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给出某导弹折叠翼展开动力学分析的仿真模型，在机构的运动学和刚体动力学分析的基础上，运用机构弹性动力学的理论对其进行了分析和仿真研究，算例证明，此方法是正确而且可靠的。其中计算程序具有相当的通用性，以适当修改可用于具有平面连杆机构的折叠翼展开动力学分析。
Based on the analysis of the kinematics and rigid body dynamics of the missile, the simulation model of the dynamic analysis of the folded wing of a missile is given. The analysis and simulation are carried out on the basis of the theory of mechanism elastic dynamics. The examples show that this method Is correct and reliable. The computational procedures are fairly generic to allow for appropriate modifications to the folding wing deployment dynamics with planar linkage mechanisms.