Simulation analysis of the deploying process of deployable landing gear based on adams

Deployable landing gear is an important part of Lunar lander. The ADAMS model of a Lunar lander with four strut groups was built in this paper. The effects of the flexibility of primary strut, joint clearance, deploying driver force and the spin of mainbody on the dynamic character of landing gear during deploying were analyzed. The simulation results show that the vibration excitated on the lock instantaneousness is difficult to be attenuated because of the flexibility of primary strut. And joint clearance is helpful to attenuation this vibration in a certain extent. The deploy velocity of landing gear increase with the augment of deploying driver force, and the swing of the vibration excitated on the lock instantaneousness also increase. But the whole time of deploying can be shorter. If the mainbody spins, the landing gear will deploy faster. The effects of spin on the vibration will increase with the angle velocity increasing. These results are useful to the design of deploy projects.