研究超音速飞机气动加热管温度优化控制问题,热管是超音速战斗机机翼热防护中减少机翼与背景环境温差的传热元件,而目前关于动载下热管传热流动特性的研究报道较少.为了建立热传导的控制数学模型,在分析热管工作机制的基础上,建立了轴向槽道热管液相和气相传热流动数学模型.通过有限体积法分别计算出气液相模型,利用不可压缩层流模型推导出了稳态下热管中两相的壁面温度分布情况,了解到旋转产生的离心力对气相的传热影响很小,对液相区的影响较大.通过仿真比较,仿真温度分布和的实验数据基本一致,满足工程要求.为热管在机翼热防护中的优化传热奠定基础.%The use of heat pipes in the thermal protection field of supersonic fighters is now under investigation. Based on the analysis of working performance of grooved heat pipes, physical models of gas and liquid phase were de veloped, and the governing equations were discrete using finite volume method as well as solved by incompressible laminar flow model. The wall temperature distribution of gas and liquid phase under steady state was obtained. Mean while , the influence of dynamic load to heat flow characteristics was investigated. The results show that the centrifugal force caused by rotation has little influence on gas phase, but much on liquid phase. Compared with experimental re sults in reference [11] and [12] , the simulation temperature distribution is identical. This research meets the engi neering needs and lays the foundation for the use of heat pipe in the field of thermal protection.
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