增材制造点阵动力学性能的变截面梁修正方法  

Dynamic simulation of additively manufactured lattice structures based on variable cross-section beam elements

作　　者：朱熙 孟亮[1] 张靖[1] 王锦涛 高彤[1] 朱继宏[1] 张卫红[1] ZHU Xi;MENG Liang;ZHANG Jing;WANG Jintao;GAO Tong;ZHU Jihong;ZHANG Weihong(Shaanxi Key Laboratory of Aerospace Structures,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学陕西省空天结构技术重点实验室,西安710072

出　　处：《航空工程进展》2024年第6期164-173,共10页Advances in Aeronautical Science and Engineering

基　　金：国防基础科研计划资助(JCKY2022205B020)。

摘　　要：增材制造点阵结构在航空航天先进结构设计领域的应用日趋广泛,对大规模点阵结构静动力学性能的高精高效仿真分析提出了迫切需求。提出增材制造点阵结构变截面梁修正的仿真分析方法,依据3D打印点阵结构动力学响应,构建并求解变截面梁单元几何参数的反问题模型,针对不同杆径尺寸(直径1.00~2.00 mm)点阵结构,分别开展变截面梁参数的反问题标定;建立变截面梁几何参数随杆径变化的插值模型,并针对不同杆径尺寸点阵结构和梯度点阵开展变截面梁几何参数插值模型的有效性验证。结果表明:本文建立的增材制造点阵结构变截面梁单元仿真分析模型与基于实体单元的模型相比,同等精度下,动力学性能分析效率提升显著,有望为复杂梯度点阵结构的动力学优化设计提供高效准确的模型基础。To meet the high-precision and efficient simulation needs for the static and dynamic performance of largescale lattice structures,this paper proposes a simulation analysis method for the calibration of tapered beams in lattice structures.Based on the dynamic response of 3D printed specimen,an inverse problem model for the geometric parameters of the tapered beam element is established and solved.For lattice structures with different diameters,the inverse problem calibration of the tapered beam parameters is carried out respectively,and an interpolation model for the geometric parameters of the tapered beam as a function of rod diameter is established.Finally,the effectiveness of the interpolation model for the geometric parameters of the variable cross-section beam is verified for lattice structures with different rod diameters and gradient lattices.Results show that:compared with the solid element model-based simulation analysis model,the simulation analysis model of tapered beam element established in this study not only has comparable dynamic performance simulation accuracy but also significantly improves the efficiency of analysis.

关 键 词：增材制造 点阵结构 变截面梁 反问题求解 动力学仿真 

分 类 号：V214.19[航空宇航科学与技术—航空宇航推进理论与工程] V414.19