Simulation analysis of indirect effects of lightning on airborne missiles
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摘要: 导弹作为军机的挂载，在雷电特殊环境中存在遭受雷击风险。为了提高机载导弹的雷电防护，根据标准SAE ARP5416的试验方法在CST中搭建仿真环境，对“军机挂载导弹”模型采用静电场仿真进行雷电附着1A区划分，并采用注入电流法仿真模型遭遇雷击时的间接效应。仿真结果表明：导弹导引头固定后沿（金属部分）和尾翼翼尖易遭受雷电初始附着，当雷电附着于导弹导引头固定后沿时，雷达罩内的电磁场环境最为恶劣，并且碳纤维复合材料（CFRP）舱段内产生的强电场环境和线缆的高感应电压会损坏弹内设备，而CFRP镀铝可将舱段内电场强度和线缆感应电压降低两个数量级，有着良好的雷电电磁屏蔽效果。Abstract: As a suspension for military aircraft, missile has potential for being struck by lightning in special thunderstorm environments. To improve the lightning protection of airborne missiles, a simulation environment of military aircraft with missiles is built in CST software according to the testing methods in SAE ARP5416 standard. The lightning 1A zones are classified through electrostatic field simulation, and the indirect effects of lightning striking on this model are simulated under injection current method. Simulation results show that the head rear edge of missile (metal parts) and tail wing tip of missile are susceptible to initial attachment from lightning. When the head rear edge of the missile is attached by lightning, the extremely harsh electromagnetic environment occurs at the radome, and the equipment in cabin of carbon fiber reinforced plastic (CFRP) can be damaged owing to the strong electric field and the high voltage induced on cables. However, the electric field strength and induced voltage amplitudes on cables can be dropped in two orders of magnitude separately in the condition of aluminum plating inside the CFRP cabin.
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图 1 雷电A电流分量电流波形和频谱分布图
Figure 1. Structural schematic diagram of military aircraft carrying cruise missiles
图 2 军机挂载导弹的模型示意图
Figure 2. Structural schematic diagram of military aircraft carrying missiles
图 3 单位电荷下的模型感应电场强度分布图
Figure 3. Electric field intensity distribution diagram of the model based on unit charge
图 5 不同棒状电极位置处导弹头部边沿与尾翼翼尖的感应电场强度百分比
Figure 5. Percentage of induced electricfield intensity at the head edge of missiles and the tail tip of missiles in various discharge positions of rod-electrode
图 6 不同平板电极位置处导弹头部边沿与尾翼翼尖的感应电场强度百分比
Figure 6. Percentage of induced electricfield intensity at the head edge of missiles and the tail tip of missiles in various discharge positions of polar-plate
图 7 导弹内部线缆布置及连接图
Figure 7. Cable layout diagram and cable connection diagram inside the missile
图 8 导弹遭受雷电附着时电流和电磁场分布图
Figure 8. Distribution diagrams of the current and electromagnetic field when the missile is struck by lightning
图 9 导弹内部探针处电场强度变化曲线
Figure 9. Curves of the electric field intensity variation at the probes inside missile
图 10 5条雷击路径下导弹内部P3、P6处的电场强度变化曲线
Figure 10. Electric field intensity variation curves at the probes of P3 and P6 based on five lightning strike paths
图 11 雷电从导弹1头部边沿进入从军机尾翼翼尖击出时的线缆感应电压变化曲线
Figure 11. Induced voltage variation curves of cables when Lightning enters from the head of misslie1 and exits from the vertical tail tip of aircraft
图 12 4种不同雷击路径下导弹内Shield-AF200线缆感应电压变化曲线
Figure 12. Induced voltage variation curves of the Shield-AF200 cables based on four different lightning strike paths
图 14 不同金属镀层厚度下P3处的电场强度曲线和Cable3的感应电压曲线
Figure 14. Electric field intensity curves at the probe of P3 and induced voltage curves of the Cable3 under different thickness of thin metal layer
表 1 军机与导弹材质的电参数
Table 1. Electrical parameter of military aircraft and cruise missile materials
physical quantily material electrical conductivity/(S·m−1) relative dielectric constant relative permeability military aircraft aluminium alloy (7050) 2.9×107 1 1 glass cockpit organic glass 0 3.4 1 cruise missile aluminium alloy (ZL114A) 2.16×107 1 1 radome fiberglass reinforced plastic composite material 0 4 1 hang beam duralumin alloy (ZL205A) 1.35×107 1 1 missile launcher duralumin alloy (ZL205A) 1.35×107 1 1 
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