新型SMA解锁分离机构紧固装置静力学仿真分析  

Static Simulation Analysis of Fastening Devices of a SMA Unlocking Separating Mechanism

作　　者：邸红儒 关世玺[1] 张孟柯 程颢 闫炳彰 DI Hong-ru;GUAN Shi-xi;ZHANG Meng-ke(College of Aerospace Engineering,North University of China,Taiyuan 030051)

机构地区：[1]中北大学航空宇航学院,太原030051

出　　处：《航空精密制造技术》2025年第1期31-34,共4页Aviation Precision Manufacturing Technology

摘　　要：为解决卫星与火箭之间的连接与解锁分离问题,设计一种新型形状记忆合金(Shape Memory Alloy,SMA)解锁分离机构,以此保证紧固牢固,并对卫星进行进一步的固定与限位。对机构中紧固装置自锁螺母以及外壳上凸台建立静力学模型。使用仿真软件从收口外圆尺寸与压痕深度两个方面分析自锁螺母的自锁性能,得出自锁螺母的自锁性能随着收口外圆尺寸的增加与压痕深度的增加而增加;通过对外壳上凸台进行静力学仿真,得到其与卫星底座接触的应力应变关系,并建立原始Swift模型得到较好的拟合效果。In order to solve the problem of connection and unlocking separation between satellite and rocket,a SMA unlocking separating mechanism is designed to ensure the firm connection and better fixing and limiting the satellite.The static model of self-locking nut and upper boss of shell,the fastening devices in the mechanism,is established.Using simulation software,the self-locking performance of self-locking nut is analyzed from two factors:the size of the convergent excircle and the indentation depth,and it is concluded that the self-locking performance of self-locking nut increases with the increase of the convergent excircle size and indentation depth.Through the static simulation of the upper boss of shell,the stress-strain relationship between the boss and the satellite base is obtained,and the original Swift model is established to get a good fitting effect.

关 键 词：解锁分离机构 紧固装置 自锁螺母 有限元仿真 

分 类 号：V42[航空宇航科学与技术—飞行器设计]