| With the advancement of China’s lunar exploration,the next major strategic goal is to achieve manned landing on the moon and to establish a permanent lunar base,this will meet many difficulties.One of the most critical technologies is soft landing on the moon.Due to the large mass and speed of the detector,a huge impact load will be generated in the moment of landing.Overload will damage astronauts and the scientific instruments carried by the detectors,resulting in the final failure of lunar exploration.As geomorphic feature of the moon,craters are widely distributed.The manned lunar detector may fall into the crater.Therefore,the landing buffering performances of different crater condition are studied in this paper.Through simplified impact simulation,the energy absorption curve of the honeycomb cushioning material used in the manned landing mechanism for the moon was obtained.With reference to the relevant parameters of the US Apollo 11 manned lunar landing vehicle,a finite element model of the lunar module landing mechanism was established with ANSYS/LS-DYNA,and the simulation was performed with only vertical speed to verification the model.Under the condition that the lunar module has only vertical velocity,the effects of the depth of the crater on the displacement,attitude angle,vertical acceleration response and energy absorption are analyzed when the number of landing legs in the crater is 1,2,3 respectively.Through the comprehensive analysis,it is determined that the lunar module can land safely when the depth of the crater is not more than 0.2 m.In the actual process of landing of the lunar module,it is inevitable to have a horizontal speed.The horizontal displacement,attitude angle and energy absorption are analyzed under different horizontal speeds.Based on this,the influence of the lunar soil friction factor and the depth of the crater on the buffering performances were studied.The results show that the influence of the lunar friction coefficient on the entire buffering process is small.The horizontal velocity directly determines the horizontal displacement of the lunar module,the attitude angle,and the energy absorption of the landing legs.Therefore,the horizontal velocity needs to be controlled in a lower range. |
