固体火箭发动机滚动球窝喷管强化接头材料性能分析  

Material performance analysis for the intensified joint of rolling ball joint socket nozzle in solid propellant rocket motor

作　　者：刘文芝[1] 武建新[1] 杜俊硕[1] 程佳庆[2] 

机构地区：[1]内蒙古工业大学机械学院,呼和浩特010051 [2]中国航天科工集团公司六院四十一所,呼和浩特010051

出　　处：《固体火箭技术》2012年第4期522-527,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金项目(50965013);内蒙古自然科学基金项目(2009BS0702)

摘　　要：为提高某固体火箭发动机滚动球窝接头接触承载能力,降低系统摆动力矩,以单珠承载试验模型为计算模型,采用摩擦接触问题的Lagrange乘子法与弹塑性耦合的有限元理论,计算分析了具有不同强化层材料性能的阳球试件与滚动体接触位置处的接触应力、摩擦应力、变形及破坏机理;解决了阳球不同强化层材料性能对接头接触承载性能的影响问题。根据计算分析结果,提出了满足弹塑性摩擦接触性能条件下,小的摩擦系数、小的弹性模量和较大的屈服极限相配合的阳球强化层材料性能要求;通过与单珠承载试验对比分析,检验了有限元建模及计算结果的合理性。To reduce system swing moment and improve contact intensity of rolling ball joint socket nozzle in a certain solid pro pellant rocket motor~ joint, contact stress, friction stress, deformation and failure mechanism between test parts convex sphere and ball were computed, which have different thickness and different material performance intensified layer. Computation model is single ball loadbearing experiment model and algorithm is the Lagrange multiplier method which is used for friction contact question and elastoplastic coupling~ finite element method. Different material performance intensified layers influencing the joint contact per formance were figured out. On the basis of computation result, the requirement for material performance intensified layers of the con vex sphere was presented, which satisfied friction contact performance, small friction coefficient, small elastic modulus and major yield limit. Rationality of FEM modeling and computation result has been validated by single ball loadbearing experiment and high load contact analysis.

关 键 词：固体火箭发动机 滚动球窝喷管 强化接头材料性能 弹塑性摩擦接触有限元 单珠承载试验 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]