摘要
在固体火箭发动机喷管结构优化设计的研究中,为了在固体火箭发动机喷管结构可靠性的评估中考虑喉衬烧蚀的影响,使喷管结构可靠性的评估更加全面,采用蒙特卡洛仿真方法,对烧蚀喷管的结构可靠性评估过程进行了仿真。研究了影响喉衬材料热化学烧蚀速率的多个设计参数的随机分布特征,建立了能够反映烧蚀现象的仿真计算式和结构功能函数。仿真结果及仿真精度与试验结果保持了较高的一致性,证明改进方法可以较为全面地仿真喷管的烧蚀现象,可用来快速评估喷管喉衬结构可靠性水平,对改进提高喷管喉衬部位的设计水平有参考意义。
In order to take the influence of throat＇s chemical ablation into account in solid rocket motor nozzle＇s structure reliability assessment, to make the assessment more comprehensive, this paper applied the Monte - Carlo method, and simulated the assessment process of a ablation nozzle＇s structure reliability. We studied the distribution characteristics of several parameters which influence the throat＇s chemical ablation rate most, and established the e- quations and structural performance functions that can reflect ablation phenomenon. The simulation result and the precision of the simulation are consistent with the test results. It proves that the method can be used to simulate the nozzle＇s ablation comprehensively, and assess the throat＇s structure reliability rapidly.
出处
《计算机仿真》
CSCD
北大核心
2013年第10期112-115,148,共5页
Computer Simulation
基金
国家自然科学基金(51005179)项目资助
关键词
蒙特卡洛仿真
固体火箭发动机
喉衬烧蚀
结构可靠性
Monte - Carlo simulation
Solid rocket motor
Throat ablation
Structure reliability
