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首页> 外文会议>AIAA/ASME/ASCE/AHS/ASC structures, structural dynamics and materials conference >CFD-CSD Coupled Aeroelastic Analysis of Flexible Flapping Wings for MAV Applications: Methodology Validation
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CFD-CSD Coupled Aeroelastic Analysis of Flexible Flapping Wings for MAV Applications: Methodology Validation

机译：用于MAV应用的柔性拍打翼的CFD-CSD耦合气动弹性分析：方法学验证

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A coupled CFD-CSD solver is used to simulate the aerodynamics of a flexible flapping wing. The CFD solver is a compressible R.ANS solver. The free general-purpose multi-body dynamics solver MBDyn is used as the structural solver after an extension to take into account non linear shell straining, making it possible to analyze plates with large deformations. Validation of the two codes for flapping wings/plates is carried out independently. The solvers are then coupled and validated against prior experiments and analysis on a spanwise flexible wing at Re = 30,000. It is observed that due to flexibility, the average chordwise propulsive force, C_t increases by 47% as a result of increase in plunge amplitude, effective angle of attack and leading edge suction towards the outer sections as compared to for a rigid wing. Additionally, the flexible wing has higher 3D flow. Then, a chordwise flexible root flapping wing is analyzed using the solver at Re = 10,000. As a result of the flexibility, camber is induced in the wing as it flaps. Highly 3D flow was observed with the strength of the vortices increasing from root to tip. Due to camber in the wing, the resultant force is vectored more in the chordwise direction as compared to for rigid wings, which results in higher thrust. The average C_t increased by 25% and average C_l increased by 10%. The current work demonstrates the capability of an aeroelastic solver to characterize the flowfield of a flexible flapping wing MAV in 3D.
机译：耦合的CFD-CSD求解器用于模拟柔性襟翼的空气动力学。 CFD求解器是可压缩的R.ANS求解器。免费的通用多体动力学求解器MBDyn在扩展后用作结构求解器，以考虑非线性壳体应变，从而可以分析变形较大的板。拍打机翼/襟翼的两个代码的验证是独立进行的。然后，求解器在Re = 30,000的翼展方向挠性机翼上进行耦合，并针对先前的实验和分析进行了验证。可以看出，由于柔韧性，与刚性机翼相比，由于插入幅度，有效攻角和前缘向外部的吸力增加，平均弦向推进力C_t增加了47％。此外，柔性机翼具有更高的3D流动性。然后，使用求解器在Re = 10,000时分析弦向柔性根扑翼。由于柔韧性，在机翼拍打时会在机翼中引起外倾。观察到高3D流动，并且涡流的强度从根部到尖端逐渐增加。由于机翼中的外倾角，与刚性机翼相比，合力在弦向方向上的矢量更多，这导致更大的推力。平均C_1增加了25％，并且平均C_1增加了10％。当前的工作展示了气动弹性求解器在3D模式下表征柔性扑翼MAV流场的能力。

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