| 王柯颖,胡杰,范宣华,牛红攀.基于PANDA平台的飞行器脉动压力激励随机振动响应分析[J].装备环境工程,2021,18(3):38-44. WANG Ke-ying,HU jie,FAN Xuan-hua,NIU Hong-pan.Random Vibration Response Analysis of Aircraft with Pulsating Pressure Excitation Based on PANDA Platform[J].Equipment Environmental Engineering,2021,18(3):38-44. |
| 基于PANDA平台的飞行器脉动压力激励随机振动响应分析 |
| Random Vibration Response Analysis of Aircraft with Pulsating Pressure Excitation Based on PANDA Platform |
| 投稿时间：2021-02-03 修订日期：2021-02-13 |
| DOI：10.7643/issn.1672-9242.2021.03.007 |
| 中文关键词: PANDA平台 自由状态 多点脉动压力激励 随机振动 有限元分析 |
| 英文关键词:PANDA platform free state multi-point pulsating pressure excitation random vibration finite element analysis |
| 基金项目: |
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| Author | Institution |
| WANG Ke-ying | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
| HU jie | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
| FAN Xuan-hua | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
| NIU Hong-pan | Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, China |
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| 中文摘要: |
| 目的 形成自主再入飞行数值模拟预测技术。方法 采用模态叠加法开展自由结构的多点脉动压力激励随机振动响应分析，基于PANDA高性能力学分析平台进行并行实现研究，构建相应的求解模块。针对飞行器再入过程，基于自主研发的软件模块，分析飞行器自由状态的模态特性及其在实测脉动压力载荷下的振动响应，并与商业软件分析结果进行比对。结果 模态振型的误差小于0.2%，位移均方根响应云纹分布一致，最大值和最小值的误差分别为1.93%和6.14%。结论 验证了相关功能的正确性，证明PANDA平台可以用于实际工程的结构分析中。 |
| 英文摘要: |
| 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. |
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