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

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.