333 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 invention belongs to the field of robot collaborative three-dimensional sensing in a large-range manufacturing scene, and particularly relates to a multi-robot collaborative three-dimensional target detection method based on a visual state space model, which comprises the following steps: building a multi-robot laser radar three-dimensional sensing platform, and collecting three-dimensional point cloud data in an aircraft manufacturing and assembling large-range scene; performing data labeling on the acquired three-dimensional point cloud data, making a three-dimensional point cloud detection data set, and dividing the three-dimensional point cloud detection data set; constructing a point cloud three-dimensional target detection model based on the visual state space model; substituting the training set into the point cloud three-dimensional target detection model to carry out iterative training, and carrying out model verification by adopting the verification set to obtain an optimal point cloud three-dimensional target detection model; and the test set is substituted into the optimal point cloud three-dimensional target detection model for prediction, a three-dimensional point cloud detection result is obtained, and collaborative three-dimensional target detection of multiple robots in a large-scale scene is realized.

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 discloses a benefit evaluation method for an aviation hybrid electric propulsion system. The benefit evaluation method comprises the following steps: S1, obtaining input of benefit evaluation from an aircraft manufacturer; s2, establishing component coefficient tables of hybrid power, pure power and traditional propulsion systems; s3, calculating the equal weight of the gas turbine engine according to the input of benefit evaluation and the component coefficient table; s4, obtaining a cruise stage distance iterative calculation formula suitable for different propulsion systems, and determining a cruise stage distance through iterative calculation; s5, calculating related parameters such as the comprehensive total cost per kilometer of unit commercial load and the maximum power capability index under the sea level high temperature condition; and S6, calculating the relative proportion of the corresponding indexes of the propulsion system by taking the related parameters of the traditional propulsion system as the reference and combining the related parameters of the to-be-evaluated propulsion system, configuring a weight coefficient, and calculating to obtain the comprehensive income coefficient of the to-be-evaluated propulsion system. The precision of the evaluation result is improved, and a reliable basis is provided for scheme design and power type selection of the flight platform.

The invention belongs to the technical field of aircraft manufacturing, and discloses a pressure-adjustable flexible blank pressing loading deep drawing die and a using method thereof.The deep drawing die comprises a female die, a blank pressing ring and a male die, the molded surface of the female die is partially matched with the outer surface of a part, and the upper surface of the blank pressing ring is provided with a sunken surface matched with an unfolded blank in shape; 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 pressure-adjustable fluid medium is tightly pressed on the upper surface of the unfolded blank in a sealed mode through the female die and the blank holder, and part drawing forming is carried out on the male die. And the technical problem of mutual contradiction of edge pressing load concentration during traditional deep drawing load increase is solved. A fluid medium flexible edge pressing mode is adopted, contact friction does not exist between the female die and the flange edge of the part, and the edge pressing load uniformity is not affected when the die bears deformation; the lubricating device has the remarkable advantages of good lubricating effect, low mold processing cost, high technical universality and the like.

The invention relates to the field of aircraft manufacturing equipment, in particular to an aircraft boarding gate turnover device and a using method, and the aircraft boarding gate turnover device can conveniently and reliably meet the requirement for angle adjustment in the aircraft boarding gate assembling process and comprises a main body framework and supporting frames arranged at the two ends of the main body framework correspondingly, and the supporting frames are arranged in the vertical direction; a positioning frame used for fixing a boarding gate is arranged between the supporting frames, the positioning frame comprises a positioning rod and a pair of lateral fixing seats, the positioning rod is of a bent structure protruding downwards, the two ends of the positioning rod are rotatably arranged on the supporting frames, and the lateral fixing seats are fixedly arranged on the two sides of the positioning rod respectively. The positioning frame comprises a pressing mechanism, and the pressing mechanism is arranged at the end of one end of the positioning rod. The method is particularly suitable for the assembly process of the boarding gate of the airplane.

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 a large-scale aircraft digital-analog automatic assembly method, which belongs to the technical field of aircraft manufacturing, and comprises the following steps: S1, defining EBOM data, S1, defining aircraft digital-analog data, S1, establishing a hierarchical relationship between the EBOM data and aircraft digital-analog, and S1, carrying out aircraft digital-analog automatic assembly. According to the large-scale airplane digital-analog automatic assembly method and automatic assembly, the production speed can be greatly increased through digital-analog automatic assembly, and compared with traditional manual assembly and automatic assembly, more assembly tasks can be completed within shorter time, so that the overall production efficiency and persistent data are improved, and the production efficiency is improved through persistent EBOM data and airplane digital-analog data. According to the method and the system, the traceability and the consistency of data are ensured, a coordinate system is set, and the set coordinate system provides a unified and accurate space reference, so that the accuracy and the consistency of assembly can be improved.

The invention belongs to the technical field of aircraft manufacturing, and discloses an automatic offset compensation boring method for a curved surface normal hole, which directly finishes boring, on-machine measurement and compensation processing of the curved surface normal hole in a machine tool in a semi-automatic manner by using a convenient and universal measuring head without designing a special tool. The technical problems that a part with a curved surface normal hole is long in machining period and large in machining difficulty are solved. Compared with a traditional method, efficient numerical control boring of the curved surface normal hole is achieved, and the machining precision and production efficiency of parts are improved.

The utility model relates to the technical field of aircraft manufacturing, in particular to an aircraft component auxiliary assembling device which comprises a bottom plate, and an electric hydraulic rod is fixedly installed on the top of the bottom plate. The electric hydraulic rod is started to drive the base and the connecting base to vertically move, the connecting base drives the top plate and the supporting plate to move, and therefore the supporting height of the aircraft component is adjusted, the first motor is started to drive the rotating shaft to rotate, the rotating shaft drives the connecting base to rotate, and the connecting base drives the top plate and the supporting plate to rotate, and therefore the aircraft component is driven to flexibly turn over. A second motor is started to drive a screw rod to rotate, the screw rod drives a sliding block to horizontally slide under limiting of a mounting groove, the sliding block drives a hinge rod to rotate around a hinge point and push a supporting plate, and therefore the supporting plate rotates around the hinge point, the vertical angle of the aircraft component is adjusted according to needs, and the assembling efficiency is improved.

The utility model relates to the technical field of commercial aircraft manufacturing, specifically to a wing assembly auxiliary device for commercial aircraft manufacturing, including a top plate, one side of the inner wall of the top plate is rotatably connected with a transport adjustment component, and the transport adjustment component includes a transmission rod, a motor, a fixed frame, a hydraulic rod, a connecting frame, a rotating rod and a roller. The utility model motor external power supply drives the transmission rod to rotate, and the transmission rod drives the fixed frame on one side to rotate. The top of the fixed frame is used to place the wing. After rotating to a specified angle, the hydraulic rod external power supply pushes the top connecting frame to move upward, and the rotating rod connected inside the connecting frame drives the roller to contact the bottom of the wing. At this time, the staff can push the wing to one side and align it with the position to be installed. The wing slides to one side on the roller surface, thereby achieving the effect of adjusting the wing installation angle, and the wing can be manually transported for installation, reducing the danger of crane transportation and installation.

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 belongs to the technical field of aircraft manufacturing, and discloses a fuselage hatch cover AO generation method, electronic equipment and a computer storage medium, and the method comprises the steps: constructing a fuselage hatch cover AO model semantic library and a fuselage hatch cover AO model relation library according to three-dimensional model data; assembling objects and connecting pieces of the assembling objects are obtained from a fuselage hatch cover AO model semantic library by adopting a semantic recognition algorithm, and an assembling object library and a connecting piece library are constructed respectively; according to the fuselage cabin cover AO model relation library, the assembly object library and the connecting piece library, a connection relation library is constructed and obtained; according to the assembly content in the assembly scheme, the assembly sequence of the assembly objects is obtained, and an assembly object logic sequence library is constructed and obtained; traversing the assembly object logic sequence library, obtaining the corresponding assembly objects in the assembly object library according to the assembly sequence of the assembly objects, obtaining the corresponding connecting pieces in the connection relation library, and generating the fuselage hatch cover AO. The method solves the problems of low efficiency and poor accuracy of existing fuselage hatch cover AO batch generation.

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 invention discloses a titanium alloy surface cobalt-based tungsten carbide coating grinding treatment method and a titanium alloy surface cobalt-based tungsten carbide coating grinding treatment device, and belongs to the field of metal hardness coating grinding of aircraft manufacturing technics.A positive electrode is applied to a grinding wheel with the surface provided with a metal bonding agent, and negative electrodes are applied to the outer surface of the grinding wheel with the surface provided with the metal bonding agent at intervals; positive electrode voltage applied to the grinding wheel and negative electrode voltage applied to the outer surface of the grinding wheel are set; the electrolytic effect is achieved by applying voltage to the grinding wheel, a hard metal bonding agent on the surface layer of the grinding wheel generates a passivation insulating film layer capable of containing a large amount of fine grinding materials on the surface of the grinding wheel, the grinding wheel is continuously sharpened through dynamic balance of the passivation insulating film layer on the electrolytic inhibition effect, and grinding wheel abrasive particles obtain the constant protruding amount; therefore, the stable and controllable grinding process is achieved, and the problems that in an existing method, pure mechanical grinding is adopted, the grinding precision of the surface of the cobalt-based tungsten carbide coating is low, and surface quality damage is large are solved. The method has the characteristic of eliminating grinding failure caused by abrasion of the granularity of the grinding wheel.

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.

An aircraft engine firewall and wing connecting structure belongs to the technical field of aircraft manufacturing, is used for improving the connecting strength between a wing and an engine nacelle, and comprises a wing and an aircraft engine nacelle, the aircraft engine nacelle comprises a front firewall, a rear firewall, an upper firewall, a box-shaped machining part, a second joint, a third joint, a reinforcing connecting rod and a reinforcing rib, the upper firewall is arranged between the front firewall and the rear firewall, the second connector is arranged on the rear end face of the front firewall, the third connector is arranged on the front end face of the rear firewall, a reinforcing connecting rod is connected between the second connector and the third connector, and the box-shaped machining part is arranged in a wing. The reinforcing rib is of a triangular structure, the reinforcing rib is arranged on the rear end face of the rear firewall, the front end of the reinforcing rib, the rear firewall and the third connector are connected through screws, and the upper end of the reinforcing rib, the wing skin and the box-shaped machining part are connected through screws.

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 invention relates to a temperature control method for an aircraft part production process, belongs to the technical field of aircraft manufacturing, and solves the problem of non-uniform temperature in a large aircraft part production process in the prior art. The method comprises the following steps: S1, inputting types, shapes and sizes of aircraft parts; the composite materials are arranged on the corresponding molds; s2, whether a flow direction adjusting plate is installed or not is judged according to the types of the aircraft parts; s3, the temperature of the composite material is controlled to rise to 150-200 DEG C, and the temperature rise rate is 2-5 DEG C / min; s4, preserving heat for 1-2 hours; and S5, cooling is conducted, the cooling rate is 2 DEG C / min-5 DEG C / min, and cooling is conducted to the normal temperature. According to the invention, the structural composition of the production equipment and the state of the shunting port can be adjusted according to the type, shape and size of the aircraft part, so that the flowing direction of gas for exchanging heat with the composite material in the production process is changed, and the temperature uniformity of the aircraft part in the production process is ensured.

The invention belongs to the technical field of aircraft manufacturing, and discloses a stainless steel deep U ship-shaped thick skin tailor-welding drawing shape control method and a forming die, which are used for reversely calculating various key sizes of a drawing process piece by constructing different drawing coefficients and controlling the deformation degree of each part of the drawing process piece. The technical problems that a stainless steel deep U-shaped ship-shaped thick skin blank is insufficient in size, prone to instability and wrinkling in the forming process and large in resilience after being formed are solved. According to different bearing strengths of all parts of a tailor-welded blank, structural design key points of the drawing die are specified in detail, including a gap between a convex die and a concave die, a blank pressing gap, a gap between a drawing rib and a drawing groove and the like, the design thought is complete, the structural design of similar dies can be guided, and the universality is high.

This invention relates to the field of aircraft manufacturing technology and discloses a cutting device for aircraft manufacturing and processing. The processing rotary table is rotatably mounted on the upper part of the support base under the drive of a drive motor. During processing, the processing station can be switched by rotating the processing rotary table. During the process, the laser cutting head does not need to make a large working displacement, which improves the processing efficiency of the equipment and greatly reduces the structural volume of the equipment. The guide block flipping clamping structure eliminates the need for manual clamping operations. Automatic clamping and release operations of workpieces can be realized according to the workpiece distribution. The rotary feeding structure drives the electromagnetic chucks on both sides of the material picking arm to complete the workpiece feeding and unloading process through reciprocating flipping. A single action can realize the synchronous picking and dropping of finished workpieces and raw workpieces. The operation is continuous and efficient. It is perfectly connected and coordinated with the rotation station switching of the processing rotary table to realize efficient and rapid material feeding and discharging.

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.