239 results about "Aircraft maintenance" patented technology

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 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 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 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.

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.

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 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 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 invention relates to the technical field of aircraft maintenance equipment, and discloses a jacking tool for aircraft maintenance, a limiting assembly is arranged on a jacking assembly, and the limiting assembly is used for clamping an undercarriage of a manned aircraft; the safety assembly is arranged on the inner side of the base and used for limiting the jacking assembly. Limiting of the other end of the second supporting arm can be relieved by pulling the first pull rod upwards to move, in the process that the other end of the second supporting arm resets and moves, the rotating base drives the first pull rod to move in the long through groove through the rotating shaft, and when the other end of the first pull rod abuts against the inner side inclined face of the guide groove, the first pull rod moves downwards; when the other end of the first pull rod is lower than the horizontal plane, the first tension spring drives the first pull rod to reset, so that one end of the first pull rod drives the limiting column to move and abut against the limiting toothed plate through the rotating shaft and the connecting frame, and therefore the device can be conveniently limited when used next time, and the using safety of the device can be guaranteed.

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.

The invention discloses a lifting steering device and a screwing detection device applied to the lifting steering device and used for aircraft maintenance, the lifting steering device comprises a base, a threaded cavity is formed in 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 lifting rod is connected with the screwing detection device. The threaded block is meshed with the inner wall of the threaded cavity through threads; a first driving wheel is mounted at the upper end part of the lifting rod, 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 gear motor is installed on the conversion box, the second driving gear motor is in power connection with a first bevel gear, 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 can be realized in the equipment, so that the working end of the device reaches a construction area which is difficult to touch for 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.

A detection tool for an aircraft axle jack relates to the technical field of aircraft maintenance, a piston rod of the aircraft axle jack is driven to extend outwards until the head end of the piston rod of the aircraft axle jack is in contact with a top, an axial pressure value generated by the aircraft axle jack is acquired in real time through a force sensor I, and the aircraft axle jack is continuously loaded; and the test load is reached. A radial force is applied to the head end of the piston rod of the aircraft axle jack through the radial force application mechanism, and a radial pressure value generated by the radial force application mechanism to the head end of the piston rod of the aircraft axle jack is obtained in real time through the force sensor II until a radial test load is reached.

The utility model relates to the technical field of aircraft maintenance, and discloses an aircraft audio control panel knob dismounting tool which comprises two handles, the middle parts of the two handles are rotationally connected with each other, the end parts of the two handles are respectively provided with a clamping part, and the opposite surfaces of the two clamping parts are respectively provided with a cavity; when the two handles rotate towards the inner side, the end faces of the two clamping parts abut against each other, so that the two cavities form a clamping space used for clamping the knob. According to the technical scheme, the technical problem that a rotary knob in the prior art is not easy to disassemble and easy to damage is solved.

The utility model provides an aircraft skin patching and repairing training device, which belongs to the technical field of aircraft maintenance and comprises an operation platform and a simulated skin structure. The simulated skin structure is designed according to a skin structure needing to be simulated and reduced and fixedly installed on the operation platform, a patching area is arranged on the simulated skin structure, and the shape of the patching area 3 is set according to the skin damage type needing to be simulated. According to the utility model, simulation reduction can be carried out according to different damage states of skin subjected to patching training, under-machine training opportunities are provided for operators, on-machine skin patching repair is simulated, and the influence of factors such as limited on-machine operation is avoided, so that operations such as patching and riveting in different states are mastered skillfully, and the operation level is improved.

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.

The utility model provides an aircraft fuel generator control simulation device, and belongs to the technical field of aircraft maintenance. In order to solve the problems that the aircraft fuel generator control simulation device is high in cost and inconvenient to maintain, the aircraft fuel generator control simulation device comprises a box body and a plurality of control parts, the top of the box body is open, and a sliding mechanism, a mounting plate, a locking part and a data acquisition plate are further arranged in the box body; one end of each control piece is connected with the mounting plate, the other end of each control piece is connected with the data acquisition plate, and operation parts of the control pieces extend out of the mounting plate; the sliding mechanism can drive the mounting plate to ascend and descend relative to the box body bottom plate so as to cover the top opening of the box body or extend out of the top opening of the box body. The plurality of control pieces are connected with the mounting plate and the data acquisition plate, and the mounting plate, the plurality of control pieces and the data acquisition plate are driven by the sliding mechanism to integrally move in and out of the box body, so that the structure and the circuit are simplified, the cost is reduced, and the maintenance is convenient.

The utility model discloses a dismounting device for an aircraft fuel filter, which relates to the technical field of aircraft maintenance tools, and comprises a guide rod, a sliding weight block, an elastic piece, a connecting piece and a hook piece, one end of the guide rod is provided with a first limiting block, and the other end of the guide rod is connected with a second limiting block; the sliding weight block is arranged between the first limiting block and the second limiting block and can slide relative to the guide rod; the elastic piece is arranged on the guide rod in a sleeving mode and arranged between the sliding weight block and the second limiting block. The connecting piece is detachably connected to the guide rod and arranged on the side, away from the first limiting block, of the second limiting block. The hook piece is detachably connected to the connecting piece and used for hooking a handle of the fuel filter. According to the dismounting device, through mutual cooperation of the guide rod, the sliding weight block and the hook piece, the sliding weight block impacts the first limiting block, the fuel filter can be gradually withdrawn from the fuel hole, and thus dismounting of the fuel filter is completed.

The present disclosure relates to a blanking cap for closing an aircraft interface during aircraft maintenance, the blanking cap having a profile capable of forming an interference fit with the aircraft interface, comprising a main body having a solid structure, at least two through holes formed in the interior of the main body substantially in the extension direction of the main body, and at least one handle, the main body is provided with a first end face and a second end face which are oppositely arranged in the extending direction of the main body, the through holes are opened in the first end face and the second end face respectively, and the handle is formed in the mode that a pull rope sequentially penetrates through the two through holes to form a closed ring. The blanking cap can be widely applied to aircrafts of various models, is wide in application range, high in adaptability, convenient to use, good in effect and diversified in selectable materials, facilitates cost reduction and efficiency improvement, effectively solves the problem that the blanking cap is prone to damage and failure, and effectively prolongs the service life.

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 present application relates to the technical field of aircraft maintenance cleaning, and provides an aircraft surface salt removal and prevention cleaning agent and a cleaning method, the cleaning agent comprising the following components in percentage by mass: 0-30% of glycerol, 15-30% of a composite metal protective agent and 2-5% of an anti-salt protective agent, and the balance being distilled water, the composite metal protective agent comprising organic amine, organic acid, ethoxylated phosphate ester and benzotriazole, and the anti-salt protective agent comprising polydimethylsilane emulsion and potassium ferrocyanide; the cleaning agent effectively avoids the corrosion of salt water solution on the aircraft body material, especially metal material and metal plating, during the cleaning process, has good corrosion protection effect, and through the steps of rinsing and air drying or wiping, a protective film can be formed on the surface of the aircraft body, the crystallization of chlorides on the surface of the aircraft body is destroyed, the adhesion is reduced, the re-salting speed is effectively slowed down, and the cleaning agent is especially suitable for the salt removal and maintenance cleaning of military shipboard aircraft and near-shore military aircraft which are exposed to high-salt marine environment for a long time and have long-time low-altitude flight during flight.