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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1996年第4期364-368,共5页
Journal of Aerospace Power
关键词
固体火箭发动机
流场
数值计算
Solid propellant rocket engines Flow fields Numerical computation
