The spacecraft deployment mechanism has phenomena such as impact, vibration and creep during the unfolding process, which has an important influence on the successful unfolding of the structure and the dynamic stability of the load after unfolding. Aiming at the shortcomings of the traditional conformal contact force calculation model, the viscous damping factor is introduced into the model to obtain an improved conformal contact force calculation model. The modified contact force model is used to calculate the normal contact force of the mechanism joints, and the improved Coulomb friction model is used to calculate the tangential contact force of the mechanism joints. Then, a multi-body system dynamic model of the truss deployment mechanism with multi-clearances is established. This model is used to numerically study the effect of clearance on spacecraft’s multi-clearances deployable truss system. The simulation results show that the clearance parameters have regular effects on the dynamic characteristics of the truss unfolding mechanism. At the same time, there is a very obvious coupling effect between different clearances.
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