Aerial device live fire extinguishing method, apparatus, aerial device, and storage medium

Abstract

The present disclosure relates to the technical field of power transmission line fire prevention, and particularly relates to an aerial equipment live fire extinguishing method and device, aerial equipment and a storage medium. The aerial equipment live fire extinguishing method comprises: obtaining a fire extinguishing agent currently used by aerial equipment live fire extinguishing; and determining working parameters of aerial equipment live fire extinguishing corresponding to the fire extinguishing agent. The working parameters are parameters for preventing flashover of insulators on a power transmission line during aerial equipment live fire extinguishing, and at least include a flight height of the aerial equipment and a fire extinguishing agent spraying duration. The technical solution of the present disclosure can determine working parameters for preventing flashover of insulators on a power transmission line during aerial equipment live fire extinguishing, thereby providing a data basis for aerial equipment safe live fire extinguishing and guiding aerial equipment live fire extinguishing operations, and being conducive to avoiding flashover of insulators on a power transmission line caused by spraying fire extinguishing agent during aerial equipment live fire extinguishing, thereby causing the risk of power transmission line tripping.

Description

Technical Field

[0001] This disclosure relates to the field of power transmission line wildfire prevention technology, and in particular to a method, device, aircraft equipment, and storage medium for extinguishing fires on energized aircraft equipment. Background Technology

[0002] The experience gained from helicopter live-line spraying of extinguishing agents over wildfires on existing transmission lines comes from rain tests on insulators and gaps. Helicopters release 1 to 5 tons of extinguishing agent within 5 to 20 seconds during high-altitude spraying. Assuming uniform spraying over a 150m × 8m area, the spray intensity per unit area is 8 mm / min and 40 mm / min. Based on historical rainfall records and maximum instantaneous rainfall intensity across my country, it is estimated that during heavy rain and torrential rain, the instantaneous rainfall intensity ranges from 2.6 to 12.4 mm / min.

[0003] However, the instantaneous spray intensity of helicopters during high-altitude firefighting is dozens of times higher than the instantaneous maximum value of heavy rain or torrential rain. When the line voltage reaches 1000kV, the risk of power line tripping due to factors such as the conductivity of the extinguishing agent and the spraying method exists, especially when spraying water with extinguishing agents at high altitudes. Existing research indicates that finer extinguishing agent atomization results in higher insulation, which helps reduce the risk of line tripping. However, during high-altitude firefighting, the higher the flight speed and altitude, the finer the atomization, and the lower the firefighting efficiency. Currently, helicopters use pure water for firefighting, but water evaporates easily at high altitudes. Using gel extinguishing agents or Class A extinguishing agents can effectively improve the firefighting efficiency of helicopters. However, gel extinguishing agents and Class A extinguishing agents significantly reduce the insulation performance of the extinguishing agent, which can easily cause flashover of insulators in power transmission lines, leading to the risk of power line tripping. When helicopters spray extinguishing agents at high altitudes, different extinguishing agents are in different diffusion states. It is unclear whether the insulation properties of the extinguishing agents in different diffusion states can meet the requirements for extinguishing fires on energized surfaces. Summary of the Invention

[0004] To address the aforementioned technical problems, this disclosure provides a method, apparatus, aircraft equipment, and storage medium for extinguishing fires while the aircraft is energized. It can determine operating parameters that prevent flashover of insulators on transmission lines during extinguishing fires while the aircraft is energized, providing a data foundation for safe extinguishing fires while the aircraft is energized and guiding such operations. This helps avoid the risk of flashover of insulators on transmission lines caused by spraying extinguishing agents during extinguishing fires while the aircraft is energized, thus preventing power line tripping.

[0005] In a first aspect, this disclosure provides a method for extinguishing fires involving energized aircraft equipment, including:

[0006] To obtain the extinguishing agents currently used in extinguishing live fires in aviation equipment;

[0007] Determine the operating parameters for extinguishing live fires in aviation equipment corresponding to the extinguishing agent currently being used;

[0008] The operating parameters are those that prevent flashover of insulators on energized fire extinguishing transmission lines of aviation equipment. These operating parameters include at least the flight altitude of the aviation equipment and the duration of fire extinguishing agent spraying.

[0009] In some embodiments, determining the operating parameters for extinguishing live fires in aircraft equipment corresponding to the currently used extinguishing agent includes:

[0010] Obtain the electrical conductivity of the extinguishing agent;

[0011] The electrical conductivity is used to determine the operating parameters for energized fire suppression of the aircraft equipment.

[0012] In some embodiments, determining the operating parameters for energized fire suppression of the aircraft equipment using the conductivity includes:

[0013] If the electrical conductivity of the extinguishing agent is less than or equal to a first electrical conductivity, the working parameter is determined as the first working parameter, which includes the flight altitude of the aircraft and the duration of the extinguishing agent spraying.

[0014] The electrical conductivity of the extinguishing agent is obtained to be greater than or equal to a first electrical conductivity and less than or equal to a second electrical conductivity. The operating parameters are then determined as the second operating parameters, which include the flight altitude of the aircraft, the duration of extinguishing agent spraying, and the flow rate of extinguishing agent spraying.

[0015] Wherein, the flight altitude of the aviation equipment is greater than or equal to an altitude threshold, the spraying duration of the fire extinguishing agent is less than or equal to a duration threshold, and the spraying flow rate of the fire extinguishing agent is less than or equal to a flow rate threshold.

[0016] In some embodiments, the method for extinguishing fires on energized aircraft equipment further includes:

[0017] If the electrical conductivity of the extinguishing agent is greater than the second electrical conductivity, it is determined that the extinguishing agent does not meet the requirements for extinguishing fires involving energized aircraft equipment.

[0018] In some embodiments, the operating parameters include the flight altitude of the aircraft; the extinguishing agent currently used includes pure water;

[0019] The flight altitude of the aircraft corresponding to the pure water was obtained through the following method:

[0020] After the fire extinguisher sprays pure water, the distance between the pure water and the spray nozzle of the fire extinguisher is obtained.

[0021] Based on the distance value, obtain the ratio of the distance value to the spray nozzle diameter;

[0022] The sum of the distance value corresponding to the first ratio and the distance between the power transmission line and the ground is taken as the flight altitude of the aircraft corresponding to pure water, where the first ratio is 11.2.

[0023] In some embodiments, the flight altitude of aircraft corresponding to extinguishing agents other than pure water is obtained using a first formula, which is:

[0024] H = (H1 - b) × α + 3 + b;

[0025] Where H represents the flight altitude of aircraft corresponding to other extinguishing agents, H1 represents the flight altitude of aircraft corresponding to pure water, α represents the diffusion correction factor of other extinguishing agents, and b represents the distance between the power transmission line and the ground.

[0026] In some embodiments, the diffusion correction factor for other extinguishing agents is obtained using a second formula, which is:

[0027] α = Aη1 / η2;

[0028] Where α represents the diffusion correction factor for other extinguishing agents, A represents the correction coefficient, η1 represents the viscosity coefficient of other extinguishing agents, and η2 represents the viscosity coefficient of pure water.

[0029] Secondly, this disclosure also provides an energized fire extinguishing device for aviation equipment, comprising:

[0030] The acquisition module is used to acquire the extinguishing agent currently being used for extinguishing live fires in aviation equipment;

[0031] The determination module is used to determine the operating parameters for extinguishing live fires in aviation equipment corresponding to the currently used extinguishing agent.

[0032] The operating parameters are those that prevent flashover of insulators on energized fire extinguishing transmission lines of aviation equipment. These operating parameters include at least the flight altitude of the aviation equipment and the duration of fire extinguishing agent spraying.

[0033] Thirdly, this disclosure also provides an aviation device, including:

[0034] A processor and a memory, wherein the processor executes the live fire extinguishing method for aircraft equipment as described in the first aspect by invoking programs or instructions stored in the memory.

[0035] Fourthly, this disclosure also provides a computer-readable storage medium storing a program or instructions that cause a computer to perform the energized fire extinguishing method for aviation equipment as described in the first aspect.

[0036] The technical solution provided in this disclosure has the following advantages compared with the prior art:

[0037] The live-line fire suppression method for aviation equipment provided in this embodiment of the invention determines the corresponding operating parameters for the live-line fire suppression of aviation equipment by acquiring the fire extinguishing agent currently used for the fire suppression. These operating parameters are those that prevent flashover of insulators on the transmission line during live-line fire suppression of aviation equipment, and include at least the flight altitude of the aviation equipment and the duration of fire extinguishing agent spraying. Therefore, by determining the operating parameters that prevent flashover of insulators on the transmission line during live-line fire suppression of aviation equipment, a data foundation is provided for safe live-line fire suppression of aviation equipment, and the operation is guided accordingly. This helps to avoid the risk of flashover of insulators on the transmission line caused by fire extinguishing agent spraying during live-line fire suppression of aviation equipment, thereby preventing the transmission line from tripping. Attached Figure Description

[0038] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure.

[0039] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0040] Figure 1 A schematic flowchart illustrating a method for extinguishing live fires in aviation equipment, provided as an embodiment of this disclosure;

[0041] Figure 2 This is a schematic diagram of the structure of an energized fire extinguishing device for aviation equipment provided in an embodiment of the present disclosure;

[0042] Figure 3 This is a schematic diagram of the structure of an aviation device provided in an embodiment of this disclosure. Detailed Implementation

[0043] To better understand the above-mentioned objectives, features, and advantages of this disclosure, the solutions disclosed herein will be further described below. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0044] Numerous specific details are set forth in the following description in order to provide a full understanding of this disclosure, but this disclosure may also be implemented in other ways different from those described herein; obviously, the embodiments in the specification are only some, and not all, of the embodiments of this disclosure.

[0045] The live-line fire extinguishing method for aviation equipment provided in this embodiment determines the operating parameters that prevent flashover of insulators on transmission lines when extinguishing fires on aviation equipment. This provides a data basis for safe live-line fire extinguishing of aviation equipment and guides live-line fire extinguishing operations. It helps to avoid the risk of flashover of insulators on transmission lines caused by spraying fire extinguishing agents when extinguishing fires on aviation equipment, thereby causing the transmission line to trip.

[0046] The following description, in conjunction with the accompanying drawings, provides an exemplary account of the fire extinguishing method, apparatus, aircraft equipment, and storage medium for energized aircraft equipment provided in the embodiments of this disclosure.

[0047] Figure 1 This is a flowchart illustrating a method for extinguishing live fires in aviation equipment, provided in an embodiment of this disclosure. This method can be executed by a live fire extinguishing device for aviation equipment provided in this embodiment, which can be implemented using software and / or hardware. For example... Figure 1 As shown, the method for extinguishing fires involving energized aircraft equipment includes the following steps:

[0048] S101. Obtain the extinguishing agent currently used for extinguishing fires involving energized aircraft equipment.

[0049] Among these, live-line firefighting refers to the application scenario of using aerial equipment to extinguish fires on power transmission lines without interrupting power supply. Specifically, when wildfires occur on power transmission lines, they seriously threaten the safe and stable operation of the power grid. Using aerial equipment for firefighting can overcome external limitations such as ground road blockages and can quickly reach the fire scene to extinguish the fire.

[0050] When extinguishing fires on energized aircraft equipment, the type of extinguishing agent currently being used by the aircraft equipment, such as pure water, can be obtained.

[0051] S102. Determine the operating parameters for extinguishing live fires on aircraft equipment corresponding to the extinguishing agent currently being used.

[0052] Specifically, after determining the extinguishing agent to be used, the corresponding operating parameters for extinguishing live fires on energized aircraft equipment are determined. These operating parameters are those that meet the insulation performance requirements for extinguishing live fires on energized aircraft equipment. Specifically, they are those that prevent flashover of insulators on power transmission lines during extinguishing live fires on energized aircraft equipment. The operating parameters include at least the aircraft's flight altitude and the duration of extinguishing agent spraying.

[0053] Therefore, by determining the operating parameters that prevent flashover of insulators on transmission lines when firefighting is carried out on energized aircraft equipment, a data foundation is provided for safe firefighting of energized aircraft equipment and guidance is given for such operations. This helps to avoid the risk of flashover of insulators on transmission lines caused by the spraying of extinguishing agents during firefighting of energized aircraft equipment, which could lead to power line tripping.

[0054] The live-line fire suppression method for aviation equipment provided in this embodiment obtains the fire extinguishing agent currently used for live-line fire suppression and determines the corresponding operating parameters for the fire extinguishing operation. These operating parameters are those that prevent flashover of insulators on transmission lines during live-line fire suppression. Therefore, by determining the operating parameters that prevent flashover of insulators on transmission lines during live-line fire suppression, a data foundation is provided for safe live-line fire suppression of aviation equipment, and guidance is offered for live-line fire suppression operations. This helps avoid the risk of flashover of insulators on transmission lines caused by fire extinguishing agents during live-line fire suppression, which could lead to power line tripping.

[0055] In some embodiments, determining the operating parameters for extinguishing live fires in aircraft equipment corresponding to the currently used extinguishing agent includes:

[0056] Obtain the electrical conductivity of the extinguishing agent;

[0057] The operating parameters for energized fire suppression of aircraft equipment are determined by electrical conductivity.

[0058] Specifically, the insulating properties of a fire extinguishing agent are related to its electrical conductivity. The higher the electrical conductivity of the fire extinguishing agent, the worse its insulating properties; conversely, the lower the electrical conductivity, the better its insulating properties.

[0059] Based on this, the electrical conductivity of the extinguishing agent is obtained in order to determine the working parameters for extinguishing fires involving energized aircraft equipment. The specific method for determining the working parameters for extinguishing fires involving energized aircraft equipment using electrical conductivity will be detailed below.

[0060] In some embodiments, determining the operating parameters for energized fire suppression of aircraft equipment by conductivity includes:

[0061] If the electrical conductivity of the extinguishing agent is less than or equal to a first electrical conductivity, the working parameters are determined as the first working parameters, which include the flight altitude of the aircraft and the duration of extinguishing agent spraying.

[0062] The electrical conductivity of the extinguishing agent is greater than or equal to the first electrical conductivity and less than or equal to the second electrical conductivity. The working parameters are then determined as the second working parameters, which include the flight altitude of the aircraft, the duration of extinguishing agent spraying, and the flow rate of extinguishing agent spraying.

[0063] Specifically, when the conductivity of the extinguishing agent is less than or equal to a first conductivity, i.e., the conductivity of the extinguishing agent is relatively low, the operating parameters of the aircraft equipment are determined as the first operating parameters. The first operating parameters include the aircraft equipment's flight altitude and the extinguishing agent spraying duration. Specifically, the aircraft equipment's flight altitude is greater than or equal to an altitude threshold, and the extinguishing agent spraying duration is less than or equal to a duration threshold. When the aircraft equipment sprays the extinguishing agent with the corresponding first operating parameters, it ensures that flashover does not occur on the insulators of the transmission lines when the aircraft equipment is energized for fire suppression.

[0064] Specifically, when the conductivity of the extinguishing agent is greater than or equal to a first conductivity and less than or equal to a second conductivity, i.e., the conductivity of the extinguishing agent is relatively high, the operating parameters of the aircraft equipment are determined as the second operating parameters. The second operating parameters include the aircraft equipment's flight altitude, the extinguishing agent spraying duration, and the extinguishing agent spraying flow rate. Among these, the aircraft equipment's flight altitude is greater than or equal to an altitude threshold, the extinguishing agent spraying duration is less than or equal to a duration threshold, and the extinguishing agent spraying flow rate is less than or equal to a flow rate threshold. When the aircraft equipment sprays the extinguishing agent with the second operating parameters corresponding to the extinguishing agent, it can ensure that the insulators on the transmission line do not flashover when the aircraft equipment is energized for fire extinguishing.

[0065] Therefore, when the conductivity of the extinguishing agent is low, it is necessary to ensure that the flight altitude of the aircraft is greater than or equal to the altitude threshold and the spraying time of the extinguishing agent is less than or equal to the duration threshold. There is no need to pay attention to the spraying flow rate of the extinguishing agent. No matter how large the spraying flow rate of the extinguishing agent is, it can be determined that the insulators on the transmission line will not flashover when the aircraft is energized for fire extinguishing.

[0066] When the extinguishing agent has a high conductivity, it is necessary to ensure that the flight altitude of the aircraft is greater than or equal to the altitude threshold, the spraying time of the extinguishing agent is less than or equal to the duration threshold, and the spraying flow rate of the extinguishing agent is less than or equal to the flow rate threshold. This ensures that flashover of insulators on power transmission lines will not occur when the aircraft extinguishes fires while the equipment is energized. Specifically, when the extinguishing agent has a high conductivity, a larger spraying flow rate is more likely to cause flashover of insulators on power transmission lines. Therefore, when the extinguishing agent has a high conductivity, the operating parameters of the aircraft are determined as the second set of operating parameters.

[0067] The first and second operating parameters, as well as the altitude threshold, duration threshold, and flow rate threshold, were all obtained through a simulation experiment of energized fire suppression of aviation equipment.

[0068] In some embodiments, the method for extinguishing fires on energized aircraft equipment further includes:

[0069] If the electrical conductivity of the extinguishing agent is greater than the second electrical conductivity, it is determined that the extinguishing agent does not meet the requirements for extinguishing fires involving energized aircraft equipment.

[0070] Specifically, when the electrical conductivity of the extinguishing agent is very high, its insulation performance is poor. When the extinguishing agent is sprayed on aviation equipment, it can easily cause flashover of the insulators on the transmission lines when the aviation equipment is energized for fire extinguishing.

[0071] Based on this, when the electrical conductivity of the extinguishing agent is greater than the second electrical conductivity, that is, when the electrical conductivity of the extinguishing agent is very high, the insulation performance of the extinguishing agent is poor, and it can be determined that the current extinguishing agent does not meet the requirements for extinguishing fires on energized aircraft equipment.

[0072] In some embodiments, the operating parameters include the flight altitude of the aircraft; the extinguishing agent currently used includes pure water.

[0073] The flight altitude of aircraft corresponding to pure water was obtained using the following method:

[0074] After the fire extinguisher sprays pure water, the distance between the pure water and the spray nozzle of the fire extinguisher is obtained.

[0075] Based on the distance value, obtain the ratio of the distance value to the spray nozzle diameter;

[0076] The sum of the distance value corresponding to the first ratio and the distance between the power transmission line and the ground is taken as the flight altitude of the aircraft corresponding to pure water, where the first ratio is 11.2.

[0077] Specifically, a simulation experiment was conducted using pure water as the extinguishing agent. Aircraft equipment sprayed pure water from different altitudes, and the diffusion state of the water during its free fall was recorded at different stages. The diffusion state of the pure water when it was sprayed onto a power transmission line, without flashover of the insulators, was defined as the target diffusion state. The spraying altitude at which the insulators on the power transmission line did not flashover was taken as the corresponding flight altitude of the aircraft. The simulation experiment showed that the droplet diameter of the extinguishing agent under the target diffusion state was less than or equal to 4 millimeters.

[0078] Based on simulation experiments, the diffusion and fragmentation of pure water after free fall from high altitude is divided into five stages according to the ΔH / d0 range: Stage 1 (ΔH / d0 ≤ 3.36) represents a single, integral volume; Stages 2 (3.36 < ΔH / d0 ≤ 5.28) and 3 (5.28 < ΔH / d0 ≤ 6.64) represent chains, jets, and large fragments; Stage 4 (6.64 < ΔH / d0 ≤ 11.2) represents discontinuous large-particle fire extinguishing agent droplets; and Stage 5 (ΔH / d0 > 11.2) represents discontinuous small-particle fire extinguishing agent droplets. Here, ΔH is the distance between the pure water and the nozzle of the fire extinguisher after spraying, and d0 is the equivalent diameter of the nozzle of the fire extinguisher (if considered as a circle). Stage 5 corresponds to the target diffusion state after pure water spraying. Simulation experiments show that in Stage 5, insulators on the transmission line do not experience flashover.

[0079] Therefore, it can be determined that the flight altitude of the aircraft corresponding to pure water as a fire extinguishing agent is greater than the sum of the distance value corresponding to the first ratio and the distance between the power transmission line and the ground. That is, the flight altitude of the aircraft corresponding to pure water is greater than the sum of 11.2d0 and the distance between the power transmission line and the ground.

[0080] In some embodiments, the flight altitude of aircraft corresponding to extinguishing agents other than pure water is obtained using a first formula, which is:

[0081] H = (H1 - b) × α + 3 + b;

[0082] Where H represents the flight altitude of aircraft corresponding to other extinguishing agents, H1 represents the flight altitude of aircraft corresponding to pure water, α represents the diffusion correction factor of other extinguishing agents, and b represents the distance between the power transmission line and the ground.

[0083] Therefore, the flight altitudes of other fire extinguishing agents, such as those corresponding to Class AB fire extinguishing agents, gel fire extinguishing agents, Class A fire extinguishing agents, and anti-evaporation fire extinguishing powder, can be obtained through the first formula.

[0084] Therefore, by using the flight altitude of aircraft corresponding to pure water as a benchmark value, and combining it with the diffusion correction factor of other fire extinguishing agents, the flight altitude of aircraft corresponding to other fire extinguishing agents can be directly obtained without the need for simulation experiments to obtain the flight altitude of aircraft corresponding to other fire extinguishing agents.

[0085] It should be noted that the flight altitude of any of the following fire extinguishing agents—Class AB fire extinguishing agents, gel fire extinguishing agents, Class A fire extinguishing agents, and anti-evaporation fire extinguishing agents—can also be obtained through experimental simulation. The flight altitude of the aircraft corresponding to this fire extinguishing agent can be used as a benchmark value. For example, the flight altitude of the aircraft corresponding to Class AB fire extinguishing agents can be used as a benchmark value to further determine the flight altitude of the aircraft corresponding to other types of fire extinguishing agents.

[0086] In some embodiments, the diffusion correction factor for other extinguishing agents is obtained using a second formula, which is:

[0087] α = Aη1 / η2;

[0088] Where α represents the diffusion correction factor for other extinguishing agents, A represents the correction coefficient, η1 represents the viscosity coefficient of other extinguishing agents, and η2 represents the viscosity coefficient of pure water.

[0089] Specifically, the viscosity of the extinguishing agent affects its diffusion state. Therefore, the viscosity coefficients of various types of extinguishing agents are obtained, and the viscosity coefficient of pure water is used as a benchmark. The diffusion correction factors for other extinguishing agents are then obtained through the second equation.

[0090] For example, the diffusion correction factor for Class AB extinguishing agents is 0.77, the diffusion correction factor for gel extinguishing agents is 1.40, the diffusion correction factor for Class A extinguishing agents is 1.05, and the diffusion correction factor for anti-evaporation extinguishing agents is 1.15.

[0091] Based on the same inventive concept, this disclosure also provides an energized fire extinguishing device for aviation equipment. Figure 2 This is a schematic diagram of the structure of an energized fire extinguishing device for aviation equipment, provided as an embodiment of this disclosure. Figure 2As shown, the lithium battery rapid lithium plating detection device includes: an acquisition module 21 for acquiring the fire extinguishing agent currently used for fire suppression of energized aircraft equipment; and a determination module 22 for determining the working parameters of the fire suppression of energized aircraft equipment corresponding to the currently used fire extinguishing agent; wherein, the working parameters are the parameters that prevent flashover of insulators on the transmission line of the fire suppression of energized aircraft equipment, and the working parameters include at least the flight altitude of the aircraft equipment and the duration of fire extinguishing agent spraying.

[0092] The energized fire extinguishing device for aviation equipment provided in the above embodiments can perform any of the energized fire extinguishing methods for aviation equipment provided in the above embodiments, and has the same or corresponding beneficial effects, which will not be described in detail here.

[0093] This disclosure also provides a computer storage medium that stores a program or instructions that cause the computer to perform the steps of any of the above-described methods for extinguishing energized fires in aviation equipment.

[0094] For example, a program or instructions cause a computer to perform a method for extinguishing fires on energized aircraft equipment, the method comprising:

[0095] To obtain the extinguishing agents currently used in extinguishing live fires in aviation equipment;

[0096] Determine the operating parameters for extinguishing live fires in aviation equipment corresponding to the extinguishing agent currently being used;

[0097] Among them, the working parameters are those that prevent flashover of insulators on the energized fire extinguishing transmission lines of aviation equipment. The working parameters include at least the flight altitude of the aviation equipment and the duration of fire extinguishing agent spraying.

[0098] In some embodiments, when executed by a computer processor, the computer-executable instructions can also be used to execute the technical solutions of any of the above-described methods for extinguishing energized fires in aviation equipment provided in the embodiments of this disclosure, thereby achieving the corresponding beneficial effects.

[0099] Based on the above description of the implementation methods, those skilled in the art can clearly understand that this disclosure can be implemented using software and necessary general-purpose hardware, and of course, it can also be implemented using hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of this disclosure, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as a computer floppy disk, read-only memory (ROM), random access memory (RAM), flash memory, hard disk, or optical disk, etc., including several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the aviation equipment energized fire extinguishing method in the various embodiments of this invention.

[0100] Based on the above embodiments, this disclosure also provides an aviation device. Figure 3 This is a structural schematic diagram of an aviation device provided as an embodiment of this disclosure. (See diagram below.) Figure 3 As shown, the aircraft equipment includes a processor 301 and a memory 302. The processor 301 executes the steps of any of the aircraft equipment live fire extinguishing methods provided in the above embodiments by calling the programs or instructions stored in the memory. Therefore, it has the beneficial effects of the above embodiments, which will not be repeated here.

[0101] like Figure 3 As shown, an aviation device may be configured to include at least one processor 301, at least one memory 302, and at least one communication interface 303. The various components of the aviation device are coupled together via a bus system 304. The communication interface 303 is used for information transmission with external devices. It is understood that the bus system 304 is used to realize communication between these components. In addition to a data bus, the bus system 304 also includes a power bus, a control bus, and a status signal bus. However, for clarity, in… Figure 3 The general designated all buses as Bus System 304.

[0102] It is understood that the memory 302 in this embodiment may be volatile memory or non-volatile memory, or may include both volatile and non-volatile memory. In some embodiments, the memory 302 stores the following elements: executable units or data structures, or subsets thereof, or extended sets thereof, operating systems, and applications. In embodiments of this disclosure, the processor 301 executes the steps of any of the energized fire extinguishing methods for aircraft equipment provided in embodiments of this disclosure by invoking programs or instructions stored in the memory 302.

[0103] The live-line fire suppression method for aviation equipment provided in this disclosure can be applied to, or implemented by, processor 301. Processor 301 can be an integrated circuit chip with signal processing capabilities. During implementation, each step of the above-mentioned live-line fire suppression method for aviation equipment can be completed through integrated logic circuits in the hardware of processor 301 or through software instructions. Processor 301 can be a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. The general-purpose processor can be a microprocessor or any conventional processor.

[0104] The steps of the live-line fire extinguishing method for aviation equipment provided in this disclosure can be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software units in the decoding processor. The software units can be located in random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, or other mature storage media in the art. This storage medium is located in memory 302. The processor 301 reads the information in memory 302 and, in conjunction with its hardware, completes the steps of the aforementioned live-line fire extinguishing method for aviation equipment.

[0105] The aircraft equipment may also include one or more physical components to execute instructions generated by the processor 301 when performing the live fire extinguishing method for aircraft equipment provided in this disclosure embodiment. Different physical components may be located inside or outside the aircraft equipment, such as a cloud server. Each physical component, together with the processor 301 and memory 302, works to realize the functions of the aircraft equipment in this disclosure embodiment.

[0106] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0107] The above description is merely a specific embodiment of this disclosure, enabling those skilled in the art to understand or implement it. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this disclosure. Therefore, this disclosure is not to be limited to the embodiments described herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for extinguishing fires involving energized aircraft equipment, characterized in that, include: To obtain the extinguishing agents currently used in extinguishing live fires in aviation equipment; Determine the operating parameters for extinguishing live fires in aviation equipment corresponding to the extinguishing agent currently being used; The operating parameters are those that prevent flashover of insulators on the energized fire extinguishing transmission lines of aviation equipment. The operating parameters include at least the flight altitude of the aviation equipment and the duration of fire extinguishing agent spraying. Determine the operating parameters for extinguishing live electrical fires in aviation equipment corresponding to the currently used extinguishing agent, including: Obtain the electrical conductivity of the extinguishing agent; The electrical conductivity is used to determine the operating parameters for energized fire suppression of the aircraft equipment.

2. The method for extinguishing live fires in aviation equipment according to claim 1, characterized in that, Determining the operating parameters for energized fire suppression of the aircraft equipment using the conductivity includes: If the electrical conductivity of the extinguishing agent is less than or equal to a first electrical conductivity, the working parameter is determined as the first working parameter, which includes the flight altitude of the aircraft and the duration of the extinguishing agent spraying. The electrical conductivity of the extinguishing agent is greater than or equal to a first electrical conductivity and less than or equal to a second electrical conductivity. The operating parameter is then determined as the second operating parameter, which includes the flight altitude of the aircraft, the duration of the extinguishing agent spraying, and the flow rate of the extinguishing agent spraying. Wherein, the flight altitude of the aviation equipment is greater than or equal to an altitude threshold, the spraying duration of the fire extinguishing agent is less than or equal to a duration threshold, and the spraying flow rate of the fire extinguishing agent is less than or equal to a flow rate threshold.

3. The method for extinguishing live fires in aviation equipment according to claim 2, characterized in that, Also includes: If the electrical conductivity of the extinguishing agent is greater than the second electrical conductivity, it is determined that the extinguishing agent does not meet the requirements for extinguishing fires involving energized aircraft equipment.

4. A method for extinguishing fires involving energized aircraft equipment, characterized in that, include: To obtain the extinguishing agents currently used in extinguishing live fires in aviation equipment; Determine the operating parameters for extinguishing live fires in aviation equipment corresponding to the extinguishing agent currently being used; The operating parameters are those that prevent flashover of insulators on the energized fire extinguishing transmission lines of the aviation equipment, and these operating parameters include at least the flight altitude of the aviation equipment; the extinguishing agent currently used includes pure water. The flight altitude of the aircraft corresponding to the pure water was obtained through the following method: After the fire extinguisher sprays pure water, the distance between the pure water and the spray nozzle of the fire extinguisher is obtained. Based on the distance value, obtain the ratio of the distance value to the spray nozzle diameter; The sum of the distance value corresponding to the first ratio and the distance between the power transmission line and the ground is taken as the flight altitude of the aircraft corresponding to pure water, where the first ratio is 11.

2.

5. The method for extinguishing live fires in aviation equipment according to claim 4, characterized in that, The flight altitude of aircraft corresponding to extinguishing agents other than pure water is obtained using the first formula, which is: H = (H1 - b) × α + 3 + b; Where H represents the flight altitude of aircraft corresponding to other extinguishing agents, H1 represents the flight altitude of aircraft corresponding to pure water, α represents the diffusion correction factor of other extinguishing agents, and b represents the distance between the power transmission line and the ground.

6. The method for extinguishing live fires in aviation equipment according to claim 5, characterized in that, The diffusion correction factor for other extinguishing agents is obtained using the second formula, which is: α = Aη1 / η2; Where α represents the diffusion correction factor for other extinguishing agents, A represents the correction coefficient, η1 represents the viscosity coefficient of other extinguishing agents, and η2 represents the viscosity coefficient of pure water.

7. A live fire extinguishing device for aviation equipment, characterized in that, include: The acquisition module is used to acquire the extinguishing agent currently being used for extinguishing live fires in aviation equipment; The determination module is used to determine the operating parameters for extinguishing fires involving energized aircraft equipment corresponding to the currently used fire extinguishing agent, specifically including: obtaining the conductivity of the fire extinguishing agent; and determining the operating parameters for extinguishing fires involving energized aircraft equipment based on the conductivity. The operating parameters are those that prevent flashover of insulators on energized fire extinguishing transmission lines of aviation equipment. These operating parameters include at least the flight altitude of the aviation equipment and the duration of fire extinguishing agent spraying.

8. A live fire extinguishing device for aviation equipment, characterized in that, include: The acquisition module is used to acquire the extinguishing agent currently being used for extinguishing live fires in aviation equipment; The determination module is used to determine the operating parameters for extinguishing live fires in aviation equipment corresponding to the currently used extinguishing agent. The operating parameters are those that prevent flashover of insulators on energized fire-fighting transmission lines for aviation equipment. These parameters include at least the flight altitude of the aviation equipment, and the extinguishing agent currently used includes pure water. The flight altitude corresponding to the pure water is obtained through the following method: obtaining the distance between the pure water and the nozzle of the fire extinguisher after the fire extinguisher has sprayed pure water; obtaining the ratio of the distance to the nozzle diameter based on the distance; and using the sum of the distance greater than a first ratio and the distance between the transmission line and the ground as the flight altitude corresponding to the pure water, where the first ratio is 11.

2.

9. An aviation device, characterized in that, include: A processor and a memory, wherein the processor executes the method for extinguishing live fires of aircraft equipment as described in any one of claims 1-6 by calling programs or instructions stored in the memory.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a program or instructions that cause a computer to perform the method for extinguishing energized fires in aviation equipment as described in any one of claims 1-6.

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