为了解得合理的直升机整机温度分布,在直升机机身表面温度场建模中综合考虑了机身蒙皮、排气系统、旋翼下洗和太阳辐射等方面的影响,并进行了数值模拟和排气系统-后机身一体化局部缩比模型的实验验证。研究结果表明:①由于辐射换热的影响,后机身内部混合管附近的表面温度升高了15 K左右;②单层蒙皮的表面温度受内部高温部件的热辐射影响较为显著,带遮挡板的双层壁结构蒙皮温度接近环境温度;③考虑太阳辐射时,受照侧机身表面温度呈现明显升高,最大温升约18 K。

In order to acquire helicopter skin temperature distribution, practical ways of modeling the helicopter skin, exhaust system, rotor downwash and solar irradiance are introduced in simulation. A numerical study is conducted and an integrative exhaust system-tail airframe scaled model is tested. The results show that: 1) because of radiation transfer, the temperature on the tail airframe skin around the mixing nozzle is about 15 K higher than the ambient temperature; 2) the temperature distribution on the single-wall skin is seriously affected by inner hot sources, while the temperature on the double-wall skin with radiation-resistance is close to ambient temperature; 3) the temperature on the direct solar irradiance side of the helicopter body is obviously higher than on the other side; the temperature increase is about 18 K in certain areas.