临近空间飞行器控制器热设计与热分析

临近空间飞行器电子设备集成度高、体积小、功率大，导致发热量大大提高，而其又直接工作在恶劣的空间热环境，因此，空间大功率电子设备的热设计成为未来飞行器安全、高效飞行的关键因素之一。本文针对临近空间的热环境特点，结合控制单元的工作模式，采用冷板散热、热控涂层、低热阻途径以及提高换热效率等有效方法对电子设备进行热设计。在结构设计基础上，用商业软件ANSYS ICEM CFD进行前处理，用FLUENT进行模拟热仿真，并对结果进行分析后给出3种合理优化的设计方案。仿真结果表明，增加冷板边缘处面积、增大辐射散热和自然对流换热表面积的设计方案可以有效地将控制器温度控制在293.15~318.15 K高效可靠的工作温度之间。

Thermal Design and Thermal Analysis of Flying-Vehicle Control Units in Near Space

High integration, miniaturization and high-power of electronic components are developed in space flying-vehicle at expense of increasing heat dissipation. Therefore, the advanced thermal management technology is becoming a major factor to restrict the safe and efficient flight of future aircraft. According to the special space environment characteristics, work pattern and requirement of thermal control of high-power control units using in near space flying-vehicle, a thermal management system is designed by means of cold plate technology, thermal control coating, decreasing thermal resistance, and improving heat-exchanging efficiency etc. The optimal design scheme is presented by means of ANSYS simulation. In view of the requirements of the object and temperature design, three kinds of structures are designed. And numerical results point out that the design scheme of increasing the edge area of cold plate and the surface area of radiation heat dissipation and natural convection heat transfer is the best choice to control the temperature at the range of 293.15-318.15 K for efficient and reliable work.