“长二丙改”上面级CPKM发动机喷管两相粘性流动数值模拟研究  

Numerical simulation investigation on two-phase viscous flow in “CZ-2C/FP”upper stage solid rocket motor (CPKM) nozzle

作　　者：许鹏[1] 梁国柱[1] 黄喻路[1] 赵永忠[2] 张立群[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]中国航天科工集团公司六院四十一所,呼和浩特010010

出　　处：《固体火箭技术》2005年第2期101-104,共4页Journal of Solid Rocket Technology

摘　　要：对“长二丙改”火箭上面级CPKM发动机喷管的高空性能进行了预示。气相采用显式MacCormack差分格式、颗粒相采用特征线法,数值求解采用轴对称二维两相粘性流动模型。对CPKM发动机喷管进行数值模拟,所得的发动机平均推力与实测性能数据相比较,相对误差为2.3%。研究表明,所采用的流动模型和数值模拟方法,对高空大面积比喷管性能进行的预示是有效的。High altitude performance of CZ-2C/FP upper stage solid rocket motor (CPKM) nozzle was predicted. The explicit MacCormack difference scheme was used for gas phase, and the characteristic method was used for particle phase. The two-dimensional axis-symmetrical viscous two-phase flow model was numerically calculated. The relative error was 2.3% when the average thrust data was compared with the measured data. The results show that the flow model and numerical simulation method can be effectively used to predict the performances of the nozzle with a large area ratio.

关 键 词：固体火箭发动机喷管 两相流 数值模拟 性能预测 

分 类 号：V435.3[航空宇航科学与技术—航空宇航推进理论与工程] V430