205 results about "Aircraft manufacturing" patented technology

The invention relates to the technical field of aircraft manufacturing, and discloses an aircraft part production quality optimization method based on data analysis. The method comprises the following steps: collecting multi-process real-time processing parameters and quality inspection data of a production line, and generating a dynamic quality weight matrix according to a process parameter coupling degree; extracting process path difference characteristics of qualified products and unqualified products in historical batches, and encoding the process path difference characteristics as a quality evolution chain matched with adjacent process parameter mutation relevance; optimizing process parameters at a quality evaluation node, driving a parameter combination to iterate to minimize quality fluctuation, generating an adjustment amount, updating an evolution chain constraint coefficient, and synchronously constructing a stability evaluation function of a correlation weight matrix and a defect propagation path; triggering process compensation according to an adjustment amount gradient, and verifying the cohesion through a tolerance rule by taking a reference parameter matched with the target evolution chain as compensation data; and generating a feedback matrix by using the quality fluctuation index and the compensation result, and correcting the mapping relation between the weight matrix and the evolution chain.

The utility model discloses an engine nacelle, which is applied to the field of aircraft manufacturing, is used for improving the structural strength of an aircraft engine nacelle, and comprises a front firewall, a rear firewall, an upper firewall, a front section skin, a middle section skin, a rear section skin and a mounting frame, a second through hole is formed in the rear firewall; the upper firewall is arranged between the front firewall and the rear firewall, the front end of the upper firewall is connected with the front firewall, the rear end of the upper firewall is connected with the rear firewall, the mounting frame and the U-shaped reinforcing beam are both of a U-shaped structure and are both located on the front side of the front firewall, and the mounting frame is arranged above the U-shaped reinforcing beam; the rear end of a front-section lower wall plate of the front-section skin is connected with the U-shaped reinforcing beam; the front ends of a middle-section left wall plate, a middle-section right wall plate and a middle-section upper wall plate of the middle-section skin are connected with the mounting frame; and the outer sides of the upper firewall, the front firewall and the rear firewall are coated with the middle-section skin.

The invention belongs to the technical field of measurement and positioning, and particularly relates to an aircraft manufacturing measurement and positioning method, which deeply combines an interference networking measurement method and a space coordinate measurement method of a laser tracker, adopts interference networking to construct a global coordinate system # imgabs0 # by reference control TB points in a small amount of open space, and performs re-system by reference control TB points in an effective distance measurement range. According to the method, an expanded reference ERS point is expanded, a local expanded reference system # imgabs1 # is established to measure and position a local measurement object, the sequence and boundary of global measurement and local measurement in the measurement process according to size chain superposition are defined, and the method has high measurement precision.

The invention relates to the technical field of aircraft manufacturing, and discloses an aircraft component assembly and connection technological procedure compiling method and system and a storage medium, and the method comprises the steps: firstly constructing an aircraft component assembly and connection technological procedure template and an aircraft component assembly and connection technological parameter library according to aircraft component assembly and connection technological requirements and technological processes; then, according to key conditions influencing the process procedure of the aircraft component assembly and connection process procedure template, connection process parameters are obtained; and finally, according to the assembly digital-analog information and the call-in connection process parameters, filling the aircraft component assembly connection process procedure template to complete the compiling of the aircraft component assembly connection process procedure, so that the efficient and accurate compiling of the aircraft component assembly connection process procedure is realized, and the problem that in the prior art, the compiling efficiency is high is solved. The technical problems of low process procedure compiling efficiency and poor accuracy of aircraft component assembly connection exist in the prior art.

The invention relates to the technical field of aircraft manufacturing process equipment, in particular to an intelligent shape maintaining tool and method for a butt joint face of an aircraft fuselage, and is suitable for shape maintaining of the aircraft fuselage in the hoisting and assembling process, especially in the three-section butt joint process. The core of the tool is a machine body butt joint surface stress monitoring system composed of force sensors and a passive control system composed of servo electric push rods. The shape maintaining tool is composed of a shape maintaining frame, an inner shape clamping plate, a force sensor and a servo electric push rod, the force sensor is fixed to the inner shape clamping plate and makes direct contact with the inner side of the machine body to monitor the stress state of the butt joint face, the bottom of the servo electric push rod is connected with the shape maintaining frame, and the top of the servo electric push rod is connected with the clamping plate to adjust the stress state of the butt joint face. The problem that a traditional shape maintaining tool cannot achieve self-sensing and self-control is solved, the requirements for high precision and low stress of aircraft fuselage assembly are met, and the fuselage assembly quality is remarkably improved.

The invention discloses an adjusting device and aircraft landing gear auxiliary mounting equipment, and relates to the technical field of aircraft manufacturing equipment.The adjusting device comprises a first adjusting mechanism, a second adjusting mechanism, a fixing mechanism and a driving mechanism; the first adjusting mechanism is provided with a first seat body; the second adjusting mechanism is provided with a second seat body and a third seat body, the second seat body is rotatably mounted on the first seat body along the axis in the vertical direction, and the third seat body is rotatably mounted on the second seat body along the axis in the left-right direction; the fixing mechanism is mounted on the third seat body and is used for being fixedly connected with an aircraft landing gear; and the driving mechanism is in driving connection with the second seat body and the third seat body so as to adjust the position and the posture of the fixing mechanism in the space. According to the technical scheme provided by the invention, the technical effect of adjusting the attitude of the aircraft landing gear is achieved through the second seat body and the third seat body which are rotationally arranged.

The invention relates to the technical field of aircraft manufacturing, and discloses a detailed process design method and system for aircraft component assembly and a medium, and the method comprises the steps: building a process procedure template corresponding to an assembly scene according to an assembly process flow and a standard process library; according to the method, technological procedure node planning and technological procedure material planning are carried out from the two dimensions of assembling scene space and time, a technological parameter library is established according to technological knowledge and technological rules, and finally technological procedure document compiling is automatically carried out, so that the detailed airplane component assembling technology is efficiently and accurately designed, and the design efficiency is improved. The technical problems that according to existing aircraft assembly technology design, technological procedure compiling is not combined with the assembly technological process, the technological procedure compiling efficiency is low, and the technological procedure compiling accuracy is low are solved.

The invention discloses an aircraft manufacturing-oriented cluster robot cross-view collaborative sensing method and system, and the method comprises the steps: building a multi-robot collaborative sensing platform, collecting large-range three-dimensional point cloud data through a laser radar, and obtaining the poses of robots in real time in combination with a motion capture system; constructing a collaborative detection data set comprising a training set, a verification set and a test set; a point cloud collaborative three-dimensional detection model based on cross-view-angle consistency space mapping is innovatively designed, three core modules of multi-agent feature extraction, cross-view-angle feature fusion and cross-view-angle consistency-difference feature reconstruction are included, multi-robot perception collaboration is achieved through hierarchical feature interaction, model parameters are optimized by adopting a joint loss function, and multi-robot perception collaboration is achieved. And finally, verifying the effectiveness and generalization ability of the method in a complex industrial scene on a verification set and a test set, and carrying out platform deployment. The adaptive capacity and expression integrity of the system to a complex structure environment are improved, and multi-agent collaborative perception is more efficient and reliable.

The invention discloses a civil aircraft cable laying quality evaluation method and system based on a 3D scanning reconstruction technology. The quality evaluation method comprises the following steps: 1) data acquisition; 2) cable segmentation; 3) performing three-dimensional reconstruction; 4) calculating parameters; 5) quality evaluation; and 6) performing man-machine interaction. According to the method, a computer vision technology and a three-dimensional reconstruction method are combined, and a high-precision, high-efficiency, objective and consistent solution is provided for cabin cable laying quality evaluation, so that the quality and efficiency of aircraft manufacturing are improved, and a more reliable guarantee is provided for aviation safety.

The utility model discloses an adjustable inclined support for an aircraft fixture, which relates to the technical field of aircraft manufacturing and comprises a base, hydraulic cylinders are fixedly connected to the periphery of the top of the base, a second rotating rod is movably connected to the middle end of the top of the base, and a second driven gear is fixedly connected to the upper end of the outer surface of the second rotating rod. Multi-degree-of-freedom and composite adjustment is achieved, the four hydraulic cylinders acting independently can achieve overall lifting and horizontal leveling of the support platform, stable supporting is provided for an aircraft fixture, a second motor drives a second driving gear to drive a second driven gear and a third supporting plate to rotate with a second rotating rod as the center, and the second rotating rod is driven to rotate. And a third motor drives a worm to be meshed with a deflection block with teeth, the deflection seat is driven to achieve accurate pitching angle deflection adjustment, deflection of the deflection seat can be accurately adjusted, and angle adjustment of the aircraft fixture in different directions can be completed through rotation and deflection matching.

The utility model discloses a curved surface compensation mounting fixture for an aircraft fixture, which relates to the technical field of aircraft manufacturing, and comprises a bottom plate, the left end and the right end of the top of the bottom plate are fixedly connected with clamping components, the top of the bottom plate is fixedly connected with a plurality of groups of first hydraulic cylinders, and the telescopic ends of the first hydraulic cylinders are rotatably provided with rotating frames; a first rotating shaft is movably connected to the surface of the rotating frame, an adjusting block is fixedly connected to the inner side of the first rotating shaft, a connecting plate is fixedly connected to the top of the adjusting block, a second hydraulic cylinder is fixedly connected to the middle end of the top of the connecting plate, and an inner supporting block is fixedly connected to the telescopic end of the second hydraulic cylinder; a plurality of annularly-distributed supporting columns are fixedly connected to the outer side of the top of the connecting plate. The multi-degree-of-freedom adjusting device can be adjusted in a multi-degree-of-freedom mode, corresponding adjustment of the position and the posture of the aircraft fixture is achieved through stretching and retracting of the first hydraulic cylinder, horizontal rotation of the rotating frame and free deflection of the adjusting block, and the aircraft fixture can be rapidly supported.

The invention discloses a stringer assembly, a stiffened wall plate, a stiffened wall plate assembling method and an aircraft, and belongs to the technical field of aircraft manufacturing. The stringer assembly comprises a cap-shaped stringer and a forming die, the cap-shaped stringer comprises a stringer main body and a lap joint part, the stringer main body extends in the first direction and is provided with a cavity, the forming die comprises a containing part extending in the first direction, the containing part is provided with a containing groove, and the lap joint part is provided with a lap joint part. The containing groove extends in the first direction and is opened in one side of the second direction, the containing groove and the opening of the cavity face the same direction, the stringer body penetrates through the opening of the containing groove and is installed in the containing groove, the end, in the first direction, of the containing groove is closed, and the lap joint part is in lap joint with the forming mold. The cap-shaped stringer is blocked by the closed end of the containing groove of the containing part, it is guaranteed that the cap-shaped stringer cannot penetrate through the containing part and pass through the net size area in the skin, the influence on the surface quality of the skin is reduced, and the forming die cost is reduced.

The invention relates to the technical field of aircraft manufacturing, and discloses a part model cross-BOM tracing method and system based on a global identifier and a medium, which are used for recording and tracing data formed in a process procedure planning and compiling process, and comprise the following steps: constructing part model metadata for each part model, defining a normal form of part model metadata; storing data formed in the process of programming the technological procedure into part model metadata; constructing a graph network of the part model metadata according to the logical relationship between the part model metadata; and adopting a graph traversal algorithm to trace the full life cycle process data of the part model in the graph network. According to the method, part model metadata is constructed for each part model, data formed in the process of planning and compiling the technological procedure is recorded according to the part model metadata, a graph network is established based on the part model metadata, and tracing of the whole life cycle of the data is achieved.

The invention relates to the technical field of aircraft manufacturing, and discloses a design method and system for an aircraft assembly technological procedure template and a storage medium. According to the method, the assembly type, the technological procedure template type and the process type of aircraft assembly and key conditions influencing the process appearance are analyzed from the essential angle of assembly; logic rules of key conditions influencing process contents are combed, and process procedure contents with fixed rules are presented in a process procedure template in a certain structural form and hierarchical relationship, so that rapid compiling of aircraft assembly process procedures is realized, and a final complete process procedure document is formed; the technical problems that technological procedure compiling is not combined with the assembly technological process, the technological procedure compiling efficiency is low, and the technological procedure compiling accuracy is low are solved.

The present application belongs to the technical field of aircraft manufacturing, and discloses a flexible pressure-adjustable blank holder loading drawing die and a use method thereof. The drawing die comprises a female die, a blank holder and a male die. The female die surface is partially matched with the outer surface of a part. The upper surface of the blank holder is provided with a sunken surface matched with the shape of an expanded blank. The working surface of the male die is matched with the lower surface of the inner side area of the root fillet of the part. The female die and the blank holder tightly press the adjustable pressure fluid medium on the upper surface of the expanded blank, and the part is drawn and formed on the male die. The technical problem of concentrated pressure loading and mutual contradiction of traditional drawing and loading is overcome. The fluid medium flexible blank holder mode is adopted, the female die and the flange edge of the part are not in contact and friction, and the die bearing deformation does not affect the uniformity of the blank holder load. The present application has the advantages of good lubrication effect, low die processing cost, strong technical universality and the like.

The utility model belongs to the technical field of aircraft manufacturing and assembling, and particularly relates to a split type self-contraction skin tensioner. The device is composed of a coil spring assembly and a tensioner connecting assembly. The coil spring assembly is composed of a coil spring support, a coil spring, a center shaft and a stop pin, the coil spring support is fixed to the tool framework, self-contraction of the tensioner mainly depends on the automatic reset function of the coil spring, the tensioning belt is wound around the coil spring and rotates around the center shaft, and rotation limiting is achieved at the end of the center shaft through the stop pin; the coil spring is connected with the tensioner connecting assembly through a tensioning belt; the tensioner connecting assembly is composed of a bottom support, a stop plate button, a tensioning wrench, a rotating shaft, a butterfly piece, a torsion spring, a ratchet wheel, an upper baffle, a lower baffle, a compression spring, a center shaft, a stop pin, a tensioning belt and a stop plate. By the adoption of the coil spring device, the self-contraction function can be achieved, and the problem that the tensioning belt is inconvenient to store is solved.

This invention relates to the field of aircraft manufacturing and maintenance technology, and in particular to a rapid identification fixture for aircraft connector parts. The fixture includes a worktable and an identification structure. The identification structure includes a connecting fixing plate, a reference positioning plate, a connecting positioning component, a first movable slider, and a first identification component. When using this rapid identification fixture to identify aircraft connector parts, the aircraft connector part to be identified is fixed to the connecting fixing plate by the connecting positioning component. Using the reference positioning plate and the connecting positioning component as a reference, the first movable slider is moved along the length of the first sliding groove until it contacts one corner surface of the aircraft connector part to be identified. The aircraft connector part is identified based on the distance between the first movable slider and the reference positioning plate at this point. This significantly improves the identification efficiency of aircraft connector parts and reduces the identification cost.

The present application relates to the field of aircraft manufacturing equipment, in particular to an aircraft section butt joint device, which comprises a fixed section support mechanism and a butt joint section support mechanism, at least one of the fixed section support mechanism and the butt joint section support mechanism is provided with a moving support device capable of moving along the section axial direction to the other, and at least one of the fixed section support mechanism and the butt joint section support mechanism is provided with a rotating support device capable of driving the corresponding section to rotate. In use, when the sections to be connected are centered, the moving support device can be used to drive the sections to move close to each other, and the rotating support device can be used to drive the sections to be screwed to each other, so as to realize the butt joint of the threaded connection sections, and solve the problem that the existing section butt joint device cannot realize the butt joint between the threaded connection sections.

The invention discloses a teaching interaction method, a cloud server and an aircraft, and the teaching interaction method is applied to the cloud server, and comprises the steps: responding to the received preset information, obtaining the inspection list teaching data corresponding to the preset information according to a preset rule, and the preset information comprises an interaction request and / or the operation data of the aircraft; the inspection list teaching data comprises an inspection task of an aircraft, safety and operation standards of an operator, design specifications of an aircraft manufacturer and industrial standards; sending the checklist teaching data to a user side to control the user side to display the checklist teaching data; and receiving an interaction result of the user side for the checklist teaching data, and making a response. Therefore, according to the technical scheme of the invention, a teaching training mode with high flexibility and low cost can be provided, so that the use training of the aircraft checklist can be better realized.

The invention belongs to the technical field of aircraft manufacturing, and discloses a separated double-sided energy conducting rib and a preparation method of the energy conducting rib, the separated double-sided energy conducting rib comprises a base plate and energy gathering structures, the two sides of the base plate in the first direction are each provided with a plurality of energy gathering structures distributed at intervals, each energy gathering structure is a pyramid boss, the edge apex angle of each pyramid boss is alpha, and the edge apex angle of each pyramid boss is alpha; and alpha is not less than 60 degrees and not more than 120 degrees. According to the ultrasonic welding device, the energy gathering structures are arranged on the two sides of the base plate, so that during ultrasonic welding operation, the surfaces of welding workpieces on the upper side and the lower side can be started at the same time, the uniformity of a welding area is improved, the strength of a welding interface is improved, and the energy gathering structures are pyramid bosses, so that the focusing effect is enhanced; by limiting the edge apex angle alpha, on one hand, excessive focusing and too fast temperature rise caused by too small edge apex angle are avoided, and on the other hand, unobvious focusing effect, slow melting speed, prolonged welding time and reduced welding efficiency caused by too large edge apex angle are avoided.

The application relates to the technical field of aircraft manufacturing, and discloses a skeleton process procedure planning method and system based on clustering and a storage medium, which comprises the following steps: constructing a skeleton part set and setting an assembly threshold and a distance threshold used for classifying skeleton parts; obtaining the centroid coordinates of each skeleton part in the skeleton part set; randomly selecting the centroid of k skeleton parts from the skeleton part set to form k clusters; distributing the skeleton parts into the k clusters to form k cluster part subsets; obtaining the centroid coordinates of each cluster part subset; calculating the contour coefficients of the skeleton parts, obtaining the skeleton part with the largest distance in the corresponding cluster part subset, and distributing the skeleton part into the cluster part subset with the smallest distance to the skeleton part, so that the classification of the skeleton parts is completed. The application classifies and groups the skeleton parts by using a clustering algorithm based on the centroid coordinates of the skeleton parts in an MBD numerical model, and solves the problems of low classification efficiency and low accuracy during skeleton process procedure planning.

The utility model relates to aircraft manufacturing and welding auxiliary equipment technical field especially, a bogie welding fixing device, including base, its bottom is provided with the mobile wheel of being convenient for device integral movement, the rotary seat is set up on the surface of base through the rotation structure, can rotate in horizontal direction relative to the base, the utility model discloses through the integral flexible movement of bottom mobile wheel, has solved bogie transfer problem, with the multidirectional adjustment of slider and connecting arm, can adapt to complex structure bogie such as arc, corner, cooperation 'U' clamping arm and the clamping block of two -way screw rod drive, can steady clamping bogie, need not manual support, and through the rotary seat of motor drive and the support rod of worm and worm wheel drive, can accurately adjust the horizontal rotation and inclination angle of bogie, ensure its to be welded position accurate docking aircraft fuselage, effectively promote the welding precision and efficiency.

Techniques for aircraft manufacture and product support are described. These techniques include providing a three-dimensional (3D) user interface for an aircraft and identifying a component relating to an area of concern for the aircraft, based on input to the 3D user interface. The techniques further include generating structured text for a service request relating to the area of concern based on the identified component, and submitting the service request to facilitate resolving the area of concern for the aircraft.

An aircraft engine nacelle mounting section belongs to the technical field of aircraft manufacturing and is used for improving the structural strength of the mounting section. Comprising a mounting frame and a pull rod system, the pull rod system comprises seven joints, a left lifting point lower pull rod, a left lifting point upper pull rod, an upper lifting point left pull rod, an upper lifting point right pull rod, a right lifting point lower pull rod and a right lifting point upper pull rod; wherein the first connector, the second connector and the third connector are arranged on the mounting frame, the fourth connector is located behind the first connector, the fifth connector is located above the fourth connector, the seventh connector is located behind the third connector, and the sixth connector is located above the seventh connector; a left lifting point lower pull rod is connected between the first joint and the fourth joint, and a left lifting point upper pull rod is connected between the first joint and the fifth joint; an upper lifting point left pull rod is connected between the second joint and the fifth joint, and an upper lifting point right pull rod is connected between the second joint and the sixth joint; a right lifting point upper pull rod is connected between the third connector and the sixth connector, and a right lifting point lower pull rod is connected between the third connector and the seventh connector.

This application relates to a method and apparatus for converting the inner and outer sides of an aircraft super panel, belonging to the technical field of large aircraft manufacturing. The apparatus includes an inner panel tooling, a conversion component, and an outer panel tooling. The inner panel tooling includes two parallel tracks and multiple panel mounting brackets located in the track mounting area. The conversion component is located in the transfer area of ​​the tracks and on the outside of the two tracks. The outer panel tooling includes a transfer fixing bracket connected to the top of the conversion component and multiple panel transfer brackets located below the transfer fixing bracket. This application replaces the support column structure surrounding the inner panel tooling in the traditional technology by setting two parallel tracks in the inner panel tooling and integrating the conversion component in the transfer area outside the tracks. This modular layout eliminates the need to reserve additional support device installation space around the tooling, allowing the conversion area of ​​the inner and outer panel tooling to be concentrated within the effective working range of the track extension, saving 30%-50% of the ground area compared to the prior art.

The utility model belongs to the technical field of aircraft manufacturing, and particularly relates to a horizontal tail co-curing forming die which is characterized in that when the horizontal tail co-curing forming die is used, firstly, a skin is laid on a die molded surface, then a beam forming mechanism is installed on the die molded surface, prepreg is laid in the beam forming mechanism, and then the prepreg is formed. And then the rib forming mechanism where the prepreg is laid in advance is fed into the beam forming mechanism and fixed, a vacuum bag is pasted on the outer side of the whole mold and vacuumized, the mold is fed into an autoclave to be cured, demolding is conducted after curing is completed, and the horizontal tail component can be obtained. The horizontal tail component manufactured through the die is formed in a co-curing mode, the components of the horizontal tail do not need to be secondarily connected in a glue joint and / or bolt connection mode, and the structural weight of the horizontal tail is effectively reduced.

This application relates to an integrated automatic clamping and riveting mechanism, belonging to the fields of aircraft manufacturing and automatic drilling and riveting technology. Utilizing the technical characteristics of compressed air within a pneumatic structure, it can buffer changes in clamping force during the riveting process, thereby ensuring stable clamping force during the riveting movement. A single displacement sensor enables multifunctional data acquisition, including recording the clamping thickness and the height of the riveted object, saving costs and reducing the burden on the data acquisition system.

The present application relates to the field of aircraft manufacturing production management and control, and particularly relates to an aviation assembly manufacturing process data verification method and device based on image recognition. The method comprises the following steps: firstly, binding the position information and the camera information to obtain the video data of the production site; secondly, pulling the streaming media data from the video data, intercepting the real-time position map according to a fixed period, and marking the real-time position map; further, pre-processing and calculating the pre-acquired empty position map and the real-time position map to determine the position state; finally, binding the real-time position map with the corresponding position information in the MES, obtaining the aircraft physical flow information after processing, and comparing and fusing the physical flow information with the information flow data in the MES. The present application can accurately determine the working time of the aircraft at each position, realize the consistency of the physical flow and the information flow, and provide strong support for the precise management and control of the whole life cycle of the aircraft manufacturing.

The utility model relates to the technical field of aircraft manufacturing, in particular to a power switching mechanism. The power switching mechanism comprises a driving shaft, a driven shaft, a telescopic assembly, a universal switching assembly and a locking assembly, the input end of the driving shaft and the output end of the electric drill body are coaxially fixed, the output end of the driven shaft and the output end of the electric drill bit are coaxially fixed, and the telescopic assembly can stretch out and draw back in the axial direction of the telescopic assembly. The universal adapter assembly comprises two universal adapter connectors, any one of the two universal adapter connectors is connected with the output end of the driving shaft and one axial end of the telescopic assembly, the other universal adapter connector is connected with the input end of the driven shaft and the other axial end of the telescopic assembly, and the locking assembly is rotationally connected with the driving shaft and the driven shaft. The locking assembly is switched between the movable state and the fixed state, the locking assembly in the movable state freely adjusts the relative position of the driving shaft and the driven shaft, the locking assembly in the fixed state relatively fixes the driving shaft and the driven shaft, and various machining requirements are met.

The invention discloses an engine body manufacturing process procedure planning method and system based on material distribution, a medium and equipment, and belongs to the technical field of engine body manufacturing assembly. A mapping model among an assembly scene, a process procedure template and a process procedure material is established; constructing a part assembly relation graph, and identifying an assembly relation; all materials of the product are divided into different material ranges according to assembly scenes; dividing a material range to obtain a plurality of minimum assembly units, and establishing a mapping model of all materials of the product and internal materials of the minimum assembly units; the assembly sequence of the minimum assembly units and the assembly sequence of the corresponding technological procedure nodes are planned; and establishing a mapping model among the minimum assembly unit, the technological procedure template and the technological procedure nodes, and distributing materials in the minimum assembly unit to the corresponding technological procedure nodes to realize technological procedure planning based on material distribution. According to the method, the to-be-assembled materials can be quickly, accurately and completely planned according to a certain sequence, and the planning efficiency and quality of the assembly process procedure are remarkably improved.