CAJ | 학술논문

　　根据导弹蒙皮温度场气动加热、辐射换热和内部导热耦合作用机理，对导弹蒙皮温度场进行数值计算，分析了飞行速度和环境温度对导弹蒙皮温度的影响关系，建立简化模型模拟了非稳态条件下蒙皮温度变化，并与稳态计算结果比对分析。结果表明：导弹蒙皮温度与导弹马赫数的平方、环境温度有良好的线性关系；环境温度以0.5 K/s速率降低时5 s后导弹蒙皮简化模型非稳态计算结果与稳态计算结果有约2.4 K的差异。
　　근거도탄몽피온도장기동가열、복사환열화내부도열우합작용궤리，대도탄몽피온도장진행수치계산，분석료비행속도화배경온도대도탄몽피온도적영향관계，건립간화모형모의료비은태조건하몽피온도변화，병여은태계산결과비대분석。결과표명：도탄몽피온도여도탄마혁수적평방、배경온도유량호적선성관계；배경온도이0.5 K/s속솔강저시5 s후도탄몽피간화모형비은태계산결과여은태계산결과유약2.4 K적차이。
The paper calculates the field-temperature distribution of missile skin taking into account three factors as follows, aerodynamic heating, radiative heat transfer and structure heat conduction. Then the influence of missile speed and ambient temperature on the field-temperature distribution is analyzed. Also, the skin temperature changes in the characteristics of unsteady conditions is simulated based on simplified model and contrasted with the calculations on steady conditions. The results show that surface temperature has good linear relationship with the square of Mach number and ambient temperature, and there is 2.4 K difference between the calculations on steady and unsteady conditions at the given condition.