Fault triggering device and fault triggering method for ground fault test

Abstract

The invention relates to a fault triggering device and a fault triggering method for a ground fault test. The device comprises an intelligent optimization control assembly, a track electromagnetic emission assembly, an aiming and target tracking assembly, an arc striking line assembly and a pneumatic supporting assembly. The aiming and target tracking assembly detects the environment and the state of the arc striking line assembly; catapulting bullets of the arc striking line assembly are connected with the arc striking line, and the catapulting bullets are installed on the track electromagnetic launching assembly; the electromagnetic launching assembly launches the catapult to penetrate through the triggering frame; an airflow conveying pipeline of the pneumatic supporting assembly is arranged at the projection position of the flying path of the catapult on the ground. Compared with the prior art, the intelligent optimization control assembly obtains the environment and arc striking line assembly state through the aiming and target tracking assembly, then the track electromagnetic launching assembly is controlled to precisely launch the catapult, and the pneumatic supporting assembly adjusts the position of the catapult in real time after the catapult is launched; and the launching stability and precision of the catapult are further improved.

Description

Technical Field

[0001] The present invention relates to fault diagnosis in a power system, and particularly to a fault triggering device and a fault triggering method for grounding fault testing. Background Art

[0002] In a power system, an artificial grounding fault triggering device is used to simulate a grounding fault for fault testing, relay protection calibration, and power grid safety assessment. Traditional grounding fault triggering methods mainly rely on arc discharge, mechanical short - circuiting, or high - voltage discharge, which have problems such as complex operation, slow response, poor repeatability, and low experimental safety. For a new type of commutation converter (CLCC) device, compared with traditional converter devices such as LCC, its device compactness is higher, which puts forward higher requirements for the accuracy of the delivery position of the grounding fault triggering device. The existing artificial grounding fault simulation methods usually use a mechanical ejection method to throw an arc - leading wire towards an overhead line or a metal grounding electrode, and their stability and accuracy are poor, unable to meet the requirements for triggering artificial grounding faults of the compact CLCC device.

[0003] After retrieval, the application publication number CN113866560A discloses a field experiment device for the dangerous influence of buried pipe networks when a grounding fault occurs in a power grid, specifically discloses that: a metal pipe is suspended below an overhead transmission line, both ends of the metal pipe are connected with down - conductors connected to the overhead transmission line, one end of an arc - leading wire is connected to the ejection bullet of a launching device and the other end is grounded, and by launching the ejection bullet through the launching device, the ejection bullet drives the arc - leading wire to fly towards the metal pipe suspended in the air to form an instantaneous fault of the transmission line to the ground. However, this prior art does not solve the problems of poor device stability and accuracy.

[0004] In summary, how to design a fault triggering device and a fault triggering method for grounding fault testing with good stability and high accuracy is a technical problem to be solved. Summary of the Invention

[0005] The purpose of the present invention is to provide a fault triggering device and a fault triggering method for grounding fault testing to overcome the above - mentioned defects existing in the prior art.

[0006] The purpose of the present invention can be achieved by the following technical solutions:

[0007] According to one aspect of the present invention, a fault triggering device for ground fault testing is provided, which includes an intelligent optimization control component, an arc leading line component, and an orbital electromagnetic emission component, a aiming and target tracking component, and a pneumatic support component connected to the intelligent optimization control component; the aiming and target tracking component detects the environment and the state of the arc leading line component; the arc leading line component includes an ejection projectile, an arc leading line, and a triggering frame, the triggering frame is arranged at an interval from the orbital electromagnetic emission component, the ejection projectile is connected to the arc leading line, and the ejection projectile is installed on the orbital electromagnetic emission component; the electromagnetic emission component launches the ejection projectile to pass through the triggering frame; the pneumatic support component includes an air flow delivery pipeline, the air flow delivery pipeline is arranged at the projection position of the flight path of the ejection projectile on the ground, and air jet holes are evenly distributed on the air flow delivery pipeline.

[0008] As a preferred technical solution, the intelligent optimization control component includes a central control unit, and an optimization algorithm module is configured in the central control unit; the central control unit receives the detection data transmitted by the aiming and tracking component, calculates the optimal thrust configuration scheme, and issues instructions to the orbital electromagnetic emission component and the pneumatic support component.

[0009] As a preferred technical solution, the orbital electromagnetic emission component includes a guide rail, coils, a pulse power supply, and an armature, a plurality of coils are arranged at intervals around the guide rail, the pulse power supply is connected to the coils, and the ejection projectile is installed on one side of the armature.

[0010] As a preferred technical solution, the aiming and target tracking component includes a meteorological sensor, a laser rangefinder, and an angle regulator, the meteorological sensor and the laser rangefinder are connected to the intelligent optimization control component; the angle regulator is installed on the orbital electromagnetic emission component, and the arc leading line is installed on the angle regulator.

[0011] As a preferred technical solution, the triggering frame includes bare copper wires and a metal tube, two ends of the metal tube are respectively connected to a bare copper wire, and the two bare copper wires are connected to two positions on the high-voltage transmission line; the ejection projectile is a conical copper block.

[0012] As a preferred technical solution, the pneumatic support component further includes an air flow supply and regulation module, a regulating valve, and a feedback sensor, the air flow supply and regulation module is connected to the air flow delivery pipeline; the regulating valve is installed in the air jet port; the feedback sensor is installed around the air jet port to detect the air flow intensity and is connected to the intelligent optimization control component.

[0013] As a preferred technical solution, the air jet holes jet air vertically upward or tangentially along the ejection projectile to adjust the position of the ejection projectile in the vertical direction or adjust the rotation speed of the ejection projectile along its own axis.

[0014] According to another aspect of the present invention, there is provided a fault triggering method using the fault triggering device for grounding fault testing according to any one of claims 1 to 7, specifically including the following steps:

[0015] Step S1, the ejection projectile with an arc-shaped lead wire is installed on the guide rail of the rail electromagnetic launch assembly;

[0016] Step S2, the intelligent optimization control component obtains the distance between the ejection projectile and the triggering frame and the meteorological conditions of the current environment through the aiming and target tracking component;

[0017] Step S3, the intelligent optimization control component controls the rail electromagnetic launch assembly to launch the ejection projectile, and the aiming and target tracking component detects the position of the ejection projectile and the meteorological conditions of the current environment in real time;

[0018] Step S4, the intelligent optimization control component controls the pneumatic support component to jet air to adjust the position of the ejection projectile according to the position of the ejection projectile;

[0019] Step S5, the ejection projectile with an arc-shaped lead wire passes through the triggering frame to form an instantaneous line-to-ground fault.

[0020] As a preferred technical solution, in the step S2, a PSO-GA hybrid optimization algorithm module is configured in the intelligent optimization control component, and the acquired data is input into the PSO-GA hybrid optimization algorithm module to calculate the thrust configuration scheme of the electromagnetic launch assembly; the thrust configuration scheme includes the activation timing of the coil, the intensity of the current in the coil, and the coil working sequence.

[0021] As a preferred technical solution, in the step S3, the launch process of the rail electromagnetic launch assembly is divided into a startup stage, an acceleration stage, and an adjustment stage, and the provided electromagnetic thrusts are F1, F2, and F3 respectively; among them, F1 < F3 < F2.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1) The intelligent optimization control component of the present invention obtains the environment and the state of the arc-shaped lead wire component through the aiming and target tracking component, and then controls the rail electromagnetic launch assembly to accurately launch the ejection projectile. The pneumatic support component adjusts the position of the ejection projectile in real time after the ejection projectile is launched, further improving the stability and accuracy of the ejection projectile launch; the intelligent optimization control component can obtain the optimal thrust configuration scheme of the electromagnetic launch assembly through the PSO-GA hybrid optimization algorithm;

[0024] 2) The present invention uses a rail electromagnetic launch assembly, so that the ejection projectile in the guide rail obtains a very high acceleration under the action of the electromagnetic field, and finally leaves the launch device at a high speed and flies towards the target. This process does not require the push of mechanical components, reduces wear, and improves stability and durability;

[0025] 3) The aiming and target tracking component of the present invention can detect meteorological information of the surrounding environment, such as wind speed, wind direction, air density, and temperature, measure the position of the ejection projectile, provide support for the intelligent optimization control component to calculate the optimal thrust configuration plan, and can also adjust the launch angle of the ejection projectile to ensure the accuracy of the launch direction of the ejection projectile;

[0026] 4) The pneumatic support component of the present invention can provide airflows with different flow rates, and the directions of the air jet holes include vertically upward or tangential to the ejection projectile, ensuring that the ejection projectile can be effectively supported during the flight stage to ensure that the flight trajectory is not affected by unexpected situations; The ejection projectile is designed to be conical, which can enhance its stability in the airflow. Description of the Drawings

[0027] Figure 1 It is a schematic diagram of the overall structure of a fault triggering device for grounding fault testing according to the present invention;

[0028] Figure 2 It is a schematic diagram of the structure of the intelligent optimization control component according to the present invention;

[0029] Figure 3 It is a schematic diagram of the structure of the rail electromagnetic launch component according to the present invention;

[0030] Figure 4 It is a schematic diagram of the structure of the aiming and target tracking component according to the present invention;

[0031] Figure 5 It is a schematic diagram of the structure of the arc guiding component according to the present invention;

[0032] Figure 6 It is a schematic diagram of the structure of the pneumatic support component according to the present invention;

[0033] Indicated by the reference numerals in the figure:

[0034] 1. Intelligent optimization control component, 2. Rail electromagnetic launch component, 20. Guide rail, 21. Coil, 22. Pulse power supply, 23. Armature, 3. Aiming and target tracking component, 30. Meteorological sensor, 31. Laser rangefinder, 32. Angle regulator, 4. Arc guiding component, 40. Ejection projectile, 41. Arc guiding wire, 42. Triggering frame, 420. Bare copper wire, 421. Metal tube, 5. Pneumatic support component, 50. Airflow conveying pipeline, 500. Air jet hole, 51. Airflow supply and regulation module, 52. Control valve, 53. Feedback sensor. Detailed Embodiments

[0035] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0036] Embodiment 1

[0037] This embodiment provides a fault triggering device for grounding fault testing, including an intelligent optimization control component 1, an orbital electromagnetic emission component 2, a aiming and target tracking component 3, an arc connecting wire component 4, and a pneumatic support component 5; the orbital electromagnetic emission component 2, the aiming and target tracking component 3, and the pneumatic support component 5 are all communicatively connected to the intelligent optimization control component 1.

[0038] The intelligent optimization control component 1 includes a central control unit, and an optimization algorithm module is configured in the central control unit; the central control unit is the core of the entire intelligent optimization control system, responsible for receiving the detection data transmitted by the aiming and tracking component, executing the optimization algorithm, calculating the optimal control strategy, and commanding the work of each module (such as the coil 21, the power supply module, the pneumatic support component 5, etc.). The optimization algorithm module is used to execute the intelligent optimization algorithm, process the data obtained from the sensor, and generate control instructions. The algorithm module can include optimization methods such as particle swarm optimization (PSO), genetic algorithm (GA), etc., for dynamically adjusting the activation sequence, current magnitude, and thrust distribution of each electromagnetic coil 21.

[0039] The orbital electromagnetic emission component 2 includes a guide rail 20, a plurality of coils 21, a pulse power supply 22, and an armature 23. The guide rail 20 uses a high-conductivity copper alloy guide rail 20 to ensure stable current transmission; the plurality of coils 21 are arranged at intervals around the guide rail 20; the pulse power supply 22 stores energy through a super capacitor and realizes adjustable electromagnetic acceleration through pulse control; the armature 23 is installed on the guide rail 20, and the ejection projectile 40 is installed on one side of the armature 23. The armature 23 drives the ejection projectile 40 to move along the track to obtain an initial launch velocity.

[0040] Rail electromagnetic launch is a launch technology that accelerates conductive objects (such as the arc wire 41, metal projectiles, etc.) through electromagnetic force. Its basic principle is based on the Lorentz force, that is, the force generated by the interaction between current and magnetic field. When current passes through a metal object (the ejection projectile 40) located between the parallel rails 20, due to the interaction between the magnetic field of the current and the magnetic field on the rails 20, a force is generated to push the metal object to accelerate along the rails 20. Specifically, if current I passes through the rails 20 and the rails 20 are in a magnetic field B, then the metal object will be subjected to the Lorentz force F, and its magnitude is calculated by the formula F = I·L·B, where: I is the current passing through the rails 20; L is the effective length of the metal object and the rails 20; B is the magnetic field strength. By providing a high-intensity current through the high-power pulse power supply 22, the metal object in the rails 20 obtains an extremely high acceleration under the action of the electromagnetic field, and finally leaves the launch device at a high speed and flies towards the target. This process does not require the push of mechanical components, reduces wear, and improves stability and durability.

[0041] In this embodiment, the segmented launch rail electromagnetic launch assembly 2 with multiple electromagnetic coils 21 aims to improve the launch accuracy and achieve precise target control.

[0042] The aiming and target tracking assembly 3 includes a weather sensor 30, a laser rangefinder 31, and an angle adjuster 32. The weather sensor 30 measures environmental factors such as wind speed, wind direction, air density, and temperature in real time, provides parameter support for ballistic calculation, and optimizes the launch parameters; the laser rangefinder 31 measures the distance between the target trigger frame 42 and the ejection projectile 40, and the measurement error does not exceed ±1 mm; the angle adjuster 32 is installed on the rails 20, and the ejection projectile 40 is installed on the angle adjuster 32, providing an adjustable accuracy of ±5° in the horizontal direction and ±10° in the pitch direction to ensure the accuracy of the launch direction.

[0043] The aiming and target tracking assembly 3 is used for high-precision target positioning. The laser rangefinder 31 emits a high-precision laser beam, monitors the relative position between the target and the laser spot in real time, and feeds back the error signal to the intelligent optimization control assembly 1 to adjust the angle of the laser emitter to ensure that the target is always within the range of the laser spot. Through the aiming and target tracking assembly 3, high-precision and dynamic target positioning are achieved.

[0044] To improve the aiming accuracy, the weather sensor 30 measures environmental data such as wind speed, wind direction, air density, and temperature in real time. These data will be sent to the intelligent optimization control assembly 1 for calculating and optimizing the launch angle and initial velocity. The intelligent optimization control assembly 1 quickly calculates the optimal launch angle and initial velocity according to the real-time environmental data, and adjusts the rail electromagnetic launch assembly 2 and the angle adjuster 32 in real time to ensure the best launch trajectory and target hit accuracy.

[0045] Servo motors and stepper motors can be adopted to finely adjust the pitch angle and horizontal angle of the laser rangefinder 31 according to the control signals output by the intelligent optimization control component 1, so as to maintain the precise alignment of the laser beam with the target position. This device can accurately correct the aiming error in a dynamic environment, ensure high-precision and high-response target positioning and tracking, and is applicable to target positioning and fault simulation under various complex environmental conditions.

[0046] The arc guiding component 4 includes an ejection projectile 40, an arc guiding wire 41 and an ignition frame 42. The ignition frame 42 is located in front of the rail electromagnetic launch component 2 with a certain distance. The ejection projectile 40 is connected to the arc guiding wire 41 and installed on the guide rail 20. The electromagnetic launch component launches the ejection projectile 40 to pass through the ignition frame 42. The ejection projectile 40 can be a conical copper block to enhance its stability in the air flow. The ignition frame 42 includes bare copper wires 420 and a metal tube 421. Both ends of the metal tube 421 are respectively connected to a bare copper wire 420, and the two bare copper wires 420 are connected to two positions on the high-voltage transmission line to form a frame structure.

[0047] The pneumatic support component 5 includes an air flow conveying pipeline 50, an air flow supply and regulation module 51, a regulating valve 52 and a feedback sensor 53. The air flow conveying pipeline 50 is arranged at the projection position of the flight path of the ejection projectile 40 on the ground. Air injection holes 500 are evenly distributed on the air flow conveying pipeline 50, and the jet direction of the air injection holes 500 is vertically upward or tangential to the ejection projectile 40. The position of the ejection projectile 40 in the vertical direction or the rotation speed of the ejection projectile 40 along its own axis can be adjusted by adjusting the air flow velocity to support the attitude of the ejection projectile 40. The air flow supply and regulation module 51 can be a compressor or a gas cylinder, which is connected to the air flow conveying pipeline 50 to provide a stable air flow for the air flow conveying pipeline 50. The regulating valve 52 is installed in the air jet port to accurately regulate the air flow velocity to ensure the adaptability of the supporting force. The feedback sensor 53 is installed around the air jet port to detect the air flow intensity and is connected to the intelligent optimization control component 1 to feedback the air flow velocity to the control system for optimization adjustment. According to the acceleration, speed and force condition of the ejection projectile 40, the air flow intensity will be adjusted in real time. A PID controller can be adopted to control the outlet speed and pressure of the air flow output.

[0048] To ensure that the arc guiding wire 41 maintains a stable and accurate trajectory during the launch process to improve the aiming accuracy. Therefore, the pneumatic support component 5 is designed to support the arc guiding wire 41 in a non-contact manner, reduce the errors caused by the offset, vibration or friction of the arc guiding wire 41, and thus ensure its accurate launch. The pneumatic support component 5 can provide a stable supporting force to prevent the instability or offset of the arc guiding wire 41 during the ejection process; and can adjust the air flow in real time to adapt to the dynamic changes of the arc guiding wire 41 and ensure its precise positioning.

[0049] The jet nozzles are the core components of the pneumatic support system. They support the arc 41 by ejecting airflows. The air jet holes 500 or air channels evenly distributed along the arc 41 of the launch pipe can evenly distribute the airflows, ensuring that the arc 41 can be effectively supported at different stages. To ensure the stability of the ejection projectile 40 during the launch process, in addition to the traditional radial airflow support, the present invention also introduces the design of tangential airflows, causing the arc 41 itself to rotate along the axis to control the rotational stability of the arc 41.

[0050] Embodiment 2

[0051] The present invention provides a fault triggering method for ground fault testing, adopting a fault triggering device for ground fault testing in Embodiment 1, specifically as follows:

[0052] Before the fault triggering device is started, ensure that all hardware components are correctly connected and there is no looseness. The ejection projectile 40 with the arc 41 is installed on the guide rail 20 of the rail electromagnetic launch assembly 2. After the power is turned on, the device system will automatically enter the initialization state, and the laser rangefinder 31 will emit a preliminary laser beam for self-check. At this time, the intelligent optimization control component 1 will perform preset value calibration according to factors such as the temperature, humidity, and air pressure of the surrounding environment. Ensure that after the initialization process of the device system is completed, the target positioning and fault simulation settings can be carried out.

[0053] The operator can set the preliminary position of the target through the touch screen or computer interface. The intelligent optimization control component 1 will use the laser sight and receiver to align the target. At the same time, the meteorological sensor 30 will continuously monitor the surrounding environmental conditions and transmit the data to the central control unit of the intelligent optimization control component 1. According to these data, the central control unit will automatically optimize the launch angle and initial velocity. The operator can view the current environmental data and aiming parameters on the display interface.

[0054] When the target and launch parameters are adjusted, start the device. The intelligent optimization control component 1 controls the rail electromagnetic launch assembly 2 to launch the ejection projectile 40. The laser rangefinder 31 will continuously track the target position and perform real-time feedback adjustment. If the wind speed or other environmental factors change during the launch process, the meteorological sensor 30 will provide new data in real time, and the intelligent optimization control component 1 will automatically adjust the launch angle and initial velocity to ensure that the target is always within the laser spot range, guaranteeing the accuracy and stability of the fault simulation. The rail electromagnetic launch assembly 2 has multiple electromagnetic coils 21, and different electromagnetic thrusts are gradually provided according to the launch requirements at different stages. Specifically, the launch process is divided into a start-up stage, an acceleration stage, and an adjustment stage. A smaller electromagnetic thrust is used in the start-up stage to help the target object start smoothly, the thrust is gradually increased in the acceleration stage to accelerate the target object, and the thrust output is optimized in the adjustment stage, that is, when approaching the target contact point, to ensure that the target accurately reaches the predetermined position.

[0055] After the ejection projectile 40 leaves the guide rail 20, if changes occur due to environmental factors, the intelligent optimization control component 1 controls the pneumatic support component 5 to jet air to adjust the position of the ejection projectile 40 according to the position of the ejection projectile 40. After the ejection projectile 40 with the arc line 41 passes through the triggering frame 42, a line-to-ground instantaneous fault is formed.

[0056] In order to improve the accuracy of the electromagnetic ejection system, this embodiment introduces an intelligent optimization control method that combines the particle swarm optimization algorithm (PSO) and the genetic algorithm (GA). The basic principle of the particle swarm optimization algorithm PSO is that the solution space of the problem is regarded as a search space composed of multiple "particles", and each particle represents a possible solution. These particles search according to their own experience and the experience of the group to find the global optimal solution, which can be used to optimize the working parameters of each electromagnetic coil 21, including the activation timing, current magnitude, and thrust distribution. The genetic algorithm (GA) is a global optimization method that simulates natural selection and genetic mechanisms, and searches for the optimal solution through operations such as selection, crossover, and mutation. In the electromagnetic launch system, GA can be used to optimize the activation sequence of multiple electromagnetic coils 21, current output, and time allocation during the launch phase.

[0057] In order to give full play to the respective advantages of the particle swarm optimization and the genetic algorithm, this embodiment combines the advantages of these two algorithms to form a PSO-GA hybrid optimization algorithm. The particle swarm optimization algorithm is used for global search and preliminary optimization, and a relatively superior solution is found through rapid convergence; while the genetic algorithm is used for further refined local search, and the local solution is deeply optimized through operations such as crossover and mutation to ensure the global optimal electromagnetic thrust configuration. During the implementation of the electromagnetic launch system, the PSO-GA hybrid algorithm will be embedded in the control unit of the system, and the control unit is responsible for receiving sensor data in real time and performing optimization calculations. The output of the algorithm will directly affect the working state of the electromagnetic coil 21, including the activation timing, current intensity, and working sequence, etc.

[0058] The training steps of the PSO part are as follows:

[0059] 1) Initialize the particle swarm:

[0060] Initialize a particle swarm, where each particle represents a potential solution in the solution space. Each particle has a position and a velocity. The position represents the candidate value of the solution, and the velocity is used to update the position of the particle. Each particle also records its historical best position (pbest) and the best position of the entire group (gbest).

[0061] 2) Calculate the fitness function:

[0062] For the position of each particle, calculate its fitness value. The fitness function is defined according to the target problem. For example, to control the accuracy of the launch trajectory of the target object, the fitness value can be measured by the deviation from the target. The smaller the fitness value of the particle, the better its solution.

[0063] 3) Update the position and velocity of the particle:

[0064] Update its new position according to the current velocity and position of the particle:

[0065] v i (t + 1)= w·v i (t)+ c1·r1(pbest i - x i (t))+ c2·r2(gbest i - x i (t)),

[0066] x i (t + 1)= x i (t)+ v i (t + 1)

[0067] Among them, v i (t) is the velocity of particle i at time t, and x i (t) is the position of the particle; w is the inertia weight, which adjusts the speed of the particle's advancement; c1 and c2 are learning factors, which control the weights of the particle when exploring the personal best and the global best; r1 and r2 are random numbers, which control the randomness of the particle's movement; pbest is the historical best position of the particle, and gbest is the global best position.

[0068] 4) Update the historical best solution:

[0069] After each update of the particle's position, calculate the fitness of the new position. If the fitness of the current particle is better than its historical best solution, then update its historical best solution (pbest).

[0070] Similarly, if the solution in the current particle population is better than the global best solution (gbest), then update the global best solution.

[0071] 5) Stop condition:

[0072] When the predetermined number of iterations is reached or the fitness value converges, stop the algorithm and output the optimal solution.

[0073] The training steps of the GA part are as follows:

[0074] 1) Initialize the population:

[0075] Randomly generate an initial population, where each individual represents a potential solution to the problem. Each individual represents a solution in the solution space through chromosome encoding (usually binary or real number encoding).

[0076] 2) Calculate fitness values

[0077] For each individual (candidate solution), calculate the fitness value according to its performance. The fitness value determines the probability of the individual entering the next generation. The fitness function is related to the problem objective. For example, it can be the accuracy of the target trajectory. The higher the fitness value, the better the solution.

[0078] 3) Selection operation:

[0079] The selection operation determines which individuals enter the next generation based on the fitness value. Use roulette wheel selection, etc. Individuals with higher fitness values have a greater chance of being selected.

[0080] 4) Crossover operation:

[0081] The crossover operation simulates genetic recombination and generates new offspring individuals by exchanging the chromosomes of two parent individuals. The purpose of crossover is to combine the advantages of parent individuals and create better offspring.

[0082] 5) Mutation operation:

[0083] The mutation operation makes small random changes to the genes of an individual to increase the diversity of the population and avoid falling into local optima. The mutation operation has a small probability and generally occurs within a certain probability range.

[0084] 6) Generate a new generation of population:

[0085] Generate a new generation of population through selection, crossover, and mutation operations. The new population will continue to evolve in the next iteration.

[0086] 7) Stopping condition:

[0087] Similar to PSO, GA training also has a stopping condition. Usually, the maximum number of iterations is set or the training stops when the target fitness value is reached.

[0088] The present invention relates to a fault triggering device and a fault triggering method for grounding fault testing based on orbital electromagnetic acceleration and with an automatic aiming system, which uses the principle of electromagnetic acceleration to quickly and accurately project an ejection projectile 40 with an arc wire 41 to a target grounding point, realizing precise, controllable, and repeatable fault triggering, so as to improve the success rate, accuracy, and safety of test personnel in fault simulation tests.

[0089] As described above, it is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of various equivalent modifications or substitutions, and these modifications or substitutions should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A fault initiation device for ground fault testing, characterized in that: The invention comprises an intelligent optimization control component (1), an arc-starting wire component (4), a track electromagnetic launch component (2), a sighting and target tracking component (3), and a pneumatic support component (5) connected to the intelligent optimization control component (1); the sighting and target tracking component (3) detects the environment and the state of the arc-starting wire component (4); the arc-starting wire component (4) comprises a projectile (40), an arc-starting wire (41), and a trigger frame (42); the trigger frame (42) and the track electromagnetic launch component (2) are arranged at intervals; the projectile (40) is connected to the arc-starting wire (41); the projectile (40) is installed on the track electromagnetic launch component (2); the electromagnetic launch component launches the projectile (40) to pass through the trigger frame (42); the pneumatic support component (5) comprises an airflow conveying pipeline (50); the airflow conveying pipeline (50) is arranged at a projection position of the flight path of the projectile (40) on the ground; and the airflow conveying pipeline (50) has air jet holes (500) evenly distributed on the airflow conveying pipeline (50).

2. A fault initiating device for ground fault testing according to claim 1, characterized in that: The intelligent optimization control component (1) comprises a central control unit, in which an optimization algorithm module is configured; the central control unit receives detection data transmitted by the aiming and tracking component, calculates the optimal thrust configuration scheme and issues instructions to the orbital electromagnetic launch component (2) and the pneumatic support component (5).

3. A fault initiating device for ground fault testing according to claim 1, characterized in that: The track electromagnetic launch assembly (2) comprises a guide rail (20), a coil (21), a pulse power supply (22) and an armature (23). The coil (21) is multiple and arranged at intervals around the guide rail (20). The pulse power supply (22) is connected to the coil (21). The catapult (40) is installed on one side of the armature (23).

4. A fault inducing device for ground fault testing according to claim 1, characterized in that: The aiming and target tracking component (3) comprises a meteorological sensor (30), a laser rangefinder (31) and an angle adjuster (32), wherein the meteorological sensor (30) and the laser rangefinder (31) are connected to the intelligent optimization control component (1); the angle adjuster (32) is installed on the track electromagnetic emission component (2), and the arc-starting wire (41) is installed on the angle adjuster (32).

5. A fault initiating device for ground fault testing according to claim 1, characterized in that: The trigger frame (42) comprises a bare copper wire (420) and a metal tube (421), two ends of the metal tube (421) are respectively connected to a bare copper wire (420), and two bare copper wires (420) are connected to two positions on a high-voltage transmission line; the projectile (40) is a conical copper block.

6. A fault inducing device for ground fault testing according to claim 1, characterized in that: The pneumatic support assembly (5) further comprises an airflow supply and regulation module (51), a regulating valve (52) and a feedback sensor (53), wherein the airflow supply and regulation module (51) is connected to the airflow delivery pipeline (50); the regulating valve (52) is installed in the air jet; the feedback sensor (53) is installed around the air jet to detect the airflow intensity and is connected to the intelligent optimization control assembly (1).

7. A fault initiating device for ground fault testing according to claim 1, characterized in that: The jet hole (500) jets out vertically upward or tangentially along the projectile (40), thereby adjusting the position of the projectile (40) in the vertical direction or adjusting the rotation speed of the projectile (40) along its own axis.

8. A fault initiation method using the fault initiation device for ground fault testing according to any one of claims 1 to 7, characterized in that: The specific steps include: Step S1, a projectile (40) with an arc-starting wire (41) is installed on a guide rail (20) of a track electromagnetic launching assembly (2); Step S2, the intelligent optimization control component (1) obtains the distance between the projectile (40) and the trigger frame (42) and the current weather conditions through the aiming and target tracking component (3); Step S3, the intelligent optimization control component (1) controls the track electromagnetic launch component (2) to launch the projectile (40), and the aiming and target tracking component (3) detects the position of the projectile (40) and the current meteorological conditions in real time; Step S4, the intelligent optimization control component (1) controls the pneumatic support component (5) to adjust the position of the projectile (40) by jetting air according to the position of the projectile (40); Step S5, the projectile (40) with the arc-starting wire (41) passes through the triggering frame (42), forming a line-to-ground instantaneous fault.

9. A fault inducing method according to claim 8, characterized in that: In step S2, the intelligent optimization control component (1) is provided with a PSO-GA hybrid optimization algorithm module, the acquired data is input into the PSO-GA hybrid optimization algorithm module, and a thrust configuration scheme of the electromagnetic launch component is calculated; the thrust configuration scheme includes the activation timing of the coil (21), the intensity of the current in the coil (21), and the working order of the coil (21).

10. A fault inducing method according to claim 8, characterized in that: In step S3, the launch process of the orbital electromagnetic launch assembly (2) is divided into a start-up phase, an acceleration phase and an adjustment phase, and the electromagnetic thrusts provided are F1, F2 and F3 respectively; wherein F1 <F3<F2。

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