一种双脉冲发动机的技术研究
A STUDY OF A DUAL-PULSE MOTOR TECHNIQUE
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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。Abstract: 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.
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Key words:
- Solid propellant rocket engines /
- Flow fields /
- Numerical computation /
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