导热增强型相变材料温控试验

Temperature Control Experiment of Thermal Conductivity Enhanced Phase Change Materials

为满足高超声速飞行器舱内温度要求,提出了在舵轴热短路区域使用相变材料进行热耗散的方案。通过开展导热增强型相变材料温控试验,获得了不同试验方案对舵轴及周围金属壳体的降温效果。结果表明,导热增强型相变材料由于良好的导热性能,能够很好地发挥相变吸热能力,对降低舵轴热短路区域的局部高温具有显著效果;金属壳体内、外同时使用低温和中温相变装置,能够将舵轴周围金属壳体温度控制在允许工作温度范围内(150℃)。本研究可为飞行器舵轴温控设计提供指导。

In order to satisfy the temperature requirement inside the hypersonic vehicle＇ s capsule, the thermal control method applying the phase change material （PCM） to the heat short regions of the rudderpost was proposed. Through the temperature control experiments of the thermal conductivity enhanced PCM, the temperature curves of the rudderpost and the metallic capsule under different schemes were achieved. The experimental results revealed that the thermal conductivity enhanced PCM could absorb the heat well and decrease the temperature of the heat short regions obviously. By using the PCM devices under the low temperature and middle temperature inside and outside the metal- lic capsule, the temperature of the capsule around the rudderpost could be controlled within the range of working per- mission. The results would be helpful to guide the temperature control design for the rudderpost of the vehicle.