Aeroservoelastic Computations in Unsteady Transonic Flow
Aeroservoelastic Computations in Unsteady Transonic Flow
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DOI：
10.2514/6.2000-4226
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发表时间：
2000-08
期刊：
影响因子：
--
通讯作者：
L. Djayapertapa;C. Alien
中科院分区：
文献类型：
--
作者：
L. Djayapertapa;C. Alien
提出了一种跨声速气动弹性和气动伺服弹性计算的时间域方法，并用于预测二维翼剖面的稳定性(颤振)边界。气动模型是一种以网格为中心的有限体积非定常欧拉求解方法，采用高效的隐式时间推进格式和结构化的运动网格。气动方程与结构运动方程相耦合，这些运动方程是由一个典型的机翼截面模型导出的。在气动弹性解算器中实施了控制律，以研究通过操纵面运动抑制颤振的主动方法。开环和闭环计算结果的比较表明，该控制律能有效地抑制颤振，并使允许速度指标提高19%。
A computational method to perform transonic aeroelastic and aeroservoelastic calculations in the time domain is presented, and used to predict stability (flutter) boundaries of 2-D wing sections. The aerodynamic model is a cell-centred finite-volume unsteady Euler solver, which uses an efficient implicit time-stepping scheme and structured moving grids. The aerodynamic equations are coupled with the structural equations of motion, which are derived from a typical wing section model. A control law is implemented within the aeroelastic solver to investigate active means of flutter suppression via control surface motion. Comparisons of open and closed loop calculations show that the control law can successfully suppress the flutter and results in an increase of up to 19% in the allowable speed index.