2605results about "Aircraft assembly" patented technology

A method of additively manufacturing an aircraft part, having steps of: forming a base, defining a shape of the aircraft part, out of first thermoplastic polymer; forming a lower support surface onto discrete locations of the base by printing a mixture of a second thermoplastic polymer and a catalyst compound formed with metal onto the discrete locations, such that the lower support surface is formed with cavities; and forming an upper support surface by depositing, via electrolysis deposition, a metal plating onto the lower support surface along the discrete locations, to thereby form the aircraft part.

The invention discloses a multifunctional aircraft skin bionic heterostructure and a preparation method thereof, belongs to the technical field of aerospace, and aims to solve the problem that a traditional aircraft skin structure is difficult to synergistically realize impact resistance, sound absorption, noise reduction and electromagnetic shielding, and a multifunctional composite skin protection structure is designed in a breakthrough manner. Through collaborative innovation of a bionic framework and a functional material, triple optimization of mechanical-acoustic-electromagnetic characteristics is realized. A bionic skeleton structure with outstanding mechanical properties is obtained through a layered annular structure of a glass sponge skeleton and a hierarchical structure design of a thighbone, and the bionic skeleton structure is combined with modified polyurethane foam with excellent sound absorption performance and electromagnetic shielding performance to obtain a multifunctional heterostructure with impact resistance, noise reduction and electromagnetic shielding.

Methods and scan systems for analyzing an object. The methods include obtaining a local operation dataset that includes a plurality of operation data points obtained from an object and a corresponding location, within the operation coordinate system, for each operation data point of the plurality of operation data points. The methods also include mapping the plurality of operation data points from the operation coordinate system to a global coordinate system for the object. The mapping includes mapping to generate a global operation dataset that includes the plurality of operation data points and a corresponding global location, within the global coordinate system, for each operation data point. The scan systems include a robot that performs a plurality of operations on an object within an operation coordinate system and a computing device that maps the plurality of operation data points from the operation coordinate system to a global coordinate system.

An inlet cover mechanism for an air launched vehicle includes a quick release pin, a chassis, a collar, and a piston pin. The inlet cover mechanism facilitates attachment and deployment of an inlet cover with the air launched vehicle. The quick release pin is connected to the inlet cover. The chassis is connected to the air launched vehicle. The collar is connected to the chassis and is releasably engageable with the quick release pin. The piston pin is slidably engaged within the chassis and is configured to contact the quick release pin.

The invention belongs to the technical field of aircraft pipeline assembly, and particularly relates to an on-line detection method and system for the off-board assembly process of a pipeline, and the method comprises the following steps: constructing a tightening control model, and initializing model parameters; adjusting the conduit and the joint to an initial state and applying tightening torque; reading tightening process information in real time and drawing a tightening curve broken line graph; the initial assembly normalization is judged in real time; fitting a linear segment slope kj in real time; the standardability of the assembly process is judged in real time; the tightening torque maximum value Tmax and the tightening angle maximum value Amax are detected in real time; calculating an assembly result in real time; and assembling reliability is detected in real time. According to the invention, an assembling tool with torque acquisition and angle acquisition is utilized to acquire tightening torque and rotation angle in the assembling process, and data information in the tightening process is read in real time. And data information of the tightening process is input into the tightening control model, and meanwhile, external assembly control parameters and boundary parameters of the guide pipe machine are set, so that real-time online detection of the whole assembly process of the guide pipe is realized.

The invention discloses an aircraft pulse type general assembly production line assembly process method, and relates to the technical field of large production line assembly. The aircraft pulse type general assembly production line assembly process method comprises the steps of determining an aircraft general assembly production line assembly task and the required yield, planning the aircraft pulse type production line layout and process, reasonably dividing system assembly process separation surfaces in all stations, designing detailed assembly process flows in all the stations, and measuring and calculating station assembly periods. Establishing an aircraft final assembly pulse type production line, and verifying and improving the aircraft final assembly production line. According to the aircraft pulse type general assembly production line assembly process method, the whole process from task determination to production line verification implementation is systematically planned in detail, the assembly period is shortened by reasonably planning the general assembly production line assembly process flow and resource allocation, the aircraft general assembly efficiency is improved, and double improvement of the production efficiency and the product quality is ensured.

The invention relates to the technical field of acoustics, in particular to a manufacturing method of an acoustic liner structure and the acoustic liner structure. The acoustic lining structure comprises a first panel, an embedded tube plate, a surrounding wall structure and a second panel which are sequentially arranged in the thickness direction of the acoustic lining structure, the embedded tube plate and the first panel are matched to form a plurality of embedded tubes, the second panel is a through hole panel, and therefore the first panel, the embedded tube plate, the surrounding wall structure and the second panel are matched to form a plurality of acoustic elements. Each acoustic element is provided with a plurality of Helmholtz cavities arranged side by side, the spaced Helmholtz cavities are communicated through embedded pipes to form an element, other Helmholtz cavities which are communicated through or not through the embedded pipes form another element, and the silencing capacity of the acoustic liner structure can be enhanced through the strong coupling effect and the weak coherent coupling effect in different acoustic elements. According to the acoustic liner structure and the manufacturing method thereof, under the condition that the thickness of the acoustic liner structure is limited, the low-frequency, broadband and efficient noise elimination characteristics can be achieved, the manufacturing process is clear, and operability is high.

Methods and apparatus for determinant assembly support are disclosed. A disclosed example apparatus to support a panel component for determinant assembly thereof includes a support frame that is releasably couplable to a jig, a first clamp to support the panel component at a first position of the panel component, a first body of the first clamp or the support frame including a nominal clearance opening to receive a first fastener to operatively couple the first clamp to the support frame, and a second clamp to support the panel component at a second position of the panel component different from the first position, a second body of the second clamp or the support frame including a slotted opening to receive a second fastener to operatively couple the second clamp to the support frame, the second fastener movable about the slotted opening to enable the second clamp to reduce forces imparted to the panel component while held by the support frame.

The invention discloses a wing design optimization method based on agent-assisted multi-initial-point simulated annealing, and belongs to the technical field of optimization design. Comprising the steps of 1, initializing algorithm parameters and a training data set; 2, constructing an agent model; 3, executing multi-initial-point parallel simulated annealing, and generating a batch of candidate new solution sets; 4, executing a double-elite active learning strategy based on the new solution set, screening the most potential sample to carry out real evaluation, and updating the agent model; 5, cooling the temperature and reducing the step length; 6, judging whether the cumulative evaluation times of the expensive objective function reach the set maximum evaluation times or not; if not, returning to the step 2; if yes, optimization is stopped; and finally, traversing the training data set, and selecting a sample point with the minimum real objective function value as a global optimal solution. According to the method, a multi-initial-point parallel simulated annealing search mechanism and a double-elite active learning strategy are combined, and the global optimal solution is quickly approached under the limited simulation times.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.

The embodiment of the invention discloses a modularized adjustable test device for simulating butt joint of large parts of an airplane and a use method thereof, a simulation test module in the device comprises at least one simulation test unit, multiple layers of steel pipes are arranged in an adjustable frame of the simulation test unit in the X and Y directions respectively, and the inner layer of steel pipes are driven to stretch out and draw back, so that the butt joint of the large parts of the airplane is simulated. The sizes of the adjustable frame in the X and Y directions are adjusted; the plurality of simulation test units are sequentially spliced along the spanwise direction or the course of the aircraft to form a spanwise structure or a course structure of the large component of the aircraft; adjusting the size of the size-adjustable frame in each simulation test unit in the X and Y directions to adjust the boundary dimension of the simulation test module in the unfolding direction of the airplane or the course of the airplane; the counterweight modules are placed on the size-adjustable frames of the simulation test units, and the weights and the gravity centers of the large components of the airplane are simulated by applying counterweights; and the center-of-gravity positions of the simulation test module and the single or partial simulation test units are measured through the numerical control positioner.

An inlet assembly of a nacelle includes an inlet cowl that has a leading edge, an outer side that extends from the leading edge to an outer aft edge, and an inner side that extends from the leading edge to an inner aft edge. An exterior surface of the inlet cowl is seamless along an entire length of the outer side from the leading edge to the outer aft edge. The inlet cowl includes a lipskin that has a metallic coating. The metallic coating defines the exterior surface of the inlet cowl along the leading edge and the entire length of the outer side.

Various embodiments of a novel monocoque aerostructure quadcopter implemented as a vertical take-off and landing vehicle are described. In one example, a vertical take-off and landing vehicle includes a fuselage having a leading end positioned in a first horizontal plane and a trailing end positioned in a second horizontal plane that is vertically below the first horizontal plane. The vertical take-off and landing vehicle further includes a first arm assembly extending from the leading end of the fuselage in the first horizontal plane. The vertical take-off and landing vehicle further includes a second arm assembly extending from the trailing end of the fuselage in the second horizontal plane. The vertical take-off and landing vehicle further includes a first rotor assembly coupled to the first arm assembly and a second rotor assembly coupled to the second arm assembly.

The invention provides an interchangeable helicopter hinge cabin door structure and a preparation method thereof, and belongs to the technical field of helicopter cabin doors, a cabin door main body is of a composite sandwich structure and is of an inner skin and outer skin structure, the cabin door main body structure is divided into inner and outer skin secondary glue joint curing, and inner cavities with different section shapes are formed after the inner and outer skin secondary glue joint curing; other cabin door accessories are arranged on the cabin door main body structure; the cabin door is provided with two metal hinge joints, the metal hinge joints are connected with the cabin door body, and the cabin door is installed on the fuselage structure through cooperation of the metal hinge joints and hinge joints on the fuselage door frame. The structure is simple, the integration is high, the process difficulty is low, the assembly is convenient, and the product consistency is good.

The invention discloses a rapid auxiliary assembly collaborative robot suitable for an aircraft cabin door, and belongs to the technical field of aircraft assembly, the rapid auxiliary assembly collaborative robot comprises a main body structure, an adsorption unit, a power system and a control system, the main body structure 1 carries the adsorption unit, the power system and the control system, and the main body structure 1 is matched with the power system and the control system to realize multi-pose follow-up control; the power system provides pneumatic power for the adsorption unit to adsorb cabin door products. The power system provides negative pressure for work of the adsorption unit and provides power for follow-up control of the main body structure. The control system controls adsorption, release and multi-degree-of-freedom free posture adjustment. The device has high degree of freedom, adapts to aircraft cabin doors with different shape and position requirements, can be accurately operated in a narrow assembly space, is flexible in structure, simple and convenient to operate, and rapid and accurate to move and position, greatly shortens the time of loading, unloading and hoisting of the cabin door, and shortens the cabin door assembly time by about 70%.

The invention relates to the field of unmanned aerial vehicle assembly, in particular to an unmanned aerial vehicle suspension frame assembly device. At present, mounting and dismounting of unmanned aerial vehicle suspension frame assembling equipment are tedious, workers need to clean the equipment, a large amount of manpower and time are consumed, and the assembling efficiency is low. An unmanned aerial vehicle suspension frame assembling device comprises a frame body and the like. A suspension frame is connected to the frame body in a sliding mode, two electric push rods are fixedly connected to the frame body, and the two electric push rods are symmetrically arranged. The suspension frame and the cradle head equipment are pre-lifted through the two rotating plates, the cradle head equipment can be buffered when the cradle head equipment is clamped into the supporting frame, deformation and damage of the cradle head equipment caused by heavy pressure of the supporting frame are prevented, and the suspension frame and the cradle head equipment can be limited and installed in multiple directions; therefore, the holder equipment can be stably installed, meanwhile, the holder equipment can be quickly assembled and disassembled, and the assembling efficiency of the holder equipment is improved.

The invention discloses a positioning tool for aircraft wing installation, and belongs to the technical field of aircraft wing installation, the positioning tool comprises three hydraulic telescopic cylinders and a supporting mechanism for installing and supporting the hydraulic telescopic cylinders; the three hydraulic telescopic cylinders are distributed on the supporting mechanism in a triangular shape. The output end of the hydraulic telescopic cylinder is provided with a rotary adjusting supporting assembly used for supporting wing installation. The rotary adjusting and supporting assembly comprises a supporting rod fixedly connected to the output end of the hydraulic telescopic cylinder; the rotating sleeve is rotationally connected to the upper end part of the supporting rod; the supporting rod rotatably supports the rotating sleeve; the bottom bracket is fixedly connected to the rotating sleeve; and the top bracket is mounted on the bottom bracket. According to the positioning tool, the wing is lifted through the whole positioning tool, and it is ensured that the position shape of the root of the wing meets the position requirement of the opening in the fuselage, so that the wing is more stable and accurate in the installation process, and the installation efficiency and the installation effect are improved.

The invention relates to the technical field of computers, in particular to a special-shaped windshield glass mounting method, device and equipment and a medium. The environment state of the mechanical arm at the current moment is obtained by initializing a control strategy of the mechanical arm provided with the special-shaped windshield glass; determining a reward item of the control strategy based on the environment state at the current moment and the control strategy; updating the value function according to the reward item of the control strategy to obtain an updated value function; optimizing the control strategy according to the updated value function to obtain an optimized control strategy; the step 102 and the step 106 are executed circularly until the updated value function is converged, the optimized control strategy at the moment serves as the final control strategy of the mechanical arm, the mechanical arm is controlled to install the special-shaped windshield according to the final control strategy, and through the configuration mode, the installation precision of the special-shaped windshield can be effectively improved.

The utility model discloses an aircraft single wallboard assembly fixture which comprises a main frame, a clamping plate assembly, a stringer end positioner, a stringer axis surface positioner, a stringer puller, a K hole positioner, a skin supporting block, a floating frame presser and a bandage, and the main frame comprises a frame, an adjustable support, a clamping plate support and a laser tracker target ball positioning seat. The laser tracker target ball mounting seat and the frame are fixedly mounted, the clamping plate supports are located at the upper end and the lower end of the frame, the adjustable support is arranged at the bottom of the frame, and the long honing and the floating frame can be conveniently fixed.

The invention belongs to the technical field of airplane structure design, and discloses a horizontal tail wing beam connecting structure, an airplane and an assembling method, and the horizontal tail wing beam connecting structure comprises a central rib plate, an upper T-shaped connector, a lower T-shaped connector, a left connecting plate, a right connecting plate and an outer side connecting plate. The upper T-shaped joint comprises a lower edge strip, a first left edge strip and a first right edge strip, the lower T-shaped joint comprises an upper edge strip, a second left edge strip and a second right edge strip, the central rib plate is arranged between the left beam and the right beam, and the left connecting plate, the right connecting plate and the outer side connecting plate are combined for use, so that the bearing capacity of a left beam web plate and a right beam web plate is improved; the first left edge strip and the first right edge strip can increase the contact area between the upper T-shaped connector and the left wing and the contact area between the upper T-shaped connector and the right wing, the second left edge strip and the second right edge strip can increase the contact area between the lower T-shaped connector and the left wing and the contact area between the lower T-shaped connector and the right wing, the connecting strength of the left beam and the right beam in the vertical direction is improved, and the lower edge strip, the upper edge strip and the central rib plate are matched with one another. And the connection strength of the left beam and the right beam in the horizontal direction is improved.

The invention relates to the technical field of aviation assembly, in particular to a method for calculating the gasket adjustment amount in the coaxiality adjustment process of a helicopter tail transmission shaft, and the method comprises the steps: constructing a target key point and a target virtual camera of the helicopter tail transmission shaft, so as to determine a first coaxiality error representation vector of the helicopter tail transmission shaft; obtaining target measurement data of the helicopter tail transmission shaft, and equivalently mapping the target measurement data to the first coaxiality error representation vector to obtain a second coaxiality error representation vector meeting a preset format; and inputting the second coaxiality error representation vector into a pre-calibrated mathematical solution model to output the adjustment amount of each gasket of the helicopter tail transmission shaft. Therefore, the problems that in the prior art, only two sets of single circular targets are measured, the coaxiality of the helicopter tail transmission shaft cannot be effectively observed, the adjustment amount of the installation gasket is estimated only according to manual experience, the labor cost is increased, and the accuracy of the adjustment amount of the gasket is reduced are solved.

The invention belongs to the technical field of aeronautical manufacturing, and particularly relates to a wing wallboard numerical control posture adjusting and positioning device and method.The positioning device is composed of four parts including a four-axis numerical control posture adjusting mechanism, a shape maintaining plate, an adapter frame and a suction cup assembly; before the wing wall plates are separated from the wall plate assembly fixture, the shape maintaining plates are connected with the wing wall plates, and each wing wall plate is provided with two shape maintaining plates; the wall plate provided with the shape-preserving plate is hoisted to a wing general assembly fixture, the wing general assembly fixture is connected with the transfer frame through bolt holes in the shape-preserving plate, and the suction cups are fixed to the wing wall plate, so that the wing wall plate is stably connected with the shape-preserving frame, and deflection and movement do not occur in the moving process; the adapter frame is arranged on the four-axis numerical control attitude adjusting mechanism, and the spatial position of the adapter frame is adjusted through the four-axis numerical control attitude adjusting mechanism, so that the attitude of the wing wallboard is adjusted. The four-axis numerical control posture adjusting mechanism can achieve movement in four directions, the movement is transmitted to the wall plate through the shape preserving frame and the shape preserving plate, and adjustment of the posture of the wall plate is achieved. The wing assembly fixture is a part of a wing assembly fixture, can realize quick and accurate attitude adjustment and positioning of wing wallboards, and improves the wing appearance assembly accuracy.

The present application belongs to the technical field of aircraft assembly, and provides a device and method for controlling the depth of a counterbore of an engine suspension fastener hole. The device is used in the process of drilling an engine suspension fastener hole and counterbore, and controls the depth of the counterbore. The device is composed of a micrometer, a sensor and a tool holder. The micrometer is fixed on the tool holder, and the end of the micrometer is a flat surface. The working end of the sensor is a half-spherical surface, which can be compressed. The tool holder moves with the deepening of the counterbore depth, so that the end surface of the micrometer and the sensor are in contact and the sensor is compressed. When the compression reaches a certain depth, the sensor triggers, the device stops the counterbore, the tool exits the product, and the assembly part is automatically counterbored to the required size. The present application can automatically control the depth of the counterbore of the assembly part and the part.

The embodiment of the invention discloses a digitalized assembling method of a helicopter fairing, which comprises the following steps of: 1, scanning the surface of the fairing and the surface of a helicopter body structure, and acquiring a three-dimensional contour model of the surface of the fairing and the surface of the helicopter body structure according to scanning data; 2, generating a visual assembly correction scheme by comparing the three-dimensional contour model with a design model imported into a controller; 3, in the fairing assembly process, a visual assembly correction scheme is projected through laser, non-contact hole making and polishing guiding are achieved, and digital assembly of the fairing is implemented; and 4, in the fairing assembling process, dynamic position information of the fairing and all the positioning targets on the aircraft body structure is obtained, the moving track of the fairing in the assembling process is solved, automatic alarming is conducted when the fairing is out of tolerance, and laser projection is frozen. The problems that an existing fairing assembling mode is low in assembling efficiency and precision, and the production efficiency and the assembling requirement of a helicopter are difficult to meet are solved.

The invention provides an aircraft passenger cabin door assembling device and a using method thereof.The device comprises a bearing base, a lifting base is arranged on the upper side of the bearing base, a movable frame plate is arranged on the upper side of the lifting base, a rotating plate is arranged on the inner side of the movable frame plate, an assembling table is arranged on the outer side of the rotating plate, and a threaded shaft is arranged in the middle of the assembling table in a penetrating mode; the threaded shaft is sleeved with two sets of first sliding blocks, the first sliding blocks are fixedly connected with movable groove bodies in a clamped mode, and the inner sides of the movable groove bodies are fixedly connected with limiting rods in a clamped mode. Position deviation of the airplane passenger cabin door in the assembling process can be avoided, the assembling stability of the passenger cabin door is remarkably improved, the passenger cabin doors of different specifications and sizes can be positioned and assembled, the application range is large, parts at different positions of the passenger cabin door can be rapidly assembled, and the assembling efficiency is improved. The assembling efficiency of the passenger cabin door is remarkably improved, the passenger cabin door can be assembled and butted at different height positions, and the assembling applicability is good.

The invention relates to a method of manufacturing a reinforced portion and a reinforced vehicle. A method of manufacturing a reinforcement portion of a vehicle includes applying a release film directly onto a surface of the vehicle, applying a first metal layer directly or indirectly onto the release film, applying a curable adhesive layer directly onto the first metal layer, and applying a second metal layer directly onto the curable adhesive layer. The method further includes applying pressure to the first metal layer, the curable adhesive layer, and the second metal layer to press the first metal layer, the curable adhesive layer, and the second metal layer against the surface. The method further includes curing the curable adhesive layer when pressure is applied to the curable adhesive layer to form the reinforced portion. The method additionally includes removing the reinforcement portion from the surface after curing the curable adhesive layer.

An aircraft wing includes a fixed structure and a linear hydraulic slat actuator attached to the fixed structure. The linear hydraulic slat actuator is oriented spanwise along the aircraft wing. The aircraft wing also includes an actuator output link and a slat attached to the actuator output link. The aircraft wing also includes a bell-crank coupled to the linear hydraulic slat actuator and to the actuator output link. In response to spanwise movement of the linear hydraulic slat actuator, the bell-crank is configured to move the actuator output link in a different direction that enables the slat to move between a retracted position and an extended position.

A method of sealing a component assembly includes applying onto a first component a first sealant bead having, in a cross-sectional view, a first width and a first height, wherein the first width is greater than the first height. The method also includes applying over the first sealant bead a second sealant bead having, in the cross-sectional view, a second width and a second height, thereby generating a sealant stack. The second width is equal to or smaller than the second height and the second width is smaller than the first width. The method additionally includes arranging over the sealant stack a second component, such that the sealant stack is positioned between the first and second components. Furthermore, the method includes fastening the second component to the first component with the sealant stack squeezed therebetween to generate a fluid-tight seal via rheological flow of the first and second sealant beads.

The invention discloses a self-adaptive assembly unwheeling system for cabin section assembly, and belongs to the technical field of aircraft section assembly. The system comprises a tray and an unwheeling system, the tray is used for supporting the cabin section, bearing the cabin section to move to the position above the unwheeling system and then placing the cabin section on the unwheeling system, and force bearing conversion of the cabin section is achieved; the unwheeling system comprises a force bearing mechanism, a bearing pad, a lifting mechanism and a movement mechanism, the upper surface of the force bearing mechanism is matched with the tray, and the cabin section is synchronously located on the upper surface of the force bearing mechanism, and the tray downwards penetrates through the upper surface of the force bearing mechanism; the bearing pad is installed on the force bearing mechanism and used for supporting the cabin section, and the cabin section can be placed in a vertical mode or a horizontal mode when assembled. Rapid carrying and switching, vertical and horizontal placement and lifting adjustment of the cabin section are achieved, and the cabin section assembling operation and transportation requirements are met.

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.