摘要
针对有导向行程长、碰撞机率大特点的套筒式导弹分离,对一种具弹性导向作用的分离机构进行了研究。该机构由弹性杆和滚轮组成,用弹性杆的阻尼效果限制分离体的相对偏转,降低分离碰撞机率,滚轮主要用于导向。根据飞行动力学原理,建立了六自由度运动模型和碰撞检测模型,分析了导向机构结构参数的单因素影响。由仿真所得相对姿态角和分离最小间距可知:在给定参数范围内进行的单因素仿真分析中,刚度系数和预紧力存在最优值,安装高度越大分离效果就越优。
Aim to the characteristics of the long guiding stroke and large collision probability for sleeve separation of missile, an elastic guiding separation mechanism was studied in this paper. The mechanism was composed of the elastic rod and roller, in which the relative deflection of the separator was limited to reduce the collision probability by the damping effect of the elastic rod and the roller was used for guiding. According to the principle of flight dynamics, a six-degree of freedom movement mathematical model and a collision detection model were established to analyze the influence of single factor, on the structure parameter of the guiding mechanism. The simulation results of the relative attitude angle and the minimum distance at separation showed that the optimal values of the stiffness coefficient and the preload existed when giving a certain range of parameter. Meanwhile, the higher the mounting height was, the better the separating effect got.
出处
《上海航天》
2015年第4期41-46,67,共7页
Aerospace Shanghai
关键词
套筒式导弹分离
碰撞概率
弹性导向
单因素
影响规律
Sleeve separation for missile
Collision probability
Elastic guide
Single factor
Influence rule
