基于热管技术的飞机电作动机构散热特性

Cooling performance of electric actuating mechanism on aircrafts based on heat pipes

针对飞机电作动机构在工作过程中发热严重的情况,开展了相关散热技术研究。利用试验数据拟合出电作动机构产热量的经验关系式,提出基于热管-燃油系统的飞机电作动机构冷却方法,建立描述电作动机构散热系统流动与传热过程的数值模型,并验证了其可靠性。通过数值模拟研究不同因素对散热系统散热性能的影响规律,结果表明:数值模拟与试验误差在14.6%以内;与自然对流散热相比,热管-燃油散热方式可使电作动器温升降低12.61%,对于驱动器,风扇冷却效果优于热管-燃油散热方式;当热管等效导热系数达到7000 W/(m·K),电作动机构已达到较好的散热状态,继续增大热管等效导热系数对提高散热系统散热性能效果不明显。研究可为电作动机构高效散热系统的设计提供参考。

Research on cooling technology was carried out considering that the electric actuating mechanism on aircrafts would produce much heat in working.The empirical formula was fitted based on the experiment data.A cooling method for an aircraft electric actuating mechanism was proposed based on the heat pipe-fuel cooling system,and a numerical model describing the flow and heat transfer of the cooling system was established and validated feasibly.The influence of some factors on the cooling performance of the cooling system was studied by numerical simulation.Results showed that the error between numerical simulation and experiment data was within 14.6%.The heat pipe-fuel cooling system could reduce the temperature rise of the electromechanical actuator by 12.61%compared with natural convection.For the driver,the fan cooling method was superior to the heat pipe-fuel cooling method.When the effective thermal conductivity of heat pipes reached 7000 W/(m·K),the heat pipe-fuel cooling system could achieve a good cooling performance,and continuously increasing the effective thermal conductivity of heat pipes couldn’t effectively improve the cooling performance of the cooling system.This research provides a reference for designing an efficient cooling system for electric actuating mechanisms.