一种双脉冲发动机的技术研究  

A STUDY OF A DUAL-PULSE MOTOR TECHNIQUE

作　　者：朱光辰[1] 胡克娴[1] 王春利[1] 蔡湘芬[1] 张玉成[1] 方蜀州[1] 

机构地区：[1]北京理工大学

出　　处：《航空动力学报》1996年第4期364-368,共5页Journal of Aerospace Power

摘　　要：提出了一种带有中间喷管的新型双脉冲固体火箭发动机技术方案，设计了一台结构参数可调的试验发动机；改变发动机的结构参数进行多次点火试验，获得了试验数据；对该发动机的多喉道流动过程建立了二维非稳态流动模型，对试验方案进行了大量计算，并与试验数据进行了比较分析。试验结果与理论计算基本吻合，结构可靠。A new type of dual-pulse solid rocket motor concept with an intermediate nozzle is presented and a test motor with changeable structural parameters was designed.Several firings of the motor with changing the structural parameters were conducted and the corresponding experimental data were obtained.A two-dimensional unsteady mathematical model was constructed for analyzing the multithroat flowfields,and numerical calculation with this model was completed.The results were compared with the test data.

关 键 词：固体火箭发动机 流场 数值计算 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]