隐式极限状态方程下的导弹吊挂寿命可靠性分析  

Missile Suspension Structural Life Reliability Analysis Under Implicit Limit State Equation

作　　者：何新党[1] 刘永寿[1] 苟文选[1] 高宗战[1] 

机构地区：[1]西北工业大学力学与土木建筑学院飞行器可靠性工程研究所

出　　处：《航空制造技术》2013年第11期69-73,共5页Aeronautical Manufacturing Technology

基　　金：高等学校学科创新引智计划项目(B07050);西北工业大学基础研究基金(G9KY1006/09);西北工业大学研究生创业种子基金(Z2011071)资助

摘　　要：某型导弹吊挂结构疲劳寿命与基本变量(尺寸、材料、载荷)之间关系难以用解析式准确表达,使得传统基于应力-强度干涉理论的解析可靠性分析方法难以被应用。借助MSC/PATRAN建立了该型导弹吊挂的有限元模型,通过静力学及疲劳寿命分析,建立了结构疲劳寿命与基本变量之间的响应关系。以结构危险部位的几何尺寸作为随机变量,采用加权二次响应面法拟合得到了吊挂结构的极限状态方程;用改进一次二阶矩法进行可靠性及灵敏度分析,得到了吊挂结构在设计寿命内发生疲劳失效的概率。灵敏度分析发现:倒角半径是影响吊挂结构寿命的主要因素,尺寸加工误差是导致寿命分散性较大的主要原因。The relationship between fatigue life and the basic variables （size, materials, loads） of a missile suspension structure is difficult to accurately express through a analytic way. which makes reliability analysis methods based on the traditional stress-strength interfer- ence theory difficult to use. In this paper, using MSC/ PATRAN, a finite element model is built to get the response between fatigue lilt： and the basic variables of the missile suspension structure. Taking the size of key parts as random variables, the limit state equation of suspension structure is fitting based on weighted quadratic polynomial RSM. AFOSM is introduced to perform for the reliability and sensitivity analysis, and the suspension structural fatigue failure probability is obtained. The results of sensitivity analysis show that chamfer radius is the main influencing factors of the stispension structural fatigue life and dimension error is the main reasons leading to dispersion of fatigue life.

关 键 词：导弹吊挂结构 疲劳寿命 可靠性 灵敏度 

分 类 号：TJ760.3[兵器科学与技术—武器系统与运用工程]