411 results about "Aircraft maintenance" patented technology

The invention discloses an ACM data analysis method and a data monitoring system, and belongs to the technical field of aircraft maintenance, and the method comprises the steps: constructing an ACM data set, setting a feature engineering processing method, carrying out coupling feature extraction through setting a dynamic window and calculating a dynamic correlation coefficient, dividing working conditions, eliminating fluctuation interference, and generating a structured time series data set; the method comprises the steps of obtaining ACM reference data of aircrafts of the same model, setting a reference fault judgment method, judging latest data in a structured time sequence data set, screening abnormal parameters, judging whether the ACM breaks down or not by combining an actual temperature adjusting effect, reducing single-parameter misjudgment, setting a coupling fault positioning method, diagnosing the faulty ACM, and distinguishing true faults and false anomalies. Meanwhile, a prediction scheduling method is set, fault prediction, health state prediction and service life evaluation are carried out on the fault-free ACM, the probability of sudden faults is reduced, and non-planned flight stopping is reduced.

The invention discloses grinding equipment with a surface self-adaption function for civil aircraft maintenance, and relates to the technical field of grinding equipment, the grinding equipment comprises a grinding mechanism, a self-adaption mechanism and a positioning mechanism, the grinding mechanism is fixedly connected with the self-adaption mechanism, and the self-adaption mechanism is fixedly connected with the positioning mechanism. The grinding mechanism is used for driving a grinding disc to work, and flexible grinding of the surfaces of different areas can be achieved. The self-adaptive mechanism is composed of a self-adaptive assembly, an expanding and contracting assembly and a rotating assembly, the grinding disc has the flexible adjusting capacity when making contact with the surface of a workpiece, the expanding and contracting assembly achieves expanding and contracting, the rotating assembly drives an expanding and contracting block to revolve, and therefore the adaptability of the grinding disc on the complex curved surface is guaranteed. And the positioning mechanism is used for positioning parts needing to be maintained, so that the purposes of adapting to complex curved surfaces, improving the polishing precision and efficiency, avoiding the problem of difficult attachment and ensuring the maintenance quality and the operation safety are achieved.

The invention discloses an aircraft intelligent maintenance and diagnosis system, and relates to the technical field of aircraft maintenance and diagnosis, and the system comprises a data collection module which is used for collecting various data in the actual operation of an aircraft. According to the invention, a digital twin model construction module is utilized to accurately simulate the operation state and fault condition of the aircraft, early discovery and accurate diagnosis of potential faults are realized, the pertinence and effectiveness of maintenance are improved, immersive fault experience and maintenance guidance are provided for maintenance personnel through fusion of VR / AR technologies, and the maintenance efficiency is improved. The maintenance accuracy and efficiency are improved, pre-diagnosis and maintenance scheme verification are carried out on the digital twin model, unnecessary disassembly and detection work is avoided, the maintenance time and labor cost are reduced, potential safety hazards can be eliminated in time through accurate fault diagnosis and an effective maintenance scheme, the flight safety of an aircraft is improved, and the safety of the aircraft is improved. And the maintenance scheme is comprehensively evaluated and optimized, so that the performance and the structural integrity of the maintained aircraft are ensured.

The invention discloses airplane wheel disassembly and assembly auxiliary equipment for civil aircraft maintenance, and relates to the technical field of tire maintenance devices.The airplane wheel disassembly and assembly auxiliary equipment comprises a traction frame body, a protruding part is inwards formed in the middle of the traction frame body, a first hydraulic jack is arranged on the protruding part, and a supporting frame is arranged at the output end of the first hydraulic jack; vertical supporting plates are arranged on the two sides of the supporting frame, combination plates are arranged on the vertical supporting plates on the two sides, transverse plates are arranged on the combination plates, supporting rods are symmetrically arranged on the transverse plates on the two sides respectively, and arc-shaped plates are arranged on the upper end faces of the supporting rods on the two sides. According to the lifting function of the airplane tire dismounting device, the airplane tire can be lifted upwards in the dismounting process, so that the gravity of the airplane tire cannot act on a fixing bolt, a user can conveniently take down the airplane tire, meanwhile, the airplane tire is rotated through cooperation of a groove-shaped structure, and therefore a worker can conveniently and rapidly maintain the state of the airplane tire.

The invention discloses an aircraft maintenance knowledge management and intelligent recommendation method based on a knowledge graph, and the method comprises the following steps: carrying out the multi-source collection of aircraft maintenance data, and carrying out the classification and coding of the maintenance data, extracting an entity and a type thereof by using a domain self-adaptive entity recognition model according to a splicing vector spliced by the classified coding data; constructing an entity co-occurrence graph according to the entities, performing relation extraction, attribute extraction and logic generation according to the entity co-occurrence graph, and constructing a knowledge graph according to the entities, the entity types, the entity relations, the entity attributes and the entity logic; aircraft fault problems, environmental conditions and maintenance preferences are manually input, and an aircraft fault maintenance scheme is intelligently recommended according to manual input and the knowledge graph; and carrying out resource conflict detection according to the recommended aircraft fault maintenance scheme, and regularly updating the knowledge graph. According to the intelligent maintenance recommendation method provided by the invention, the knowledge graph composed of multi-source maintenance data and multi-factor training are provided, and the accuracy of intelligent recommendation is improved.

The invention relates to a damage assessment method and device for a composite material structure and electronic equipment, and relates to the technical field of aircraft maintenance, and the method comprises the steps: obtaining an aircraft typical structure operation and maintenance database and an actual service environment database; extracting structure damage characteristics from the aircraft typical structure operation and maintenance database, and extracting service environment factor data of the aircraft from the actual service environment database; performing clustering analysis on the extracted service environment factor data to obtain a clustering analysis result, and performing correlation analysis on the extracted structure damage features and the clustering analysis result to obtain a correlation analysis result; and based on the correlation analysis result, constructing an evaluation index system, and performing damage evaluation on the composite material structure of the aircraft by using the evaluation index system. According to the scheme, various environmental factors and structural damage characteristics can be comprehensively considered, the service reliability and safety of the structure are evaluated more accurately, a more reliable basis is provided for structure maintenance decision, and potential risks for flight safety are reduced.

The utility model relates to the technical field of aircraft maintenance, and discloses a metal skin pit eliminating tool which comprises a shell, one end of the shell extends to form a connecting column, the connecting column is configured to be in transmission connection with a pneumatic riveter, and a mounting groove and a conical hole which are communicated are sequentially formed in the shell in the direction away from the connecting column. The shell is further provided with a first through hole communicating with the mounting groove in the radial direction of the shell. The core claw comprises an installation part and a plurality of contraction parts distributed at intervals, the installation part is correspondingly arranged in the installation groove, a second through hole is formed in the installation part in the radial direction of the shell, an elastic sleeve and a shaft pin are sequentially installed in the second through hole, and the two ends of the shaft pin extend out of the second through hole to be installed in the first through hole of the shell; the other end of the contraction part extends out of the shell in the radial direction of the shell to form abutting parts, and elastic washers are arranged between the abutting parts and the shell. The tool disclosed by the utility model can be used for effectively repairing the pit of the metal skin, and meanwhile, the damage to the metal skin is avoided.

The invention belongs to the field of automatic testing, and particularly relates to an automatic testing system and method for aviation fly-by-wire flight control equipment, and the system comprises a system self-inspection unit, a system resource unit, a system interface adaption unit, and a system testing control unit. And the system self-checking unit controls the automatic test system to execute a self-checking function through operation software. The test efficiency and the test coverage rate can be remarkably improved, the problem of function test omission can be effectively solved, the fault of the tested airborne avionics equipment is analyzed by adding the YMECA fault analysis module and combining the definition event and the structure function of the fault tree, qualitative analysis is carried out on the fault, a professional basis is provided for fault diagnosis, the maintenance difficulty is reduced, and the test efficiency is improved. The aircraft maintenance guarantee efficiency is improved, and joint test of a plurality of airborne avionics devices and parallel test of a plurality of airborne avionics devices of the same model in a fly-by-wire flight control system of a certain type of fighter can be realized.

The invention relates to a composite material structure damage probability assessment method and device and electronic equipment, and relates to the technical field of aircraft maintenance, and the method comprises the steps: obtaining the structure influence factor data of a to-be-assessed composite material structure; inputting the structure influence factor data into the trained random forest model, and performing damage probability evaluation processing on the to-be-evaluated composite material structure through all decision trees in the random forest model to generate an evaluation result; the evaluation results are subjected to voting processing, the evaluation result with the maximum voting number serves as a predicted structure damage evaluation result of the composite material structure to be evaluated, and the predicted structure damage evaluation result at least comprises slight damage, moderate damage and serious damage. According to the scheme, the limitation of a traditional method in the absence of sensor data is effectively overcome, and the damage prediction requirement under the condition of no sensor data or incomplete data is met.

The invention belongs to the field of aircraft maintenance, and particularly relates to a comprehensive maintenance management system for on-condition maintenance of an aero-engine. The system comprises a database used for storing historical data of an engine; the PHM module is used for generating engine state evaluation according to the engine state information and engine historical data; the RCM module is used for generating preventive maintenance suggestions according to historical data of the engine; the maintenance management unit is used for generating a maintenance decision according to engine historical data, engine state evaluation and preventive maintenance suggestions; the IETM module is used for calling a maintenance program or a troubleshooting program according to the maintenance decision, and is also used for generating maintenance resume information according to an engine maintenance result; the guarantee resource management module is used for generating guarantee resource information according to the maintenance decision; and the maintenance management unit is also used for generating maintenance evaluation information according to the maintenance decision, the maintenance resume information and the guarantee resource information, and updating historical data of the engine.

The invention discloses an aircraft surface damage three-dimensional positioning method, device and equipment, a medium and a product, and relates to the technical field of damage detection. The method comprises the steps of determining a damage detection result according to a target image based on a damage detection model; determining a three-dimensional coordinate of the damage point in a camera coordinate system by adopting a binocular vision positioning algorithm based on a pixel coordinate of a center point of a damage area contained in a damage detection result; based on the relative pose relation between the binocular camera and the aircraft, according to the three-dimensional coordinates of the damage point in the camera coordinate system, determining the three-dimensional coordinates of the damage point in the aircraft body coordinate system; and mapping the three-dimensional coordinates of the damage point in the aircraft body coordinate system to a three-dimensional point cloud model of the aircraft, and carrying out visualization processing to obtain a visualization display result. The invention aims to accurately determine the position of the damage on the aircraft body and improve the aircraft maintenance efficiency.

The invention relates to the technical field of aircraft maintenance, and particularly discloses a guide supporting structure for replacing large components of an aircraft. The longitudinal supporting seat can be movably arranged on the vehicle body in the horizontal direction; the linkage operation adjusting mechanism is arranged on the side wall of the longitudinal supporting seat and is used for providing two independent transmission powers with variable speeds for the longitudinal supporting seat; the lifting mechanism can be movably arranged on the longitudinal supporting seat in a sleeving mode in a lifting mode, the lifting mechanism is further provided with a rotatable retainer, the retainer is used for fixing an aircraft landing gear in a disassembly and assembly state, and lifting power of the lifting mechanism and rotating power of the retainer both come from the longitudinal supporting seat. According to the invention, multi-degree-of-freedom adjustment in a limited space is realized, and meanwhile, a guide supporting structure with high positioning precision and operation convenience is taken into account, so that the safety and efficiency of replacement operation of large components of an aircraft are improved.

A method for aircraft maintenance scheduling includes using a scheduling environment as a reinforcement learning (RL) environment to simulate an operational concept, train an RL agent, and generate aircraft maintenance decisions and explanations; providing a decomposed reward Deep Q-Network (drDQN) algorithm, wherein the drDQN algorithm includes a first Deep Q-Network (DQN) and a second DQN; using the first DQN to maximize a mission accomplishment objective; using the second DQN to minimize a maintenance cost objective; providing a trained drDQN agent; using the trained drDQN agent to obtain the aircraft maintenance decisions and corresponding mission accomplishment and maintenance cost rewards; using a scheduling module to arrange aircraft maintenance activities; and using an explainable module to get reasons to detail why the decisions are made and present tradeoffs between the decisions and non-selected alternatives.

The invention belongs to the technical field of aircraft maintenance, and particularly discloses aircraft maintenance belly skin dismounting and mounting equipment which comprises supporting levers arranged in pairs and moving wheels on the lower portions of the supporting levers, the two supporting levers are connected together through a plurality of bidirectional hydraulic rods, the bidirectional hydraulic rods are fixed to a middle lever, and telescopic hydraulic cylinders are arranged on the lower wall of the middle lever in an array mode. The lower end of the telescopic hydraulic cylinder is provided with a vacuum suction cup, supporting rods are arranged on the upper wall of the supporting lever in an array mode, the upper ends of the supporting rods are connected together through a transverse lever, lifting assemblies are arranged on the supporting lever and the transverse lever, self-matching adjusting assemblies are arranged on the lifting assemblies, and an automatic contour adapting assembly is arranged between every two opposite self-matching adjusting assemblies. The connecting blocks are sequentially connected through the curable connecting assemblies to form a chain-shaped structure, the chain-shaped structure is automatically attached to the surface of the airplane belly skin according to the shape of the airplane belly skin, fixing of the positions of the connecting blocks is automatically completed, and deformation of the airplane belly skin in the hoisting process is avoided.

The invention discloses a paint remover which comprises the following components in percentage by mass: 90-96% of a main solvent, 0-4% of a thickening agent, 0-5% of an accelerant and 0-4% of a corrosion inhibitor, and the thickening agent, the accelerant and the corrosion inhibitor are not zero at the same time; the main solvent comprises dichloromethane and benzyl alcohol; the mass ratio of dichloromethane to benzyl alcohol is (2-4): 1. Additives in the paint remover can be adjusted in a targeted mode according to soaking removal or brush coating removal to adapt to a construction mode, and a base material subjected to paint removal can be protected against the problem that the quality of secondary recoating is affected by pulverization, corrosion and the like. The main solvent in the paint remover is compounded, so that on one hand, a polyurethane polymer main chain can be solvated, and on the other hand, part of functional groups of the main chain can be permeated, so that volume swelling of the polymer main chain is replaced, and a coating is efficiently removed. The paint remover has great significance in airplane repair, airplane maintenance cost reduction and material utilization efficiency improvement, and is suitable for popularization and application.

The invention relates to the technical field of composite material digital detection, in particular to a composite material skin grinding amount calculation method based on clustering analysis and a symbolic distance field, which specifically comprises the following steps: acquiring three-dimensional measurement data of the surface of a composite material skin, and designing a three-dimensional measurement point feature descriptor; based on the feature descriptors, a clustering analysis algorithm is designed, and a grinding area three-dimensional measuring point class and a non-grinding area three-dimensional measuring point class are divided; aiming at the three-dimensional measuring points of the non-grinding area, carrying out implicit curved surface reconstruction based on a radial basis function; aiming at the three-dimensional measuring point of the grinding area, a grinding area symbol distance field is constructed, and the symbol distance is the grinding amount of the measuring point; according to the method, the problem that in the prior art, profile tolerance estimation cannot be obtained during aircraft CAD mathematical model is solved, the grinding allowance of the aircraft skin repairing area can be accurately analyzed, and aircraft maintenance personnel are guided to conduct grinding. Compared with a traditional method for judging the profile tolerance based on manual touch, the method has the advantages that interference of human subjective factors is eliminated, the grinding allowance is quantified, and the precision is higher.

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.

Systems, methods, and other embodiments described herein relate to developing a comprehensive set of rules for evaluating the health of an aircraft system. In one embodiment, a method includes receiving text from one or more sources. Each of the sources describes operation of at least a portion of a system. The method includes generating, using at least one natural language processing model, one or more sets of rules based on the text. The method includes generating, using at least one generative model, one or more formatted sets of rules based on at least the sets of rules, a relationship between the sets of rules, and a selected format. The method also includes outputting at least a portion of the formatted sets of rules to an aircraft maintenance system. The aircraft maintenance system is being operated based on at least the portion of the sets of formatted rules.

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 utility model discloses an aircraft landing gear installation assistive device, which relates to the technical field of aircraft maintenance equipment, and comprises a movable base, the right part of the top end of the movable base is fixedly connected with a fixed box, the left part of the bottom end of the movable base is fixedly connected with a support frame, and the top end of the fixed box is fixedly connected with a lifting mechanism. A clamping mechanism is fixedly connected to the left end of the lifting mechanism, a bearing mechanism is fixedly connected to an inner cavity of the supporting frame, and the lifting mechanism comprises a first motor and a mounting plate. According to the auxiliary installation tool for the aircraft landing gear, by starting the telescopic cylinder, the telescopic cylinder drives the bearing plate to rise upwards, the bearing plate slides on the outer wall of the second guide rod, the bearing plate is limited and guided through the second guide rod, the bearing plate is more stable in the moving process, the bottom of the aircraft landing gear is borne through the bearing plate, and the installation efficiency of the aircraft landing gear is improved. And the downward gravity borne by the clamping mechanism is reduced, so that clamping is more stable, and the bearing effect is achieved.

The invention discloses an aircraft maintenance scheme execution effect evaluation dynamic monitoring method. The method comprises the following steps: step 1, calculating monthly fault indexes before and after optimization of a maintenance scheme; 2, whether the two overall mean values are equal or not is checked, and distribution of differences of sample mean values of the two data sets before and after optimization of the maintenance scheme is given; step 3, obtaining a combined standard deviation of two data set samples before and after optimization of the maintenance scheme; and step 4, establishing an alarm value of the failure rate of the fleet system, i.e., determining the alarm value by calculating the standard deviation of the failure rate (x) of the fleet system per thousand flight hours in adjacent three months by using the flight hours in the past 14 months, the unit report failure and the ground maintenance discovery times. The invention belongs to the technical field of aircraft maintenance reliability evaluation and monitoring, and performs evaluation and dynamic monitoring on the maintenance scheme optimization effect of long-period maintenance data through reasonable classification and integration of maintenance data, setting of original hypothesis and inconsistent hypothesis and the like.

The invention relates to the technical field of radio testing, in particular to a radio comprehensive detector which comprises a main control part, an upper computer part and a radio frequency part. The main control part is composed of an MCU and an FPGA in a cooperative mode, the MCU communicates with an upper computer through a communication interface, and the FPGA is connected with the radio frequency part through a parallel bus and is provided with a PS mode program loading interface; the radio frequency part adopts a zero intermediate frequency software radio architecture and comprises a receiving channel and a transmitting channel; the upper computer part comprises a touch screen and is connected with the main control board through a communication interface, communication navigation signals of an airplane, a ship, a control tower and a satellite can be simulated, and function testing of 17 types of radio airborne equipment such as a short wave / ultra-short wave radio station, a microwave / instrument landing system and a radio altimeter is completed; the outfield maintenance targets of single-person carrying, single-person operation and single-person flying are achieved, and the universality, efficiency and environmental adaptability of maintenance are remarkably improved.

The invention relates to the field of aircraft maintenance, in particular to an intelligent aviation kerosene and bactericide mixed filling device which comprises a shell and an oil conveying pipeline, the oil conveying pipeline penetrates through the shell, and a fuel oil input connector and a fuel oil output connector are arranged at the two ends of the oil conveying pipeline correspondingly; the bactericide distribution bin is communicated with one end of the bactericide conveying pipeline, the other end of the bactericide conveying pipeline is inserted into the oil conveying pipeline and connected with a three-stage impeller with holes, the three-stage impeller with the holes and the oil conveying pipeline are coaxially arranged, and a fuel oil flow sensor is embedded in the oil conveying pipeline and used for detecting the oil amount in the oil conveying pipeline. An electromagnetic valve and an electromagnetic diaphragm metering pump are installed on the bactericide conveying pipeline, a controller is installed in the shell, the controller is electrically connected with the fuel flow sensor, the electromagnetic valve and the electromagnetic diaphragm metering pump, in the refueling process, kerosene and a bactericide can be intelligently controlled to be mixed, and the mixing effect is guaranteed.

The invention relates to the technical field of component measurement, in particular to auxiliary measurement equipment for aircraft maintenance and detection, which comprises a measurement table, a measurement positioning part, a detection part and a marking part, and is characterized in that the measurement positioning part is fixedly arranged at the top of the measurement table, the detection part is fixedly arranged at the top of the measurement table, and the marking part is fixedly arranged in the detection part; a PC control electric box is fixedly arranged at the bottom of the measuring table, and supporting legs are fixedly installed at the circle center of the bottom of the measuring table and used for supporting and fixing the auxiliary measuring equipment for aircraft maintenance and detection. The aircraft hub is positioned through the measurement positioning part, the measurement stability is guaranteed, the deformation position of the aircraft hub is accurately measured through the arranged detection part, meanwhile, the deformation of the aircraft hub can be measured through the detection part, and therefore a maintainer can know the deformation of the hub, and the maintenance efficiency of the maintainer is improved. And judging whether the hub meets the standard of maintenance and reuse or not.

The invention provides a civil aircraft fault information retrieval method and system based on a knowledge graph and vector retrieval. The method comprises the following steps: firstly, carrying out batch vectorization processing on knowledge in a knowledge graph library, and constructing a vector index library; after a user query is received, the system preprocesses the user query and extracts information by adopting a hybrid strategy: special codes are accurately matched and recognized through a dictionary, and meanwhile, natural language description is converted into query vectors by utilizing a deep semantic model. Then, the system executes two kinds of retrieval in parallel: one is structured graph query based on accurate information, and the other is semantic similarity search in a vector index database; and finally, performing intelligent fusion and sorting on results returned by the two kinds of retrieval. By combining the accuracy of structured query and the recall capability of vector retrieval, the problems of various expressions, fuzzy semantics and the like in civil aircraft fault information query are effectively solved, the accuracy and comprehensiveness of fault information retrieval are remarkably improved, and more accurate and efficient decision support is provided for aircraft maintenance personnel.

The invention relates to the technical field of aircraft maintenance project management, and discloses an aircraft defect accurate recording system and method, and the system comprises a data collection module, an image processing module, a feature processing module, a defect recognition module and a result output module. The data acquisition module comprises an image acquisition unit and an auxiliary information acquisition unit; the image processing module is used for preprocessing the surface image; the feature processing module is used for extracting target features; the target features are converted into feature vectors; an identification model is arranged in the defect identification module; the recognition model takes the feature vector as input, and takes the defect rate and the defect category as output; and the result output module is used for positioning a defect position and visually displaying and storing a defect analysis result according to the output result of the defect identification module and the corresponding feature vector. According to the method, defect feature analysis dimensions are diversified, defect information can be fully captured, the identification precision is high, and systematic intelligent management of aircraft defects can be realized.

The utility model relates to the field of aircraft maintenance, in particular to a vehicle for replacing aircraft wheels, which comprises mounting rods, the mounting rods are oppositely arranged, a lifting assembly for lifting the height of the vehicle wheels is arranged between the mounting rods, a fixing rod is further arranged between the mounting rods, a positioning column is arranged on the fixing rod, and the positioning column is arranged on the fixing rod. The positioning column is arranged to be telescopic, the installation height of the positioning column is consistent with the height of an airplane axle after being lifted, the positioning column can be arranged in an installation shaft of an airplane tire in a penetrating mode, and a universal locking wheel used for driving the installation rod to move is arranged at the bottom of the installation rod. According to the invention, the manpower consumed for replacing the aircraft tire can be reduced, and the aircraft tire replacement efficiency is improved.

The utility model discloses a handheld tool for aircraft maintenance, which comprises a shell and a motor, the motor is fixedly mounted in the shell, the output end of the motor is connected with a screwdriver blade through a connector, and a track is fixedly mounted on the outer surface of the shell. The screw driver has the advantages that the suction cup and the connecting rod are adopted, when the aircraft shell is overhauled and disassembled, the screw driver head can be inserted into a cutter groove of a screw cap of the aircraft shell, then the suction cup and the surface of the aircraft shell are adsorbed and fixed, the motor can be started to drive the screw driver head to rotate, and then a screw is disassembled; the connecting rod and the suction cup resist torsion generated during rotation, workers are prevented from slipping out of the hands, maintenance and disassembly by the workers are greatly facilitated, use convenience is improved, meanwhile, the characteristic that the surface of an airplane shell is smooth is utilized, the suction cup is adopted for fixing, mounting and disassembly are convenient, fixing stability is high, the workers do not need to tightly abut against the device vigorously, and use is convenient. The use is more flexible and labor-saving.

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.