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| Model of Large Spacecraft Integrated Structure-Control-Optical and Fast Calculation of Micro-vibration Response |
| Received:March 31, 2020 Revised:April 01, 2020 |
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| DOI：10.7643/issn.1672-9242.2020.06.001 |
| KeyWord:integrated model micro-vibration response additional stiffness method fast calculation |
| Author | Institution |
| LI Jian-hong-yu |
National key Laboratory of Science and Technology on Reliability and Environmental Engineering, Beijing Institute of Spacecraft Environment Engineering, Beijing , China |
| PANG He-wei |
China Academy of Space Technology, Beijing , China |
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| Abstract: |
| The paper aims to control the calculation cost of integrated model for large spacecraft. The state-space method and the additional stiffness method were used to build the structure-control-optical integration model and solve the micro-vibration response. The sparse matrix LU decomposition method and iterative method were used to solve linear equations to accelerate the solution speed of the micro-vibration response. An integrated model was established for a large spacecraft and the micro vibration response was solved. The total time was 10.35s, among which the time used to calculate the 2794 frequency points by iterative method was 7.20s, and that used to calculate 6 frequency points by sparse LU decomposition method was 3.15s. Numerical examples show the efficiency of the method. It is an efficient algorithm for the prediction of micro vibration of large spacecraft in practical engineering. |
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