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| Modal Analysis of the Whole Launch Vehicle Based on Three-Dimensional Dynamic Numerical Model and Test Data Reuse Techniques |
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| DOI：10.7643/issn.1672-9242.2022.09.016 |
| KeyWord:three-dimensional structural dynamic model model synthesis method connection stiffness modal parameters |
| Author | Institution |
| LI Shuang |
Beijing Institute of Structure and Environment Engineering, Beijing , China |
| ZHU Xi-quan |
Beijing Institute of Structure and Environment Engineering, Beijing , China |
| HONG Liang-you |
Beijing Institute of Structure and Environment Engineering, Beijing , China |
| YANG Shu-tao |
Beijing Institute of Astronautical Systems Engineering, Beijing , China |
| LIU Liang |
Beijing Institute of Structure and Environment Engineering, Beijing , China |
| LIU Si-hong |
Beijing Institute of Structure and Environment Engineering, Beijing , China |
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| Abstract: |
| Obtaining accurate modal data of the whole launch vehicle can provide the key input data in the overall design. In order to solve the problem of obtaining high-efficiency and high-precision of dynamic characteristic data of the whole launch vehicle, an acquisition method of modal parameters, integrating the three-dimensional high-precision dynamic numerical model, reuse techniques of test data, multi-state model updating method and model synthesis method, is proposed and practiced on the basis of the model synthesis theory and test data. Under the premise of unknown interface connection stiffness, the high-precision modal parameters of whole launch vehicle is predicted, and the high-precision dynamic characteristic data is given during the design process of vehicle. The error between the numerical analysis results and the test results is less than 2% in first-order bending frequency, and less than 4% in first-order bending slope. Moreover, the numerical results are in good agreement with the verification results of range vertical modal test and the first-flight test. With the verification of range vertical modal test and the first-flight test, the virtual-real combination method proposed in this paper can obtain the dynamic characteristic parameters of whole launch vehicle efficiently and reliably. |
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