Lift potential safety hazard inspection method, aircraft, unmanned aerial vehicle, computer equipment and medium

Abstract

The invention provides an elevator potential safety hazard inspection method, an aircraft, an unmanned aerial vehicle, computer equipment and a medium, and the method comprises the steps: sequentially carrying out the state inspection of each key part of an elevator according to a preset inspection sequence, and obtaining the part state of each key part, determining the component state of the first key component according to the component actual image of the first key component; and / or, determining component actual data of a second key component, and determining a component state of the second key component according to the component actual data of the second key component; and whether the elevator has potential safety hazards or not is determined according to the component state of each key component. By the adoption of the scheme, the labor cost consumed when potential safety hazard inspection is conducted on the elevator is reduced, and the efficiency and accuracy of potential safety hazard inspection are improved.

Description

Technical Field

[0001] The present invention relates to the field of equipment automation management. Specifically, it relates to a method for inspecting potential safety hazards of a lift, an aircraft, a drone, a computer device, and a medium. Background Art

[0002] In fields such as construction and logistics warehousing, as an important device for vertical transportation, the safety and reliability of a lift are directly related to the life safety and operation efficiency of operators. However, the traditional inspection of potential safety hazards of a lift mainly relies on manual labor, and this method has many deficiencies.

[0003] Firstly, manual inspection requires a large amount of manpower and time. Inspectors need to check each key component of the lift one by one, such as the guide rail frame, the cage, the transmission mechanism, the electrical system, etc. This not only has a large workload but also low efficiency. Especially in high-rise buildings or large logistics warehouses, the number of lifts is large and they are widely distributed, making manual inspection even more difficult. Secondly, manual inspection has potential safety hazards. When inspectors are performing high-altitude operations, they face a relatively high risk of falling. At the same time, for some components that are difficult to reach or have blocked visibility, inspectors may need to take risky behaviors or use unsafe tools for inspection, further increasing the safety risk. In addition, manual inspection is also easily affected by the experience, skill level, and subjective judgment of inspectors. Different inspectors may have different judgments on the state of the same component, resulting in inconsistencies in inspection results. At the same time, it is difficult for manual inspection to achieve real-time monitoring and data analysis of the operating state of the lift and cannot detect potential safety hazards in a timely manner. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to provide a method for inspecting potential safety hazards of a lift, an aircraft, a drone, a computer device, and a medium, so as to reduce the labor cost required for inspecting potential safety hazards of a lift and improve the efficiency and accuracy of inspecting potential safety hazards.

[0005] In a first aspect, an embodiment of the present application provides a method for inspecting potential safety hazards of a lift, which is applied to an aircraft. The method includes: Performing status inspections on each key component of the lift in sequence according to a preset inspection order to obtain the component status of each key component, where: Collecting the actual image of the first key component, and determining the component status of the first key component according to the actual image of the first key component; And / or, determining the actual data of the second key component, and determining the component status of the second key component according to the actual data of the second key component; Determining whether there are potential safety hazards in the lift according to the component status of each key component.

[0006] Optionally, collecting the actual image of the first key component includes: Flying according to the shooting route configured for the first key component; During the flight, collecting the actual image of the first key component through the camera installed on its pan-tilt head; Optionally, determining the component state of the first key component based on the actual image of the first key component includes: Transmitting the actual image of the first key component to the AI recognition box; Determining the component state of the first key component through the AI recognition box based on the actual image of the first key component.

[0007] Optionally, the key components include ground protection fences, standard sections, wall attachments, and cages; The inspection of the state of the ground protection fence includes the inspection of its height, integrity, rust level, and the fastening state of the anchor bolts; The inspection of the state of the standard section includes the inspection of whether there is pin withdrawal, bolt loosening, and structural deformation, as well as the inspection of its wire rope; The inspection of the state of the wall attachment includes the inspection of its pins and split pins, as well as the inspection of whether there is structural rust, bolt loosening, and strut deformation; The inspection of the state of the cage includes the inspection of whether there is structural rust, deformation, damage, and loosening.

[0008] Optionally, the actual component data includes the actual height. Determining the actual component data of the second key component includes: For the ground protection fence, collecting the starting height of the aircraft and the ending height when the aircraft is facing the ground protection fence; Determining the actual height of the ground protection fence based on the starting height and the ending height; For the standard section, collecting the height of the top of the free end of the standard section and the height of the upper limit baffle of the standard section; Determining the actual height of the free end of the standard section based on the height of the top of the free end and the height of the upper limit baffle.

[0009] Optionally, determining the component state of the second key component based on the actual component data of the second key component includes: Obtaining the standard component data of the second key component; Comparing the actual component data of the second key component with its standard component data; Determine the component status of the second key component according to the comparison result.

[0010] In a second aspect, an embodiment of the present application provides an aircraft, which includes: A component status inspection module, configured to sequentially perform status inspections on each key component of the elevator according to a preset inspection sequence to obtain the component status of each key component, where: Collect the actual image of the first key component, and determine the component status of the first key component according to the actual image of the first key component; And / or, determine the actual component data of the second key component, and determine the component status of the second key component according to the actual component data of the second key component; A safety hazard inspection module, configured to determine whether there are safety hazards in the elevator according to the component status of each key component.

[0011] Optionally, the collecting the actual image of the first key component includes: Fly according to the shooting route configured for the first key component; During the flight, collect the actual image of the first key component through a camera installed on its pan-tilt head; Optionally, the determining the component status of the first key component according to the actual image of the first key component includes: Transmit the actual image of the first key component to the AI recognition box; Through the AI recognition box, determine the component status of the first key component according to the actual image of the first key component.

[0012] Optionally, the key components include a ground protection fence, a standard section, an attachment wall, and a cage; The status inspection of the ground protection fence includes inspections of its height, integrity, rust degree, and the fastening status of the anchor bolts; The status inspection of the standard section includes inspections of whether there is pin outer withdrawal, bolt loosening, structural deformation, and inspections of its steel wire rope; The status inspection of the attachment wall includes inspections of its pins and split pins, and inspections of whether there is structural rust, bolt loosening, and strut deformation; The status inspection of the cage includes inspections of whether there is structural rust, deformation, damage, and loosening.

[0013] Optionally, the actual component data includes the actual height, and the determining the actual component data of the second key component includes: For the ground protection fence, collect the starting height of the aircraft and the ending height when the aircraft is facing the ground protection fence; Determine the actual height of the ground protection fence according to the starting height and the ending height; For the standard section, collect the height of the top of the free end of the standard section and the height of the upper limit baffle of the standard section; Determine the actual height of the free end of the standard section according to the height of the top of the free end and the height of the upper limit baffle.

[0014] Optionally, determining the component state of the second key component according to the actual component data of the second key component includes: Obtain the standard component data of the second key component; Compare the actual component data of the second key component with its standard component data; Determine the component state of the second key component according to the comparison result.

[0015] In a third aspect, an embodiment of the present application provides a drone, which includes a remote controller and the aircraft in any optional implementation manner of the second aspect above. The remote controller is used to control the aircraft to check the safety hazards of the elevator; the remote controller is also used to check the working state of the aircraft.

[0016] In a fourth aspect, an embodiment of the present application provides a computer device, including: a processor, a memory, and a bus. The memory stores machine-readable instructions executable by the processor. When the computer device runs, the processor communicates with the memory through the bus. When the machine-readable instructions are executed by the processor, the steps of the elevator safety hazard inspection method in any optional implementation manner of the first aspect above are executed.

[0017] In a fifth aspect, an embodiment of the present application provides a computer-readable storage medium, on which a computer program is stored. When the computer program is run by a processor, the steps of the elevator safety hazard inspection method in any optional implementation manner of the first aspect above are executed.

[0018] The technical solutions provided by the present application include but are not limited to the following beneficial effects: This application uses an aircraft to sequentially check the status of each key component of the elevator according to a preset inspection order to obtain the component status of each key component. Compared with manual inspection of component status, it can avoid potential safety hazards when inspectors perform high-altitude operations, reduce safety risks such as falling, reduce the consumption of labor costs, and can shorten the inspection time, improving the inspection efficiency. Specifically, the component status of each key component is determined based on the component data and / or images of each key component, and the status is determined by combining various different forms of component information, which can improve the accuracy and reliability of status detection. Finally, whether there are safety hazards in the elevator is determined based on the status detection result, which can realize the automatic detection of safety hazards in the elevator through a unified detection standard. Compared with manual inspection, it can reduce errors caused by human factors and the influence of subjective judgment, and improve the accuracy and consistency of the inspection results. Especially in the safety inspection of a large-scale elevator group, it can greatly improve the efficiency of component status inspection.

[0019] In summary, by introducing an aircraft for safety hazard inspection of the elevator, this application can not only reduce the labor costs required for safety hazard inspection of the elevator, avoid safety risks, but also improve the efficiency and accuracy of safety hazard inspection.

[0020] To make the above objects, features, and advantages of the present invention more obvious and understandable, the following specific preferred embodiments are given, and in conjunction with the accompanying drawings, the detailed description is as follows. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] To more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for use in the embodiments. It should be understood that the following drawings only show some embodiments of the present invention, and therefore should not be regarded as limiting the scope. For those of ordinary skill in the art, without creative efforts, other related drawings can also be obtained based on these drawings.

[0022] Figure 1 Shows the flowchart of a method for inspecting safety hazards of an elevator provided in Embodiment 1 of the present invention; Figure 2 Shows the flowchart of a method for collecting actual images of components provided in Embodiment 1 of the present invention; Figure 3 Shows the flowchart of a method for determining the status of components provided in Embodiment 1 of the present invention; Figure 4 Shows the structural schematic diagram of the key components of an elevator provided in Embodiment 1 of the present invention; Figure 5 Shows the schematic diagram of inspecting the status of the ground protection fence provided in Embodiment 1 of the present invention; Figure 6 Shows a schematic diagram of a standard section status check provided by Embodiment 1 of the present invention; Figure 7 Shows a schematic diagram of a second standard section status check provided by Embodiment 1 of the present invention; Figure 8 Shows a schematic diagram of an attachment wall status check provided by Embodiment 1 of the present invention; Figure 9 Shows a schematic diagram of a second attachment wall status check provided by Embodiment 1 of the present invention; Figure 10 Shows a schematic diagram of a cage status check provided by Embodiment 1 of the present invention; Figure 11 Shows a schematic diagram of a second cage status check provided by Embodiment 1 of the present invention; Figure 12 Shows a flowchart of a second method for determining component status provided by Embodiment 1 of the present invention; Figure 13 Shows a schematic diagram of the structure of an aircraft provided by Embodiment 2 of the present invention; Figure 14 Shows a schematic diagram of the structure of a computer device provided by Embodiment 4 of the present invention. Detailed implementation manners

[0023] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, rather than all of the embodiments. Usually, the components of the embodiments of the present invention described and illustrated herein can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed present invention, but merely represents selected embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0024] Embodiment 1 For the convenience of understanding the present application, the following will Figure 1 describe Embodiment 1 of the present application in detail with reference to the content described in the flowchart of a method for checking safety hazards of a lift provided by Embodiment 1 of the present invention shown.

[0025] See Figure 1 as shown, Figure 1The flowchart of a method for inspecting potential safety hazards of a lift provided in Embodiment 1 of the present invention is shown. Among them, the method is applied to an aircraft and includes steps S101 to S102: S101: Perform status inspections on each key component of the lift in sequence according to a preset inspection order to obtain the component status of each key component, where: collect the actual component images of the first key component, and determine the component status of the first key component according to the actual component images of the first key component; and / or, determine the actual component data of the second key component, and determine the component status of the second key component according to the actual component data of the second key component.

[0026] Specifically, the aircraft uses devices such as cameras and sensors carried on it to conduct a detailed inspection of the appearance, structure, functional status, etc. of each key component of the construction lift in accordance with a preset inspection order. The inspection order can be set according to factors such as the structural characteristics of the lift and the priority of safety inspections to ensure comprehensive and efficient coverage of all parts that need to be inspected. The key components include but are not limited to the ground protection fence, standard sections, wall attachments, cages, etc.

[0027] Furthermore, when collecting the actual component images of the first key component and determining the component status of the first key component according to the actual component images of the first key component, for the first key component (such as the ground protection fence), the actual component images are collected through a camera or other sensors carried on the aircraft, and then these images are transmitted to an AI recognition box connected to the aircraft. This AI recognition box is embedded with an identification program for the main components of the construction lift and an automatic detection program for corresponding potential safety hazards. By analyzing and processing these images, the AI recognition box can determine the height, integrity, rust level of the ground protection fence, and the fastening status of the anchor bolts, etc., that is, the component status of the first key component.

[0028] When determining the actual component data of the second key component and determining the component status of the second key component according to the actual component data of the second key component, for the second key component (such as the standard section), since it mainly involves inspections of structural dimensions and material status, devices such as rangefinders and sensors carried on the aircraft, combined with the analysis algorithm of the AI recognition box, can determine the actual dimension data of the standard section (such as the outer withdrawal amount of the pin shaft, the looseness of the bolts, the structural deformation amount, etc.) and the status data such as the wear and broken strands of the wire rope. These data will be used to evaluate whether there are potential safety hazards in the standard section, that is, the component status of the second key component.

[0029] S102: Determine whether there are potential safety hazards in the lift according to the component status of each key component.

[0030] Specifically, after completing the status check of each key component, the aircraft processes and analyzes the collected data. This includes comparing the actual status of each component with the preset safety standards or specifications, and using technical means such as artificial intelligence and machine learning to deeply mine and intelligently identify the data. Through the above data analysis, it can be judged whether there are abnormalities or potential safety hazards in each component. Once a safety hazard is found, an alarm or prompt will be given immediately, and the relevant information will be transmitted to the ground control center or relevant management personnel, so as to take timely measures for repair or rectification to ensure the safe operation of the lift. By adopting the above steps, this application can realize the automatic and intelligent inspection of the key components of the construction lift, which not only improves the inspection efficiency and accuracy, but also reduces the risks and costs brought by manual inspection.

[0031] In an alternative embodiment, refer to Figure 2 as shown Figure 2 The flowchart of a method for collecting the actual image of a component provided in the first embodiment of the present invention is shown, wherein the step of collecting the actual image of the first key component includes steps S201 to S202: S201: Fly according to the shooting route configured for the first key component.

[0032] Specifically, according to the specific position, shape and inspection requirements of the first key component, a suitable shooting route is configured for it. This route should ensure that the aircraft can approach and fly around the first key component safely and stably, while ensuring that the camera can capture clear and complete component images from multiple angles and distances.

[0033] S202: During the flight, collect the actual image of the first key component through the camera installed on its pan-tilt head.

[0034] Specifically, the aircraft will fly according to the preset shooting route. During the flight, the pan-tilt head on the aircraft will be adjusted according to the preset shooting parameters (such as angle, focal length, exposure, etc.) to ensure that the camera can accurately capture the actual image of the first key component. These images will contain information such as the appearance, structure and details of the component, providing data support for subsequent status analysis. After collecting the actual image of the first key component, these images will be transmitted to an AI recognition box or other data processing devices connected to the aircraft for further analysis and processing. By extracting, matching and identifying the features in the images, the component status (such as height, integrity, rust degree, etc.) of the first key component can be determined, and then whether there are safety hazards can be evaluated.

[0035] In an alternative embodiment, refer to Figure 3 as shown Figure 3The flowchart of a method for determining the component status provided in the first embodiment of the present invention is shown. Among them, determining the component status of the first key component according to the actual component image of the first key component includes steps S301 to S302: S301: Transmit the actual component image of the first key component to the AI recognition box.

[0036] S302: Determine the component status of the first key component according to the actual component image of the first key component through the AI recognition box.

[0037] Specifically, the actual component image of the first key component collected is transmitted to the AI recognition box in real time or offline through wireless transmission or other means. The AI recognition box will use the built-in image processing algorithm and deep learning model to analyze the actual component image of the first key component. For example, for the ground protection fence, check whether the height of the fence meets the safety standards, whether the integrity of the fence is maintained well (without missing or damaged parts), and whether the rust degree of the fence exceeds the acceptable range. In addition, the AI recognition box will also check the fastening status of the anchor bolts to ensure that they are not loose or fallen off.

[0038] Based on these analysis results, the AI recognition box will be able to determine the component status of the first key component. This status can be a quantitative index (such as the percentage of rust degree) or a qualitative judgment (such as "safe", "potential hazard", etc.). Finally, the AI recognition box will send the determined component status and related analysis data and image information to the ground control center or relevant management personnel through wireless transmission or other means. These information will be used as an important basis for subsequent safety assessment, maintenance decision-making or improvement suggestions.

[0039] In an alternative embodiment, see Figure 4 as shown Figure 4 The structural schematic diagram of a key component of a lift provided in the first embodiment of the present invention is shown. Among them, the key component includes a ground protection fence 401, a standard section 402, an attachment wall 403 and a cage 404.

[0040] The status check of the ground protection fence includes the check of its height, integrity, rust degree and the fastening status of the anchor bolts.

[0041] Specifically, use the shooting function of the aircraft to obtain the image data of the ground protection fence; analyze the image data through the image recognition algorithm, measure the height of the ground protection fence, and detect its integrity, rust degree and the fastening status of the anchor bolts; compare the recognition and analysis results with the preset safety standards to judge whether there are potential safety hazards in the ground protection fence.

[0042] Further, referring to Figure 5 shown in Figure 5 FIG. 5, there is shown a schematic diagram of the state inspection of a ground protection fence provided in the first embodiment of the present invention. Among them, the ground protection fence faces the wall, and the UAV operator manually guides the aircraft to fly to the top of the ground protection fence ( Figure 5 at the position of point P11 in FIG. 5, and record the three-dimensional coordinates of this point as P11 _longtitude, P11 _latitude , P11 _altitude ), and ensure that the pan-tilt is horizontally aligned with the ground protection fence. At this time, the flight inspection module in the aircraft automatically reads the yaw angle of the aircraft at this position (the offset angle of the nose direction relative to the due north direction) and records it as , the distance between the aircraft and the basic ground protection fence is recorded as D _fence , and the altitude of this point is read and recorded as H _fence . Thus, the actual height H of the basic ground fence can be automatically calculated _actualfence as follows: H _actualfence =H _fence -H _start . Compare H _actualfence with the specification requirements built in the flight inspection module to check whether the height of the basic ground protection fence meets the requirements.

[0043] After the aircraft is at the position of point P11 in Figure 5 FIG. 5, record the length of the basic ground protection fence as L _fence , the width as W _fence , the aircraft moves 1 meter along the Figure 5 X direction in FIG. 5, that is, the east-west direction, and the longitude change amount is EW _latitude , and when moving 1 m along the Y direction, that is, the north-south direction, the corresponding latitude change amount is NS _longtitude . At this time, the three-dimensional coordinates of points P12, P13, P14, P15, and P16 in Figure 5 FIG. 5 are as follows:

[0044] Wherein, the three-dimensional coordinates of point P11 are (P11_longtitude, P11_latitude, P11_altitude), the three-dimensional coordinates of point P12 are (P12_longtitude, P12_latitude, P12_altitude), the three-dimensional coordinates of point P13 are (P13_longtitude, P13_latitude, P13_altitude), the three-dimensional coordinates of point P14 are (P14_longtitude, P14_latitude, P14_altitude), the three-dimensional coordinates of point P15 are (P15_longtitude, P15_latitude, P15_altitude), and the three-dimensional coordinates of point P16 are (P16_longtitude, P16_latitude, P16_altitude); the subscript _longtitude represents longitude, the subscript _latitude represents latitude, and the subscript _altitude represents altitude.

[0045] At this time, the flight inspection module automatically generates the flight path P11 - P12 - P13 - P14 - P15 - P16, and the aircraft takes pictures around the ground guardrail with the pan-tilt angle of the gimbal being zero degrees. To ensure a more comprehensive inspection of the basic ground guardrail, after the aircraft flies to point P16, the pan-tilt angle of the aircraft's gimbal is set to a 45-degree downward view, and the reverse flight path P16 - P15 - P14 - P13 - P12 - P11 is set. After the aircraft flies along this reverse flight path and finishes taking pictures, the AI box identifies and reads the captured image data, and analyzes the potential safety hazards included, such as damage, rust, and loosening of the anchor bolts of the guardrail. Thus, the inspection of the foundation (including the ground guardrail) is completed.

[0046] The inspection of the state of the standard section includes the inspection of whether there is pin outward movement, bolt loosening, and structural deformation, as well as the inspection of its steel wire rope.

[0047] Specifically, the image data of the standard section is obtained through the shooting function of the aircraft; image recognition algorithms are used to detect whether there are problems such as pin outward movement, bolt loosening, and structural deformation of the standard section, and to inspect the wear and broken strands of the steel wire rope; the recognition and analysis results are compared with the preset safety standards to determine whether there are safety hazards in the standard section.

[0048] Further, as shown in Figure 6 shown, Figure 6 FIG. shows a schematic diagram of the inspection of the state of a standard section provided in the first embodiment of the present invention. As shown in Figure 7 shown, Figure 7 FIG. shows a schematic diagram of the second inspection of the state of a standard section provided in the first embodiment of the present invention, whereinFigure 6 For Figure 7 the cross-section, after completing the inspection of the ground protection fence, the aircraft returns to Figure 5 point P11 in _mast , and then starts to inspect the standard sections of the construction hoist. Denote the distance between the aircraft and the standard section as D _mast and _mast the lengths of the struts perpendicular and parallel to the wall of the standard section are LV _mast and LH _mast respectively. The height of the main limb of the standard section is H _mast , and the total number of standard sections is N _mast . Since the size of the standard section is relatively small, to avoid unnecessary repeated shooting and improve the efficiency of shooting inspection, the inspection path of the aircraft for the standard section is designed as shown in Figure 6 and Figure 7 . The designed flight path of the aircraft is P21 - P22 - P22a - P23a - P23 - P24 - P24a. P21 is the position at the bottom of the standard section, and P22a, P23a, and P24a are the corresponding positions at the top of the free end of the standard section. At this time, the coordinate positions of each point in Figure 7 can be calculated as follows:

[0049] In the formula, the three-dimensional coordinates of point P21 are (P21 _longtitude, P21 _latitude , P21 _altitude ), the three-dimensional coordinates of point P22 are (P22 _longtitude, P22 _latitude , P22 _altitude ), the three-dimensional coordinates of point P23 are (P23 _longtitude, P23 _latitude , P23 _altitude ), the three-dimensional coordinates of point P24 are (P24 _longtitude, P24 _latitude , P24 _altitude ), the three-dimensional coordinates of point P22a are (P22a _longtitude, P22a _latitude , P22a _altitude ), the three-dimensional coordinates of point P23a are (P23a _longtitude, P23a _latitude , P23a _altitude ), the three-dimensional coordinates of point P24a are (P24a _longtitude, P24a _latitude , P24a _altitude ); the subscript _longtitude represents longitude, the subscript _latitude represents latitude, and the subscript _altitude represents altitude.

[0050] After the aircraft flies along the above path and takes pictures, the inspection of the standard sections of the construction hoist can be completed. Then, all the image data related to the standard sections is transmitted into the AI recognition box, and the AI recognition box automatically checks for relevant safety hazards of the standard sections, such as pin outward movement, bolt loosening, structural deformation, wire rope strand breakage, etc.

[0051] After the aircraft reaches Figure 7 point P24a in and completes the inspection of the standard section, it flies vertically downward from this point. When the AI recognition box detects the upper limit baffle, it stops flying, and the aircraft automatically reads the altitude at this time as P _uppermast , and at this time, the height H of the free end of the standard section can be calculated _uppermast as:

[0052] Compare the obtained H _uppermast with the maximum allowable height of the free end of the standard section built into the system to check whether the height of the free end of the standard section meets the specification requirements.

[0053] The inspection of the state of the attachment wall includes the inspection of its pins and split pins, as well as the inspection of whether there is structural corrosion, bolt loosening, and strut deformation.

[0054] Specifically, the image data of the attachment wall is obtained through the shooting function of the aircraft; the image recognition algorithm is used to detect the states of components such as the pins and split pins of the attachment wall, as well as whether there are problems such as structural corrosion, bolt loosening, and strut deformation; the recognition and analysis results are compared with the preset safety standards to determine whether there are safety hazards in the attachment wall.

[0055] Furthermore, referring to Figure 8 shown, Figure 8 shows a schematic diagram of the inspection of the state of an attachment wall provided in the first embodiment of the present invention. Referring to Figure 9 shown, Figure 9 shows a schematic diagram of the second inspection of the state of an attachment wall provided in the first embodiment of the present invention. Among them, after the inspection of the height of the free end of the standard section is completed, the inspection of the attachment wall of the construction hoist is carried out. At this time, the UAV operator guides the aircraft to fly to the highest attachment wall, such as Figure 8 and Figure 9 shown position, Figure 8 is Figure 9Cross-section. It should be noted that, to cover the inspection surface of the wall-attached structure more comprehensively, each section of the wall-attached structure contains two shooting points P31 and P32. Both points are located at the middle distance between the standard section and the wall. At the same time, the pan-tilt can cover the entire range of the wall-attached structure. Point P31 is about 1 meter above the wall-attached structure to be inspected, and the pan-tilt looks down at an angle of 15°. Point P32 is about 2 meters directly below point P31, that is, about 1 meter below the wall-attached structure to be inspected, and the pan-tilt looks up at an angle of 15°. The above shooting method can avoid many blind spots in the inspection of the wall-attached structure by the pan-tilt of a single aircraft looking straight ahead, especially for important inspection contents such as pin shafts, split pins, and screws.

[0056] After inspecting the highest section of the wall-attached structure, based on the vertical installation spacing of adjacent wall-attached structures, the aircraft sequentially conducts all inspections on one side of the wall-attached structure from high to low. After that, for the other side of the wall-attached structure, the inspections on the other side are completed from low to high in a similar manner. After receiving all the image data of the wall-attached structure taken by the aircraft, the AI recognition box automatically inspects potential safety hazards included in the wall-attached structure, such as the outward movement of pin shafts, structural corrosion, bolt loosening, deformation of struts, and too small opening angle of split pins.

[0057] The inspection of the state of the cage includes checking whether there are structural corrosion, deformation, damage, and loosening.

[0058] Specifically, when the cage is in a stationary state (for example, the two cages are parked in a staggered manner), the shooting function of the aircraft is used to obtain the image data of the cage from multiple angles; the structure of the cage is carefully inspected through an image recognition algorithm, including whether there are structural corrosion, deformation, damage, and loosening; the recognition and analysis results are compared with the preset safety standards to determine whether there are safety hazards in the cage.

[0059] Further, as shown in Figure 10 shown, Figure 10 Figure 1 shows a schematic diagram of the inspection of the state of a cage provided in the first embodiment of the present invention. As shown in Figure 11 shown, Figure 11 Figure 2 shows a second schematic diagram of the inspection of the state of a cage provided in the first embodiment of the present invention. Among them, Figure 10 is Figure 11 the cross-section. After that, the aircraft inspects the cage. To maximize the inspection coverage of the cage, it is necessary to ensure that the two cages are staggered with each other before the UAV inspection. The UAV operator guides the aircraft to fly to the position of point P41 in the cage Figure 10 and Figure 11 . The coordinates of this point are denoted as P41 _longitude , P41 _latitude , P41 _altitude . Denote the distance between point P41 and the cage as D _elevator . The width of the rectangular outer contour of the cage is W _elevator . The length is L_elevator , with a height of H _elevator , at this time, the aircraft can fly automatically along Figure 11 the bottom of the middle suspension cage P41 - P42 - P43 - P44 - P45 - P46 - P47, where the coordinate calculations of points P42 to P47 are as follows:

[0060] In the formula, the three - dimensional coordinates of point P41 are (P41 _longtitude, P41 _latitude , P41 _altitude ), the three - dimensional coordinates of point P42 are (P42 _longtitude, P42 _latitude , P42 _altitude ), the three - dimensional coordinates of point P43 are (P43 _longtitude, P43 _latitude ,P43 _altitude ), the three - dimensional coordinates of point P44 are (P44 _longtitude, P44 _latitude , P44 _altitude ), the three - dimensional coordinates of point P45 are (P45 _longtitude, P45 _latitude , P45 _altitude ), the three - dimensional coordinates of point P46 are (P46 _longtitude, P46 _latitude ,P46 _altitude ), the three - dimensional coordinates of point P47 are (P47 _longtitude, P47 _latitude , P47 _altitude ); the subscript _longtitude represents longitude, the subscript _latitude represents latitude, and the subscript _altitude represents height.

[0061] After the aircraft completes the inspection of the bottom of the suspension cage, for P41, P42, P43, P44, P45, P46, P47, while keeping the longitude and latitude unchanged, the altitude increases by H _elevator , and the corresponding points are denoted as P41a, P42a, P43a, P44a, P45a, P46a, P47a. Then the aircraft completes the inspection of the top of the suspension cage along P47a - P46a - P45a - P44a - P43a - P42a - P41a. For the suspension cage on the other side of the elevator, the inspection method is similar and will not be elaborated here. After the AI inspection box receives the image data of the suspension cage, it automatically inspects the potential safety hazards of the suspension cage, such as structural corrosion, deformation, damage, looseness, etc.

[0062] After completing the cage inspection, you can also enter the custom inspection mode, allowing users to perform more flexible and personalized inspections on other parts of the elevator. In this mode, after the drone operator guides the aircraft to fly to any given location for high-definition shooting, the AI ​​recognition box receives the aircraft image data in real time and analyzes and identifies the corresponding safety hazards. After the above steps, all on-site inspections of the construction elevator are completed. The image data taken by the drone, the safety hazards detected by the AI ​​recognition box, and the project information are all wirelessly transmitted to the construction elevator safety hazard management module. This module provides functions such as rapid filtering of construction elevator project information, efficient query of hazards, and one-click generation of safety reports, which facilitate users to conduct real-time, dynamic and refined management of construction elevators.

[0063] Through the above steps, the present application can utilize the high maneuverability and shooting capabilities of the aircraft, combined with image recognition algorithms, to conduct a comprehensive and detailed safety hazard inspection of key components of the construction elevator, thereby improving inspection efficiency and accuracy while reducing the risks and costs of manual inspections.

[0064] In an optional embodiment, the actual component data includes an actual height, and the actual component data of the second key component is determined, including: For the ground protection fence, the starting height of the aircraft and the ending height when the aircraft is facing the ground protection fence are collected; and the actual height of the ground protection fence is determined according to the starting height and the ending height.

[0065] Specifically, after the aircraft takes off and flies stably, but before approaching the ground protection fence, the aircraft's altitude at this time is obtained through the aircraft's built-in GPS or barometric altimeter and other sensors as the starting altitude and recorded. When the aircraft is flying directly towards the ground protection fence and its bottom (or preset reference point) is flush with the top of the ground protection fence, the aircraft's altitude at this time is recorded as the ending altitude. The actual height of the ground protection fence is calculated using the difference between the starting altitude and the ending altitude.

[0066] For the standard section, the top height of the free end of the standard section and the height of the upper limit baffle of the standard section are collected; and the actual height of the free end of the standard section is determined according to the top height of the free end and the height of the upper limit baffle.

[0067] Specifically, when the aircraft approaches and stably hovers near the top of the free end of the standard section, the height of the aircraft at this time is recorded as the free end top height. Subsequently, when the aircraft rises slightly and stably hovers near the upper limit baffle of the standard section, the height of the aircraft at this time is recorded as the upper limit baffle height. The actual height of the free end of the standard section can be obtained by subtracting the free end top height from the upper limit baffle height.

[0068] In an alternative embodiment, participate in Figure 12 As shown Figure 12 FIG. shows a flowchart of a second method for determining the component state provided in the first embodiment of the present invention. Among them, determining the component state of the second key component according to the actual component data of the second key component includes steps S1201 to S1203: S1201: Obtain the component standard data of the second key component.

[0069] S1202: Compare the actual component data of the second key component with its component standard data.

[0070] S1203: Determine the component state of the second key component according to the comparison result.

[0071] Specifically, obtain the standard data and the actual component data related to the second key component (such as the standard section height), and compare these two sets of data. For the standard section, the difference between its actual height and the designed height, as well as whether the actual size is within the allowable deviation range, will be compared. If the actual component data matches the standard data or the difference is within an acceptable range, the component is considered to be in a normal state. However, if there is a significant difference between the actual data and the standard data, exceeding the range allowed by the safety regulations or industry standards, the component may be marked as having a safety hazard.

[0072] In practical applications, the traditional manual inspection method requires at least two people about one day to complete a comprehensive inspection of a construction elevator. However, the inspection method provided by this application only requires one person to complete the same inspection task in about 30 minutes, thus greatly shortening the inspection cycle and improving work efficiency. In the prior art, especially when inspecting the outside of the cage of a construction elevator, inspectors often need to work at heights and face a relatively high risk of falling. While this application combines the use of drones and AI technology, and only requires a drone operator to operate on the ground to achieve a comprehensive inspection of the construction elevator, thus completely avoiding the safety hazards brought by working at heights. Areas that are difficult to reach or are too dangerous for manual inspection, such as the bottom of the cage, the free end at the top of the standard section, and the wall attachment struts, often become omission points in the inspection. With the high mobility of the drone and the flexible pitching angle of the pan-tilt camera in this application, it can easily reach and inspect these inaccessible areas, effectively making up for the blind spots in manual inspection. The traditional manual inspection method requires the construction elevator to stop operating during the inspection, which to a certain extent affects the usage efficiency of the equipment. While this application allows the inspection of the construction elevator to be carried out in the normal working state of the equipment, and only when it is necessary to inspect the cage, it briefly stops and misaligns the two cages, thus reducing the equipment downtime and improving the usage efficiency. Moreover, the prior art completely relies on the experience and ability of inspectors, and due to the difficulty of process tracking during working at heights, the inspection results have a certain degree of uncertainty and are difficult to review, and are usually presented in the form of a paper report. While this application transmits all inspection image data wirelessly in real time to the construction elevator safety hazard management module, uses an AI model to identify, present, and manage safety hazards, and generates a safety hazard report with one key, significantly improving the digital and intelligent levels of construction elevator inspection, management, and historical traceability.

[0073] Embodiment 2 See Figure 13 as shown Figure 13 shows a schematic structural diagram of an aircraft provided by Embodiment 2 of the present invention, wherein the aircraft includes: A component status inspection module 1301, configured to sequentially perform status inspections on each key component of the elevator according to a preset inspection sequence to obtain the component status of each key component; A safety hazard inspection module 1302, configured to determine whether there are safety hazards in the elevator according to the component status of each key component.

[0074] In an optional implementation, the sequentially performing status inspections on each key component of the elevator according to a preset inspection sequence to obtain the component status of each key component includes: Collect the actual image of the first key component, and determine the component state of the first key component according to the actual image of the first key component; and / or determine the actual component data of the second key component, and determine the component state of the second key component according to the actual component data of the second key component.

[0075] In an optional implementation, the collecting the actual image of the first key component includes: Fly according to the flight route configured for the first key component; During the flight, collect the actual image of the first key component through the camera set on its pan-tilt head; The determining the component state of the first key component according to the actual image of the first key component includes: Transmit the actual image of the first key component to the AI recognition box; Through the AI recognition box, determine the component state of the first key component according to the actual image of the first key component.

[0076] In an optional implementation, the key components include a ground protection fence, a standard section, an attachment wall and a cage; The inspection of the state of the ground protection fence includes the inspection of its height, integrity, rust degree and the fastening state of the anchor bolts; The inspection of the state of the standard section includes the inspection of whether there is pin withdrawal, bolt loosening, structural deformation, and the inspection of its steel wire rope; The inspection of the state of the attachment wall includes the inspection of its pins and split pins, and the inspection of whether there is structural rust, bolt loosening and strut deformation; The inspection of the state of the cage includes the inspection of whether there is structural rust, deformation, damage and loosening.

[0077] In an optional implementation, the actual component data includes the actual height. The determining the actual component data of the second key component includes: For the ground protection fence, collect the starting height of the aircraft and the ending height when the aircraft is facing the ground protection fence; Determine the actual height of the ground protection fence according to the starting height and the ending height; For the standard section, collect the top height of the free end of the standard section and the height of the upper limit baffle of the standard section; Determine the actual height of the free end of the standard section according to the top height of the free end and the height of the upper limit baffle.

[0078] In an optional embodiment, determining the component status of the second key component according to the actual component data of the second key component includes: Obtaining the standard component data of the second key component; Comparing the actual component data of the second key component with its standard component data; Determining the component status of the second key component according to the comparison result.

[0079] Embodiment III The embodiment of the present application provides a drone, which includes a remote controller and the aircraft in any optional implementation manner in the second embodiment above. The remote controller is used to control the aircraft to perform safety hazard inspection of the lift; the remote controller is also used to check the working status of the aircraft.

[0080] Specifically, when performing the safety hazard inspection of the lift, first start the aircraft and the remote controller to ensure that the aircraft and the remote controller are successfully frequency - paired. Open the pre - flight inspection setting module in the remote controller, and check the connection status between the aircraft and the AI box through this module to ensure a successful connection. The aircraft is equipped with RTK (Real - time kinematic) high - precision positioning function so that the aircraft can fly and take pictures precisely when inspecting the construction lift.

[0081] In the pre - flight inspection setting module, input the size information of the main components of the construction lift, including the length, width and height of the ground safety fence, the number of standard sections, the height of the main limb, the length of the strut, the maximum width of the wall attachment, the distance between the standard section and the wall, the designed height and number of the wall attachment, the length, width and height of the cage. On this basis, input the flight speed and camera shooting frequency of the drone flight inspection. In addition, to ensure as comprehensive inspection of the cage as possible, the two cages of the construction lift must be placed in a staggered manner.

[0082] The drone operator first checks the RTK working status of the aircraft through the remote controller. If it works normally, the inspection of the construction lift can be directly started; if the RTK status is abnormal, the aircraft must first be guided to a relatively open and unobstructed place, or higher than the surrounding tallest building to ensure that the RTK can search for satellites normally and work properly. Before the aircraft takes off, the flight inspection module memorizes the altitude of the location where the aircraft is located (denoted as H _start )

[0083] Embodiment IV Based on the same inventive concept, as shown in Figure 14 shown, Figure 14 shows a schematic structural diagram of a computer device provided by the fourth embodiment of the present invention. Among them, as Figure 14As shown in the figure, a computer device 1400 provided in the fourth embodiment of the present application includes: A processor 1401, a memory 1402, and a bus 1403. The memory 1402 stores machine-readable instructions executable by the processor 1401. When the computer device 1400 runs, communication is carried out between the processor 1401 and the memory 1402 through the bus 1403. When the machine-readable instructions are run by the processor 1401, the steps of the elevator safety hazard inspection method shown in the first embodiment above are executed.

[0084] Embodiment Five Based on the same inventive concept, the embodiment of the present application further provides a computer-readable storage medium. A computer program is stored on the computer-readable storage medium. When the computer program is run by a processor, the steps of the elevator safety hazard inspection method described in any one of the above embodiments are executed.

[0085] Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working processes of the systems and devices described above can refer to the corresponding processes in the foregoing method embodiments, and will not be elaborated here.

[0086] The computer program product for performing elevator safety hazard inspection provided by the embodiment of the present invention includes a computer-readable storage medium storing program code. The instructions included in the program code can be used to execute the method described in the foregoing method embodiments. For the specific implementation, reference can be made to the method embodiments and will not be elaborated here.

[0087] The aircraft provided by the embodiment of the present invention can be specific hardware on the device or software or firmware installed on the device, etc. The implementation principle and the technical effects generated by the aircraft provided by the embodiment of the present invention are the same as those of the foregoing method embodiments. For the sake of brief description, for the parts not mentioned in the aircraft embodiment, reference can be made to the corresponding content in the foregoing method embodiments. Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working processes of the systems, devices, and units described above can all refer to the corresponding processes in the above method embodiments, and will not be elaborated here.

[0088] In the embodiments provided by the present invention, it should be understood that the disclosed aircraft and methods can be implemented in other ways. The aircraft embodiments described above are merely illustrative. For example, the division of the units is only a logical function division. In actual implementation, there may be other division methods. For another example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the displayed or discussed coupling or direct coupling or communication connection between each other can be through some communication interfaces. The indirect coupling or communication connection of the devices or units can be in electrical, mechanical or other forms.

[0089] The units described as separate components may or may not be physically separated. The components displayed as units may or may not be physical units, that is, they can be located in one place or distributed to multiple network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0090] In addition, each functional unit in the embodiments provided by the present invention can be integrated in a processing unit, or each unit can exist physically alone, or two or more units can be integrated in one unit.

[0091] If the function is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or this part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to enable a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present invention. The foregoing storage medium includes: USB flash drives, mobile hard disks, read-only memories (ROM, Read-Only Memory), random access memories (RAM, Random Access Memory), magnetic disks or optical disks and other various media that can store program codes.

[0092] It should be noted that similar reference numerals and letters represent similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. In addition, the terms "first", "second", "third", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0093] Finally, it should be noted that the above-described embodiments are only specific embodiments of the present invention, used to illustrate the technical solutions of the present invention, rather than limiting it. The protection scope of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that any technician familiar with the technical field of the present invention can still modify the technical solutions recorded in the foregoing embodiments, or can easily think of changes, or perform equivalent replacements on some of the technical features; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention. All should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A method for checking potential safety hazards of a lift, characterized in that, Applied to an aircraft, the method includes: Performing status checks on each key component of the lift in sequence according to a preset inspection order to obtain the component status of each key component, where: Collecting the actual component image of the first key component, and determining the component status of the first key component based on the actual component image of the first key component; And / or, determining the actual component data of the second key component, and determining the component status of the second key component based on the actual component data of the second key component; Determining whether there are potential safety hazards in the lift according to the component status of each key component.

2. The method according to claim 1, wherein The collecting the actual component image of the first key component includes: Flying according to the shooting route configured for the first key component; During the flight, collecting the actual component image of the first key component through a camera installed on its pan-tilt.

3. The method according to claim 1, wherein The determining the component status of the first key component based on the actual component image of the first key component includes: Transmitting the actual component image of the first key component to the AI recognition box; Determining the component status of the first key component through the AI recognition box based on the actual component image of the first key component.

4. The method according to claim 1, characterized in that The key components include a ground protection fence, a standard section, an attachment wall, and a cage; The status check of the ground protection fence includes checking its height, integrity, rust degree, and the fastening status of the anchor bolts; The status check of the standard section includes checking whether there is pin withdrawal, bolt loosening, and structural deformation, and checking its wire rope; The status check of the attachment wall includes checking its pins and split pins, and checking whether there is structural rust, bolt loosening, and strut deformation; The status check of the cage includes checking whether there is structural rust, deformation, damage, and loosening.

5. The method according to claim 4, characterized in that, The actual component data includes the actual height. The determining the actual component data of the second key component includes: For the ground protection fence, collecting the starting height of the aircraft and the ending height when the aircraft is facing the ground protection fence; Determining the actual height of the ground protection fence based on the starting height and the ending height; For the standard section, collecting the top height of the free end of the standard section and the height of the upper limit baffle of the standard section; Determining the actual height of the free end of the standard section based on the top height of the free end and the height of the upper limit baffle.

6. The method according to claim 1, characterized in that, The determining the component status of the second key component based on the actual component data of the second key component includes: Obtaining the component standard data of the second key component; Comparing the actual component data of the second key component with its component standard data; Determining the component status of the second key component according to the comparison result.

7. An aircraft, characterized in that, The aircraft includes: A component status check module for performing status checks on each key component of the lift in sequence according to a preset inspection order to obtain the component status of each key component, where: Collecting the actual component image of the first key component, and determining the component status of the first key component based on the actual component image of the first key component; And / or, determine the actual component data of the second key component, and determine the component status of the second key component according to the actual component data of the second key component; A safety hazard inspection module, configured to determine whether there are safety hazards in the elevator according to the component statuses of the key components.

8. A drone, characterized in that, The drone includes the aircraft and the remote controller as claimed in claim 7; the remote controller is configured to control the aircraft to perform safety hazard inspection on the elevator; the remote controller is further configured to inspect the working status of the aircraft.

9. A computer device, characterized in that, Comprising: A processor, a memory and a bus, wherein the memory stores machine-readable instructions executable by the processor. When the computer device runs, the processor communicates with the memory through the bus. When the machine-readable instructions are executed by the processor, the steps of the elevator safety hazard inspection method as claimed in any one of claims 1 to 6 are executed.

10. A computer-readable storage medium, characterized in that, A computer program is stored on the computer-readable storage medium. When the computer program is run by the processor, the steps of the elevator safety hazard inspection method as claimed in any one of claims 1 to 6 are executed.

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