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超音速导弹温度场的计算对其红外辐射特性研究具有重要的参考价值。对超音速导弹的两个主要辐射源蒙皮和羽流进行了深入分析,建立了超音速导弹温度场模型,仿真验证了模型的可行性。采用理论模型与半经验公式对导弹温度分布进行了计算,将羽流近似成超音速轴对称无伴随绝热等熵流,利用特征线法计算气流参数分布。此外,建立了超音速导弹尾焰形状的理论模型与计算方法。最后进行仿真,计算了导弹各部分的温度分布,并与实验结果比较,结果表明,该方法是一种计算超音速导弹温度分布的有效方法。
The calculation of the temperature field of supersonic missile has important reference value for the research of infrared radiation characteristics. The main skin and plume of two main radiation sources of the supersonic missile are analyzed. The temperature field model of the supersonic missile is established. The feasibility of the model is verified by simulation. The theoretical model and semi-empirical formula were used to calculate the temperature distribution of the missile. The plume was approximated to supersonic axisymmetric without adiabatic isentropic flow, and the characteristic parameters were calculated by the characteristic line method. In addition, the theoretical model and calculation method of supersonic missile tail flame shape are established. Finally, the simulation is carried out, the temperature distribution of each part of the missile is calculated and compared with the experimental results. The results show that this method is an effective method to calculate the temperature distribution of the supersonic missile.