发表机构
GISPA, Facultad Politécnica, Universidad Nacional de Asunción（亚松森国立大学理工学院 GISPA）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
本研究利用频率与阻尼的物理关系，通过耦合审计的SU2欧拉模拟和临界极点轨迹约束，将近颤振阻尼识别精度提升约3.9倍，并将所需观测记录从15周期减至5周期。
AI 中文摘要
在近颤振状态下，模态频率可以通过累积相位很好地解析，而小的模态增长率符号仍然不确定，因为响应包络在有限记录上仅微弱变化。本研究测试了经过验证的频率与阻尼之间的物理关系是否可以利用解析更好的相位信息来改进近颤振稳定性识别。针对马赫数0.85下改进的Isogai参数化NACA 64A010翼型，开展了一项耦合审计的SU2欧拉计算活动，并进行了系统的网格和时间验证、多通道临界极点跟踪、自举轨迹闭合、有限记录信息分析以及非线性蒙特卡洛验证。时间研究表明，每个结构周期50步虽然频率已接近更精细解，但预测了错误的阻尼符号。经过验证的临界轨迹给出了颤振速度指数0.537665和局部频率-阻尼斜率3.754。将自由极点估计限制在该轨迹上，可获得约3.89倍的阻尼精度提升，蒙特卡洛模拟重现了这一结果，中位数RMSE增益为3.915。在代表性运行偏移和30 dB幅度信噪比下，超过95%正确符号概率的最小测试记录从15个周期减少到5个周期。因此，经过物理验证的极点轨迹可以大幅减少可靠近边界气动弹性稳定性识别所需的观测时间。
英文摘要
Near flutter, modal frequency can be well resolved from accumulated phase while the sign of a small modal growth rate remains uncertain because the response envelope changes only weakly over a finite record. This work tests whether a validated physical relation between frequency and damping can exploit the better-resolved phase information to improve near-flutter stability identification. A coupling-audited SU2 Euler campaign for a modified Isogai-parameterized NACA 64A010 section at Mach 0.85 is subjected to systematic grid and temporal verification, multichannel critical-pole tracking, bootstrap trajectory closure, finite-record information analysis, and nonlinear Monte Carlo validation. The temporal study shows that 50 steps per structural period predict the wrong damping sign although frequency is already close to the finer solutions. The verified critical trajectory gives a flutter-speed index of 0.537665 and a local frequency-to-damping slope of 3.754. Restricting a free pole estimate to this trajectory gives an approximately 3.89-fold damping-precision gain, reproduced by Monte Carlo with a median RMSE gain of 3.915. At a representative operating offset and 30 dB amplitude SNR, the minimum tested record exceeding 95% correct-sign probability decreases from 15 to 5 cycles. Physically validated pole trajectories can therefore substantially reduce the observation time required for reliable near-boundary aeroelastic stability identification.
