GARTEUR飞机模型的模态试验与模型修正技术

Modal Test and Dynamic Model Updating for GARTEUR Aircraft Model

为了获得精确的结构动力学模型,需要对结构动力学模型进行修正与确认。首先,采用相位共振/相位分离一体化技术对模型进行模态参数识别。其次,提出一种设计参数的灵敏度分析方法,根据工程经验、误差定位技术以及灵敏度分析技术调整动力学模型的建模细节,以试验与仿真结果的模态频率误差为目标函数,研究了序列二次规划算法、自适应模拟退火算法、多岛遗传算法等三种算法的修正效果,最终选择多岛遗传算法进行动力学模型修正研究。最后,引入三级质量标准来评估模型修正质量。结果表明:修正后的模型具有复现与预测响应水平的能力,证明本文所提出修正方法的正确性和有效性。

In order to obtain an accurate structural dynamics model,it is necessary to modify and validate the model. Firstly,the phase resonance/phase separation integration technique is used to identify the modal parameters of the model. Secondly,a sensitivity analysis method for design parameters is proposed,the modeling details of the dynamic model are adjusted according to engineering experience,error location technology and sensitivity analysis technology. The modal frequency error of the test and simulation results is taken as the objective function,and the updating effects of three algorithms,such as sequential quadratic programming algorithm,adaptive simulated annealing algorithm and multi-island genetic algorithm,are studied,finally multi-island genetic algorithm is selected for dynamic model modification research. Finally,a three-level quality criteria is introduced evaluate the quality of the model updating. The results show that the modified model has the ability to reproduce and predict the response level,the correctness and effectiveness of the proposed correction method is verified.