145 results about "Aircraft maintenance" patented technology

The invention relates to the technical field of aircraft health management, and discloses a system and a method for realizing aircraft health management. The method comprises the following steps: acquiring health data of each monitoring point on an aircraft and state information of each ground processing node; processing based on the data and information to obtain a target monitoring point cluster of each ground processing node; then health data sent by the target monitoring point cluster is subjected to preprocessing configuration, and cluster health data of all ground processing nodes are gathered after preprocessing and uploaded to a health database to-be-stored interface; and finally, synchronously acquiring operation data of each storage interface through a to-be-stored interface of the health database for analysis, and performing distributed storage management on the cluster health data. The method can provide a scientific basis for aircraft maintenance, effectively improves the safety, reliability and operation efficiency of the aircraft, reduces the operation cost, and has an important application value in the field of aircraft health management.

The invention provides a training method of an aircraft maintenance simulation model and an aircraft maintenance simulation method, relates to the technical field of aircraft maintenance simulation, and aims to predict future evolution of aircraft maintenance so as to improve authenticity of aircraft maintenance simulation. The method comprises the following steps: acquiring training data related to maintenance simulation; training a maintenance simulation model based on the training data; the aircraft maintenance simulation model comprises a video word segmentation device, a multi-modal input encoder, a multi-modal token sequence and a multi-modal output encoder, wherein the video word segmentation device is used for encoding videos related to aircraft maintenance simulation into a video token sequence; the multi-modal input encoder is used for encoding multi-modal input data related to aircraft maintenance into a multi-modal token sequence; the potential action model is used for determining a potential action representation of a maintenance action based on the video token sequence and the multi-modal token sequence, and the dynamic prediction model is used for predicting a prediction token at the next moment based on the video token sequence, the multi-modal token sequence and the potential action representation so as to simulate a maintenance scene at the next moment.

The invention discloses a shipboard aircraft maintenance process simulation method and system based on virtual reality, and relates to the technical field of analogue simulation. According to the method, the environment sensing data packets of the shipboard aircraft and the maintenance environment are collected through the multi-modal sensor array, the shipboard aircraft maintenance simulation space is constructed based on the environment sensing data packets, and the regional maintenance step association network under different maintenance events is established according to the maintenance event records; mapping the regional maintenance step associated networks to the surface of a shipboard aircraft maintenance simulation space, and matching the regional maintenance step associated networks with one another to obtain a maintenance step associated network; and a user performs communication interaction with the shipboard aircraft maintenance simulation space through the VR equipment, collects a user interaction process through the VR equipment, inputs a user interaction action into the maintenance step association network, and further outputs a corresponding special reference scheme to judge whether the user interaction process is compliant or not.

The invention relates to an aircraft maintenance stand scheduling method based on a graph neural network and reinforcement learning, and relates to the technical field of aircraft maintenance stand scheduling. Comprising the steps of constructing a space-time coupling heterogeneous graph model based on a disjunction graph of a maintenance project and a space topological graph of a maintenance machine position, designing an adaptive time window division method for increasing and decreasing nodes and edges in a dynamic scene, discretizing a large-scale dynamic heterogeneous graph into static sub-graphs, and improving the calculation efficiency. And designing a reinforcement learning framework in combination with the two-channel graph attention network and the gated cycle space-time memory network to realize dynamic solution of the sub-graph. Compared with the prior art, the problems that space-time coupling constraint modeling is insufficient in a high-density maintenance scene, the multi-target collaborative optimization effect is limited, and a dynamic scene is difficult to adapt can be solved.

The invention relates to the technical field of civil aircraft maintenance and repair, in particular to a flap health state prediction method based on transferable trend grouping autocorrelation comparative learning, which comprises the following steps of: firstly, mining a typical degradation trend from total data by utilizing a clustering algorithm; dividing the individual samples with differentiation into a plurality of trend data groups with high consistency; secondly, introducing an autocorrelation comparison mechanism into each group, capturing common time sequence dependence crossing a long period among samples, and constructing a plurality of pre-training models capable of representing a specific decline mode; then, dynamic matching is carried out according to the characteristics of the flap to be detected, and the most adaptive trend category and the pre-training model are selected; and finally, on the basis of a migration fine tuning strategy, a small amount of data is used for carrying out directional fine tuning on the pre-trained model, so that an exclusive prediction model of the flap is efficiently obtained, compared with the prior art, a model does not need to be built for each aircraft from zero, migration can be carried out on the basis of a limited model library, and effective management of the health state of the civil aircraft is achieved.

This invention relates to an ultrasonic-assisted laser cleaning device for the inner wall of an air intake using negative pressure adsorption, belonging to the field of aircraft maintenance and surface treatment. It includes: a housing with an opening on one side of its working surface, and a flexible sealing member circumferentially disposed around the opening; a laser cleaning head disposed inside the housing; an ultrasonic amplitude transformer arranged in a ring around the laser cleaning area; an ultrasonic transducer connected to the ultrasonic amplitude transformer; a negative pressure suction unit connected to the housing for creating a negative pressure airflow field within the housing; and a high-pressure gas injection unit disposed opposite to the negative pressure suction unit for assisting in the formation of the airflow field. The ultrasonic amplitude transformer has a ring-shaped structure and is arranged in a ring array on the inner wall of the housing, with the ultrasonic transducer mounted thereon, converting electrical signals into ultrasonic vibrations via piezoelectric ceramics. This invention, by combining ultrasonic technology with laser cleaning, can adapt to cleaning areas with different radii of curvature, thereby achieving all-position cleaning.

The application discloses a lifting steering device and a screwing detection device for aircraft maintenance applied by the lifting steering device, and belongs to the technical field of aircraft maintenance. The lifting steering device comprises a base, a threaded cavity is arranged on the base, a threaded block is arranged in the threaded cavity, the threaded block is installed at the lower end of a lifting rod, and the threaded block is engaged with the inner wall of the threaded cavity through threads. The upper end of the lifting rod is provided with a first driving wheel, a second driving wheel is arranged above the first driving wheel, and a gap is kept between the second driving wheel and the first driving wheel. The screwing detection device comprises a main shaft, a conversion box is installed on the main shaft, a second driving reduction motor is installed on the conversion box, the second driving reduction motor is connected with a first bevel gear in a power manner, and a second bevel gear is installed on one side of the first bevel gear. By controlling the forward and reverse rotation of each motor, the lifting, screwing and clamping operations of the working end in the equipment can be realized, so that the working end of the device reaches the construction area which is difficult to reach to perform detection and operation.

A lifting device for aircraft engine maintenance belongs to the field of aircraft maintenance equipment and comprises a base and an adjusting platform, a magnetic lifting assembly is fixedly arranged in the middle of the base, the top end of the magnetic lifting assembly is detachably connected with the adjusting platform, and a plurality of positioning supports are mounted on the adjusting platform; the magnetic attraction lifting assembly comprises a first lifting unit fixedly arranged on the base, a first magnetic attraction unit is fixedly installed at the top end of the first lifting unit and used for being fixed to the bottom of the adjusting platform in a magnetic attraction mode, the height of the adjusting platform can be controlled through the first lifting unit, and the height of the adjusting platform can be adjusted through the arrangement of the first magnetic attraction unit. The base and the adjusting platform are rapidly disassembled and assembled, the aircraft engine can be hoisted to the adjusting platform in advance, the modular replacement effect is achieved, the overhaul and maintenance time is greatly shortened, and the working efficiency is improved.

The utility model relates to the technical field of aircraft maintenance, in particular to an aircraft control surface angle measuring scale which comprises a measuring scale body, the measuring scale body comprises a vertical edge, a transverse edge, a first bevel edge and a second bevel edge, and the vertical edge and the second bevel edge are located on the two opposite sides of the measuring scale body respectively. The transverse edge is arranged between the vertical edge and the second bevel edge and located at the bottom of the measuring ruler body, the first bevel edge is arranged between the vertical edge and the second bevel edge and located at the top of the measuring ruler body, an angle ruler is integrally formed on the measuring ruler body, the angle ruler is an arc-shaped plate and located between the first bevel edge and the second bevel edge, and scales are arranged on the angle ruler. A protruding block is integrally formed on the measuring ruler body and located between the vertical edge and the second bevel edge. According to the invention, the problems of poor portability, dependence on electric power and environmental influence when a maintainer uses a laser measuring instrument to measure the control surface of an airplane are solved.

The invention discloses a closed lock catch detection method and device for an aero-engine thrust reverser, and belongs to the field of aircraft maintenance. The device comprises a rack assembly, a transmitter placing box, a pressure transmitter, a support, an extension spring, a testing assembly, a hanging ring, a balancing weight assembly, a rotating shaft and the like. A design load is simulated through the balancing weight assembly, a handle of the testing assembly is rotated to enable a contact of a pressure sensor to make contact with a closing lock catch trigger or a handle mark, a force signal is transmitted to a pressure transmitter, and opening force and closing force are detected respectively. The problems that in the prior art, a detection device is large in size, complex in operation, low in safety and insufficient in measurement precision are solved. By optimizing the mechanical structure and integrating the sensor, the fine measurement of the closing force within the range of 2210-2230 N is realized, meanwhile, personnel are prevented from directly contacting the closing lock catch trigger, and the operation safety is ensured.

Aircraft are provided with kits and procedures for aircraft maintenance. One procedure involves covering an aircraft display panel with a display cover, the display cover having a transparent area configured to allow viewing of the display panel even when covered; covering an aircraft control panel with a control panel cover having a transparent area configured to allow viewing of the control panel even when covered; using a tool to service an aircraft component while shielding the display panel with the display cover and the control panel with the control panel cover from the tool; and reading information displayed on the display panel through the display cover and / or on the control panel through the control panel cover while the component is being serviced.

A method for assembling pipe joints in an aircraft actuator hydraulic system assembly block is disclosed to achieve precise assembly between the bent pipe joint and the assembly block base. First, a measurement reference conversion component is used to derive the vertical distance from the intersection of the two central axes of the first and second bent joints to the upper reference plane of the assembly block base. Then, based on the derived values, a measurable assembly dimension B is determined. This measurable assembly dimension B is then used as the reference dimension, and the assembly of the upper bent joint of the assembly block is completed using an aircraft actuator hydraulic system assembly block assembly fixture. This method for assembling pipe joints in an aircraft actuator hydraulic system assembly block meets the assembly dimension requirements for upper bent pipe joints during aircraft maintenance, thus ensuring aircraft maintenance quality and safe flight.

This invention discloses a knowledge base system and method for establishing failure effects of aircraft maintenance activities for typical aircraft systems, belonging to the field of failure mode analysis (FMEA) technology for aircraft maintenance activities. It aims to solve problems such as traditional failure effect analysis methods not fully considering the associated effects of maintenance objects and the fact that maintenance activities are mostly stored in text format, which is not conducive to computer storage and reuse. The method includes: using FMEA to conduct failure effect analysis on typical aircraft systems and components; decomposing key operating state parameters for typical systems and components; constructing a knowledge base for the failure effects of maintenance objects; classifying maintenance activity steps and determining the maintenance objects and corresponding operating state parameters according to category correspondences; and associating failure modes and effects through operating state parameters. This improves the efficiency and accuracy of finding failure effects in maintenance activities, providing important data references for failure mode severity analysis and maintenance procedure improvement.

The application provides a mode switching method of an engine electronic controller, a mode switching system of the engine electronic controller and a computer readable storage medium. The mode switching method of the engine electronic controller comprises the following steps: S1, checking a software verification code, and setting a working mode as a normal working mode in response to the software verification code being a complete verification code; S2, modifying the software verification code as an error verification code in response to an aircraft maintenance request and an engine running state meeting a safe maintenance condition, the aircraft maintenance request being sent by an aircraft cabin through a bus; and S3, resetting and checking the software verification code, and switching the working mode to a cabin maintenance mode in response to the software verification code being the error verification code.

The invention discloses an aircraft structure maintenance auxiliary system and method based on labview, relates to the technical field of aircraft structure maintenance, and can improve the aircraft maintenance efficiency and accuracy and reduce the maintenance cost at the same time. According to the scheme, the system comprises an interaction module which comprises an interaction interface and is used for receiving aircraft damage information input by a user and transmitting the damage information to a decision module, and the damage information comprises damage positions, damage types and damage parameters; the decision module is used for matching a target judgment rule corresponding to the damage position and the damage type from a pre-stored expert knowledge base according to the damage position and the damage type after receiving the damage information, inputting the damage parameter into the target judgment rule for evaluation and then generating an evaluation result, and if the evaluation result indicates that maintenance is needed, outputting the damage parameter to the decision module; if yes, the damage information is transmitted to the generation module; and the generation module is used for matching a corresponding maintenance scheme from the expert knowledge base after receiving the damage information, and transmitting the maintenance scheme to the interactive interface.

The invention relates to the crossing field of aircraft ground operation and maintenance and digital twinning technologies, in particular to a digital twinning-based risk monitoring method and system applied to an aircraft ground transportation warehousing trailer, and is suitable for risk identification, evaluation, early warning and management and control of an aircraft ground hauling warehousing whole process in scenes such as civil aviation airports and aircraft maintenance bases. And the safety and reliability of aircraft ground transfer can be improved. The method comprises the following steps of: carding physical entity elements and deploying a data acquisition terminal; a step of constructing and initializing a digital twinborn model; a step of multi-source data fusion and real-time synchronization; constructing a risk index system; a step of risk index weight calculation based on an improved entropy weight-analytic hierarchy process; a dynamic risk quantitative evaluation step; a step of risk simulation and pre-judgment based on digital twinning; a step of graded early warning and response strategy generation; a step of response measure execution and effect feedback; and optimizing and iterating the model and the strategy.

The utility model relates to the technical field of aircraft maintenance, in particular to a clamping bracket for aircraft engine maintenance, which comprises a bottom plate, two movable plates are slidably arranged on the bottom plate, and a driving assembly for driving the two movable plates to move relatively is arranged on the bottom plate. A movable plate is arranged on the bottom plate, a fixing frame is connected to the movable plate, supporting rollers are connected to the fixing frame, roller shafts of the supporting rollers are arranged in the length direction of the bottom plate, the two supporting rollers are arranged on the fixing frame and are oppositely arranged in parallel, and a rotating assembly used for driving the two supporting rollers to rotate in the same direction is arranged on the fixing frame. The maintenance bracket has the effects that the maintenance bracket can support and rotate the aircraft engine, and the maintenance efficiency is improved.

The invention belongs to the technical field of aircraft maintenance and debugging, particularly relates to a force sensing calibration method for an aircraft throttle lever, and aims to solve the problems that an existing aircraft throttle lever force sensing calibration technology depends on manpower, and is low in efficiency, insufficient in precision and the like. The method comprises the following steps: generating a continuous force-position curve; identifying a positioning point in the force-position curve, and dividing the whole stroke into a positioning section and a smooth stroke section; calculating basic friction force and positioning retention force, and calculating deviation values of the basic friction force and the positioning retention force relative to target values; the method comprises the following steps: applying a test adjustment amount to an adjustment mechanism, measuring a generated cross variation, and constructing an influence coefficient matrix; and calculating an inverse matrix of the influence coefficient matrix, calculating a target physical adjustment amount in combination with the deviation amount, and driving the friction adjustment mechanism and the positioning adjustment mechanism to act simultaneously. According to the invention, the basic friction force and the positioning retention force are rapidly, accurately and synchronously adjusted, so that the calibration efficiency and precision are remarkably improved.

An auxiliary tool for oil bottom discharge of a main oil tank of a Boeing B737NG airplane relates to the technical field of airplane maintenance tools, a lift valve is driven by a lift valve driving mechanism to slide upwards in a containing cavity of an oil discharge pipe by utilizing a piston, a valve core of a water discharge valve is gradually opened when the lift valve moves upwards, fuel oil is discharged from the water discharge valve, and the oil bottom discharge of the main oil tank of the Boeing B737NG airplane is realized. Due to the fact that the piston isolates the long hole I from the long hole II, fuel oil enters the oil storage cavity of the lifting valve from the long hole I, then flows out from the long hole II and finally flows into an oil barrel to be stored through the connecting pipe and the hose. A worker does not need to use an oil drainage rod to always prop the water drainage valve in the oil drainage process, the oil drainage efficiency is improved, and manpower is saved.

The invention discloses an aircraft maintenance task allocation and scheduling method based on a cutting strategy and time constraint, and relates to the technical field of aviation maintenance management and operation planning optimization. The method comprises the following steps: determining a maintenance opportunity that each airplane stays on the ground and meets a maintenance resource condition according to a known flight timetable; according to the technical scheme, a mathematical heuristic solving algorithm is designed, a hybrid algorithm combining a constructive heuristic algorithm and an accurate solving technology is developed, an infeasible solution is dynamically repaired through two core processes of resource monitoring and airworthiness monitoring, and an approximate optimal solution is quickly found in a large-range search space; a maintenance task is decomposed into feasible parts through a cutting strategy to adapt to a limited time box, and the problem of infeasibility caused by resource conflicts is solved; and meanwhile, solving is performed through a mathematical heuristic algorithm, so that the total cost including direct maintenance cost and extra waste cost caused by advanced maintenance is minimized while the calculation efficiency is ensured.

The invention discloses a flexible telescopic platform capable of being automatically attached to the cambered surface of a fuselage, and relates to the technical field of aircraft overhaul, the flexible telescopic platform comprises a main body assembly, the main body assembly comprises an outer pipe, an inner pipe is slidably arranged in the outer pipe, wood plates are fixed on the outer pipe and the inner pipe, a motor is fixed in the outer pipe, and a lead screw is fixed at the output end of the motor; the lead screw is in threaded connection with the inner wall of the inner pipe. The device has the beneficial effects that the telescopic unit is jointly formed by the inner pipe, the outer pipe, the motor and the pressure sensor, during working, the motor drives the lead screw to rotate, the lead screw rotates in the inner pipe and can drive the inner pipe to independently stretch out or retract, and the inner pipe of the telescopic unit can adaptively adjust the stretching length according to the shape of the cambered surface of the aircraft body at the corresponding position; therefore, a gap between the platform and the fuselage is eliminated, a maintainer can conveniently approach each to-be-maintained area of the fuselage, and the maintenance efficiency is improved.

A method in an aircraft of using prognostic indicators for aircraft maintenance includes retrieving aircraft health data for a plurality of aircraft components wherein the aircraft health data includes at least one of mechanical systems condition indicator (CI) data, vibration spectrum data, resampled time-domain (RTD) data, and RTD spectrum data. The method includes estimating component health status information for the plurality of aircraft components using a plurality of prognostic modules wherein each prognostic module is configured to generate health status information for at least one of the aircraft components, the health status information includes at least one of a current health indicator and a prognostic indicator. The method also includes storing the component health status information for the aircraft components in a database onboard the aircraft, and causing the display of the health status information for the specific component on an aircraft display.

The utility model discloses an auxiliary lighting device for engine maintenance, which relates to the technical field of aircraft maintenance and comprises an auxiliary supporting seat inserted outside a rail column. According to the attachment assembly, the threaded locking mode of a traditional attachment clamp is reserved, and meanwhile, the use distance between the fixed supporting plate and the movable supporting plate can be rapidly adjusted and controlled, so that the function of rapidly adjusting and controlling the use distance between the fixed supporting plate and the movable supporting plate can be achieved; the attachment clamp can be quickly mounted and dismounted on attachment plate bodies with different thicknesses, the working efficiency is greatly improved, and the problems that the distance between two clamping plates of an attachment clamp of an existing lighting device is completely adjusted and controlled through threads, so that when the two clamping plates need large-span adjustment and control, the adjustment and control speed is low, and the adjustment and control efficiency is poor are solved. And the maintenance efficiency of the aircraft engine and accessories thereof is reduced.

The application relates to the technical field of aircraft maintenance, and particularly discloses a guide support structure for replacing large components of an aircraft, which comprises a vehicle body, a longitudinal support seat arranged on the vehicle body and capable of moving in the horizontal direction, a linkage operation adjusting mechanism arranged on the side wall of the longitudinal support seat and used for providing two-speed variable independent transmission power to the longitudinal support seat, a lifting mechanism capable of lifting and arranged on the longitudinal support seat, a rotatable holding frame arranged on the lifting mechanism and used for fixing an aircraft landing gear in a disassembled state, and lifting power of the lifting mechanism and rotating power of the holding frame are both from the longitudinal support seat. The guide support structure has the advantages of multi-degree-of-freedom adjustment in a limited space, high positioning precision and convenient operation, and can improve the safety and efficiency of the replacement operation of large components of the aircraft.

The invention discloses an AR image-based aircraft maintenance method, device and equipment and a storage medium, and the method comprises the steps: obtaining an aircraft maintenance task and a corresponding image collection requirement through an AR image collection terminal, collecting an aircraft maintenance image according to the aircraft maintenance task and the image collection requirement, and carrying out the image quality evaluation, the aircraft maintenance image with qualified image quality is uploaded to the cloud; and the cloud end adopts a preset large language model to perform anomaly detection of aircraft maintenance according to the aircraft maintenance image, generates a fault list and a maintenance rectification task if an anomaly exists, and archives the aircraft maintenance image to a database if the anomaly does not exist. According to the invention, the accuracy and efficiency of maintenance and inspection can be improved, and the quality of the retained image is ensured.

The application provides a method and device for converting maintenance intervals of an aircraft in low utilization, comprising the following steps: S1, obtaining an aircraft maintenance outline; S2, determining the number of months to be counted and counting the utilization of the aircraft; S3, predicting the low utilization of the aircraft; S4, converting the maintenance task intervals, including screening the maintenance tasks whose maintenance interval units are not calendar days; judging the importance of the maintenance tasks and performing conversion calculation of the maintenance task intervals; and S5, summarizing new maintenance tasks. The device comprises a database, an aircraft utilization counting module, a low utilization predicting module, a maintenance task converting module and a maintenance task output module, wherein the maintenance task converting module comprises a screening module, a weight module and a converting module. The application directly adopts the maintenance interval conversion method for unimportant maintenance tasks, reduces the number and complexity of reliability-centered maintenance analysis tasks, and can quickly obtain the maintenance tasks and their maintenance intervals under low utilization.

The invention discloses an aircraft maintenance monitoring early-warning analysis method and system based on image recognition. The method comprises the steps that an intelligent head-mounted camera device obtains video stream data of all inspection point positions of aircraft winding inspection work; the analysis and identification model divides the video stream data according to inspection point locations to form an inspection point location image data set containing a target detection frame; the improved YOLOv8 model comprises a backbone network, a neck network and an attention mechanism, the backbone network is used for acquiring a standard video stream database and checking multi-scale features of a point location image data set, the neck network performs multi-scale feature fusion, and the attention mechanism is used for capturing fine features and obtaining fused features; and the analysis identification model carries out key frame fusion feature and key frame time sequence information comparison on the check point image data set to obtain a monitoring analysis result. According to the invention, the image recognition technology and the maintenance business process are deeply fused, and dual monitoring of the component state and standard operation of winding inspection is realized.

The application relates to a body pit detection device and method based on point cloud data, which comprises the following modules: a point cloud acquisition module for acquiring body surface point cloud data; a point cloud processing module for carrying out point cloud processing on the body surface point cloud data; a point cloud reconstruction module for carrying out point cloud reconstruction to obtain a three-dimensional CAD model of the body surface; a target detection module for extracting body surface pit data to obtain pit information; a pit discrimination module for determining pit repairability based on the pit information to generate a body surface pit detection result and body repair position information; a result output module for outputting and displaying information; and a remote control module for information interaction with the point cloud acquisition module through a wireless communication mode. The application can be used for detecting and recording pit damage after impact on an aircraft body surface, can reduce the visual inspection workload of aircraft maintenance personnel, and can effectively improve detection accuracy.

The invention provides a test flight preparation-oriented aircraft maintenance electronic work card design and support method. The method comprises the steps of aircraft basic data preparation and management; test flight task list data preparation and association: based on the preprocessed aircraft basic information, importing or creating test flight task list information, and establishing an association mapping relationship between the aircraft basic information and a test flight task list; creating and configuring maintenance electronic work cards: creating multiple types of maintenance electronic work cards based on the basic information of the airplane and the test flight task requirements, configuring basic attributes for the various types of maintenance electronic work cards, and associating and binding the configured electronic work cards with corresponding task lists; work card task structured configuration: adding specific task items in the created electronic work card; data consistency and compatibility guarantee: establishing a data synchronization mechanism among the aircraft basic data, the test flight task list and the electronic work card; according to the invention, the risk of human errors is reduced, and the standardization and data traceability of test flight preparation work are guaranteed.

The utility model belongs to the technical field of aircraft maintenance, and discloses a gap measuring assembly, which comprises a reference piece and a measuring piece, the reference piece is provided with an arc surface, the arc surface is provided with scale marks extending along a first direction, and the measuring piece is arranged on the reference piece in a sliding manner along the first direction. The measuring piece is provided with a mark for pointing to the scale line, one end of the measuring piece in the first direction is provided with a measuring surface, the corresponding outer diameter of the measuring surface is gradually increased from one end away from the mark to one end close to the mark in the first direction, the arc surface is used for being in contact with one measured surface, and the measuring surface is used for being in contact with the other measured surface; the gap measuring assembly can measure the gap between the two measured surfaces, solves the problem that a traditional feeler gauge cannot measure the two measured surfaces which are curved surfaces, and is accurate and rapid in measurement and convenient to operate.