1076results 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 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.

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 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 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.

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.

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

A brake in combination with a slider for holding an aircraft workpiece in position for maintenance. The combination has a slider which circumscribes and moves on a support bar and a brake configured to lock the slider in place on the support bar. The brake has a brake pad internal to the slider and at least partially congruent with the support bar. The brake pad is engageable and disengageable from the support bar by respective insertion and retraction of a key pin extending outwardly from the wall of the slider. The key pin and the brake pad are connected by a driver pin, so that insertion of the key pin towards the support bar urges the driver pin towards the support bar and the brake pad into locking contact with the support bar. A method of locking an aircraft workpiece in position for maintenance is also disclosed. The method comprises the steps of: providing a stand having X, Y, Z adjustability of a fixture for holding the aircraft workpiece moving a slider to a predetermined position on a spreader, locking the slider the in the predetermined maintenance position with a brake and joining an aircraft workpiece to the fixture.

The invention relates to the technical field of aircraft assembly, and discloses a six-degree-of-freedom attitude adjusting system and method based on a series-parallel connection structure, the attitude adjusting system comprises a moving seat, a mounting frame, a multi-shaft driving assembly and a mounting platform, each driving assembly is provided with a servo motor and a hand wheel dual power source, and is connected with a lead screw module through a bevel gear transmission mechanism; an elastic deflection mechanism is arranged between the power source and the bevel gear and used for achieving auxiliary torque supply, and the multi-shaft driving assembly can achieve adjustment of six postures of front-back, left-right, up-down, pitching, rolling and rotation in the horizontal plane when the large power part of the aircraft is assembled. According to the six-degree-of-freedom attitude adjusting system, through the innovative design of series-parallel mechanism fusion, double-power-source redundant drive, electric cooperative control and the like, high-precision assembly and installation of heavy-weight parts such as aero-engines can be achieved, and high-precision assembly and installation of the heavy-weight parts are high in precision, high in reliability, low in labor intensity and high in adaptability.

A backscatter x-ray system has an x-ray device, a movable platform, and a processor. The x-ray device includes an x-ray emitter and an x-ray detector. The movable platform positions the x-ray device relative to a frontside of a structure. The processor is communicatively couplable to the x-ray device. The x-ray emitter emits x-rays that penetrate the structure from the frontside. The x-ray detector detects a backscatter of the x-rays reflected from the structure. The processor generates x-ray images of the structure based on the backscatter, and analyzes the x-ray images in a manner facilitating at least one of manufacturing and inspection of the structure.

The present disclosure provides techniques for improving aircraft machining process using machine learning-based predictive models and many-objective optimization algorithms. Data from a machining process is collected, where the data comprises a plurality of machining parameters and at least two performance metrics. For each respective performance metric, a respective predictive model is trained using one or more machine learning (ML) techniques, where the plurality of machining parameters are used as inputs, the respective performance metric as target outputs, and the respective predictive model learns to correlate the inputs to the target output. For each respective performance metric, a respective objective function is generated for the respective predictive model. Many-objective optimization is performed on the respective objective functions, and a set of solutions are generated for the machining process based on the many-objective optimization.

A floor-bound vehicle, in particular for a movable production plant with a processing unit for processing a workpiece, with at least two drive units, wherein the drive units each comprise at least one drive wheel, a travel drive for driving the at least one drive wheel, a wheel carrier on which the at least one drive wheel is arranged, and a steering drive for adjusting the wheel carrier with the drive wheel about a geometric steering axis and thus steering the drive wheel, wherein for steering, the respective wheel carrier can be adjusted relative to the respective travel drive by means of the respective steering drive is provided.

Disclosed herein is a hoist tool including a hoist frame and a base structure. The hoist frame includes a structural framework having a first end and a second end and at least one first rotation-enabling coupling at the second end of the structural framework. The base structure includes at least one second rotation-enabling coupling configured to engage with the at least one first rotation-enabling coupling of the hoist frame. The at least one second rotation-enabling coupling of the base structure defines a rolling axis. The hoist frame is selectively movable by the hoist to position the at least one first rotation-enabling coupling into engagement with the at least one second rotation-enabling coupling and when coupled and when the assembled structure is coupled to the hoist frame, the hoist frame is selectively rotatable about the rolling axis, relative to the base structure, to enable a rollover of the assembled structure.

The application belongs to the technical field of aircraft assembly design, and particularly relates to an aircraft fuselage assembly method, which realizes the arrangement of corresponding measurement stations, measurement reference points and object measurement points of each small wallboard, and the pre-positioning, pre-coordination, posture adjustment and secondary coordination of each small wallboard through the space outward deviation of the theoretical assembly positions of the upper, lower, left and right long strip wallboards, and can well eliminate the problem of large deformation in the assembly process of the four long strip wallboards with weak rigidity, has high assembly precision and efficiency, and can well guarantee the aerodynamic performance of the aircraft fuselage assembly.