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摘要: 基于刚柔耦合多体动力学理论,提出了一种基于三维实体造型、有限元分析与多体动力学分析的刚柔耦合动力学仿真分析方法;利用该方法建立了月球着陆器着陆动力学模型,分别在地球重力环境和月球重力环境(1/6地球重力环境)下,对某典型着陆工况下的着陆动力学进行了仿真分析,得到了着陆器着陆的缓冲性能分析结果,包括主支柱最大缓冲行程、左右辅助支柱最大缓冲行程、最大质心加速度响应;将仿真结果与试验结果相比较,验证了着陆器动力学模型的正确性以及仿真分析方法的有效性,为今后的着陆器缓冲试验提供了动力学模型和仿真分析方法.从能量角度对月球着陆器的着陆过程进行分析,弥补了缓冲试验难以进行能量分析的不足.Abstract: Based on the rigid-flexible coupled multibody dynamics theory, an analysis method involved three-dimensional solid modelling, finite element analysis and multi-body system dynamics analysis was proposed. With such a method, the landing dynamics model for a lunar lander was established and used to analyze the landing performance for a typical touchdown case in both Earth-s gravity and Lunar-s gravity (1/6 Earth-s gravity) environments. The results include the max strut stroke in both the primary struts and secondary structs, the lunar lander mass center-s max acceleration. The analysis results were contrasted with those from the shock testing, showing that the rigid-flexible coupled dynamics model has been correctly built and the analysis method is valid and efficient. The model and method developed can then be used for future evaluating the landing performance of the lunar lander. The landing performance of the dynamics model was analyzed in energy prospect, making up shortage of shock testing’s failure of doing energy prospect.
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Key words:
- lunar lander /
- rigid-flexible coupled model /
- dynamic analysis /
- shock testing
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