Aircraft, missiles, rockets, reentry vehicles and other aircraft will inevitably encounter lightning environment during takeoff and landing. Any interference of electronic systems or units will cause serious flight accidents. Due to the characteristics of high lightning voltage (over 100 million volts) and large current (over 200kA), it is impossible to conduct the simulation test directly in the laboratory. According to different characteristics of lightning and test purposes, the lightning effect test is divided into two parts: direct effect of lightning and indirect effect of lightning.
The direct lightning effect test is used to simulate the effect of combustion, corrosion, blasting crack, structural distortion and intensity reduction of the aircraft when it is subjected to direct lightning action. In general, the direct lightning effect is divided into high voltage (attachment point) test and physical damage test with large current (injection).
The high voltage attachment zone test system can simulate the probability of lightning attack in different areas of the aircraft surface when the equipment such as aircraft is hit by lightning. The large current physical damage test system is used to simulate the damage effect of high temperature and strong electric power on aircraft structure when the aircraft is hit by lightning.
Standard
MIL-STD-464C Electromagnetic Environmental Effects Requirements for SystemsVehicular high voltage test system
Physical damage test with large current
Vehicular high voltage test system
1.Summarize
2.Characteristic
Indoor type adopts open main loop design and h-type tower mechanism, thus achieving overall subminiature (figure 1)3.Definition of waveform parameters
According to standards such as mil-std-464c and SAE ARP5412, the test waveform mainly consists of four voltage waveforms A, B, C and D, as shown in the figure below.
Main technical parameters and features
LVG3000Technical parameters: |
||||
Output waveform |
A waveform |
B waveform |
C waveform |
D waveform |
Wavefront time |
1000(+500)kV/μs |
1.2μs±20% |
2μs±20% |
50-250μs |
Decay time |
-- |
50±20% |
-- |
Is greater than 2000 |
Peak efficiency |
More than 80% |
More than 90% |
More than 80% |
More than 60% |
The voltage level |
200kV |
|||
series |
15 |
|||
Voltage grade |
3000kV |
|||
Discharge switch |
Copper ball, triple play ignition |
|||
Switch forms |
Linear drive 0-100mm adjustable, accuracy 0.1 mm |
|||
Form mode |
A multistage Marx generator is used |
|||
Use the power supply |
AC220V 100A |
|||
Charging voltage |
20~200kV |
|||
Charge polarity |
Positive/negative |
|||
Voltage measurement |
If the damping voltage divider |
The plane's lightning high voltage is attached to the zoning test schematic
It can be used in vehicle high voltage lightning simulator
Indoor high-voltage test equipment (reference)
The test contents can be completed
Physical damage test with large current
Description of the apparatus
满足标准
characteristic
Introduction to test project
Continuous waveform as defined by the aircraft lightning direct effect standard
Control system general parameters | |
viewing screen |
A 15-inch color touch screen+Industrial PC |
Working power range |
AC 220 V 50 / 60 Hz 32A/The generator |
controlCommunication methods |
Industrial fiber networking controlCC-Link |
Measurement communication mode |
Industrial fiber Ethernet control |
Discharge interval |
20-999s,Can be set up |
The output polarity |
Positive and negative |
Instrument working status indication |
Touch screen, alarm light, alarm bell |
Instrument ground connection mode |
The use of copper platoon+Soft connect the ground wire |
size |
4m measurement and control vehicle (optional including vehicle) |
Instrument weight |
about3tons |
Temperature range |
-20~+50℃ |
Humidity range |
≤90% |
The altitude |
No more than1500m |