|
| Random Vibration Response Analysis of Aircraft with Pulsating Pressure Excitation Based on PANDA Platform |
| Received:February 03, 2021 Revised:February 13, 2021 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/issn.1672-9242.2021.03.007 |
| KeyWord:PANDA platform free state multi-point pulsating pressure excitation random vibration finite element analysis |
| Author | Institution |
| WANG Ke-ying |
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang , China |
| HU jie |
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang , China |
| FAN Xuan-hua |
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang , China |
| NIU Hong-pan |
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang , China |
|
| Hits: |
| Download times: |
| Abstract: |
| In order to form autonomous and contrallable numerical simulation and prediction technology of reentry flight, in this paper, based on self-developed PANDA parallel computing platform, the modal superposition method is used to by the algorithm design of the random vibration response of free structure which should be implemented under multi-point pulsating pressure excitation. The algorithm design and parallel implementation are carried out, and the corresponding solving module is constructed. For the reentry process of the aircraft, based on the self-developed software module, the modal characteristics of the aircraft under free state and its vibration response under the measured pulsating pressure load were analyzed. The results were compared with software commercial analysis to verify the related software. The error of modal shapes is less than 0.2%, the distribution of mean square root deform response is consistant, and the error of maximum and minimum response is 1.93% and 6.14% respectively. The correctness of the module and the usability of the PANDA platform are verified in the actual engineering structure analysis. |
| Close |
|
|
|