All-climate aviation electrical AC / DC fault arc simulation experiment device

Abstract

The invention relates to an all-weather aviation electrical alternating current and direct current fault arc simulation experiment device. Comprising an experiment cabin, an experiment box, a movable sliding table, a stepping motor, an electrode bar, an arc generator, an arc temperature measuring mechanism, a temperature and humidity detecting mechanism, a humidity adjusting mechanism, a gas detecting mechanism, a gas concentration adjusting mechanism, an air pressure adjusting mechanism, a salt mist adjusting mechanism, an electrical device PLC and an operation control panel. The movable sliding table is arranged in the experiment cabin and driven by the stepping motor, the arc generator is arranged on the movable sliding table, the electrode bar is arranged on the arc generator, and the arc temperature measuring mechanism is arranged on one side of the movable sliding table. The operation control panel, the temperature and humidity detection mechanism, the humidity adjusting mechanism, the gas detection mechanism, the gas concentration adjusting mechanism and the gas pressure adjusting mechanism are all electrically connected to the electrical device PLC. The device has the beneficial effects that aviation AC / DC fault arc simulation experiments of large-range voltage and current in different environments can be realized, and the application field is wide.

Description

Technical Field

[0001] The present invention relates to the technical field, and particularly to a full-climate aviation electrical AC / DC fault arc simulation experimental device. Background Art

[0002] The electrification of power plants has the dual effects of improving energy utilization efficiency and reducing the emission of poisonous gases. Therefore, aircraft are developing towards more electric (MEA) and all-electric (AEA) directions, gradually replacing the subsystems that traditionally use mechanical, pneumatic, and hydraulic power with electrical systems. Commercial aircraft such as Boeing 787 and Airbus A350 have bus voltages of 230V AC and ±270V DC in their electrical systems, and there are plans to increase the voltage to 1kV - 5kV. Moreover, the design voltage level of future more electric aircraft (MEA) will reach as high as 10kV DC and higher medium-voltage DC (MVDC) systems. However, the increase in voltage will lead to an increase in arc faults and pose a fire risk. Since a large number of cables on aircraft are arranged in narrow channels and are often in extreme environments such as vibration, humidity, high temperature, and low air pressure, there are problems such as large temperature differences, high humidity, salt spray corrosion, and dust abrasion. It is very easy to induce fault arcs due to insulation damage, poor contact, etc., thus resulting in a fire risk on the aircraft. An arc is a gas discharge phenomenon with concentrated energy, extremely high temperature, and great brightness, and it is an electric ionization phenomenon with strong light and high temperature. The arc temperature is usually 5000 - 12000°C, which is much higher than the combustion temperature of most combustibles. The molten droplets produced by the high-temperature erosion of the conductor by the arc can not only ignite the surrounding combustibles but also rapidly expand the scope of the fire. Once the cable insulation fails, as long as the voltage exceeds 13V and the arc point current exceeds 0.13A, uncontrolled dynamic open arc behavior is likely to occur on the copper wire. The research on the prevention and damage of aviation arcs has gradually become the focus of attention in the aviation field.

[0003] In recent years, scholars at home and abroad have conducted a large number of studies and experiments on the mechanism and detection methods of arcs, mainly focusing on arc additive manufacturing, high and low voltage switchgear, power systems, etc., but less attention has been paid to the mechanism and detection methods of aviation arcs, especially the influence of environmental factors. Moreover, with the increase in bus voltage, the existing technology will not be able to meet the conditions for experiments. Therefore, how to detect and prevent aviation AC / DC fault arcs in different environments has become the key to ensuring aviation safety. Summary of the Invention

[0004] The purpose of the present invention is to overcome the shortcomings of the existing technology and provide a full-climate aviation electrical AC / DC fault arc simulation experimental device, which can realize the simulation experiments of aviation AC / DC fault arcs with a wide range of voltages and currents in different environments and has a wide application field.

[0005] The purpose of the present invention is achieved through the following technical solutions:

[0006] Full-climate aviation electrical AC / DC fault arc simulation experimental device, including:

[0007] An experimental chamber and an experimental box, the experimental chamber is arranged on the top of the experimental box;

[0008] A moving slide, a stepping motor, an electrode rod, an arc generator and an arc temperature measurement mechanism, the moving slide is arranged in the experimental chamber and driven by the stepping motor, the arc generator is arranged on the moving slide, the electrode rod is arranged on the moving slide, and the arc temperature measurement mechanism is arranged on one side of the moving slide;

[0009] A temperature and humidity detection mechanism and a humidity adjustment mechanism, the temperature and humidity detection mechanism is arranged in the experimental chamber, and the humidity adjustment mechanism is arranged in the experimental box;

[0010] A gas detection mechanism and a gas concentration adjustment mechanism, the gas detection mechanism is arranged on the top of the experimental chamber, and the gas concentration adjustment mechanism is arranged in the experimental box;

[0011] A pressure adjustment mechanism and a salt spray adjustment mechanism, the pressure adjustment mechanism is arranged in the experimental box, and the salt spray adjustment mechanism is arranged in the experimental chamber;

[0012] An electrical device PLC and an operation control panel, the operation control panel, the temperature and humidity detection mechanism, the humidity adjustment mechanism, the gas detection mechanism, the gas concentration adjustment mechanism, and the pressure adjustment mechanism are all electrically connected to the electrical device PLC.

[0013] Further, the arc temperature measurement mechanism includes a K-type thermocouple, a paperless recorder, and a thermocouple bracket. The thermocouple bracket is arranged on one side of the moving slide, the K-type thermocouple is arranged on the thermocouple bracket, and the paperless recorder is electrically connected to the K-type thermocouple.

[0014] Further, the temperature and humidity detection mechanism includes a temperature and humidity sensor arranged on the inner wall of the experimental chamber, and the temperature and humidity sensor is electrically connected to the electrical device PLC.

[0015] Further, the humidity adjustment mechanism includes a humidity valve, a water pump, an atomizer, and a water tank. The atomizer, the water pump, and the water tank are sequentially connected through a water pipe. The humidity valve is arranged on the water pipe between the atomizer and the water pump, and the humidity valve, the water pump, and the atomizer are all electrically connected to the electrical device PLC.

[0016] Further, the gas detection mechanism includes a carbon dioxide sensor and a nitrogen and oxygen sensor arranged on the top of the experimental chamber, and the carbon dioxide sensor and the nitrogen and oxygen sensor are both electrically connected to the electrical device PLC.

[0017] Furthermore, an intake main pipe is provided inside the bottom of the experimental cabin, and four intake branch pipes are provided inside the experimental chamber. The four intake branch pipes are all connected to the intake main pipe. The gas concentration adjustment mechanism includes an oxygen ball valve, a nitrogen ball valve, a carbon dioxide ball valve, and an air ball valve. The oxygen ball valve, the nitrogen ball valve, the carbon dioxide ball valve, and the air ball valve are respectively arranged on the four intake branch pipes, and the oxygen ball valve, the nitrogen ball valve, the carbon dioxide ball valve, and the air ball valve are all electrically connected to the electrical device PLC.

[0018] Furthermore, the air pressure adjustment mechanism includes an electric ball valve and a vacuum pump. The vacuum pump is arranged inside the experimental chamber. The vacuum pump is connected to the experimental cabin through an exhaust pipe. The electric ball valve is arranged on the exhaust pipe. The vacuum pump and the electric ball valve are both electrically connected to the electrical device PLC.

[0019] Furthermore, the salt spray adjustment mechanism includes a salt spray pipe and a peristaltic pump. The salt spray pipe is arranged inside the top of the experimental cabin and is connected to the peristaltic pump.

[0020] Furthermore, the arc generator is electrically connected to a waveform recorder, a power supply, and a resistance load box. The power supply is an AC power supply or a DC power supply.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. Through the settings of the temperature and humidity detection mechanism, the humidity adjustment mechanism, the gas detection mechanism, the gas concentration adjustment mechanism, the air pressure adjustment mechanism, the salt spray adjustment mechanism, the electrical device PLC, and the operation control panel, the present invention can realize the aviation AC / DC fault arc simulation experiment under different environments, and further obtain the fault arc characteristics of the cables in the aircraft under real conditions.

[0023] 2. Through the settings of the moving slide, the stepping motor, the electrode rod, the arc generator, and the arc temperature measurement mechanism, the present invention can realize the movement of the electrode rod in three directions of x, y, and z at different speeds, with a long moving distance and high moving accuracy, and can measure the arc temperature at different positions.

[0024] 3. The cable used in the main circuit of the present invention is 95m 2 , and the voltage of the equipped main circuit can reach 1000V, and the current can reach 350A, and the voltage at different frequencies can be realized, making the application field of the simulation experiment device wider. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is a three-dimensional schematic diagram of the overall structure of the present invention;

[0026] Figure 2 is a front view schematic diagram of the external structure of the present invention;

[0027] Figure 3 is a side view schematic diagram of the external structure of the present invention;

[0028] Figure 4 Rear view schematic diagram of the external structure of the present invention;

[0029] Figure 5 Top view schematic diagram of the external structure of the present invention;

[0030] Figure 6 For the present invention in Figure 2 Cross-sectional structure schematic diagram in the D-D direction;

[0031] Figure 7 For the present invention in Figure 4 Cross-sectional structure schematic diagram in the B-B direction;

[0032] Figure 8 For the present invention in Figure 5 Cross-sectional structure schematic diagram in the C-C direction;

[0033] Figure 9 Circuit connection schematic diagram of the arc generator in the present invention.

[0034] In the figure: 1. Experimental cabin; 2. Experimental box; 3. Moving slide; 4. Stepper motor; 5. Electrode rod; 6. Arc generator; 7. Operation control panel; 8. K-type thermocouple; 9. Thermocouple support; 10. Temperature and humidity sensor; 14. Water tank; 15. Carbon dioxide sensor; 16. Nitrogen and oxygen sensor; 17. Main intake pipe; 18. Intake branch pipe; 19. Oxygen ball valve; 20. Nitrogen ball valve; 21. Carbon dioxide ball valve; 22. Air ball valve; 23. Electric ball valve; 24. Vacuum pump; 25. Exhaust pipe; 26. Salt spray pipe. Specific embodiments

[0035] The present invention will be further described below with reference to the accompanying drawings, but the protection scope of the present invention is not limited to the following description.

[0036] As Figures 1 - 8 shown, a full-climate aviation electrical AC / DC fault arc simulation experimental device includes an experimental cabin 1, an experimental box 2, an electrical device PLC, and an operation control panel 7, wherein the experimental cabin 1 is fixed on the top of the experimental box 2.

[0037] As Figure 6As shown in the figure, a moving slide 3, a stepping motor 4, an electrode rod 5, an arc generator 6 and an arc temperature measuring mechanism are provided in the experimental chamber 1. The moving slide 3 is installed in the experimental chamber 1, the arc generator 6 is installed on the moving slide 3, the electrode rod 5 is installed on the moving slide 3, and the moving slide 3 is driven by the stepping motor 4. There are two moving slides 3. One moving slide 3 can move in the x and y directions, and the other moving slide 3 can move in the z direction. The electrode rod 5 is installed on the two moving slides 3, and under the drive of the stepping motor 4, the electrode rod 5 can move at different speeds in the x, y, and z directions. The arc temperature measuring mechanism is arranged on one side of the moving slide 3 and is used to measure the arc temperature at different positions. In this embodiment, the size of the electrode rod 5 is adjustable and the size range is 6 mm - 19 mm, the moving speed range of the electrode rod 5 is 0 mm / s - 39 mm / s; the effective moving distance of the moving slide 3 is 500 mm; the step size of the stepping motor 4 is 10 um / s, and the accuracy is ±5%.

[0038] The arc temperature measuring mechanism includes a K-type thermocouple 8, a paperless recorder and a thermocouple bracket 9. The thermocouple bracket 9 is installed on one side of the moving slide 3, the K-type thermocouple 8 is installed on the thermocouple bracket 9, and the paperless recorder is electrically connected to the K-type thermocouple 8. The maximum temperature that the K-type thermocouple 8 can measure is 1300 °C, and the response time is in the millisecond level. The arc temperature at different positions is measured by the K-type thermocouple 8, and the paperless recorder is used to collect the temperature data at different positions.

[0039] In order to implement simulation experiments under different temperature and humidity environments, a temperature and humidity detection mechanism is provided in the experimental chamber 1, and a humidity adjustment mechanism is provided in the test chamber. Specifically, the temperature and humidity detection mechanism includes a temperature and humidity sensor 10 provided on the inner wall of the experimental chamber 1, and the temperature and humidity sensor 10 is electrically connected to the electrical device PLC; the humidity adjustment mechanism includes a humidity valve, a water pump, an atomizer and a water tank 14. The water pump and the atomizer are both installed in the water tank 14. The atomizer, the water pump and the water tank 14 are connected in sequence through a water pipe. The humidity valve is installed on the water pipe between the atomizer and the water pump. The humidity valve, the water pump and the atomizer are all electrically connected to the electrical device PLC. The water pump transports the water in the water tank 14 to the atomizer, and then the atomizer turns the water into water mist and sprays the water mist into the experimental chamber 1 through a spray pipe, so as to realize the humidity environment in the experimental chamber 1. The temperature and humidity in the experimental chamber 1 can be detected by the temperature and humidity sensor 10, and the electrical device PLC can control the opening degree of the humidity valve according to the detected humidity data, so as to realize the adjustment of different humidities. In this embodiment, the humidity adjustment range is 20% - 80%.

[0040] In order to conduct simulation experiments under environments with different gas concentrations, a gas detection mechanism is provided at the top of the experimental chamber 1, and a gas concentration adjustment mechanism is provided inside the experimental box 2. An intake main pipe 17 is installed inside the bottom of the experimental chamber 1. There are four intake branch pipes 18 inside the experimental box 2, and the four intake branch pipes 18 are all connected to the intake main pipe 17. The four intake branch pipes 18 are respectively used to introduce oxygen, nitrogen, carbon dioxide, and air, and the introduced gases then enter the experimental chamber 1 through the intake main pipe 17. The gas detection mechanism includes a carbon dioxide sensor 15 and a nitrogen-oxygen sensor 16 provided at the top of the experimental chamber 1. The carbon dioxide sensor 15 and the nitrogen-oxygen sensor 16 are both electrically connected to the electrical device PLC. The carbon dioxide concentration inside the experimental chamber 1 can be detected through the carbon dioxide sensor 15, and the nitrogen concentration and oxygen concentration inside the experimental chamber 1 can be detected through the nitrogen-oxygen sensor 16. The gas concentration adjustment mechanism includes an oxygen ball valve 19, a nitrogen ball valve 20, a carbon dioxide ball valve 21, and an air ball valve 22. The oxygen ball valve 19, the nitrogen ball valve 20, the carbon dioxide ball valve 21, and the air ball valve 22 are respectively installed on the four intake branch pipes 18. The oxygen ball valve 19, the nitrogen ball valve 20, the carbon dioxide ball valve 21, and the air ball valve 22 are all electrically connected to the electrical device PLC. The electrical device PLC can adjust the oxygen concentration, nitrogen concentration, and carbon dioxide concentration inside the experimental chamber 1 by controlling the opening degrees of the oxygen ball valve 19, the nitrogen ball valve 20, the carbon dioxide ball valve 21, and the air ball valve 22 according to the detected gas concentrations.

[0041] In order to conduct simulation experiments under different air pressure environments, a air pressure adjustment mechanism is provided inside the test box. The air pressure adjustment mechanism includes an electric ball valve 23 and a vacuum pump 24. The vacuum pump 24 is installed inside the experimental box 2. The vacuum pump 24 is connected to the experimental chamber 1 through an exhaust pipe 25. The electric ball valve 23 is installed on the exhaust pipe 25. The vacuum pump 24 and the electric ball valve 23 are both electrically connected to the electrical device PLC. By using the vacuum pump 24 to evacuate the experimental chamber 1, a low air pressure environment inside the experimental chamber 1 can be achieved. By controlling the opening degree of the electric ball valve 23 through the electrical device PLC, the air pressure inside the experimental chamber 1 can be adjusted. In this embodiment, the range of air pressure adjustment is 30 kPa - 101 kPa.

[0042] In order to conduct simulation experiments under different salt spray environments, a salt spray adjustment mechanism is provided inside the experimental chamber 1. The salt spray adjustment mechanism includes a salt spray pipe 26 and a peristaltic pump. The salt spray pipe 26 is installed inside the top of the experimental chamber 1 and is connected to the peristaltic pump. The peristaltic pump can transport brine through the salt spray pipe 26 to the arc generation area, and different salt spray environments can be achieved by adjusting the transport rate of the brine.

[0043] As Figure 9As shown in the figure, the arc generator is electrically connected to a waveform recorder, a power supply, and a resistive load box. The power supply can be an AC power supply or a DC power supply. The DC power supply can provide a DC voltage of 0V - 1000V, and the current can reach 350A; the AC power supply can provide a voltage of 0V - 300V, and the frequency range can be freely adjusted within 15HZ - 1000HZ; the resistive load box can provide a resistance of 0Ω - 101Ω; the waveform recorder is used to collect data on the voltage across the arc and the circuit current. The memory of the waveform recorder is 256G, and the maximum sampling rate is 200Ms / s. The electrical device PLC can be used to adjust and control different experimental environments; the operation control panel 7 is located outside the experimental chamber 1 and is used to adjust different settings and functions. The cable used in the main circuit of this simulation experiment device is 95m 2 , the main circuit voltage equipped can reach 1000V, the current can reach 350A, and the voltage at different frequencies can be achieved, making the application field of the simulation experiment device wider.

[0044] Based on the above fault arc simulation experiment device, the present invention has carried out two specific experiments. The specific experimental steps and experimental results are as follows:

[0045] Experimental step one:

[0046] (1). Inspection of experimental layout: Verify the power supply, electrode rod, and load model required for this test; a 6mm electrode rod is selected for this experiment.

[0047] (2). Install the electrode rod, adjust the position of the electrode rod to make it aligned and seamless, lay tinfoil paper at the test position, and adjust the moving speed of the electrode rod to 0.02mm;

[0048] (3). Arrange the positions of the thermocouples. The horizontal positions are 5, 10, 15, 25, 35mm from the butt joint surface respectively, and the vertical arrangement positions are 0, 5, 10, 20mm from the electrode rod respectively;

[0049] (4). Record the initial data (power supply voltage, load, electrode material, electrode diameter, moving speed, air pressure, ambient temperature and humidity, etc.);

[0050] (5). Turn on the power supply, and select an AC output voltage of 200V and a resistance value of 20Ω according to the experimental requirements;

[0051] (6). Turn on the constant voltage mode on the operation control panel, start the vacuum pump, and pump the air pressure in the chamber to 80kPa.

[0052] (7). Turn on the waveform recorder, high-speed camera, and paperless recorder, set the parameters, and start recording the voltage and current waveforms before, during, and after the arc, the arc image, and the temperature of the thermocouple;

[0053] (8), Start the stepper motor, the electrode rod starts to move, observe and record data such as the distance, arc shape, and arc length of arc generation and arc extinction;

[0054] (9), When the electrode rods are separated until no arc is generated anymore, the experiment ends. Then, polish the carbon electrode rods and repeat the above steps to meet the requirements of repeated experiments.

[0055] After Experiment 1, observing the arc from generation to disappearance, the duration of the arc is obtained as 7.5 s.

[0056] Steps of Experiment 2:

[0057] (1), Inspection of experimental setup: Verify the power supply, electrode rods, and load models required for this experiment; a 6-mm electrode rod is selected for this experiment.

[0058] (2), Install the electrode rods, adjust the positions of the electrode rods so that they are aligned and there are no gaps, lay tinfoil paper at the test position, and adjust the moving speed of the electrode rods to 0.02 mm;

[0059] (3), Arrange the positions of the thermocouples. The horizontal positions are 5, 10, 15, 25, and 35 mm from the butt joint surface respectively, and the vertical arrangement positions are 0, 5, 10, and 20 mm from the electrode rods respectively;

[0060] (4), Record the initial data (power supply voltage, load, electrode material, electrode diameter, moving speed, air pressure, environmental temperature and humidity, etc.);

[0061] (5), Turn on the power supply, select an AC output voltage of 200 V and a resistance value of 20 Ω according to the experimental requirements;

[0062] (6), Turn on the constant voltage mode on the operation control panel, start the vacuum pump, and pump the air pressure in the chamber to 30 kPa.

[0063] (7), Turn on the waveform recorder, high-speed camera, and paperless recorder, set the parameters, and start recording the voltage and current waveforms before, during, and after the arc, the arc image, and the temperature of the thermocouples;

[0064] (8), Start the stepper motor, the electrode rod starts to move, observe and record data such as the distance, arc shape, and arc length of arc generation and arc extinction;

[0065] (9), When the electrode rods are separated until no arc is generated anymore, the experiment ends. Then, polish the carbon electrode rods and repeat the above steps to meet the requirements of repeated experiments.

[0066] After Experiment 2, observing the arc from generation to disappearance, the duration of the arc is obtained as 5 s.

[0067] Although embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. All-climate aviation electrical AC / DC fault arc simulation experimental device, characterized in that, Including: An experimental cabin (1) and an experimental box (2), the experimental cabin (1) is arranged on the top of the experimental box (2); A moving slide table (3), a stepping motor (4), an electrode rod (5), an arc generator (6) and an arc temperature measuring mechanism, the moving slide table (3) is arranged in the experimental cabin (1) and driven by the stepping motor (4), the arc generator (6) is arranged on the moving slide table (3), the electrode rod (5) is arranged on the moving slide table (3), and the arc temperature measuring mechanism is arranged on one side of the moving slide table (3); A temperature and humidity detection mechanism and a humidity adjustment mechanism, the temperature and humidity detection mechanism is arranged in the experimental cabin (1), and the humidity adjustment mechanism is arranged in the experimental box (2); A gas detection mechanism and a gas concentration adjustment mechanism, the gas detection mechanism is arranged on the top of the experimental cabin (1), and the gas concentration adjustment mechanism is arranged in the experimental box (2); A pressure adjustment mechanism and a salt spray adjustment mechanism, the pressure adjustment mechanism is arranged in the experimental box (2), and the salt spray adjustment mechanism is arranged in the experimental cabin (1); An electrical device PLC and an operation control panel (7), the operation control panel (7), the temperature and humidity detection mechanism, the humidity adjustment mechanism, the gas detection mechanism, the gas concentration adjustment mechanism, and the pressure adjustment mechanism are all electrically connected to the electrical device PLC.

2. The all-climate aviation electrical AC / DC fault arc simulation experimental device according to claim 1, wherein: The arc temperature measuring mechanism includes a K-type thermocouple (8), a paperless recorder, and a thermocouple bracket (9), the thermocouple bracket (9) is arranged on one side of the moving slide table (3), the K-type thermocouple (8) is arranged on the thermocouple bracket (9), and the paperless recorder is electrically connected to the K-type thermocouple (8).

3. The all-climate aviation electrical AC / DC fault arc simulation experimental device according to claim 1, characterized in that: The temperature and humidity detection mechanism includes a temperature and humidity sensor (10) arranged on the inner wall of the experimental cabin (1), and the temperature and humidity sensor (10) is electrically connected to the electrical device PLC.

4. The all-climate aviation electrical AC / DC fault arc simulation experimental device according to claim 1, characterized in that: The humidity adjustment mechanism includes a humidity valve, a water pump, an atomizer, and a water tank (14), the water pump and the atomizer are both arranged in the water tank (14), the atomizer, the water pump, and the water tank (14) are sequentially connected through a water pipe, the humidity valve is arranged on the water pipe between the water pump and the water tank (14), and the humidity valve (11), the water pump (12), and the atomizer (13) are all electrically connected to the electrical device PLC.

5. The all-climate aviation electrical AC / DC fault arc simulation experimental device according to claim 1, characterized in that: The gas detection mechanism includes a carbon dioxide sensor (15) and a nitrogen and oxygen sensor (16) arranged on the top of the experimental cabin (1), and the carbon dioxide sensor (15) and the nitrogen and oxygen sensor (16) are both electrically connected to the electrical device PLC.

6. The all-climate aviation electrical AC / DC fault arc simulation experimental device according to claim 1, characterized in that: An intake main pipe (17) is arranged inside the bottom of the experimental cabin (1), four intake branch pipes (18) are arranged inside the experimental box (2), the four intake branch pipes (18) are all communicated with the intake main pipe (17), the gas concentration adjustment mechanism includes an oxygen ball valve (19), a nitrogen ball valve (20), a carbon dioxide ball valve (21), and an air ball valve (22), the oxygen ball valve (19), the nitrogen ball valve (20), the carbon dioxide ball valve (21), and the air ball valve (22) are respectively arranged on the four intake branch pipes (18), and the oxygen ball valve (19), the nitrogen ball valve (20), the carbon dioxide ball valve (21), and the air ball valve (22) are all electrically connected to the electrical device PLC.

7. The all-climate aviation electrical AC / DC fault arc simulation experimental device according to claim 1, characterized in that: The air pressure regulating mechanism includes an electric ball valve (23) and a vacuum pump (24). The vacuum pump (24) is arranged inside the experimental chamber (2). The vacuum pump (24) is communicated with the experimental cabin (1) through an air extraction pipe (25). The electric ball valve (23) is arranged on the air extraction pipe (25). Both the vacuum pump (24) and the electric ball valve (23) are electrically connected to the electrical device PLC.

8. The all-climate aviation electrical AC / DC fault arc simulation experimental device according to claim 1, characterized in that: The salt spray regulating mechanism includes a salt spray pipe (26) and a peristaltic pump. The salt spray pipe (26) is arranged inside the top of the experimental cabin (1) and is connected to the peristaltic pump.

9. The all-climate aviation electrical AC / DC fault arc simulation experimental device according to claim 1, characterized in that: The arc generator is electrically connected to a waveform recorder, a power supply, and a resistance load box. The power supply is an AC power supply or a DC power supply.

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