材料机翼受载变形之后机翼的升力系数,升阻比都比刚性体机翼略小,但是随着攻角的增加,弹性体机翼升力系数增加较快,甚至会超过刚体机翼的升力系数。调整机翼蒙皮处的碳纤维铺层角,气动特性变化明显,当铺层角在±45°时机翼扭转刚度达到最大;升力系数和升阻比达到最大。

     

    Abstract: The aerodynamic performance and flying safety of HALE (High Altitude and Long Endurance) UAVs are largely affected by the aeroelastic distortion of its large aspect ratio wing. Large aspect ratio wing of UAV is bended and twisted by the air load during flight and thus is not to be treated as a traditional rigid wing. The effect of static aeroelastic distortion to the aeroelasticity is analyzed for a large aspect ratio composite wing under different angle of attack statuses and the anisotropy of composite. The integrated design method combining aerodynamics with structural dynamics is adopted by computational fluid dynamics (CFD) program Fluent and computational structural dynamics (CSD) program ABAQUS. The results show that a lift coefficient? and lift drag ratio drop, but with the increase of angle of attack, the lift coefficient of the elastic wing increases faster, even more than the rigid body wing. The aerodynamic characteristics are obviously changed by adjusting the carbon fiber ply angle at the wing skin. When the ply angle is ±45°, the torsional rigidity of the wing reaches the maximum, and the lift coefficient and lift drag ratio are the largest.

     

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