Lightening direct effect test system LCG

Specifications

High current injection system
Aircraft is vulnerable to lightening direct adhesion in severe convection weather, which will produce over temperature, high voltage and strong electromagnetic force to cause the aircraft to be on fire, corrosion, explosion, structure distortion and strength reduction, etc. The aircraft lightning protection test system researched and developed independently by 3ctest is a very complicated pulse current test system, fully meets American military MIL-STD-464C, SAE ARP5412 and DO160 section23, the direct adhesion lightening area of the aircraft should bear the continuous waveforms composed of A, B, C and D, this system includes four pulse current generators.

Six waveforms generated by four generators
Charging polarity automatic switching by using rotating mechanism
Electrical safety interlock, automatic short circuit capacitor and protect personal safety
Non-gap Crowbar feedback circuit, waveform without oscillation
Optical isolation of control signal between control and itself
Every generator used independently with independent control system
Many test modes can be programmed freely, meet kinds of test waveform requirements within test range
Centralized control system can operate four generators and complete the test with one key
High voltage switching by using multi-way air-operated units, waveforms switching over automatically

About Waveforms

Test waveforms include 6 waveforms: A, AH, B, C, C* and D, shown as below:

Component A: peak current 200kA±10%, action integral 2×106A2·s±20% (within 500μs), rise time (10%-90% before peak)≤50μs, decay to 1% of peak wave≤500μs. Current could be one-way or oscillatory.
Component AH: peak current 150kA±10%, action integral 0.8×106A2·s±20% (within 500μs), rise time (10%-90% before peak)≤37.5μs, decay to 1% of peak wave≤500μs. Current could be one-way or oscillatory.
Component B: current amplitude average 2kA±10%, max. electric charge＜10C ± 10%, duration ≤5ms. Current could be one-way square wave or replaced by exponential current or linear decay current.
Component C: current amplitude 200-800A, electric charge 200C ± 20%, duration 0.25-1s. Current could be one-way square wave or replaced by exponential current or linear decay current.
Component C*: current amplitude average≥400A, duration = dwell time of combination wave -5ms. Duration of combination wave: 1-50ms. Current could be one-way square wave or replaced by exponential current or linear decay current.
Component D, peak current 100kA±10%, unidirectional current or oscillatory current, rise time (10%-90% before peak)≤25μs, decay to 1% of peak ≤500μs, action integral 0.25×106A2·s±20% (within 500μs).
MIL-464C/DO-160G Section 23 Aircraft lightning protection system configuration:
This lightning system includes 5 set control system, 1 set measurement analysis system, 4 generators used to produce four components A, B, C, D, communication among generators by industry field bus to achieve independent experiments for 4 generators and centralized total control function.
Generator A and D use non-gap self-adaption Crowbar units, for non-gap Crowbar switch, there is no need to trigger by impulse voltage generator, no need to ignite by secondary delay control, it is a real self-adaption trigger. For non-gap switch, the noise is reduced greatly and the output reliability of equipments is improved.