A fault simulation device for aviation power supply system and its control method

Abstract

This invention discloses an aviation power supply system fault simulation device and its control method, comprising: an AC aviation power module, an aviation DC power module, a multiplexer, a poor contact and overload fault simulator, an RLC load, and a signal collector; the poor contact and overload fault simulator is used to simulate the generation of series arcs of poor contact faults in aviation AC power supply and aviation DC power supply under different RLC load conditions and to collect arc images and arc temperatures, as well as to collect wire images and temperatures during overload faults; the signal collector is used to collect the voltage values ​​between the neutral and live wires, the voltage values ​​between the positive and negative terminals, the current flowing through the neutral or negative terminal, and the current flowing through the live or positive terminal between the multiplexer and the poor contact and overload fault simulator after the series arc is generated; the RLC load is used to simulate the generation of different types of loads, including resistive loads, inductive loads, and capacitive loads.

Description

Technical Field

[0001] This invention relates to the field of aviation power supply system technology, and more specifically to an aviation power supply system fault simulation device and its control method. Background Technology

[0002] Aviation power supply systems are a crucial guarantee for the normal operation of modern aircraft. Their main function is to provide reliable power supply for airborne electronic equipment, navigation systems, communication systems, and so on. However, due to the complex operating environment and diverse electrical loads of aircraft, power supply systems are susceptible to faults such as poor contact and overload, which can lead to unstable equipment operation and even safety hazards.

[0003] Currently, traditional fault analysis of aviation power supply systems mainly relies on theoretical research and the summary of actual fault cases.

[0004] However, due to the sporadic and complex nature of actual faults, it is difficult to fully reproduce the fault phenomena and obtain relevant data in a real environment. At the same time, most existing fault simulation devices have limited functions and cannot fully cover various faults of different types of power supply systems. In particular, there is a lack of effective experimental means for fault simulation of aviation-specific power supply environments (such as AC115V 400Hz and 28V DC).

[0005] In addition, fault phenomena in aviation power supply systems, such as series arcing caused by poor contact and overcurrent characteristics under overload conditions, involve complex physical processes. These phenomena not only affect the safety of power supply lines and equipment, but also pose new demands for the development of fault diagnosis technology.

[0006] Therefore, how to provide an aviation power supply system fault simulation device that can cover multiple power supply modes, simulate poor contact and overload faults, and collect key data is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0007] In view of this, the present invention provides an aviation power supply system fault simulation device and its control method to solve some of the technical problems mentioned in the background art.

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] An aviation power supply system fault simulation device includes: an AC aviation power module, an aviation DC power module, a multiplexer, a poor contact and overload fault simulator, an RLC load, and a signal collector;

[0010] Both the AC aviation power module and the aviation DC power module have their input terminals connected to 220V AC power.

[0011] The neutral output terminal of the AC aviation power module and the negative output terminal of the aviation DC power module are respectively electrically connected to the neutral / negative input terminal of the poor contact and overload fault simulator through one of the switches of the multiplexer.

[0012] The AC aviation power module's fire wire output terminal and the aviation DC power module's positive output terminal are respectively electrically connected to the fire wire / positive input terminal of the poor contact and overload fault simulator through one of the switches of the multiplexer.

[0013] The output of the poor contact and overload fault simulator is electrically connected to the input of the RLC load;

[0014] The signal collector is used to collect the voltage values ​​between the neutral and live wires, the voltage values ​​between the positive and negative terminals, the current flowing through the neutral or negative wire, and the current flowing through the live or positive wire after the series arc is generated.

[0015] RLC loads are used to simulate different types of loads, including resistive loads, inductive loads, and capacitive loads.

[0016] The poor contact and overload fault simulator is used to simulate series arcs in the power supply line under different RLC load conditions, generating poor contact in the AC power supply and poor contact in the DC power supply of aviation power, and to collect arc images and arc temperatures. It also simulates overload faults in the AC power supply and overload faults in the DC power supply of aviation power, and collects wire images and temperatures.

[0017] Preferably, the aviation power supply system fault simulation device further includes a control and display module. The signal collector, multiplexer, poor contact and overload fault simulator, and RLC load are all electrically connected to the control and display module. The control and display module is used to control the operation of the signal collector, multiplexer, poor contact and overload fault simulator, and RLC load, and to display data graphics in real time.

[0018] Preferably, the aircraft power supply system fault simulation device further includes a first voltage sensor, a second voltage sensor, a first current sensor, and a second current sensor.

[0019] The first voltage sensor is connected in parallel between the neutral wire and the live wire, and the second voltage sensor is connected in parallel between the positive terminal and the negative terminal.

[0020] The first current sensor is connected in series with the neutral wire and the negative terminal to measure the current flowing through the neutral wire or the negative terminal. The second current sensor is connected in series with the live wire and the positive terminal to measure the current flowing through the live wire or the positive terminal.

[0021] The first voltage sensor, the first current sensor, the second voltage sensor, and the second current sensor are all electrically connected to the signal collector.

[0022] Preferably, the AC aviation power module has a voltage of 115V AC and a frequency of 400Hz; the aviation DC power module has a voltage of 28V DC.

[0023] Preferably, the poor contact and overload fault simulator includes: an insulating column, an experimental wire clamp, a stepper motor slide, a vibration table, a controller, a high-speed photography module, and an infrared temperature measurement module;

[0024] The experimental wire clamp includes a first experimental wire clamp, a second experimental wire clamp, a third experimental wire clamp, and a fourth experimental wire clamp; the insulating column includes a first insulating column, a second insulating column, a third insulating column, and a fourth insulating column; the stepper motor slide includes a first stepper motor slide and a second stepper motor slide; and the vibration table includes a first vibration table and a second vibration table.

[0025] The first experimental wire clamp is electrically connected to the live / positive input terminal; the second experimental wire clamp is electrically connected to the L live / positive terminal of the RLC load; the third experimental wire clamp is electrically connected to the neutral / negative input terminal; and the fourth experimental wire clamp is electrically connected to the N neutral / negative terminal of the RLC load.

[0026] The first experimental wire clamp, the second experimental wire clamp, the third experimental wire clamp, and the fourth experimental wire clamp are respectively fixed to the upper ends of the first insulating column, the second insulating column, the third insulating column, and the fourth insulating column.

[0027] The first experimental lead clamp and the second experimental lead clamp, the third experimental lead clamp and the fourth experimental lead clamp are connected by a whole or segmented experimental lead to be tested;

[0028] The lower end of the second insulating column is fixed to the slide of the first stepper motor, and the lower end of the fourth insulating column is fixed to the slide of the second stepper motor; the lower ends of the first insulating column and the third insulating column are respectively fixed to the first vibration table and the second vibration table;

[0029] The controller is electrically connected to the first stepper motor slide and the second stepper motor slide respectively, and is used to control the stepper motor slide to move left and right, thereby driving the second experimental wire clamp and the fourth experimental wire clamp to move left and right to generate a series arc; the controller is electrically connected to the first vibration table and the second vibration table respectively, and is used to control the vibration table to vibrate up and down to simulate a series arc with poor contact under vibration.

[0030] The high-speed photography module and the infrared temperature measurement module are used to acquire arc images and temperatures of the series arcs generated by the experimental wires under test between the first experimental wire clamp and the second experimental wire clamp, and between the third experimental wire clamp and the fourth experimental wire clamp, when there is a poor contact fault, as well as wire images and temperatures when there is an overload fault.

[0031] Preferably, the controller, high-speed photography module, and infrared temperature measurement module are all electrically connected to the control and display module;

[0032] The controller receives control commands from the control and display module to control the left and right movement of the first stepper motor slide and the second stepper motor slide, and sends control commands to control the up and down vibration of the first vibration table and the second vibration table.

[0033] The high-speed photography module and the infrared temperature measurement module transmit the measured series arc images and temperature data, as well as the wire images and temperatures, to the control and display module.

[0034] Preferably, the poor contact and overload fault simulator also includes a shielding cover;

[0035] The insulating column, experimental wire clamp, stepper motor slide, high-speed photography module, controller and infrared temperature measurement module are all placed inside the shielding cover; the lower end of the first insulating column is fixed to the bottom of the shielding cover, and the lower end of the third insulating column is fixed to the bottom of the shielding cover; the high-speed photography module and infrared temperature measurement module are fixed to the upper inner wall of the shielding cover.

[0036] Preferably, the signal collector includes: a power module, a power supply circuit, a filter circuit, a level conversion circuit, and an interface;

[0037] The power module is electrically connected to the input terminal of the power supply circuit; the output terminal of the power supply circuit is electrically connected to the filter circuit and the level conversion circuit respectively, providing power to the filter circuit and the level conversion circuit.

[0038] The interface includes interface A and interface B;

[0039] Interface A is electrically connected to the first voltage sensor, the second voltage sensor, the first current sensor, the second current sensor, and the filter circuit. The level conversion circuit is electrically connected to the output of the filter circuit and interface B, respectively. Interface B is electrically connected to the control and display module.

[0040] The sensor signal is connected to the signal collector through interface A, and after being filtered, it is processed by the level conversion circuit and then output to the control and display module.

[0041] A control method for an aviation power supply system fault simulation device, based on the aforementioned aviation power supply system fault simulation device, includes:

[0042] S1. Based on the types of simulated AC power supply contact failure, AC power supply overload failure, DC power supply contact failure, and DC power supply overload failure, select the test lead for the contact failure and overload failure simulator and select the load type.

[0043] S2. Control the closing of each corresponding switch of the multiplexer switch according to the fault type of the model;

[0044] S3. The simulator for controlling poor contact and overload faults simulates series arcs in the power supply line under different RLC load conditions, generating poor contact in both AC and DC power supply of aviation power, and collects arc images and arc temperatures. It also simulates overload faults in both AC and DC power supply of aviation power, and collects conductor images and temperatures. After the series arc is generated, the signal collector is activated to collect the current and voltage in the power supply line at this time.

[0045] Preferably, the experimental lead wire to be tested is a whole segment or segments;

[0046] When simulating poor contact in AC and DC power supply for aviation applications, and simulating a series arc on the live wire or positive terminal, the section between the first and second experimental lead clamps represents the segmented experimental lead, while the section between the third and fourth experimental lead clamps represents the entire segmented experimental lead. Conversely, when simulating a series arc on the neutral or negative terminal, the section between the first and second experimental lead clamps represents the entire segmented experimental lead, while the section between the third and fourth experimental lead clamps represents the segmented experimental lead.

[0047] When simulating AC power supply overload faults and DC power supply overload faults in aviation power supplies, the entire test conductor is located between the first and second experimental conductor clamps, and between the third and fourth experimental conductor clamps.

[0048] As can be seen from the above technical solution, compared with the prior art, the present invention discloses a fault simulation device and control method for aviation power supply systems. Through modular design, it can simulate poor contact and overload faults in aviation power supply systems, and supports experiments under AC115V and DC28V power supply environments. By adjusting the spacing of the conductors under test through a stepper motor slide, it simulates the series arc when a poor contact fault occurs. With the help of high-speed photography and infrared temperature measurement modules, it collects arc images and temperature data, and obtains conductor temperature rise data from conductor images and temperatures during overload faults. The signal collector monitors current and voltage signals in real time. The RLC load can simulate various load types of aviation power supply systems, realizing accurate simulation, data recording and subsequent analysis of aviation power supply system faults, which helps to provide reliable technical support for fault analysis and teaching experiments of aviation power supply systems. Attached Figure Description

[0049] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0050] Figure 1 A schematic diagram of the structure of an aviation power supply system fault simulation device provided by the present invention;

[0051] Figure 2 This is a schematic diagram of the structure of the poor contact and overload fault simulator provided by the present invention;

[0052] Figure 3 A circuit diagram of the signal collector provided by the present invention. Detailed Implementation

[0053] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0054] This invention discloses a fault simulation device for an aviation power supply system, such as... Figure 1 As shown, it includes: AC aviation power module, aviation DC power module, multiplexer, poor contact and overload fault simulator, RLC load and signal collector;

[0055] The input terminals of both the AC aviation power module and the aviation DC power module are electrically connected to 220V AC power via wires N1 and L1.

[0056] The neutral output terminal of the AC aviation power module and the negative output terminal of the aviation DC power module are respectively electrically connected to the neutral / negative input terminal of the poor contact and overload fault simulator through one of the switches of the multiplexer.

[0057] The AC aviation power module's fire wire output terminal and the aviation DC power module's positive output terminal are respectively electrically connected to the fire wire / positive input terminal of the poor contact and overload fault simulator through one of the switches of the multiplexer.

[0058] The output of the poor contact and overload fault simulator is electrically connected to the input of the RLC load;

[0059] The signal collector is used to collect the voltage values ​​between the neutral and live wires, the voltage values ​​between the positive and negative terminals, the current flowing through the neutral or negative wire, and the current flowing through the live or positive wire after the series arc is generated.

[0060] RLC loads are used to simulate different types of loads, including resistive loads, inductive loads, and capacitive loads.

[0061] The poor contact and overload fault simulator is used to simulate series arcs in the power supply line under different RLC load conditions, generating poor contact in the AC power supply and poor contact in the DC power supply of aviation power, and to collect arc images and arc temperatures. It also simulates overload faults in the AC power supply and overload faults in the DC power supply of aviation power, and collects wire images and temperatures.

[0062] To further implement the above technical solution, an aviation power supply system fault simulation device also includes a control and display module. The signal collector, multiplexer, poor contact and overload fault simulator, and RLC load are all electrically connected to the control and display module. The control and display module is used to control the operation of the signal collector, multiplexer, poor contact and overload fault simulator, and RLC load, and to display data graphics in real time.

[0063] To further implement the above technical solution, an aviation power supply system fault simulation device further includes a first voltage sensor, a second voltage sensor, a first current sensor, and a second current sensor.

[0064] The first voltage sensor is connected in parallel between the neutral wire and the live wire, and the second voltage sensor is connected in parallel between the positive terminal and the negative terminal.

[0065] The first current sensor is connected in series with the neutral wire and the negative terminal to measure the current flowing through the neutral wire or the negative terminal. The second current sensor is connected in series with the live wire and the positive terminal to measure the current flowing through the live wire or the positive terminal.

[0066] The first voltage sensor, the first current sensor, the second voltage sensor, and the second current sensor are all electrically connected to the signal collector.

[0067] To further implement the above technical solution, the AC aviation power module has a voltage of 115V AC and a frequency of 400Hz; the aviation DC power module has a voltage of 28V DC.

[0068] To further implement the above technical solution, the poor contact and overload fault simulator includes: an insulating column, an experimental wire clamp, a stepper motor slide, a vibration table, a controller, a high-speed photography module, and an infrared temperature measurement module;

[0069] The experimental wire clamp includes a first experimental wire clamp, a second experimental wire clamp, a third experimental wire clamp, and a fourth experimental wire clamp; the insulating column includes a first insulating column, a second insulating column, a third insulating column, and a fourth insulating column; the stepper motor slide includes a first stepper motor slide and a second stepper motor slide; and the vibration table includes a first vibration table and a second vibration table.

[0070] The first experimental wire clamp is electrically connected to the live / positive input terminal; the second experimental wire clamp is electrically connected to the L live / positive terminal of the RLC load; the third experimental wire clamp is electrically connected to the neutral / negative input terminal; and the fourth experimental wire clamp is electrically connected to the N neutral / negative terminal of the RLC load.

[0071] The first experimental wire clamp, the second experimental wire clamp, the third experimental wire clamp, and the fourth experimental wire clamp are respectively fixed to the upper ends of the first insulating column, the second insulating column, the third insulating column, and the fourth insulating column.

[0072] The first experimental lead clamp and the second experimental lead clamp, the third experimental lead clamp and the fourth experimental lead clamp are connected by a whole or segmented experimental lead to be tested;

[0073] The lower end of the second insulating column is fixed to the slide of the first stepper motor, and the lower end of the fourth insulating column is fixed to the slide of the second stepper motor; the lower ends of the first insulating column and the third insulating column are respectively fixed to the first vibration table and the second vibration table;

[0074] The controller is electrically connected to the first stepper motor slide and the second stepper motor slide respectively, and is used to control the stepper motor slide to move left and right, thereby driving the second experimental wire clamp and the fourth experimental wire clamp to move left and right to generate a series arc; the controller is electrically connected to the first vibration table and the second vibration table respectively, and is used to control the vibration table to vibrate up and down to simulate a series arc with poor contact under vibration.

[0075] The high-speed photography module and the infrared temperature measurement module are used to acquire arc images and temperatures of the series arcs generated by the experimental wires under test between the first experimental wire clamp and the second experimental wire clamp, and between the third experimental wire clamp and the fourth experimental wire clamp, when there is a poor contact fault, as well as wire images and temperatures when there is an overload fault.

[0076] In this embodiment, the first vibration table and the second vibration table simulate vibration to study the effect of vibration on the generated series arc under the condition of poor contact fault.

[0077] In practical applications, the test lead is a dedicated lead for aviation power supply systems. The molten metal beads generated by the series arc of the test lead fall to the bottom of the shield and are collected for later fault analysis.

[0078] To further implement the above technical solution, the controller, high-speed photography module, and infrared temperature measurement module are all electrically connected to the control and display module.

[0079] The controller receives control commands from the control and display module to control the left and right movement of the first stepper motor slide and the second stepper motor slide, and sends control commands to control the up and down vibration of the first vibration table and the second vibration table.

[0080] The high-speed photography module and the infrared temperature measurement module transmit the measured series arc images and temperature data, as well as the wire images and temperatures, to the control and display module.

[0081] In practical applications, the control and display module includes a computer and a software operation interface. The software operation interface is self-programmed and is used to output control signals and display the electrical signals of the signal acquisition unit in real time.

[0082] To further implement the above technical solutions, the poor contact and overload fault simulator also includes a shielding cover;

[0083] The insulating column, experimental wire clamp, stepper motor slide, high-speed photography module, controller and infrared temperature measurement module are all placed inside the shielding cover; the lower end of the first insulating column is fixed to the bottom of the shielding cover, and the lower end of the third insulating column is fixed to the bottom of the shielding cover; the high-speed photography module and infrared temperature measurement module are fixed to the upper inner wall of the shielding cover.

[0084] In this embodiment, the shielding material is a transparent, insulating, and explosion-proof material.

[0085] To further implement the above technical solution, the signal collector includes: a power module, a power supply circuit, a filter circuit, a level conversion circuit, and an interface;

[0086] The power module is electrically connected to the input terminal of the power supply circuit; the output terminal of the power supply circuit is electrically connected to the filter circuit and the level conversion circuit respectively, providing power to the filter circuit and the level conversion circuit.

[0087] The interface includes interface A and interface B;

[0088] Interface A is electrically connected to the first voltage sensor, the second voltage sensor, the first current sensor, the second current sensor, and the filter circuit. The level conversion circuit is electrically connected to the output of the filter circuit and interface B, respectively. Interface B is electrically connected to the control and display module.

[0089] The sensor signal is connected to the signal collector through interface A, and after being filtered, it is processed by the level conversion circuit and then output to the control and display module.

[0090] A control method for an aviation power supply system fault simulation device, based on an aviation power supply system fault simulation device, includes:

[0091] S1. Based on the types of simulated AC power supply contact failure, AC power supply overload failure, DC power supply contact failure, and DC power supply overload failure, select the test lead for the contact failure and overload failure simulator and select the load type.

[0092] S2. Control the closing of each corresponding switch of the multiplexer switch according to the fault type of the model;

[0093] S3. The simulator for controlling poor contact and overload faults simulates series arcs in the power supply line under different RLC load conditions, generating poor contact in both AC and DC power supply of aviation power, and collects arc images and arc temperatures. It also simulates overload faults in both AC and DC power supply of aviation power, and collects conductor images and temperatures. After the series arc is generated, the signal collector is activated to collect the current and voltage in the power supply line at this time.

[0094] To further implement the above technical solution, the experimental lead wire to be tested can be a whole segment or in segments;

[0095] When simulating poor contact in AC power supply and poor contact in DC power supply of aviation power, if a series arc occurs in the live wire or positive terminal, the section between the first and second experimental wire clamps is the test wire segmented, and the section between the third and fourth experimental wire clamps is the test wire segmented. If a series arc occurs in the neutral wire or negative terminal, the section between the first and second experimental wire clamps is the test wire segmented.

[0096] When simulating AC power supply overload faults and DC power supply overload faults in aviation power supplies, the entire test conductor is located between the first and second experimental conductor clamps, and between the third and fourth experimental conductor clamps.

[0097] The control method is explained in detail using a simulation of a poor contact fault in the AC power supply of an aircraft as an example:

[0098] (1) Open the shielding cover of the poor contact and overload fault simulator, clamp the first section of the test wire with the first test wire clamp, clamp the second section of the test wire with the second test wire clamp, clamp the entire test wire with the third and fourth test wire clamps, and close the shielding cover.

[0099] (2) Select the load type on the control and display module software operation interface, and the control and display module sends control commands to control the RLC load type;

[0100] (3) Click the K1 icon and K2 icon on the control and display module software operation interface. After the multiplexer receives the control signal, the corresponding K1 and K2 switches will close.

[0101] (4) Click the leftward movement icon of the first stepper motor slide on the control and display module software operation interface. The first stepper motor slide drives the second experimental wire clamped by the second experimental wire clamp to move to the left. As the distance between the first experimental wire and the second experimental wire decreases, a series arc is generated between them.

[0102] (5) After the series arc is generated, the signal collector module, high-speed photography module and infrared temperature measurement module are activated to collect the current, voltage, arc image and arc temperature in the power supply line at this time.

[0103] (6) The control and display module software interface displays the above data in real time. After recording for a period of time, the first step motor slide can be controlled to continue to move to the left to realize the electric arc simulation under different spacing between the first section of the experimental wire to be tested and the second section of the experimental wire to be tested.

[0104] (7) After the experiment is completed, save the experimental data and graphs, disconnect the K1 and K2 switches of the multiplexer, and collect the metal beads generated by the electric arc in the first and second sections of the experimental wire to be tested.

[0105] (8) Click the experiment end icon on the control and display module software operation interface. The first stepper motor slide moves to the right and returns to the initial position, and the experiment is completed.

[0106] If an overload fault simulation of the AC power supply of aviation power is to be performed, the K1 and K2 of the multiplex switch are closed, the complete test wire is clamped between the first experimental wire clamp and the second experimental wire clamp, and the complete test wire is clamped between the third experimental wire clamp and the fourth experimental wire clamp.

[0107] If a fault simulation of poor DC power supply contact is to be performed, close the multiplex switch K3 and K4, clamp two sections of the test wire between the first and second test wire clamps, and clamp the complete test wire between the third and fourth test wire clamps.

[0108] If an overload fault simulation of the DC power supply for aviation is to be performed, the K3 and K4 of the multiplexer are closed, the complete section of the test wire is clamped between the first and second test wire clamps, and the complete section of the test wire is clamped between the third and fourth test wire clamps.

[0109] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to the method section.

[0110] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A fault simulation device for an aviation power supply system, characterized in that, include: AC aviation power modules, aviation DC power modules, multiplex switches, poor contact and overload fault simulators, RLC loads and signal collectors; Both the AC aviation power module and the aviation DC power module have their input terminals connected to 220V AC power. The neutral output terminal of the AC aviation power module and the negative output terminal of the aviation DC power module are respectively electrically connected to the neutral / negative input terminal of the poor contact and overload fault simulator through one of the switches of the multiplexer. The AC aviation power module's fire wire output terminal and the aviation DC power module's positive output terminal are respectively electrically connected to the fire wire / positive input terminal of the poor contact and overload fault simulator through one of the switches of the multiplexer. The output of the poor contact and overload fault simulator is electrically connected to the input of the RLC load; The signal collector is used to collect the voltage values ​​between the neutral and live wires, the voltage values ​​between the positive and negative terminals, the current flowing through the neutral or negative wire, and the current flowing through the live or positive wire after the series arc is generated. RLC loads are used to simulate different types of loads, including resistive loads, inductive loads, and capacitive loads. The poor contact and overload fault simulator is used to simulate series arcs in the power supply line under different RLC load conditions, such as poor contact faults in the AC power supply and poor contact faults in the DC power supply of aviation power, and to collect arc images and arc temperatures. It also simulates overload faults in the AC power supply and overload faults in the DC power supply of aviation power, and collects wire images and temperatures. The poor contact and overload fault simulator includes: an insulating column, experimental wire clamps, a stepper motor slide, a controller, a vibration table, a high-speed photography module, and an infrared temperature measurement module; The experimental wire clamp includes a first experimental wire clamp, a second experimental wire clamp, a third experimental wire clamp, and a fourth experimental wire clamp; the insulating column includes a first insulating column, a second insulating column, a third insulating column, and a fourth insulating column; the stepper motor slide includes a first stepper motor slide and a second stepper motor slide; and the vibration table includes a first vibration table and a second vibration table. The first experimental wire clamp is electrically connected to the live / positive input terminal; the second experimental wire clamp is electrically connected to the L live / positive terminal of the RLC load; the third experimental wire clamp is electrically connected to the neutral / negative input terminal; and the fourth experimental wire clamp is electrically connected to the N neutral / negative terminal of the RLC load. The first experimental wire clamp, the second experimental wire clamp, the third experimental wire clamp, and the fourth experimental wire clamp are respectively fixed to the upper ends of the first insulating column, the second insulating column, the third insulating column, and the fourth insulating column. The first experimental lead clamp and the second experimental lead clamp, the third experimental lead clamp and the fourth experimental lead clamp are connected by a whole or segmented experimental lead to be tested; The lower end of the second insulating column is fixed to the slide of the first stepper motor, and the lower end of the fourth insulating column is fixed to the slide of the second stepper motor; the lower ends of the first insulating column and the third insulating column are respectively fixed to the first vibration table and the second vibration table; The controller is electrically connected to the first stepper motor slide and the second stepper motor slide respectively, and is used to control the stepper motor slide to move left and right, thereby driving the second experimental wire clamp and the fourth experimental wire clamp to move left and right to generate a series arc; the controller is electrically connected to the first vibration table and the second vibration table respectively, and is used to control the vibration table to vibrate up and down to simulate a series arc with poor contact under vibration. The high-speed photography module and the infrared temperature measurement module are used to acquire arc images and temperatures of the series arcs generated by the experimental wires under test between the first experimental wire clamp and the second experimental wire clamp, and between the third experimental wire clamp and the fourth experimental wire clamp, when there is a poor contact fault, as well as wire images and temperatures when there is an overload fault.

2. The aircraft power supply system fault simulation device according to claim 1, characterized in that, It also includes a control and display module. The signal collector, multiplexer, poor contact and overload fault simulator, and RLC load are all electrically connected to the control and display module. The control and display module is used to control the operation of the signal collector, multiplexer, poor contact and overload fault simulator, and RLC load, and to display data graphics in real time.

3. The aircraft power supply system fault simulation device according to claim 2, characterized in that, It also includes a first voltage sensor, a second voltage sensor, a first current sensor, and a second current sensor; The first voltage sensor is connected in parallel between the neutral wire and the live wire, and the second voltage sensor is connected in parallel between the positive terminal and the negative terminal. The first current sensor is connected in series with the neutral wire and the negative terminal to measure the current flowing through the neutral wire or the negative terminal. The second current sensor is connected in series with the live wire and the positive terminal to measure the current flowing through the live wire or the positive terminal. The first voltage sensor, the first current sensor, the second voltage sensor, and the second current sensor are all electrically connected to the signal collector.

4. The aircraft power supply system fault simulation device according to claim 1, characterized in that, The AC aviation power module has a voltage of 115V AC and a frequency of 400Hz; the aviation DC power module has a voltage of 28V DC.

5. The aircraft power supply system fault simulation device according to claim 2, characterized in that, The controller, high-speed photography module, and infrared temperature measurement module are all electrically connected to the control and display module; The controller receives control commands from the control and display module to control the left and right movement of the first stepper motor slide and the second stepper motor slide, and sends control commands to control the up and down vibration of the first vibration table and the second vibration table. The high-speed photography module and the infrared temperature measurement module transmit the measured series arc images and temperature data, as well as the wire images and temperatures, to the control and display module.

6. The aircraft power supply system fault simulation device according to claim 1, characterized in that, The poor contact and overload fault simulator also includes a shielding cover; The insulating column, experimental wire clamp, stepper motor slide, high-speed photography module, controller and infrared temperature measurement module are all placed inside the shielding cover; the lower end of the first insulating column is fixed to the bottom of the shielding cover, and the lower end of the third insulating column is fixed to the bottom of the shielding cover; the high-speed photography module and infrared temperature measurement module are fixed to the upper inner wall of the shielding cover.

7. The aircraft power supply system fault simulation device according to claim 3, characterized in that, The signal collector includes: a power module, a power supply circuit, a filter circuit, a level conversion circuit, and an interface; The power module is electrically connected to the input terminal of the power supply circuit; the output terminal of the power supply circuit is electrically connected to the filter circuit and the level conversion circuit respectively, providing power to the filter circuit and the level conversion circuit. The interface includes interface A and interface B; Interface A is electrically connected to the first voltage sensor, the second voltage sensor, the first current sensor, the second current sensor, and the filter circuit. The level conversion circuit is electrically connected to the output of the filter circuit and interface B, respectively. Interface B is electrically connected to the control and display module. The sensor signal is connected to the signal collector through interface A, and after being filtered, it is processed by the level conversion circuit and then output to the control and display module.

8. A control method for an aviation power supply system fault simulation device, characterized in that, An aviation power supply system fault simulation device according to any one of claims 1-7 includes: S1. Based on the types of simulated AC power supply contact failure, AC power supply overload failure, DC power supply contact failure, and DC power supply overload failure, select the test lead for the contact failure and overload failure simulator and select the load type. S2. Control the closing of each corresponding switch of the multiplexer switch according to the fault type of the model; S3. The simulator for controlling poor contact and overload faults simulates series arcs in the power supply line under different RLC load conditions, generating poor contact in both AC and DC power supply of aviation power, and collects arc images and arc temperatures. It also simulates overload faults in both AC and DC power supply of aviation power, and collects conductor images and temperatures. After the series arc is generated, the signal collector is activated to collect the current and voltage in the power supply line at this time.

9. The control method for an aviation power supply system fault simulation device according to claim 8, characterized in that, The experimental lead wire to be tested can be a whole segment or in segments; When simulating poor contact faults in AC power supply and DC power supply of aviation power, if a series arc occurs in the live wire or positive terminal, the section between the first and second experimental wire clamps is the test wire segmented, and the section between the third and fourth experimental wire clamps is the test wire segmented. If a series arc occurs in the neutral wire or negative terminal, the section between the first and second experimental wire clamps is the test wire segmented. When simulating AC power supply overload faults and DC power supply overload faults in aviation power supplies, the entire test conductor is located between the first and second experimental conductor clamps, and between the third and fourth experimental conductor clamps.

Images