| 黄虎,吴兴文,张帆,胡利.飞机重载大变形伸缩变体机构动力学仿真研究[J].装备环境工程,2022,19(9):61-68. HUANG Hu,WU Xing-wen,ZHANG Fan,HU Li.Dynamic Simulation of Telescopic Mechanism for Morphing Aircraft in the Condition of Heavy Loads and Large Deformations[J].Equipment Environmental Engineering,2022,19(9):61-68. |
| 飞机重载大变形伸缩变体机构动力学仿真研究 |
| Dynamic Simulation of Telescopic Mechanism for Morphing Aircraft in the Condition of Heavy Loads and Large Deformations |
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| DOI：10.7643/issn.1672-9242.2022.09.010 |
| 中文关键词: 变体飞机 伸缩机构 结构/机构综合建模 刚柔混合多体动力学 轮轨滚动接触动力学 机构带载伸缩试验中图分类号:TJ85 文献标识码:A 文章编号:1672-9242(2022)09-0061-08 |
| 英文关键词:morphing aircraft telescopic mechanism mechanical and structural integration modeling rigid-flexible mixed multibody dynamics wheel-rail rolling contact dynamics mechanical system telescope movement test with loads |
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| 目的 为适应先进战斗机外形变体需求，设计复杂严重载荷环境下的伸缩机构，在整体弯曲、扭转等大变形条件下发挥支持变体运动和传递大载荷的系统功能。方法 针对此类重载大变形伸缩机构，构建一种结合机构动力学和结构动力学的仿真分析方法，综合考虑运动过程中整体刚度分布变化带来的载荷、运动传递特性变化，以及局部轮轨运动组件的接触动力学细节，开展伸缩过程中的动力学仿真。结果 计算获取了整个伸缩机构在严重外载荷下的伸缩过程运动参数变化和机构动响应，与典型盒段带载伸缩运动试验测试相比，机构连接交点载荷最大值的计算误差不超过7.9%，自由端位移最大值的计算误差不超过13.2%。结论 建立的方法为各组件的传动传载性能优化和结构强度设计分析提供了一种可靠高效的仿真手段，对于变体飞机伸缩运动部件的结构/机构一体化设计有重要的应用价值。 |
| 英文摘要: |
| In order to adapt to advanced fighter shape variation, it’s necessary to design the telescopic mechanism under complex and severe load environment, and to fulfill the system function of supporting variant movement and transmitting large loads under large deformation conditions such as overall bending and torsion. For this kind of heavy load and large deformation telescopic mechanism, in this paper, a simulation analysis method combining mechanism dynamics and structural dynamics has been constructed. The method is used to consider the change of load and motion transmission characteristics caused by the change of overall stiffness distribution during the variant movement, and to analyze the contact dynamics details of local wheel-rail moving components. This paper has carried out the dynamic simulation in the process of expansion and contraction, and obtained the change of motion parameters and dynamic responses of the complete telescopic mechanism under severe external loads. Compared with the test of typical box section’s telescoping movement with loads, the calculation error of the maximum load at the intersection point of the mechanism is less than 7.9%, and the calculation error of the maximum free end displacement is less than 13.2%. The method established in this paper provides a reliable and efficient simulation method for the optimization of movement and load transmission performance and structural strength design analysis of each component of the mechanism, and has important application value for the integrated design of the aircraft structure and telescopic mechanism of morphing aircraft. |
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