飞机电脉冲除冰系统峰值电流测量  

Peak Current Measurement of Electro-impulse De-icing System

作　　者：杜骞[1] 朱春玲[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《科学技术与工程》2015年第35期81-86,共6页Science Technology and Engineering

基　　金：江苏高校优势学科建设工程项目资助

摘　　要：电脉冲除冰通过高压电容器瞬间向脉冲线圈迅速放电,在金属蒙皮内引起涡流,产生一类似锤击的脉冲力使冰破裂、脱离蒙皮并弹走。其显著优点是低能耗、高可靠性,且几乎不需要维护。通过提出电脉冲除冰系统理想放电模型,得到峰值电流随回路电阻、线圈电感的变化曲线。进行峰值电流理论计算数据与试验数据对比,为人工结冰状态下进行除冰试验提供参考依据。Electro-impulse de-icing（ EIDI） is accomplished by rapidly discharging high voltage capacitors into a wire coil rigidly supported just insided the aircraft skin. Induced eddy currents in the skin create a repulsive force resulting in a hammer-like force which cracks,debonds and expels ice on the skin surface. The promised advantages were very low engery,high reliability of de-icing and low maintenance. An ideal under-damped R-L-C circuit was managed to modeling,obtain the curve that peak current changed with R,L and T. Compared theoretical calculations with experimental data,can we provide reference for artificial de-icing tests.

关 键 词：电脉冲除冰 模型 涡流 峰值电流 试验 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]