1345results about "Aircraft assembly" patented technology

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 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 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.

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.

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 provides a fixed-wing aircraft fuselage equal straight section assembly deformation prediction method, which comprises the following steps: establishing a three-dimensional simplified structure model of a skin assembly, a fuselage frame assembly and a bottom plate beam assembly according to geometric features; the skin assembly, the fuselage frame assembly and the bottom plate beam assembly are assembled, a constraint relation is applied, and a three-dimensional simplified structure model of the straight section of the middle fuselage is formed; grid division is carried out on the three-dimensional simplified structure model of the straight section of the middle fuselage; setting material attributes and mechanical boundary conditions for the three-dimensional simplified structure model of the straight section of the middle fuselage; solving a deformation result of the three-dimensional simplified structure model for the straight section of the middle fuselage; and evaluating and optimizing a calculation result. According to the method, the influence of the skin size of the middle fuselage straight section, the fuselage frame assembly size, the bottom plate beam size, the material attribute and the connection mode can be considered, and the deformation of the middle fuselage straight section of the fixed-wing aircraft can be rapidly calculated.

A structure system for installation into a fuselage structure in an interior of an aircraft is proposed, the system comprising at least one first carrier element, at least one second carrier element, at least one elongate frame element having a first end and a second end, at least one first attachment device for attaching the first carrier element to the fuselage structure or to an element coupled with the fuselage structure, at least one first coupling device mounted to the first end for coupling the first carrier element to the at least one frame element, and at least one second coupling device mounted to the second end for coupling the second carrier element to the at least one frame element, wherein the at least one frame element is adapted for holding at least one component to be installed in the interior, wherein the at least one first carrier element is designed for coupling with the at least one first coupling device, wherein the at least one second carrier element is designed for coupling with the at least one second coupling device, and wherein one of the at least one first coupling device and the at least one second coupling device is adapted to snap into the respective carrier element, to be moved relative to the respective end of the frame element and to be arrested in a desired relative position thereto.

The present disclosure provides for pneumatic deicer boot assemblies, and related methods of fabrication and use. More particularly, the present disclosure provides for bartack stitched pneumatic deicer boot assemblies for aircraft or the like, with the bartack stitched pneumatic deicer boot assemblies having an inflatable carcass formed by two layers (e.g., a stretchable layer and a non-stretchable layer) stitched together using bartack stitches.

The invention discloses an aircraft skin assembly control method and system, and the method comprises the following steps: segmenting a skin and a frame from an image based on a skin surface image through employing a deep learning segmentation model; registering and splicing the images captured by different spectrum cameras to obtain a complete skin image; based on the complete skin image, using a region expansion method to identify and track a skin surface deformation region; preprocessing the original skin model through a finite element method to obtain a corresponding grid model; estimating stress distribution in the current assembly state based on the force haptic image and a stress transfer model; and based on the deformation area and the stress distribution, generating an assembly path and a pressure adjustment instruction by adopting a self-adaptive control strategy, and controlling the assembly process. Through fusion of a multispectral vision technology and a high-precision force tactile perception technology and combination of a deep learning algorithm and a nonlinear mechanical model, accurate identification of skin surface features and accurate positioning of a deformation area are realized, and the assembly control precision is improved.

The invention discloses a lifting device and method for storage and transfer of an airship pod, and relates to the technical field of storage and transfer of airship pods.The lifting device comprises an upper bracket, two lifting driving assemblies, a middle support, a damping spring, a base, four wheels and a traction rod; through the modular truss structure design, the bearing capacity and the lightweight requirement are both considered; a multi-dimensional vibration reduction system is formed by the vibration reduction springs which are arranged horizontally, longitudinally and transversely and the soft rubber buffer cushion, and the structure and function integrity of the pod in the storage and transfer process can be effectively protected by matching with the flexible moving and locking functions of the universal wheels with brakes; the lifting driving assembly adopts worm and gear transmission to achieve stable lifting and + / -15-degree pitch angle adjustment, an operating hand wheel designed in an ergonomic mode is combined, electric drive is matched, and the requirement for precise adjustment and control of pods is met. And the operation efficiency is greatly improved through the quick disassembly and assembly design of the positioning and fixing assembly and the traction rod.

An aircraft pylon comprising a box-section primary structure and at least one tank positioned inside the primary structure. To facilitate mounting or demounting the tank, the pylon is equipped with a guide system configured to move the tank from its mounted position toward a through-hole, including a guide rail fastened to the primary structure and positioned above the tank and a guide pin fastened to the tank cooperating with the guide rail so that the tank is supported by the guide rail and is able to slide along the latter. This guide system contributes to simplifying manipulation of the tank when mounting or demounting the tank by at least partly compensating its weight and guiding the tank.

The invention discloses a composite blade electroforming metal wrapping sheet and a production device thereof, and relates to the technical field of blade metal wrapping sheets, the composite blade electroforming metal wrapping sheet comprises a plurality of wrapping sheet sections, one side surface of each wrapping sheet section is provided with a fixing slot, a reinforcing assembly is arranged in each wrapping sheet section, and the reinforcing assembly comprises an additional side plate arranged on one side surface of each wrapping sheet section, the multiple wrapping sheet sections and the additional side plates are combined into a wrapping sheet finished product piece, a fixed side block is arranged at one end of the wrapping sheet finished product piece, the surface of one side of the fixed side block is connected with the surface of one side of the additional side plate at one tail end of the wrapping sheet finished product piece, a connecting shaft rod is arranged on the upper surface of the fixed side block, and a turnover anchoring plate is arranged on the surface of one side of the connecting shaft rod. And a plurality of anchoring screws are arranged on the upper surface of the overturning anchoring plate, and in the scheme, by arranging the reinforcing assembly and the machining mechanism, the stability of the wrapping piece in the using process and the production efficiency are 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.

Metal to composite joints and methods of forming are presented. A metal to composite joint for a platform comprises two metal structural components forming a portion of a first surface and a portion of a second surface of the metal to composite joint; and a dividing set of composite plies between the two metal structural components providing an escape path for volatiles between the two metal structural components.

The invention provides a middle-sized unmanned aerial vehicle structure and function integrated grating oil tank capable of being automatically and integrally formed and a forming method, and relates to the field of unmanned aerial vehicle structure design. The oil tank body is formed by integral compression molding of an upper skin and a lower skin, the grating separation layer is co-cured with the skins through insert injection molding by chopped carbon fiber reinforced thermoplastic resin to form honeycomb grids, and the oil inlet and outlet connector is an aluminum alloy flange and is fixed to the bottom of the oil tank through welding of aluminum alloy and thermoplastic composite materials. Based on the long and short fiber mixed integrated oil tank design and process technology, full-automatic integrated forming of the main bearing shell can be achieved, the oil tank skin guarantees the bearing capacity through the long continuous fiber composite material, the oil tank grating is made of the chopped fiber composite material, and the functions of sequential oil supply, overload resistance, shaking prevention and the like are achieved; and the number of oil tank parts is greatly reduced, and the potential of full-automatic manufacturing is achieved.

The invention relates to a multi-degree-of-freedom adjustable unmanned aerial vehicle booster rocket mounting trolley, and belongs to the technical field of unmanned aerial vehicle launching. Comprising a base, a lifting mechanism is arranged on the base and comprises a lifting plate, a longitudinal moving mechanism is arranged at the upper end of the lifting plate and comprises a longitudinal moving plate horizontally sliding in the Y direction, and a transverse moving mechanism is arranged at the upper end of the longitudinal moving plate and comprises a transverse moving plate horizontally sliding in the X direction; a rolling mechanism is arranged at the upper end of the transverse moving plate through a pitching mechanism, the rolling mechanism is driven by the pitching mechanism to rotate in the X direction, the rolling mechanism comprises a fixed support and a rotary support, the rotary support is rotationally arranged on the fixed support, a hoop mechanism is arranged on the rotary support, and the hoop mechanism is arranged on the fixed support. The booster rocket is fixedly connected with the rotary bracket through a hoop mechanism; the problem that a booster rocket of an existing large unmanned aerial vehicle cannot be hoisted in the docking process and cannot be accurately docked with the unmanned aerial vehicle is solved.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

An aircraft wing assembly includes a wing box including an upper surface, a lower surface, and a leading edge structure connecting the upper surface to the lower surface and secured to the upper surface at a connection point. The aircraft wing assembly includes a drive mechanism secured to the wing box and a high lift device mounted to the drive mechanism. The drive mechanism is configured to move the high lift device between a retracted position and an extended position in use, and wherein the high lift device is configured to overlap the connection point when in the retracted position.

The invention belongs to the technical field of aircraft structure design, and discloses a fuselage frame preparation process and a fuselage frame. According to the fuselage frame preparation process, preparation of the first woven preformed body and the second woven preformed body is achieved through the weaving operation of the weaving machine, the preparation efficiency and the structural integrity of the first woven preformed body and the second woven preformed body are improved, and the influence of manual operation on the fuselage frame forming quality is avoided. The preparation of the first weaving body and the second weaving body is realized by cutting operation of cutting guide parts arranged on the first weaving auxiliary core mold and the second weaving auxiliary core mold in advance, so that the preparation precision is guaranteed, and the forming quality of the fuselage frame is improved. The invention further provides the machine body frame, the machine body frame is prepared through the machine body frame preparation technology, the manual operation participation degree is reduced in the machine body frame preparation process, the influence of manual operation errors on the forming quality of the machine body frame is avoided, the forming quality and forming efficiency of the machine body frame are improved, and the manual labor intensity is relieved.

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 application discloses a kind of based on six degrees of freedom parallel mechanism's aircraft cabin section butt joint method, comprising: S1: construct global assembly coordinate system, ground reference point is laid to specified position;S2: numerical control positioner is hoisted to specified work station;S3: fuselage shape frame is hoisted to specified work station;S4: middle and rear fuselage is connected with fuselage shape frame;S5: middle and rear fuselage pose is adjusted;S6: rear fuselage is connected with fuselage shape frame;S7: rear fuselage pose is adjusted;S8: by numerical control positioner, middle and rear fuselage is connected with rear fuselage;The application compact structure is stable, with good rigidity and carrying capacity, suitable for large, heavy fuselage cabin body butt joint work, process planning efficiency is high, reliable high strength.

The invention provides a robot tail end hole making system and method based on contact type normal correction, and relates to the technical field of aeronautical manufacturing and airplane digital assembly. The system is connected with a tail end mechanical arm of the industrial robot through a detachable connecting interface and comprises a hole forming actuator and a control subsystem. The control subsystem is configured to control the hole forming actuator to move to the position, where holes are to be formed, on the wall plate. A hole forming actuator is controlled to make contact with the surface of the wall plate, and normal information of the to-be-formed hole position is detected through a sensor arranged on the hole forming actuator; according to the normal direction information, the adjusting posture of a drilling actuator is controlled, so that the axis of the cutter is consistent with the normal direction of the position to be drilled; by measuring the back-off amount of the wall plate, the hole forming actuator is controlled to compensate the TCP position of the cutter; and after the posture adjustment and the TCP displacement compensation are completed, a hole forming actuator is controlled to complete hole forming machining. According to the invention, the high-precision drilling requirement for aircraft assembly can be met, and support is provided for an aircraft digital assembly technology.

The present disclosure provides a method of inspection of a surface of an aerodynamic structure. The method includes acquiring image(s) of the surface using image sensor(s) disposed adjacent to the surface, and determining, using the image(s) applied to a model, predicted defect(s) of the surface and corresponding location information. The method further includes controlling, using the location information, the position of tactile sensor(s) disposed adjacent to the surface to acquire dimensioning information for at least a first predicted defect of the predicted defect(s). The method further includes characterizing the first predicted defect using the dimensioning information.

The invention relates to the technical field of aviation sealant construction, in particular to an aviation fastener row positioning frame and an operation method thereof.The row positioning frame comprises a row positioning frame body, and a double faced adhesive tape with release paper is arranged on the back face of the row positioning frame body; a plurality of mounting grooves which are in one-to-one correspondence with fasteners to be packaged are formed in the row positioning frame main body in a penetrating manner, the peripheral wall of each mounting groove extends from the front surface to the back surface of the row positioning frame main body to form an obliquely arranged corner cut type inclined surface, and a plurality of guide columns respectively surround the surface of each corner cut type inclined surface. According to the invention, the main body of the row positioning frame adopts an integral design, so that all fasteners in the whole area of the aircraft wing can be positioned at one time, and the occupied space around the row positioning frame is extremely small and can be reduced to a limit position without interference with other parts; the defect that a traditional independent positioning frame is prone to operation interference in a dense fastener arrangement scene is thoroughly overcome.