摘要
机翼极限环振荡(LCO)是典型的非线性气动弹性问题,严重的会造成机翼的结构破坏。为了精确捕捉极限环振荡初始临界点,准确预测极限环的幅值,为机翼的设计提供准确的数据参考,本文综合考虑了气动与结构非线性的影响,提出了一种松耦合气动弹性仿真方法。在子迭代过程中分别采用LUSGS双时间推进和多步推进法交替求解气动和结构动力学方程;一种高效的插值技术应用于耦合界面数据的映射与传递;采用精确动网格技术模拟气体的非定常流动。对标准模型切尖三角翼的跨音速极限环振荡的计算与分析,表明相比同类仿真方法,通过此方法得到结果与实验值吻合更好;证明了结构几何非线性与气动非线性是诱发LCO的重要原因。耦合仿真方法保真度高,能为强非线性结构的强度设计提供重要依据。
The limit cycle oscillation （LCO） of wings is one of the typical nonlinear aeroelasticity phenomenon. Accurate emulation platform is provided to calculate the critical dynamic pressure and the amplitude of LCOs, which will be useful to the wing＇s aerodynamic and structural design. The platform provides a new time domain computational aeroelastic model, which includes a well-validated NS difference solver with the LUSGS scheme coupled a high-fidelity nonlinear finite element f structure solver in MSCiNastran by using highly efficient interpolation method and moving mesh generation technology. The emulation of the cropped delta wing＇s LCO behavior based on this platform provides a high-fidelity result compared to the experimental data. The result shows geometric nonlinearity and complex fluid are the most important inducements to come into LCO, and the platform is proved to be able to provide an reliable reference basis for structural design.
出处
《电子设计工程》
2013年第13期4-8,共5页
Electronic Design Engineering
基金
国家自然科学基金(90816008
11202165)
