基于内外传热耦合的热气防冰系统仿真计算

基于内外传热耦合原理，建立了热气防冰系统的AMESim仿真模型，研究热气防冰系统在不同引气状态下，管路流量、压力及蒙皮温度的变化规律.采用所建立的仿真方法，计算飞机机翼热气防冰系统的内部流动特性和内外耦合传热特性，将计算结果与热气防冰系统流量分配试验结果进行对比.结果表明:管路流量、压力和蒙皮温度的仿真计算结果与试验结果最大误差为9%，验证了该仿真模型的正确性.在此基础上，对飞机短舱热气防冰系统进行了仿真，分析了飞行包线下系统内外的换热、温度变化、加热效率等关键参数的瞬态特性.仿真结果为热气防冰系统的设计、分析与优化提供依据. 

Simulation calculation of hot air anti-icing system based on internal-external comjugate heat transfer

Based on the principle of conjugate heat transfer between the external and internal chamber, AMESim simulation model was established for the hot air anti-icing system. The change rules of the flux, pressure and skin temperature in different bleeding conditions were researched. The internal flow characteristics and the conjugate heat transfer characteristics of the aircraft wing anti-icing system were calculated using this model. The predictions of the flux, temperature and pressure were verified against those in the flow distribution experimental data of the wing anti-icing system, showing a satisfactory agreement. The maximum error was less than 9%. Its accuracy and validity were validated with the comparison of results. On the basis of modeling, a nacelle hot air anti-icing system was simulated. The transient characteristics of key parameters under a certain flight envelop, such as the heat flux, temperature and heating efficiency, were analyzed. The results can be provided as a reference for design, analysis and optimization of hot air anti-icing system.