摘要
建立了固体火箭发动机点火瞬态过程一维非定常流场仿真模型,采用系统辨识方法进行了模型参数不确定性研究。基于点火试验用缩比发动机试验结果,得到了传热模型参数和瞬态燃速模型参数的最优估计,提高了点火瞬态过程一维仿真模型的预估精度。采用近似方法,构建Kriging近似函数,有效解决了一维非定常流场仿真的计算复杂性问题。
One-dimensional unsteady flow simulation model during ignition transient process of SRM was established, and uncertainty of model parameters was investigated by means of system identification method. Based on experiment results of subscale motors for ignition test, optimum estimation of heat transfer model and transient burning-rate model parameters was obtained. The predicted accuracy of one-dimensional simulation model during ignition transient process was improved. The complex calculation for one-dimensional unsteady flow field simulation was effectively settled by using approximate method and Kriging approximate func- tion.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2007年第4期287-291,共5页
Journal of Solid Rocket Technology
