| 冯金龙,王宏宏,赵营,王一楠,杜骊刚.航天器结构声振耦合问题的有限元-边界元方法数值仿真研究[J].装备环境工程,2018,15(11):37-43. FENG Jin-long,WANG Hong-hong,ZHAO Ying,WANG Yi-nan,DU Li-gang.Finite Element - Boundary Element Method Simulation for Acoustic-Vibration Problems of Spacecraft Structures[J].Equipment Environmental Engineering,2018,15(11):37-43. |
| 航天器结构声振耦合问题的有限元-边界元方法数值仿真研究 |
| Finite Element - Boundary Element Method Simulation for Acoustic-Vibration Problems of Spacecraft Structures |
| 投稿时间：2018-08-08 修订日期：2018-11-25 |
| DOI：10.7643/ issn.1672-9242.2018.11.007 |
| 中文关键词: 航天器 声振耦合 数值仿真 有限元-边界元方法 |
| 英文关键词:spacecraft acoustic-vibration coupling numerical simulation finite element-boundary element method |
| 基金项目: |
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| Author | Institution |
| FENG Jin-long | Beijing Machinery Electricity Research Institute, Beijing, 100854, China |
| WANG Hong-hong | Beijing Machinery Electricity Research Institute, Beijing, 100854, China |
| ZHAO Ying | Beijing Machinery Electricity Research Institute, Beijing, 100854, China |
| WANG Yi-nan | Beijing Machinery Electricity Research Institute, Beijing, 100854, China |
| DU Li-gang | Beijing Machinery Electricity Research Institute, Beijing, 100854, China |
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| 中文摘要: |
| 针对高超声速、结构轻量化带来的航天器复杂结构声振耦合动力学环境难以精准预示问题，提出一种基于有限元-边界元（FEM-BEM）方法的声振耦合问题数值仿真方法。分析国内外求解声振耦合问题的主要数值仿真方法，从影响航天器性能设计的低中频声振耦合动力学特性入手，采用有限元-边界元方法，以航天器典型结构截锥壳为研究对象，开展混响噪声作用下的声振耦合研究。建立了声振耦合模型，获得了主体结构、主要支撑结构及设备的声振耦合响应。提出的数值仿真方法和仿真分析过程，为航天器声振耦合分析提供了理论基础和仿真手段。 |
| 英文摘要: |
| A numerical simulation technology based on finite element-boundary element method (FEM-BEM) method was proposed to solve the acoustic-vibration problem of spacecraft structures caused by hypersonic speed flights and lightweight structure applications. Main numerical simulation methods on acoustic-vibration coupling at home and abroad were studied. To obtain dynamic characteristics of the low-medium frequency affecting design of spacecraft performance, the FEM-BEM was used to establish an acoustic-vibration coupling model of the typical structure of the spacecraft. The acoustic-vibration coupling response in the case of reverberant noise was carried out, and the acoustic-vibration coupling response of body and main support structure was obtained. The numerical simulation method and simulation analysis process presented in this paper provide theoretical basis and simulation reference for the acoustic-vibration coupling analysis of spacecraft. |
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