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一种新型可重复缓冲着陆机构的设计、分析与实验

Design, analysis and experiment of a novel repeatable buffer landing mechanism.

作者信息

Han Daoguang, Zhang Dongsheng, Zhou Jinhua, Jia He, Fang Jishou, Wang Yongbin

机构信息

School of Construction Machinery, Shandong Jiao tong University, Jinan, 250357, China.

Beijing Institute of Space Mechanics and Electricity, Beijing, 100094, China.

出版信息

Sci Rep. 2025 Aug 9;15(1):29175. doi: 10.1038/s41598-025-14598-5.

DOI:10.1038/s41598-025-14598-5
PMID:40783595
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC12335524/
Abstract

The traditional lunar landing buffering structure uses multi-stage aluminum honeycomb materials to absorb impact energy. However, due to irreversible deformation and abrupt acceleration changes during the buffering process, it fails to meet reusability and compliant buffering requirements. Additionally, star table detectors have short landing times, typically completing buffering and energy absorption within 1 s. Therefore, this study employs a PZT-driven reusable buffering mechanism for rapid response. The mechanical structure converts linear impact motion into rotational motion via a large lead screw nut, enabling bidirectional movement with a compact, lightweight design. Dynamic responses under varying impact forces were analyzed using finite element impact dynamics, revealing relationships among structural deformation, stress, strain, and impact force. The reasoning system based on Takagi-Sugeno fuzzy neural networks compensates for control lag. Buffering experiments at landing velocities of 2, 3, and 4 m/s showed maximum reverse accelerations of 1.94, 2.04, and 2.13 m/s², and experimental accelerations of 2.59, 2.73, and 2.97 m/s², respectively. Compared to the Chang'e-3 lander, the mechanism exhibits smaller and more stable acceleration changes. Main contributions include: (1) design of a new PZT-based reusable buffering mechanism; (2) development of an adaptive fuzzy neural network lag compensation strategy; (3) comprehensive simulation and experimental validation.

摘要

传统的月球着陆缓冲结构采用多级铝蜂窝材料来吸收冲击能量。然而，由于缓冲过程中存在不可逆变形和加速度突变，它无法满足可重复使用性和柔顺缓冲要求。此外，星表探测器着陆时间短，通常在1秒内完成缓冲和能量吸收。因此，本研究采用一种由压电陶瓷（PZT）驱动的可重复使用缓冲机构来实现快速响应。该机械结构通过一个大型丝杠螺母将线性冲击运动转换为旋转运动，实现了紧凑、轻量化设计下的双向运动。利用有限元冲击动力学分析了不同冲击力下的动态响应，揭示了结构变形、应力、应变与冲击力之间的关系。基于高木-关野（Takagi-Sugeno）模糊神经网络的推理系统补偿了控制滞后。在2、3和4米/秒的着陆速度下进行的缓冲实验显示，最大反向加速度分别为1.94、2.04和2.13米/秒²，实验加速度分别为2.59、2.73和2.97米/秒²。与嫦娥三号着陆器相比，该机构的加速度变化更小、更稳定。主要贡献包括：（1）设计了一种基于PZT的新型可重复使用缓冲机构；（2）开发了一种自适应模糊神经网络滞后补偿策略；（3）进行了全面的仿真和实验验证。

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