Simulation and analysis of asteroid force closure anchoring performance based on discrete element method  

作　　者：Tingzhang WANG Qiquan QUAN Hongshuai GAO Mengxue LI Dewei TANG Zongquan DENG 

机构地区：[1]State Key Laboratory of Robotics and System,Harbin Institute of Technology,Harbin 150001,China

出　　处：《Chinese Journal of Aeronautics》2023年第8期381-394,共14页中国航空学报（英文版）

基　　金：co-supported by the National Natural Science Foundation of China(Nos.52105012,51975139 and 52111530038);Support by Self-Planned Task of State Key Laboratory of Robotics and System(No.SKLRS202101C).

摘　　要：Asteroid exploration is significant for studying the origin of the solar system,establishing planetary defenses,and alleviating the resource crisis of the Earth.Asteroid anchoring is the basis of in-situ exploration and resource development and utilization.Therefore,the performance of asteroid force-closure anchoring is investigated using the discrete element method.The micro parameters of the simulated materials are calibrated with angle of repose and uniaxial compression experiments,based on which the regional modeling method is adopted to establish the anchoring discrete element model.Asteroid anchoring experiments are conducted on a self-developed microgravity simulation platform to verify the accuracy of the simulation model.The asteroid anchoring simulations are performed to investigate the influence of external force on the anchoring performance.The analysis of anchoring force varying with time and the interaction between the anchor and regolith particles reveals the influence mechanism of external force direction on the anchoring performance.The external force direction affects the critical anchoring force by influencing the failure of the force-closure structure.The comprehensive analysis of simulation results clarifies the variation of the critical anchoring force with the external forces.Finally,a stable anchoring region is established,beneficial for asteroid anchoring device design.

关 键 词：Anchoringforce Asteroid exploration Discrete element method Force closureanchoring Simulationverification 

分 类 号：V476.4[航空宇航科学与技术—飞行器设计]