Simulation Analysis On Soft Landing’s Buffer And Stability Of Lunar Exploration

In the new round of international space exploration, lunar resourc es developedcountries the focus of competition, and landing on the moon for probing has graduallybecome an important trend. China’s “Chang’e” project includes the following threeperiods "surround""fall" and "back", which, an important part of the second and thethird phase is to achieve a soft landing on the moon. Buffering mechanism of thelander, selection of landing surface topography and landing initial conditions is the keyto success of soft landing. Leg type landing gear is internationally a majority of thelander which has strong adaptability of soft landing. While study of the basic structureof legged lander and dynamics achieved some results from the current research of thedomestic and foreign, but for the stability of the lander during landing had beenlacking. So, this paper base on the kinetic theory of landing impact, through theestablishment of the whole dynamic model, analysis of stability during landing, to getthe parameters of the buffer structure design and stability initial condition, providing atheoretical basis for the development of China’s lunar lander and support.Firstly, a summary of the application of the current status of legged planet softlanding has been presented, which elaborate the basic types and configuration of thesoft landing gear. The analysis of ideas of lander stability judgment basis has been putforwarded after summarizing the robot stable basis. Next, based on the compressioncharacteristics of aluminum honeycomb, the aluminum honeycomb crushing dynamicsprogram has been written by C language, and a dynamic model of the primary andsecondary buffer has been established. Based on the mechanical properties of the lunarregolith, lunar regolith constitutive model has been constructed and the lunar regolithdynamics subroutine has been written. By the means of the experimental data of NASAfor the Apollo, verify the validity of the dynamic model.In this paper, based on the establishment of the lander machine simulation model,we investigated the important parameters of the cushioning mechanism, and analyzetheir effect of the landing impact. Then draw on Papadopoulos’s power-angle stabilitymetric method, the stable cone angle method and lander landing stability criterion isproposed. By this criterion, a numerical simulation analysis of a variety of typicaloperating conditions the soft landing of the lander is made. Finally, it proposes acomprehensive stability index, and to optimize the crushing load of the target landingmain pillar of aluminum honeycomb reasonable to optimize the compression stroke. The research results provide guidance to the lander buffer mechanism design as well asachieving soft landing of the lunar environment and the choice of the initial conditions,or similar engineering designing.