Aviation power supply system fault simulation device and control method thereof

Abstract

The invention discloses an aviation power supply system fault simulation device and a control method thereof. The aviation power supply system fault simulation device comprises an AC aviation power supply module, an aviation DC power supply module, a multipath change-over switch, a poor contact and overload fault simulator, an RLC load and a signal collector. The poor contact and overload fault simulator is used for simulating series arcs generating poor contact faults of aviation power supply alternating current power supply and aviation power supply direct current power supply under different RLC load conditions, collecting arc images and arc temperatures, and collecting lead images and temperatures during overload faults; the signal collector is used for collecting a voltage value between a zero line and a live line between the multipath change-over switch and the poor contact and overload fault simulator, a voltage value between a positive electrode and a negative electrode, a current flowing through the zero line or the negative electrode, and a current flowing through the live line or the positive electrode after the series arc is generated; and the RLC load is used for simulating and generating different types of loads, including a resistive load, an inductive load and a capacitive load.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation power supply systems, and more particularly to an aviation power supply system fault simulation device and its control method. Background Art

[0002] The aviation power supply system is an important guarantee for the normal operation of modern aircraft. Its main function is to provide reliable power supply for on-board electronic equipment, navigation systems, communication systems, etc. However, due to the complex operating environment of aircraft and diverse electrical loads, the power supply system is prone to faults such as poor contact and overload, which can lead to unstable operation of equipment and even pose safety hazards.

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

[0004] However, due to the occasional and complex nature of actual faults, it is difficult to fully reproduce fault phenomena and obtain relevant data in a real environment. At the same time, most of the existing fault simulation devices have single functions and are difficult to comprehensively cover various faults of different types of power supply systems. In particular, there is a lack of effective experimental means for fault simulation in the aviation-specific power supply environment (such as AC115V 400Hz and 28V DC).

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

[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 an urgent problem 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 object, the present invention adopts the following technical solutions:

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

[0010] The input ends of the AC aviation power supply module and the aviation DC power supply module are both electrically connected to 220V alternating current;

[0011] The neutral output terminal of the AC aviation power supply module and the negative output terminal of the aviation DC power supply module are respectively electrically connected to the neutral / negative input terminal of the poor contact and overload fault simulator through one switch of the multi-way switch;

[0012] The live output terminal of the AC aviation power supply module and the positive output terminal of the aviation DC power supply module are respectively electrically connected to the live / positive input terminal of the poor contact and overload fault simulator through one switch of the multi-way switch;

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

[0014] A signal collector, which is used to collect the voltage value between the neutral and live wires, the voltage value between the positive and negative poles, the current flowing through the neutral or negative pole, and the current flowing through the live or positive pole between the multi-way switch and the poor contact and overload fault simulator after the series arc is generated;

[0015] The RLC load is 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 and generate series arcs in the power supply line under the conditions of poor contact faults in AC power supply of aviation power supply and poor contact faults in DC power supply of aviation power supply, and collect arc images and arc temperatures, as well as simulate overload faults in AC power supply of aviation power supply and overload faults in DC power supply of aviation power supply, and collect wire images and temperatures.

[0017] Preferably, the aviation power supply system fault simulation device further includes a control and display module, and the signal collector, the multi-way switch, the poor contact and overload fault simulator, and the RLC load are all electrically connected to the control and display module; the control and display module is used to control the signal collector, the multi-way switch, the poor contact and overload fault simulator, and the RLC load to work, and display data graphs in real time.

[0018] Preferably, the 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;

[0019] The first voltage sensor is connected in parallel between the neutral and live wires, and the second voltage sensor is connected in parallel between the positive and negative poles;

[0020] The first current sensor is respectively connected in series with the neutral and negative poles to measure the current flowing through the neutral or negative pole, and the second current sensor is respectively connected in series with the live and positive poles to measure the current flowing through the live or positive pole;

[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 voltage of the AC aviation power module is 115V AC and the frequency is 400Hz; the voltage of the aviation DC power module is 28V DC.

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

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

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

[0026] The first experimental wire fixture, the second experimental wire fixture, the third experimental wire fixture, and the fourth experimental wire fixture 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 wire fixture and the second experimental wire fixture, the third experimental wire fixture and the fourth experimental wire fixture are connected by the whole or segmented experimental wires to be tested;

[0028] The lower end of the second insulating column is fixed to the first stepping motor slide, and the lower end of the fourth insulating column is fixed to the second stepping motor slide; 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 stepping motor slide and the second stepping motor slide respectively, and is used to control the left and right movement of the stepping motor slide, so as to drive the second experimental wire fixture and the fourth experimental wire fixture 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 up and down vibration of the vibration table to simulate the poor contact series arc under vibration conditions;

[0030] A high-speed photography module and an infrared temperature measurement module are used to collect the arc images and temperatures of the series arc generated by the test experimental wire 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 during a poor contact fault, as well as the wire images and temperatures during an overload fault.

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

[0032] The controller receives the control instructions issued by the control and display module to control the left and right movement of the first stepping motor slide and the second stepping motor slide, and the control instructions issued 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 image and temperature data, as well as the wire image and temperature, to the control and display module.

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

[0035] The insulating columns, the experimental wire clamps, the stepping motor slides, the high-speed photography module, the controller, and the 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 the infrared temperature measurement module are fixed to the upper inner wall of the shielding cover.

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

[0037] The power supply module is electrically connected to the input end of the power supply circuit; the output end of the power supply circuit is electrically connected to the filtering circuit and the level conversion circuit respectively to supply power to the filtering 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 filtering circuit, the level conversion circuit is electrically connected to the output end of the filtering circuit and interface B respectively, and interface B is electrically connected to the control and display module;

[0040] The sensor signals are accessed into the signal collector through interface A, and after being filtered, they are 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 described aviation power supply system fault simulation device, includes:

[0042] S1. Select the test experimental wires of the open-circuit and overload fault simulator according to the types of the simulated open-circuit faults of AC power supply for aircraft, the overload faults of AC power supply for aircraft, the open-circuit faults of DC power supply for aircraft, and the overload faults of DC power supply for aircraft, and select the load type.

[0043] S2. Control the corresponding switches of the multiplexer to close according to the model fault type.

[0044] S3. Control the open-circuit and overload fault simulator to simulate and generate series arcs in the power supply lines in the cases of open-circuit faults of AC power supply for aircraft and open-circuit faults of DC power supply for aircraft under different RLC load conditions, and collect arc images and arc temperatures, and simulate the overload faults of AC power supply for aircraft and the overload faults of DC power supply for aircraft, and collect wire images and temperatures; and after generating the series arcs, start the signal collector to collect the current and voltage in the power supply line at this time.

[0045] Preferably, the test experimental wires are in whole or in segments.

[0046] When simulating the open-circuit faults of AC power supply for aircraft and the open-circuit faults of DC power supply for aircraft and simulating series arcs occurring on the live wire or positive pole, the test experimental wires between the first experimental wire clamp and the second experimental wire clamp are in segments, and the test experimental wires between the third experimental wire clamp and the fourth experimental wire clamp are in whole; when simulating series arcs occurring on the neutral wire or negative pole, the test experimental wires between the first experimental wire clamp and the second experimental wire clamp are in whole, and the test experimental wires between the third experimental wire clamp and the fourth experimental wire clamp are in segments.

[0047] When simulating the overload faults of AC power supply for aircraft and the overload faults of DC power supply for aircraft, the test experimental wires between the first experimental wire clamp and the second experimental wire clamp are in whole, and the test experimental wires between the third experimental wire clamp and the fourth experimental wire clamp are in whole.

[0048] As can be seen from the above technical solutions, compared with the prior art, the present invention discloses an aviation power supply system fault simulation device and its control method. Through modular design, it can simulate the phenomena of poor contact and overload faults in the aviation power supply system, and support experiments in power supply environments of AC115V and DC28V. By adjusting the distance between the wires to be measured through a stepper motor slider, it simulates the series arc generated during poor contact faults, and cooperates with a high-speed photography and infrared temperature measurement module to collect arc images and temperature data, and obtains wire temperature rise data from the wire images and temperatures during overload faults. The signal collector monitors current and voltage signals in real time, and the RLC load can simulate various types of aviation power supply system loads, realizing the precise simulation, data recording and subsequent analysis of aviation power supply system faults, and helping to provide reliable technical support for the fault analysis and teaching experiments of the aviation power supply system. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only the embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained according to the provided drawings.

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

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

[0052] Figure 3 Circuit schematic diagram of the signal collector provided by the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0053] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0054] An embodiment of the present invention discloses an aviation power supply system fault simulation device, as Figure 1 shown, including: an AC aviation power supply module, an aviation DC power supply module, a multi-way switch, a poor contact and overload fault simulator, an RLC load, and a signal collector;

[0055] The input ends of the AC aviation power supply module and the aviation DC power supply module are both electrically connected to the 220V AC power supply through wires N1 and L1;

[0056] The zero - line output end of the AC aviation power supply module and the negative - pole output end of the aviation DC power supply module are respectively electrically connected to the zero - line / negative - pole input end of the poor - contact and overload fault simulator through one switch of the multi - way switch;

[0057] The live - line output end of the AC aviation power supply module and the positive - pole output end of the aviation DC power supply module are respectively electrically connected to the live - line / positive - pole input end of the poor - contact and overload fault simulator through one switch of the multi - way switch;

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

[0059] A signal collector, which is used to collect the voltage value between the zero - line and the live - line, the voltage value between the positive - pole and the negative - pole, the current flowing through the zero - line or the negative - pole, and the current flowing through the live - line or the positive - pole between the multi - way switch and the poor - contact and overload fault simulator after a series arc is generated;

[0060] An RLC load, which is used to simulate different types of loads, including resistive loads, inductive loads, and capacitive loads;

[0061] A poor - contact and overload fault simulator, which is used to simulate and generate a series arc in the power supply line in the case of poor - contact faults in AC power supply of the aviation power supply and poor - contact faults in DC power supply of the aviation power supply, and collect the arc image and arc temperature under different RLC load conditions, and simulate the overload faults in AC power supply of the aviation power supply and overload faults in DC power supply of the aviation power supply, and collect the wire image and temperature.

[0062] To further implement the above - mentioned technical solution, an aviation power supply system fault simulation device further includes a control and display module, and the signal collector, the multi - way switch, the poor - contact and overload fault simulator, and the RLC load are all electrically connected to the control and display module; the control and display module is used to control the signal collector, the multi - way switch, the poor - contact and overload fault simulator, and the RLC load to work, and display data graphs in real time.

[0063] To further implement the above - mentioned 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 zero - line and the live - line, and the second voltage sensor is connected in parallel between the positive - pole and the negative - pole;

[0065] The first current sensor is connected in series with the neutral line and the negative electrode respectively, and is used to measure the current flowing through the neutral line or the negative electrode. The second current sensor is connected in series with the live wire and the positive electrode respectively, and is used to measure the current flowing through the live wire or the positive electrode;

[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 voltage of the AC aviation power supply module is 115V AC and the frequency is 400Hz; the voltage of the aviation DC power supply module is 28V DC.

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

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

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

[0071] The first experimental wire fixture, the second experimental wire fixture, the third experimental wire fixture and the fourth experimental wire fixture 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 wire fixture and the second experimental wire fixture, the third experimental wire fixture and the fourth experimental wire fixture are connected by the whole or segmented experimental wire to be measured;

[0073] The lower end of the second insulating column is fixed on the first stepping motor slide, and the lower end of the fourth insulating column is fixed on the second stepping motor slide; the lower ends of the first insulating column and the third insulating column are respectively fixed on 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 left and right movement of the stepper motor slide, so as to drive the second experimental wire fixture and the fourth experimental wire fixture to move left and right, so as 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 up and down vibration of the vibration table to simulate the series arc with poor contact under vibration conditions;

[0075] The high-speed photography module and the infrared temperature measurement module are used to collect the arc images and temperatures of the series arcs generated by the experimental wires to be measured between the first experimental wire fixture and the second experimental wire fixture and between the third experimental wire fixture and the fourth experimental wire fixture during poor contact faults, as well as the wire images and temperatures during overload faults.

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

[0077] In practical applications, the experimental wire to be measured is a special wire for the aviation power supply system. The metal beads generated by the series arc of the experimental wire to be measured fall on the bottom of the shielding cover, and the metal beads are collected for later fault analysis.

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

[0079] The controller receives the control instructions issued by 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 issues control instructions 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. Among them, the software operation interface is self-programmed, and the software operation interface is used to output control signals and display the electrical signals of the signal collector in real time.

[0082] In order to further implement the above technical solution, the poor contact and overload fault simulator further includes a shielding cover;

[0083] The insulating columns, experimental wire fixtures, stepper motor slides, 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 the infrared temperature measurement module are fixed to the upper inner wall of the shielding cover.

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

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

[0086] The power supply module is electrically connected to the input end of the power supply circuit; the output end of the power supply circuit is respectively electrically connected to the filter circuit and the level conversion circuit to supply 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 end of the filter circuit and interface B respectively, and interface B is electrically connected to the control and display module;

[0089] The sensor signal is accessed into 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. According to the types of simulated aviation power AC power supply poor contact fault, aviation power AC power supply overload fault, aviation power DC power supply poor contact fault, and aviation power DC power supply overload fault, select the test experimental wire of the poor contact and overload fault simulator, and select the load type;

[0092] S2. Control the corresponding switches of the multiplexer to close according to the model fault type;

[0093] S3. Control the poor contact and overload fault simulator to simulate and generate series arcs in the power supply line in the case of aviation power AC power supply poor contact fault and aviation power DC power supply poor contact fault, and collect arc images and arc temperatures under different RLC load conditions, and simulate aviation power AC power supply overload fault and aviation power DC power supply overload fault, and collect wire images and temperatures; and after generating the series arc, start the signal collector to collect the current and voltage in the power supply line at this time.

[0094] To further implement the above technical solution, the test experimental wire is in whole or in segments;

[0095] When simulating the poor contact fault of the AC power supply of the aviation power supply and the poor contact fault of the DC power supply of the aviation power supply, if a series arc is simulated on the live wire or positive pole, the experimental wire to be measured between the first experimental wire clamp and the second experimental wire clamp is a segmented experimental wire to be measured, and the experimental wire to be measured between the third experimental wire clamp and the fourth experimental wire clamp is a whole experimental wire to be measured; if a series arc is simulated on the neutral wire or negative pole, the experimental wire to be measured between the first experimental wire clamp and the second experimental wire clamp is a whole experimental wire to be measured, and the experimental wire to be measured between the third experimental wire clamp and the fourth experimental wire clamp is a segmented experimental wire to be measured;

[0096] When simulating the overload fault of the AC power supply of the aviation power supply and the overload fault of the DC power supply of the aviation power supply, the experimental wire to be measured between the first experimental wire clamp and the second experimental wire clamp is a whole experimental wire to be measured, and the experimental wire to be measured between the third experimental wire clamp and the fourth experimental wire clamp is a whole experimental wire to be measured.

[0097] Taking the simulation of the poor contact fault of the AC power supply of the aviation power supply as an example, the control method is described in detail:

[0098] (1) Open the shield of the poor contact and overload fault simulator, clamp the first section of the experimental wire to be measured with the first experimental wire clamp, clamp the second section of the experimental wire to be measured with the second experimental wire clamp, and clamp a whole experimental wire to be measured with the third experimental wire clamp and the fourth experimental wire clamp, then close the shield;

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

[0100] (3) Click the K1 icon and the K2 icon on the software operation interface of the control and display module. After the multi-way switch receives the control signal, the corresponding K1 and K2 switches close;

[0101] (4) Click the icon for the first stepping motor slide to move left on the software operation interface of the control and display module. The first stepping motor slide drives the second section of the experimental wire to be measured clamped by the second experimental wire clamp to move left. As the distance between the first section of the experimental wire to be measured and the second section of the experimental wire to be measured becomes smaller, a series arc is generated between them;

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

[0103] (6) The software operation interface of the control and display module displays the graphs of the above data in real time. After recording for a period of time, the first stepping motor slide can be continuously controlled to move left to realize the arc simulation at different distances between the first section of the experimental wire to be measured and the second section of the experimental wire to be measured;

[0104] (7) After the experiment is completed, save the experimental data and figures, disconnect K1 and K2 of the multiplexer switch, and collect the metal beads generated by the arc on the first experimental wire to be measured and the second experimental wire to be measured.

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

[0106] If simulating the overloading fault of the AC power supply of the aviation power supply, close K1 and K2 of the multiplexer switch, clamp the complete whole experimental wire to be measured between the first experimental wire clamp and the second experimental wire clamp, and clamp the complete whole experimental wire to be measured between the third experimental wire clamp and the fourth experimental wire clamp.

[0107] If simulating the poor contact fault of the DC power supply of the aviation power supply, close K3 and K4 of the multiplexer switch, clamp two experimental wires to be measured between the first experimental wire clamp and the second experimental wire clamp, and clamp the complete whole experimental wire to be measured between the third experimental wire clamp and the fourth experimental wire clamp.

[0108] If simulating the overloading fault of the DC power supply of the aviation power supply, close K3 and K4 of the multiplexer switch, clamp the complete whole experimental wire to be measured between the first experimental wire clamp and the second experimental wire clamp, and clamp the complete whole experimental wire to be measured between the third experimental wire clamp and the fourth experimental wire clamp.

[0109] In this specification, each embodiment is described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. For the same or similar parts between the embodiments, reference can be made to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and reference can be made to the description of the method part for the relevant parts.

[0110] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be obvious to those skilled in the art. The general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will 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 module, aviation DC power module, multi-way conversion switch, poor contact and overload fault simulator, RLC load and signal collector; The input terminals of the AC aviation power module and the aviation DC power module are both connected to 220V AC power; The neutral line output terminal of the AC aviation power module and the negative electrode output terminal of the aviation DC power module are electrically connected to the neutral line / negative electrode input terminal of the poor contact and overload fault simulator through one switch of the multi-way conversion switch respectively; The live wire output end of the AC aviation power module and the positive electrode output end of the aviation DC power module are electrically connected to the live wire / positive electrode input end of the poor contact and overload fault simulator through one switch of the multi-way conversion switch respectively; The output end of the poor contact and overload fault simulator is electrically connected to the input end of the RLC load; A signal collector is used to collect the voltage value between the neutral line and the live line, the voltage value between the positive and negative poles, the current flowing through the neutral line or the negative pole, and the current flowing through the live line or the positive pole between the multi-way conversion switch and the contact failure and overload fault simulator after the arc is generated in series; RLC load, used to simulate different types of loads, including resistive load, inductive load, and capacitive load; The poor contact and overload fault simulator is used to simulate the series arc in the power supply line under the conditions of poor contact fault of aviation power supply AC power supply and poor contact fault of aviation power supply DC power supply under different RLC load conditions and collect arc images and arc temperatures, as well as simulate aviation power supply AC power supply overload fault and aviation power supply DC power supply overload fault, and collect wire images and temperatures.

2. The aviation power supply system fault simulation device according to claim 1, characterized in that: It also includes a control and display module, and the signal collector, the multi-way conversion switch, the poor contact and overload fault simulator and the RLC load are all electrically connected to the control and display module; the control and display module is used to control the signal collector, the multi-way conversion switch, the poor contact and overload fault simulator and the RLC load to work, and display data graphics in real time.

3. The device for simulating faults in an aviation power supply system according to claim 1, characterized in that: 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 line and the live line, and the second voltage sensor is connected in parallel between the positive electrode and the negative electrode; The first current sensor is connected in series with the neutral line and the negative electrode respectively, and is used to measure the current flowing through the neutral line or the negative electrode. The second current sensor is connected in series with the live line and the positive electrode respectively, and is used to measure the current flowing through the live line or the positive electrode. 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 device for simulating faults in an aviation power supply system according to claim 1, characterized in that: The voltage of the AC aviation power module is 115V and the frequency is 400Hz; the voltage of the aviation DC power module is 28V.

5. The aviation power supply system fault simulation device according to claim 1, characterized in that: The poor contact and overload fault simulator includes: insulating columns, experimental wire fixtures, stepper motor slides, controllers, vibration tables, high-speed photography modules and infrared temperature measurement modules; The experimental wire fixture includes a first experimental wire fixture, a second experimental wire fixture, a third experimental wire fixture and a fourth experimental wire fixture, 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 fixture is electrically connected to the live wire / positive electrode input terminal, the second experimental wire fixture is electrically connected to the L live wire / positive electrode of the RLC load, the third experimental wire fixture is electrically connected to the neutral wire / negative electrode input terminal, and the fourth experimental wire fixture is electrically connected to the N neutral wire / negative electrode 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 end of the first insulating column, the upper end of the second insulating column, the upper end of the third insulating column, and the upper end of the fourth insulating column; The first experimental wire fixture and the second experimental wire fixture, and the third experimental wire fixture and the fourth experimental wire fixture are connected through a whole or segmented experimental wire to be tested; The lower end of the second insulating column is fixed to the first stepper motor slide, and the lower end of the fourth insulating column is fixed to the second stepper motor slide; the lower end of the first insulating column and the lower end of the third insulating column are fixed to the first vibration table and the second vibration table respectively; 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, simulating a series arc caused by poor contact under vibration conditions; The high-speed photography module and the infrared temperature measurement module are used to collect arc images and temperatures of series arcs generated by the experimental wires to be tested between the first experimental wire fixture and the second experimental wire fixture and between the third experimental wire fixture and the fourth experimental wire fixture when there is a poor contact fault, as well as wire images and temperatures during overload faults.

6. The device for simulating faults in an aviation power supply system according to claim 5, 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 instructions from the control and display module to control the first stepper motor slide and the second stepper motor slide to move left and right, and sends control instructions to control the first vibration table and the second vibration table to vibrate up and down; The high-speed photography module and the infrared temperature measurement module transmit the measured series arc image and temperature data as well as the wire image and temperature to the control and display module.

7. The device for simulating faults in an aviation power supply system according to claim 5, 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 in 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 the infrared temperature measurement module are fixed to the upper inner wall of the shielding cover.

8. An aviation power supply system fault simulation device according to claims 2 and 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 end of the power supply circuit; the output end of the power supply circuit is electrically connected to the filter circuit and the level conversion circuit respectively to supply 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 end of the filter circuit and interface B respectively, and 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 output to the control and display module.

9. 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 to 8, comprising: S1. According to the types of simulated aviation power supply AC power supply poor contact fault, aviation power supply AC power supply overload fault, aviation power supply DC power supply poor contact fault and aviation power supply DC power supply overload fault, select the experimental wire to be tested of the poor contact and overload fault simulator, and select the load type; S2. Control the corresponding switches of the multi-way switch to close according to the model fault type; S3. Control the poor contact and overload fault simulator under different RLC load conditions to simulate the series arc in the power supply line in the case of poor contact fault of aviation power AC power supply and poor contact fault of aviation power DC power supply, and collect arc images and arc temperatures, as well as simulate the aviation power AC power supply overload fault and aviation power DC power supply overload fault, and collect wire images and temperatures; and after the series arc is generated, start the signal collector to collect the current and voltage in the power supply line at this time.

10. The control method of the aviation power supply system fault simulation device according to claim 9, characterized in that: The experimental conductor to be tested is a whole section or segmented; When performing the fault simulation of poor contact of AC power supply of aviation power supply and the fault simulation of poor contact of DC power supply of aviation power supply, the simulation of series arc of live wire or positive pole is performed, then the section of experimental wire to be tested is between the first experimental wire fixture and the second experimental wire fixture, and the whole section of experimental wire to be tested is between the third experimental wire fixture and the fourth experimental wire fixture; when performing the simulation of series arc of neutral wire or negative pole, the section of experimental wire to be tested is between the first experimental wire fixture and the second experimental wire fixture, and the section of experimental wire to be tested is between the third experimental wire fixture and the fourth experimental wire fixture; When performing aviation power supply AC power supply overload fault simulation and aviation power supply DC power supply overload fault simulation, the entire section of the experimental wire to be tested is between the first experimental wire fixture and the second experimental wire fixture, and the entire section of the experimental wire to be tested is between the third experimental wire fixture and the fourth experimental wire fixture.

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