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为满足组合发动机总体热防护的需要,分别采用参考温度法和大气透过率计算软件MODTRAN4计算了组合发动机蒙皮所受的气动加热和环境热辐射。利用本文建立的稳态热平衡方程,迭代求解得到组合发动机蒙皮在典型飞行工况下的一维稳态温度分布。将本文计算的结果与美国航空航天局(NASA)的实验结果进行对比,误差不大于6%。对典型飞行工况下不同蒙皮壁面发射率、不同飞行攻角进行了系列研究。结果表明:随着发射率的提高,蒙皮壁温逐渐降低,随着攻角的增加,蒙皮壁温逐渐增高。在某标准工况下,发射率为1.0的蒙皮温度比发射率为0.1的蒙皮温度低98.01K,降幅为12.76%。攻角为45°的蒙皮温度比攻角为0°的蒙皮温度高95.45K,增幅为13.14%。
In order to meet the needs of the overall engine thermal protection, the aerodynamic heating and ambient heat radiation of the combined engine skin were calculated by using the reference temperature method and the atmospheric transmittance calculation software MODTRAN4 respectively. Using the steady-state heat balance equation established in this paper, the one-dimensional steady-state temperature distribution of the composite engine skin under typical flight conditions is obtained iteratively. The results calculated in this paper are compared with the experimental results of NASA, the error is not more than 6%. A series of researches on emissivity of different skin layers and angles of attack of different flights under typical flight conditions were carried out. The results show that with the increase of emissivity, the temperature of skin wall gradually decreases. With the increase of angle of attack, the temperature of skin wall gradually increases. Under certain standard conditions, the skin temperature of emissivity 1.0 is 98.01K lower than the skin temperature of emissivity 0.1, a decrease of 12.76%. Skin temperature of 45 ° angle of attack was 95.45K higher than that of 0 ° skin angle, an increase of 13.14%.