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| Modal Test and Simulation Analysis of Multi-lattice Structure |
| Received:August 10, 2024 Revised:September 06, 2024 |
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| DOI：10.7643/issn.1672-9242.2024.09.014 |
| KeyWord:airborne equipment integrated structure top control panel modaltest modal parameters modal simulation vibration characteristic |
| Author | Institution |
| WANG Yao |
AVIC the First Aircraft Institute, Xi'an , China |
| QIN Jin |
AVIC the First Aircraft Institute, Xi'an , China |
| GAO Peng |
AVIC the First Aircraft Institute, Xi'an , China |
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| Abstract: |
| The work aims to carry out modal tests and simulation model correction with a large integrated top control panel as an example. Firstly, the principle, measuring points andtest proceduresof modal tests were briefly described. In order to understand its inherent vibration characteristics in multi-dimensions, modal tests of different boundary states were designed, including free boundary before assembly of internal equipment, free boundary and the fixed-supported boundary after assembly of internal equipment. Finally, the accuracy of the test results were verified by modal indication function, and the vibration modal parameters (natural frequency, mode shape, damping ratio, etc.) were obtained, then the results of modal tests and modal simulation were compared. It is shown that the modified dynamic finite element model can be used for the vibration characteristic analysis and optimization design of the top control plate. |
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