2007results about "Aircraft assembly" patented technology

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.

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.

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.

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 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 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.

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 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 invention relates to a variable-gauge knitted flexible inflatable wing and a preparation method thereof, and relates to the technical field of aircrafts. The variable-gauge knitted flexible inflatable wing comprises a variable-gauge knitted base body, an airtight film covering layer, a shaping film covering layer and an air nozzle, the upper surface layer and the lower surface layer of the variable-gauge knitted base body are connected through spacing wires, and the spacing wires are knitted through an empty needle to form a telescopic structure; the airtight film covering layer covers the outer surface of the variable-gauge knitted base body to form a closed air cavity; the shaping film coating layer covers the outer surface of the airtight film coating layer and is at least used for restraining deformation of the airtight film coating layer, and the thickness of the shaping film coating layer is larger than that of the airtight film coating layer; the air nozzle is communicated with the air cavity. Through the telescopic spacing wires, the wings are tightly folded after being deflated, and the transportation and storage convenience is improved; during inflation, the spacing wires accurately control the distance between the upper layer and the lower layer, and high-precision control over the aerodynamic configuration is achieved in combination with constraint of the sizing film coating layer.

An aircraft sub-assembly manufacturing system is arranged over multiple floors of a manufacturing facility. A production line of workstations is provided at locations at both a first floor and a second floor of the facility, each of the workstations being arranged for providing manufacturing steps for the aircraft sub-assembly. Elevator apparatus is arranged to transport the assembled aircraft sub-assembly between the first floor and the second floor of the facility.

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 provides a multi-stage progressive assembly method suitable for double-curvature weak-rigidity components of a large aircraft, and belongs to the technical field of aircraft assembly.The multi-stage progressive assembly method comprises the steps that firstly, an upper left wall plate assembly, a lower left wall plate assembly, an upper right wall plate assembly, a lower right wall plate assembly, a top wall plate assembly and a bottom wall plate assembly are assembled respectively; the left half shell part and the right half shell part are assembled; thirdly, the right half shell part and the bottom wall plate assembly are assembled into a super wall plate part; and finally, the super wall plate component, the floor beam assembly, the left half shell component and the top wall plate assembly are assembled to complete final assembly. A traditional technology is broken through, a brand-new process separation surface division mode, a vertical posture assembly mode and a multi-stage progressive key element control mode are adopted, the product quality and the assembly efficiency can be effectively improved, the assembly coordination difficulty is greatly reduced, human engineering is met, the labor productivity is improved, and the production cost is reduced. And the requirement for rapidly improving the assembly capacity of the double-curvature part of the large civil aircraft can be met.

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.

A first method includes: accessing a coating thickness range; triggering sensors to capture scan and depth data of a workpiece; assembling a virtual model; defining initial spray parameters and a toolpath; driving a coating applicator to apply coating; capturing updated depth data; calculating coating thickness; and, if the thickness falls below the minimum target, redefining spray parameters and toolpaths to reapply coating until the target thickness is applied. A second method for media blasting a workpiece includes, during a scan cycle: capturing images via an optical sensor along a scan path; compiling a virtual model; accessing blast parameters; and generating a tool path for a workpiece region based on the model and parameters. During a processing cycle, the second method includes navigating a blast nozzle along the tool path with actuators and projecting blasting media onto the workpiece according to the blast parameters.

An aircraft that is certifiable for freighter transport is disclosed herein. The aircraft can include a hybrid fuselage including a plurality of modular sections, wherein the plurality of modular sections includes a first section, a second section, and an intermediate section, and wherein the intermediate section is disposed intermediate the first section and the second section. The aircraft can further include a plurality of systems traversing the plurality of modular sections and a plurality of structural components configured to mechanically couple the intermediate section to the first section and the second section of the plurality of modular sections. The first section and the second section are configured for use with a fuselage of a passenger aircraft, and wherein the intermediate section is configured for use with a fuselage of a freighter aircraft.