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长航时无人机在飞行过程中受气动载荷影响,其大展弦比机翼产生弯曲和扭转变形,这种弹性变形严重影响飞机的飞行性能和飞行安全,不能将此种飞机机翼当作传统的刚性机翼进行气动分析.针对一真实复合材料大展弦比前掠机翼,采用气动/结构一体化的分析方法,利用计算流体动力学(CFD)软件FLUENT和计算结构动力学(CSD)软件NASTRAN联合求解,研究了在不同载荷情况下大展弦比柔性机翼静气动弹性变形对机翼气动特性的影响.结果表明,大展弦比无人机机翼受载变形后升阻比降低,滚转力矩和偏航力矩显著增大,对飞机的纵向和横侧向气动性能产生不利影响,同时也证明此CFD/CSD耦合计算方法可以应用到柔性机翼的气动/结构一体化设计中.
Long flight unmanned aerial vehicle during the flight by the aerodynamic load, the large aspect ratio wing bending and torsion deformation, such a serious impact on the flexibility of the aircraft flight performance and flight safety, can not be such aircraft wing The traditional rigid wing is used for aerodynamic analysis. For a real composite material with large aspect ratio sweep front wing, the aerodynamic / structural integrated analysis method is used, and CFD software FLUENT and structural dynamics CSD) software NASTRAN was used to study the influence of static aerodynamic elastic deformation of flexible wing with large aspect ratio on wing aerodynamic performance under different loads. The results show that the large aspect ratio UAV wing is subjected to deformation The drag reduction, roll torque and yaw moment increase significantly, which have an adverse effect on the aerodynamic performance of the aircraft in both longitudinal and lateral directions. It also proves that the CFD / CSD coupling calculation method can be applied to the aerodynamic / structural integration of the flexible wing In the design.