Investigation on Friction Coefficient between Solid Rocket Motor Nozzle Throat Components
The thermal structure characteristic of the Solid Rocket Motor (SRM) nozzle component under thermal and flow field is investigated by finite element method (FEM). The sensitivity of contact parameter of friction coefficient between multi-layer structures on thermo-structure coupled simulation is priority analyzed and the individual test of the friction coefficient between real material of carbon/carbon material and molded asbestos/phenolic material with temperature under real work condition is also designed. The numerical results and the experimental conclusions can provide some important value to the reliability design of nozzle thermal structure.
Nozzle Throat Multi-layer Structure Friction coefficient
Qin Liu Zhifei Sheng Hongbin Shi Hui Chen Jingwei Gu
The 41st Institute of the Academy Of China Aerospace Science and Technology Corporation,Xian, P.R.China
国际会议
贵阳
英文
288-292
2011-06-12（万方平台首次上网日期，不代表论文的发表时间）