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| Finite Element - Boundary Element Method Simulation for Acoustic-Vibration Problems of Spacecraft Structures |
| Received:August 08, 2018 Revised:November 25, 2018 |
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| DOI：10.7643/ issn.1672-9242.2018.11.007 |
| KeyWord:spacecraft acoustic-vibration coupling numerical simulation finite element-boundary element method |
| Author | Institution |
| FENG Jin-long |
Beijing Machinery Electricity Research Institute, Beijing, , China |
| WANG Hong-hong |
Beijing Machinery Electricity Research Institute, Beijing, , China |
| ZHAO Ying |
Beijing Machinery Electricity Research Institute, Beijing, , China |
| WANG Yi-nan |
Beijing Machinery Electricity Research Institute, Beijing, , China |
| DU Li-gang |
Beijing Machinery Electricity Research Institute, Beijing, , China |
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| Abstract: |
| 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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