某客机垂尾雷电流分布仿真与雷电试验研究

Research on the Lightning Current Distribution Simulation and Lightning Test of a Passenger Aircraft’s Vertical Tail

针对大尺度舱段级雷电直接效应试验难度较大和成本较高的问题,本文提出用机身模拟件代替真实机身的方法。为验证机身模拟件试验结果的有效性,首先进行了垂直安定面含有机身与机身模拟件的雷电流分布仿真,分别对比了注入点为翼尖与垂尾根部的情形。结果显示采用机身模拟件时典型垂尾外周电流密度分布平均最大偏差为9%和14%。在此基础上进行了直接效应试验,注入电流波形的组合分别为A+B+C*和D+B+C*。损伤部位主要为注入点周围区域,观察有螺钉的烧蚀与漆层剥落的现象,对损伤区域及周围未起翘区域进行超声波探伤,起翘区域最大损伤面积为100mm×100mm,最大损伤深度为0.2mm。

In view of the difficulty and high cost of large-scale cabin-level lightning direct effect test, in order to verify the validity of the fuselage prosthesis test results, the lightning current distribution simulation with the fuselage and fuselage dummy on the vertical stabilizer was first carried out., And compared the injection points at the wing tip and the vertical tail root respectively. The results show that the average maximum deviation of the current density distribution around the typical vertical tail when the fuselage is used is 9% and 14%. On this basis, a direct effect test was carried out, and the combinations of injection current waveforms were A+B+C* and D+B+C*. The damaged area is mainly the area around the injection point. Observe the phenomenon of screw ablation and peeling of the paint. Ultrasonic inspection is performed on the damaged area and the surrounding unskinned area. The unskinned area is not damaged. The maximum damage area of the peeled area is 100×100 mm, the maximum damage depth is 0.2 m.