基于变可信度模型的飞行器翼结构模态分析  

Modal Analysis of Flight Vehicle Wing Structure Based on Multi-fidelity Surrogate Model

作　　者：张海瑞[1] 李先航 方伟光 吴志培 洪东跑[1] ZHANG Hairui;LI Xianhang;FANG Weiguang;WU Zhipei;HONG Dongpao(China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《宇航学报》2023年第10期1496-1502,共7页Journal of Astronautics

基　　金：国家自然科学基金(U20B2028)。

摘　　要：针对飞行器翼结构的模态快速分析需求,通过研究翼结构几何参数对其模态频率的影响,提出了一种基于变可信度模型的飞行器翼结构模态分析方法。结合翼结构几何模型和有限元模型,采用变可信度模型来描述结构几何参数对模态的影响;针对有限元仿真样本不足的问题,提出了基于序贯加点策略的变可信度模型建模方法,并结合数值算例分析了序贯建模方法的有效性。以飞行器典型梯形翼为应用对象,序贯建模方法能更准确地预测不同尺寸的翼结构模态频率,前3阶模态频率预测偏差在6%以下;利用变可信度模型能够快速分析几何参数对模态频率的影响,为飞行器翼结构设计提供支撑。A modal analysis method based on the multi-fidelity model is proposed for the rapid modal analysis of flight vehicle wing structure by studying the influence of the wing geometry parameters on its modal frequency.Combining the wing geometry model and the finite element model,the multi-fidelity model is used to describe the influence of the structural geometry parameters on the modal frequency.Aiming at the problem of modeling efficiency of small samples,the multi-fidelity model is established by the sequential test method,and the effectiveness of the multi-fidelity modeling based on the sequential test is analyzed with numerical examples.Taking the typical trapezoidal wing of aircraft as the application object,the modeling method based on the sequential test can estimate the modal frequencies of different sizes of wing structures more accurately,and the deviation of the first 3 orders of modal frequencies estimation is below 6%.Using the multi-fidelity model can quickly analyze the influence of geometric parameters on the modal frequencies,which improves the efficiency of aircraft wing structure design.

关 键 词：飞行器 翼结构 模态分析 变可信度模型 序贯采样 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]