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Flutter and Divergence Analysis using the Generalized Aeroelastic Analysis Method

机译:广义气弹分析法的颤振和发散分析

摘要

The Generalized Aeroelastic Analysis Method (GAAM) is applied to the analysis of three well-studied checkcases: restrained and unrestrained airfoil models, and a wing model. An eigenvalue iteration procedure is used for converging upon roots of the complex stability matrix. For the airfoil models, exact root loci are given which clearly illustrate the nature of the flutter and divergence instabilities. The singularities involved are enumerated, including an additional pole at the origin for the unrestrained airfoil case and the emergence of an additional pole on the positive real axis at the divergence speed for the restrained airfoil case. Inconsistencies and differences among published aeroelastic root loci and the new, exact results are discussed and resolved. The generalization of a Doublet Lattice Method computer code is described and the code is applied to the calculation of root loci for the wing model for incompressible and for subsonic flow conditions. The error introduced in the reduction of the singular integral equation underlying the unsteady lifting surface theory to a linear algebraic equation is discussed. Acknowledging this inherent error, the solutions of the algebraic equation by GAAM are termed 'exact.' The singularities of the problem are discussed and exponential series approximations used in the evaluation of the kernel function shown to introduce a dense collection of poles and zeroes on the negative real axis. Again, inconsistencies and differences among published aeroelastic root loci and the new 'exact' results are discussed and resolved. In all cases, aeroelastic flutter and divergence speeds and frequencies are in good agreement with published results. The GAAM solution procedure allows complete control over Mach number, velocity, density, and complex frequency. Thus all points on the computed root loci can be matched-point, consistent solutions without recourse to complex mode tracking logic or dataset interpolation, as in the k and p-k solution methods.
机译:广义气弹分析方法(GAAM)用于分析三个经过充分研究的检查案例:约束和无约束的机翼模型以及机翼模型。特征值迭代过程用于收敛于复数稳定性矩阵的根。对于机翼模型,给出了确切的根轨迹,可以清楚地说明颤振和发散不稳定性的性质。列举了所涉及的奇点,包括在无约束翼型情况下在原点处有一个额外的极点,在有约束翼型情况下以发散速度在正实轴上出现了一个额外的极点。讨论并解决了已发布的气动弹性根轨迹与新的精确结果之间的不一致和差异。描述了Doublet格子法计算机代码的一般化,并将该代码应用于机翼模型不可压缩和亚音速流动条件的根轨迹计算。讨论了将非稳态提升面理论的奇异积分方程式简化为线性代数方程式时引入的误差。认识到这种固有误差,GAAM代数方程的解被称为“精确”。讨论了问题的奇异性,并显示了用于核函数评估的指数级数逼近,以在负实轴上引入极点和零点的密集集合。再次,讨论并解决了已公布的气动弹性根基因座与新的“精确”结果之间的不一致和差异。在所有情况下,气动弹性颤振和发散的速度和频率与已发表的结果非常吻合。 GAAM解决方案程序可以完全控制马赫数,速度,密度和复数频率。因此,计算的根轨迹上的所有点都可以是匹配点的一致解,而无需求助于k和p-k解方法中的复杂模式跟踪逻辑或数据集插值。

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