稀疏灰色预测模型学习及其在飞机搭接结构疲劳寿命预测中的应用。

Lu Yang, Qiuhui Xu, Baolei Wei, Naiming Xie, Shenfang Yuan
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引用次数: 0

摘要

灰色预测模型研究中的一个关键挑战是模型结构发现:将测量数据转换为不仅具有预测性的方程,而且可以更深入地了解观测中固有的潜在动态。主要的方法依赖于累积和算子,这是一种基于知识的技术,需要具有良好特征的形状和广泛的经验经验。在这项工作中,我们提出了一种数据驱动建模的范式,该范式同时学习灰色预测模型的结构并估计每个观测点的测量噪声。首先,在利用灰色模型的积分表示作为状态方程的状态空间框架的背景下,设计候选特征库以显式描述模型方程,可能以冗余形式,并通过稀疏学习求解。然后,结合信噪分解和时间步进约束,构造正则化目标函数,共同学习模型结构和噪声。其次,设计了大规模仿真来研究该方法的有限样本性能,包括模型结构识别精度、预测精度和去噪能力。结果表明,该方法具有较高的模型结构学习精度和对测量噪声的鲁棒性。最后对飞机搭接接头进行疲劳试验,收集裂纹扩展数据。应用该方法揭示了飞机搭接结构疲劳裂纹演化的动态规律,并对其剩余使用寿命进行了预测。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Sparse grey forecasting model learning and applications to fatigue life prediction of aircraft lap joint structures.

A key challenge in the study of grey forecasting models is model structure discovery: converting measurement data into equations that are not only predictive, but provide a deeper understanding of the underlying dynamics inherent in the observations. The predominant approach relies on the cumulative sum operator, a knowledge-based technique that requires a well-characterized shape and extensive empirical experience. In this work, we propose a paradigm for data-driven modelling that simultaneously learns the structures of grey forecasting models and estimates the measurement noise at each observation. First, in the context of a state-space framework utilizing the integral representation of the grey model as a state equation, a candidate feature library is designed to explicitly depict the model equation, likely in a redundant form, and solved by sparse learning. Then, by combining signal-noise decomposition and time-stepping constraints, a regularized objective function is formulated to jointly learn model structure and noise. Next, large-scale simulations are designed to investigate the finite sample performance of the proposed method, including model structural identification accuracy, forecasting accuracy, and denoising capability. The results demonstrate high accuracy in model structure learning and robustness to measurement noise. Finally, we conduct fatigue testing on aircraft lap joints to collect crack propagation data. The proposed method is then applied to uncover dynamic patterns in the evolution of fatigue cracks and predict the remaining useful life of aircraft lap joint structures.

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