In general, there is a mismatch between a finite element model of a structure and its real behaviour. In aeronautics, this mismatch must be small because finite element models are a fundamental part of the development of an aircraft and of increasing importance with the trend to more flexible wings in modern designs. Finite element model updating can be computationally expensive for complex structures and surrogate models can be employed to reduce the computational burden. A novel approach for finite element model updating, namely assembly-like, is proposed and validated using real experimental data. The assembly-like model updating framework implies that the model is updated as parts are assembled. Benchmarking against the classical global, or one-shot, approach demonstrates that the proposed method is more computationally efficient since it takes 20% fewer iterations to obtain convergence, of which 95% comes from the subassembly models, which have fewer degrees of freedom and so are more computationally efficient. Despite requiring fewer model evaluations, the new approach retains the fidelity, within 1% of a joint natural frequencies and modal shapes index, of the global approach.

翻译：通常，结构的有限元模型与其实际行为之间存在不匹配。在航空领域，这种不匹配必须很小，因为有限元模型是飞机研发的基本组成部分，并且随着现代设计中更柔性机翼的趋势，其重要性日益增加。对于复杂结构，有限元模型更新可能计算成本高昂，而代理模型可用于减轻计算负担。本文提出并利用真实实验数据验证了一种新颖的有限元模型更新方法，即类装配式方法。类装配式模型更新框架意味着模型在部件装配过程中进行更新。与经典的全局（或一次性）方法进行基准测试表明，所提出的方法计算效率更高，因为它需要少20%的迭代次数即可达到收敛，其中95%来自子装配体模型，这些模型具有更少的自由度，因此计算效率更高。尽管需要更少的模型评估次数，新方法仍保持了与全局方法相当的保真度，在连接点固有频率和模态振型指标上的差异在1%以内。