Numerical simulation of infrared characteristics of liquid rocket plume
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摘要: 用传输方程积分法计算液体火箭喷焰在光谱2~5 μm的红外特性,并考虑了经过海平面一定长度的水平路程后大气对液体火箭喷焰辐射的衰减作用.计算喷焰的形状为圆柱形,温度和组分的摩尔分数沿轴向和径向变化.计算中考虑气体组分H2O,CO2,CO的吸收与发射,喷焰内燃气的光谱透过率用SLG模型计算,大气的光谱透过率用LOWTRAN7.0计算.给出一台推力为1.125×106N的液体火箭发动机喷焰表面以及经过海平面0.88 km水平路程大气衰减后的光谱辐射强度,经比较与参考文献给出的结果基本一致.Abstract: The infrared characteristics of liquid rocket plume, in spectrum 2~5 μm, was calculated using integral method of radiation transfer equation. The absorption of air at sea level was considered. The temperature and mole fraction of components in the cylindrical plume vary in axial and radial directions. The absorption and emission of gaseous components: H2O, CO2, CO were considered in computation. The spectral transmission of gas were calculated by the SLG model and air by LOWTRAN7.0. The spectral radiation intensity outgoing plume surface, and that after being absorbed by the air path of 0.88 km was calculated. By comparing, the results was basically accord with that in reference.
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Key words:
- rockets engines /
- exhaust gases /
- infrared radiation /
- numerical analysis
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