High Current Physical Damage Testing System for Lightning Direct Effects on Aircraft

(model SXFJ-180612)

The aircraft is easy to be attacked by the direct lightning when it flies in the convective environment, which will generate high temperature, high pressure and strong electromagnetic force. This will cause some bad affection to the aircraft, such as burn, explosion, structural aberration, etc.

High Current Physical Damage Testing System for Lightning Direct Effects on Aircraft (model SXFJ-180612) is developed by our company and can simulate the direct lightning stroke with component A,B,C,D waveforms. It includes four sets impulse current test systems.

• Model SXFJ-180612
• Component A: exponential wave, peak amplitude=200kA±10%,minimum amplitude=20kA,action integral＝2*10⁶A²S±20%, time duration within 500μs, wave front time (10%~90% before peak amplitude)≤ 5μs;

• Component A_H: exponential wave, peak amplitude =200kA±10%, action integral＝8*10⁶A²S±20%, time duration within 500s, wave front time (10%~90% before peak amplitude)≤37.5μs;

• Component B: exponential wave, average amplitude＝2kA±10%, maximum charge transfer less than 10 Coulombs±10%, duration time ≤5ms, long duration impulse current waveform (square wave);

• Component C: DC current, average output current=200A~400A ,charge transfer=200 Coulombs±20%, duration time 1s (200A outputcurrent), 0.5s (400A output current);

• Component C*: DC current, average output current=200A~400A ,charge transfer=200 Coulombs±20%, duration time 1s (200A outputcurrent), 0.5s (400A output current);

• Component D: exponential wave, peak amplitude＝100kA±10%, action integral＝25*10⁶A²S±20%, time duration within 500μs, wave front time (10%~90% before peak amplitude)≤20μs;

• MIL-STD-464C Electromagnetic environmental effects requirements for systems
• SAE ARP5412 Aircraft lightning environment and related test waveforms
• RTCA/DO-160F/G Environmental conditions and test procedures for airborne equipment section 23 lightning direct effects