摘要
以某固体火箭发动机推力向量控制系统摆动接头的单珠承载试验模型为计算模型,采用摩擦接触问题的La-grange乘子法与弹塑性耦合的有限元理论,计算分析了摆动接头阳球试件在不同强化层厚度下的接触应力、变形及破坏机理;为降低系统摆动力矩,同时考虑大尺寸球面的表面强化和加工工艺,提出了满足接触性能的阳球表面强化层为1～1.4mm的厚度要求。通过与单珠承载试验对比分析,检验了有限元建模及算法的合理性;确定了小变形条件下摆动接头弹塑性摩擦接触应力限额为5 384.9 MPa。
In this paper,a single ball load-bearing experiment model of the swing joint of thrust vector control system in a solid propellant rocket motor was used as computation model.By using the Lagrangian multiplier method for friction contact question,and elasto-plastic coupling＇s finite element method,the contact stress,deformation and destruct principle under different thickness of strengthening layer of the test swing joint convex sphere were computed and analyzed.To reduce system swing moment,and consider manufacturing techniques of large size intensify sphere,1~1.4 mm thickness of strengthening layer satisfied for contact performance was presented.Rationality of FEM modeling and algorithm was validated by single ball load-bearing experiment.The elasto-plastic friction contact stress of the swing joint was limited to 5 384.9 MPa in small deformation condition.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第5期573-578,共6页
Journal of Solid Rocket Technology
基金
自然科学基金项目(50965013)
关键词
固体火箭发动机
推力向量控制系统
摆动接头
弹塑性摩擦接触有限元法
单珠承载试验
solid propellant rocket motor
thrust vector control system
swing joint
elasto-plastic friction contact finite element method
single ball load-bearing experiment
