固体火箭燃气射流近场形成与发展的数值模拟

Numerical simulation of the form and development of rocket gas near flow field

关键词:  固体火箭推进  火箭排气  喷管气流  流动分布  数值仿真

Key words:  Solid rocket propulsion  Rocket exhaust  Nozzle flow  Flow distribution  Numerical simulation

摘要:

固体火箭武器燃气射流的近场区域存在有复杂的波系,膨胀波、压缩波的混合作用是机 弹、弹 舰相容性研究的重要内容,复杂波系压力、温度场的分布是燃气射流动力冲击和热冲击作用的直接因素。因为这一区域流动的复杂性,使得实验研究非常困难。为此应用数值分析的方法,研究了固体火箭高度欠膨胀燃气射流流场起始冲击波、近场波系的形成及发展。计算结果揭示了近场区域的一些特性,与文献提供的数据较为吻合,为工程应用提供了帮助。

Abstract:

The complicated wave system exists around the near region of the solid rocket motor. The interaction between expansion and compressed wave is the important part of correlated study on plane-missile and missile-warship. The distribution of the pressure and temperature field of complicated wave system is the direct factor which causes the dynamical and hot impact. It is difficult to study the complicated properties of jet flow field by means of experimental method. A method of numerical analysis was applied to study the wave system existing in near rocket gas field and the initial shock wave of high-unexpanded gas jet flow. The properties of the near region of gas flow field have obtained from the numerical result. The data accord with those given in reference and provide helpful information.