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目的使空间飞行器地面传热实验的结果能够有效地应用到空间微重力条件下。方法用数值模拟的方法研究了矩形空间内 45°对称间隔斜进风以及垂直进风的流动和换热情况 ,壁面条件为等壁温或等热流。对重力和微重力两种情况进行了对比。结果对等壁温情况 ,提出了表征空间飞行器舱内换热的关系式 ,并且将数值计算所得数据按这些关系式进行了最小二乘拟合 ,得到了空间微重力工况和地面工况下的换热关系式。对等热流情况 ,本文列出了重力和微重力条件下的最高壁面温度值 ,给出了两种情况时最高壁面温度的拟合公式。结论根据本文的方法 ,可以对地面模型装置的实验结果进行修正 ,得到空间飞行器原型内的换热情况。
The purpose is to make the results of the ground-based heat transfer experiment on spacecraft effectively applied to the space microgravity. Methods Numerical simulations were carried out to study the flow and heat transfer of oblique inlet air and vertical inlet air at 45 ° symmetrical intervals in a rectangular space. The wall conditions are isothermal wall temperature or isothermal flow. The two cases of gravity and microgravity are compared. Results Based on the wall temperature, the relationship between the heat transfer in the spacecraft and the spacecraft was put forward, and the least square fitting was performed according to these relations. The results obtained under the conditions of space microgravity and ground conditions The heat transfer relationship. Equivalent heat flow conditions, the paper lists the maximum wall temperature under gravity and microgravity conditions, gives the fitting formula of the maximum wall temperature in two cases. Conclusion According to the method in this paper, the experimental results of the ground model device can be modified to obtain the heat transfer in the spacecraft prototype.