固体火箭发动机气动喉部非定常过程

Unsteady process of aerodynamic throat for solid rocket motor

关键词:  固体火箭发动机  气动喉部  二次流  非定常  数值仿真

Key words:  Solid rocket motor  Aerodynamic throat  Secondary flow  Nonsteady  Numerical simulation

摘要:

利用流体计算软件FLUENT,通过UDF编程对气动喉部调节固体火箭发动机推力的典型工作过程进行了数值模拟。对推力调节过程中的瞬态轴对称燃烧室流场进行了分析,得到了压强-时间曲线。分析了发动机空腔容积、二次流喷射角度对推力响应特性的影响,并得到了典型的推力-二次流总压调节特性曲线。其研究结果可为利用气动喉部技术的变推力发动机设计提供一定依据。

Abstract:

By using the computational fluid dynamics software FLUENT and UDF programming, this paper performed numerical simulation on typical operation process of thrust modulation using the aerodynamic throat. The instant flow field of the motor during the thrust modulation process was analyzed, and pressure-time curve was gained. The influence of cavity capacity and injection angle of secondary flow on thrust response character was analyzed, and typical thrust-total pressure of secondary flow Curve was gained. The research results can provide reference for the thrust modulation motor design using the aerodynamic throat technique.