航天飞行器折叠翼锁紧机构力学模型

Mechanical model of locking mechanisms of folding wing for spacecraft

针对折叠翼插-拔式锁紧机构建模问题,采用平面应变假设和叠加原理对模型简化降维,构建了考虑间隙效应的连接刚度解析模型。首先,采用能量法求解接触摩擦引起的非静定问题,获得法向和切向接触力;其次,基于Hertz基本解计算出等效接触刚度,并采用梁模型计算弹性销的弯曲变形;通过将解析解与文献试验值进行对比,对方法的适用性进行验证,并进一步针对不同接触模式开展参数影响分析,最终给出了载荷和间隙对连接刚度的影响规律。结果表明:当载荷由20 N·m变为50 N·m时,锁紧机构的连接刚度增大约3%~5%,存在刚度渐硬非线性效应;而随间隙增大,连接刚度呈现下降趋势,其原因为配合尺寸影响弹性销与孔壁的相对姿态。

To model the plug-in locking mechanism,the plane strain assumption and superposition principles were used for dimensionality reduction and simplification,and an analytical model of connection stiffness considering the effect of gap was established.Firstly,the energy method was used to solve the indeterminate problem caused by contact friction,and the normal and tangential contact forces were obtained.Then,the equivalent contact stiffness was calculated by using Hertz’s theory,and the bending deformation of elastic pins was calculated through beam model.To validate the applicability of the method,the analytical results were compared with the experimental results from the reference paper.Finally,the parameter influence analysis was carried out,and the effect of load and clearance on connection stiffness was proposed.The results showed that when the load changed from 20 N·m to 50 N·m,the connection stiffness of the locking mechanism increased by about 3%—5%,demonstrating a hardening spring nonlinear effect.With the increase of the clearance,the connection stiffness showed a downward trend,owing to the fact that the fit size affected the relative attitude of the elastic pin and the hole.