Abstract
To improve the soft-landing crash performance of the movable lander (ML), this study presents an investigation of a newly designed gradual energy-absorbing structure subjected to impact loads using an ML for theoretical calculation and numerical simulations. In this work, we present a novel computational approach to optimizing the energy absorption (EA) of the ML. Our framework takes as inputting the geometrical parameter (GP) as well as EA. The finite element model of the HB1, HB2, and HB3 was established and effectively verified using numerical simulation and experimental data. The relationship between the GP of the buffer material and the EA was obtained through static experiment and impact experiment, and the cushioning performance of the lander was optimized according to the ML load mass, contact speed, and EA function. According to the optimization results, we chose an outer diameter of 240 mm, an inner diameter of 50 mm, heights of HB1 = 140 mm, HB2 = 110 mm, and HB3 = 225 as the collocation, and completed the numerical simulation of three different cases. By comparing the results of theoretical calculation and numerical simulation experiments, it can be found that the overload response rates of the main body in 4 type landing, 2-2 type landing, and 1-2-1 type landing are 4.72 G, 2.61 G, and 2.33 G, respectively. It also laid the foundation for the theoretical and methodological research of the ML and manned lander in the future.
Highlights
In the process of lunar exploration, only relying on the rover can no longer meet the requirements of lunar reconnaissance with heavy equipment in the future
The structure of the primary strut and secondary strut is composed of inter tube, outer tube, aluminum honeycomb-I, aluminum honeycomb-II, driving mechanism, ball screw, screw nut, aluminum honeycomb-I, aluminum honeycomb-II, driving mechanism, ball screw, screw nut, and and push-pull locking mechanism
A new-type composite energy absorbing structure was combining the characteristics of aluminum honeycomb (AH) structures
Summary
In the process of lunar exploration, only relying on the rover can no longer meet the requirements of lunar reconnaissance with heavy equipment in the future. The process of creating new types of MLs, is notoriously challenging because their energy absorption (EA) capabilities is intimately related to their design For this reason, creating new ML requires a great deal of experience, and is a largely manual and time-consuming task. Rather than relying on trial-and-error approaches, we seek to develop a computational model with the predictive power required to inform design decisions. The structure of the primary strut and secondary strut is composed of inter tube, outer tube, aluminum honeycomb-I, aluminum honeycomb-II, driving mechanism, ball screw, screw nut, aluminum honeycomb-I, aluminum honeycomb-II, driving mechanism, ball screw, screw nut, and and push-pull locking mechanism. The inter tube of the primary strut is connected with the rotary joint, joint, and the inter tube of the secondary strut is connected with the spherical joint, which is the and the inter tube of the secondary strut is connected with the spherical joint, which is the only only difference between the primary strut and the secondary strut
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