A Computational Method for Structurally Nonlinear Joined Wings Based on Modal Derivatives
A Computational Method for Structurally Nonlinear Joined Wings Based on Modal Derivatives
复制标题
DOI：
10.2514/6.2014-0494
复制
发表时间：
2014-01
期刊：
影响因子：
--
通讯作者：
N. Teunisse;L. Demasi;P. Tiso;R. Cavallaro
中科院分区：
文献类型：
--
作者：
N. Teunisse;L. Demasi;P. Tiso;R. Cavallaro
过去的研究表明，联接翼的过约束性质和强的结构几何非线性使得难以使用标准的气动弹性求解器包（通常是模态简化的和基于频域的），这些求解器包已被工业界有效地采用了几十年。我们在这里提出了一个研究的计算成本的减少存在的结构非线性效应，不能忽视的连接翼，即使在小迎角和附着流。特别是，实现了一个降阶模型的基础上增加相应的模态导数的振动模式。与全阶参考解决方案相比，结果可以被认为是优秀的。然而，收敛性测试表明，所需的向量数量相对较高，并且需要经常更新基以实现最佳性能。为了在工业中有效地使用，需要进行更多的研究，并使涉及空气动力学非定常性的动力学问题复杂化。
Past studies showed that the overconstrained nature of Joined Wings and the strong structural geometric nonlinearities make difficult the use of standard packages of aeroelastic solvers (usually modally reduced and frequency domain based) which have been effectively adopted by the industry for decades. We present here a study on the reduction of the computational cost in presence structural nonlinear effects that cannot be neglected in Joined Wings, even at small angles of attack and attached flow. In particular, a reduced order model is achieved with a basis constituted by vibration modes augmented with the corresponding modal derivatives. The results can be considered excellent when compared to the full order reference solution. However, a convergence test showed that the required number of vectors is relatively high and the basis needs to be often updated to achieve the best performance. More investigations will be necessary for an effective use in the industry and complicate dynamic problems involving the unsteadiness of the aerodynamics.