112 results about "Pre stretching" patented technology

The invention relates to the technical field of inductors, in particular to an inorganic insulation integrally-formed power inductor and a preparation method thereof. The method comprises the following steps: S1, selecting a coil; s2, pre-stretching the coil; s3, pre-coating of inorganic powder is carried out; s4, pressing the magnetic powder; s5, sintering the ceramic layer at high temperature; and S6, integrally forming the inductor. By reasonably selecting the material and shape of the coil and the type of the magnetic powder and combining high-temperature sintering at the temperature of 250 DEG C or above, the magnetic conductivity and the bias resistance are improved, the diversified requirements of high frequency, high temperature, high power density and the like are met, and the performance of insulation, heat conduction and the like can be optimized; according to the integrated forming process, coil pre-packaging and magnetic core forming are completed in one step, production procedures are reduced, process integration and production efficiency are improved, production cost is reduced, the utilization rate of a magnetic core window reaches 100%, and the product size is reduced.

The lead screw pre-stretching mechanism for the numerical control machine tool comprises a lead screw, a tail end bearing seat is arranged at the end of the lead screw, the tail end bearing seat comprises a tail end bearing sleeve, a plurality of first bearings, a first gasket, a load cell, a load cell gasket, a disc spring and a first outer spacer ring, and the first bearings, the first gasket, the load cell, the load cell gasket, the disc spring and the first outer spacer ring are located in the tail end bearing sleeve. The disc spring, the load cell gasket and the load cell are sequentially arranged on the first outer distance ring in a sleeved mode, the end of the tail end bearing sleeve is bent to form a contact step, the two ends of the disc spring abut against the contact step and the load cell gasket respectively, the end of the lead screw sequentially penetrates through the first outer distance ring, the first gasket and all the first bearings, and the load cell is tightly attached to the first gasket. The first gasket is tightly attached to the first bearing, and the end of the lead screw is exposed out of the tail end bearing seat and provided with a locking nut. The disc spring can well balance the pre-stretching force of the lead screw and the pre-tightening force of the tail end bearing seat, automatic compensation of thermal elongation of the lead screw can also be achieved, and high precision and high stability are provided for a transmission system of a machine tool.

The invention discloses a heat treatment process for a high-elongation aluminum alloy plate, and particularly relates to the field of aluminum alloy material processing, and the heat treatment process comprises the following specific heat treatment steps: S1, component design preparation, S2, low-temperature solution treatment, S3, pre-stretching optimization and S4, graded aging. According to the invention, through a synergistic process of combining low-temperature solution treatment, pre-stretching optimization and graded aging, the contradiction between the strength and the elongation of the aluminum alloy plate is successfully solved, the strength of the aluminum alloy plate is maintained while the elongation of the aluminum alloy plate is remarkably improved, a high-performance aluminum alloy material solution is provided for lightweight of automobiles, and the application prospect is wide. Wide market prospects and industrial application values are realized; and although the steps of pre-stretching and grading aging are added, the energy consumption is saved by reducing the solid solution temperature, and the comprehensive production cost is equivalent to that of a traditional process.

The invention relates to a plate three-point incremental forming track designing and forming method. The method comprises the following steps that S100, a two-point incremental forming track is generated according to a three-dimensional model of a target part; s200, the track is divided into two areas, the two parts of the track are achieved through two forming tools (2 and 3) respectively, and the connecting line of cutter location points of the two forming tools at the same moment always passes through the same central symmetry axis; s300, a simple support (7) is installed, the periphery of the plate (8) is clamped, a forming tool is installed, and tool setting is conducted; s400, pre-stretching is applied to the plate, and then the two execution tail ends of the machining equipment are made to run according to the tracks of the two forming tools correspondingly to machine the plate; and S500, after machining is completed, the clamping force is removed, and the formed workpiece is taken down. Three-point constraint is formed on the plate through the simple support and the two forming tools, the overall deflection and shaking of the plate during forming are remarkably reduced, and then the geometric accuracy of a final part is improved.

The invention belongs to an aluminum alloy stretching plate flatness control technology, and particularly discloses an aluminum alloy stretching plate flatness control method. The problem that the flatness of a stretching plate is not qualified is solved. The technological process comprises the steps of hot rolling, edge cutting, pre-stretching, solid solution quenching, stretching, aging and packaging inspection, the finish rolling temperature of hot rolling ranges from 260 DEG C to 360 DEG C, and the cooling mode is fan blowing cooling; the edge cutting amount is 15 to 50 mm; the stretch rate of pre-stretching is 0.5%-1.0%; in the solid solution quenching treatment, the flow ratio of quenching water to water is 0.65-0.85, the transfer speed is 100-500mm / s, the temperature of quenching water is 20-37 DEG C, and the hot rolled plate is secondarily cooled after being discharged from the furnace; the stretching rate of the stretching treatment is 1.5%-3.0%, and the stretching retention time is within 30 min. The method is beneficial for controlling the final product plate shape and improving the economic benefits and social benefits of enterprises.

The invention discloses a method for improving the interlayer performance uniformity of a large-size high-toughness 7xxx aluminum alloy pre-stretched super-thick plate, and relates to the field of improvement of interlayer performance differences of high-strength aluminum alloy pre-stretched super-thick plates. The method aims at solving the problems that in the subsequent part machining and application process of the 7xxx alloy super-thick pre-stretched thick plate, the performance difference of a plate thickness layer is large, the damage resistance of the position where the performance of the plate is weak is reduced, the part loses efficacy, and the model safety is reduced. The method comprises the steps of controlling the uniformity of cross-section structure components of a large-size cast ingot, performing strong rolling deformation of plate interlayer performance uniformity, and performing strong quenching for improving the hardenability of the plate. According to the plate prepared through the method, the bottleneck that the comprehensive performance of the plate is synergistically improved is broken through, the overall performance of the thick plate is improved, the service life of parts is prolonged, the structural safety is enhanced, and the market competitiveness of products is improved. The method disclosed by the invention is used for controlling the interlayer performance uniformity of the 7xxx large-specification, super-thick and ultrahigh-strength aluminum alloy pre-stretched thick plate.

The invention discloses an aluminum alloy high-rib ultrathin skin component forming method which comprises the following steps: carrying out solid solution, water quenching and pre-stretching on an aluminum alloy plate to obtain a quenched flat and straight aluminum alloy plate, and processing the quenched flat and straight aluminum alloy plate into an aluminum alloy plate blank; the aluminum alloy plate blank is subjected to roll bending to obtain a cone part, and the cone part is subjected to cold-heat cycle treatment; the cone part obtained after cold-heat cycle treatment is milled, and vertical ribs and skin of the component are machined; and the member obtained through milling is subjected to creep age forming treatment, and the aluminum alloy high-rib ultra-thin skin member is obtained. According to the method, the component forming precision is high, the final residual stress is small, and the method has important guiding significance on forming of the high-performance large-scale integrated high-rib ultra-thin skin component.

The preparation method of the aluminum-lithium alloy profile with the high batch stability comprises the following steps that forging is conducted, specifically, an aluminum-lithium alloy cast ingot is heated and then forged, and the single-pass upsetting deformation of upsetting and drawing during forging is 60-75%; extrusion: heating the forged blank, the extrusion container and the die, and then carrying out extrusion treatment; solid solution quenching: carrying out solid solution quenching treatment on the blank subjected to extrusion treatment to obtain a profile; low-temperature heat preservation is conducted, specifically, the profile obtained after solution quenching treatment is subjected to low-temperature heat preservation treatment, the temperature ranges from 0 DEG C to 5 DEG C, and the heat preservation time is not shorter than 30 min; and carrying out pre-stretching and aging treatment on the profile subjected to low-temperature heat preservation treatment. According to the invention, the production efficiency can be improved, and the aluminum-lithium alloy material with high batch stability and excellent performance can be prepared, so that the requirements of a new generation of airplanes on the profile can be better met.

The invention relates to an aircraft skin plate residual stress relieving device which comprises a base and further comprises a pre-stretching mechanism arranged on the base, a clamping assembly is arranged on the pre-stretching mechanism, a back plate is fixed to the base through a vertical frame, a reciprocating type driving mechanism is arranged on the back plate, and a frame is arranged on the reciprocating type driving mechanism. A plurality of hammer heads are arranged in the frame, the reciprocating type driving mechanism drives the frame to move in a reciprocating mode and simultaneously drives the hammer heads to knock a skin plate, two pump cylinders are fixed to the back plate, a sliding cylinder is fixed to the base, a rack is arranged in the sliding cylinder, and the two pump cylinders are communicated with the interior of the sliding cylinder through pipelines. The reciprocating type driving mechanism is used for intermittently conveying air into the sliding barrel through the two pump barrels to pressurize, so that the rack drives the pre-stretching mechanism to intermittently stretch the skin plate. According to the residual stress eliminating device for the aircraft skin plate, the residual stress is removed by knocking, stretching, knocking and stretching for many times, and the stress eliminating effect on the skin plate is greatly improved.

The invention discloses a design method and system for a simulation part considering the stress gradient of a pre-rotated wheel disc, and relates to the technical field of wheel disc fatigue life detection.The method comprises the steps that a geometric model of the pre-rotated wheel disc is obtained, and physical property parameters of a wheel disc preparation material at different temperatures are determined; determining first maximum stress distribution of the non-pre-rotating wheel disc and the pre-rotating wheel disc according to the geometric model and the physical property parameters based on finite element simulation software; based on a stress gradient theory, determining an effective assessment distance of the maximum principal stress of the non-pre-rotating wheel disc and the pre-rotating wheel disc; determining second maximum stress distribution according to the first maximum stress distribution and an effective assessment distance between the maximum principal stress of the non-pre-rotating wheel disc and the maximum principal stress of the pre-rotating wheel disc; and according to the second maximum stress distribution, designing the key geometric dimension, the pre-stretching load and the fatigue load of the simulation piece. According to the invention, the design complexity of the simulation part can be reduced, and the fatigue change of the pre-rotated wheel disc can be effectively verified.

The invention discloses a thermomechanical treatment method for improving the obdurability and the plate shape of an Al-Cu-Mg alloy plate. The thermomechanical treatment method comprises the following steps: (1) carrying out pre-stretching treatment on a deformed plate; (2) carrying out single-stage or graded solid solution heat treatment on the pre-stretched plate, wherein the final solid solution heat treatment temperature is T1; (3) cooling the plate subjected to solid solution treatment to a temperature T2 at an average cooling rate V1, and then cooling the plate from T2 to a room temperature at an average cooling rate V2; (4) the quenched plate is subjected to cold deformation treatment after being placed at the room temperature; and (5) the plate subjected to cold deformation treatment is subjected to pre-stretching treatment, and then natural aging is conducted under the room temperature condition. According to the method, the Al-Cu-Mg alloy plate is subjected to pre-stretching, solid solution heat preservation, graded controlled cooling quenching, room temperature standing, cold deformation, pre-stretching and natural aging treatment, and the Al-Cu-Mg alloy can obtain an ideal obdurability matching relation on the premise of controlling residual stress and the plate shape.

The invention relates to the technical field of aero-engine manufacturing, in particular to an aero-engine deep-drawing deep-step thin-wall guide sleeve machining method which comprises the steps that S1, the structure of a deep-drawing part is determined, specifically, the structure of the deep-drawing part is designed according to the structure of a thin-wall guide sleeve, and the large port part of the deep-drawing part is provided with a flange edge; s2, the size of a blank is determined, specifically, the blank is a disc-shaped plate, and the diameter phi D of the blank is determined according to the surface area S of the deep drawing part; s3, the blank is pre-stretched through a pre-stretching die, and a pre-stretched part is obtained; s4, the flange edge of the pre-stretching part is trimmed; s5, a deep drawing die is adopted for conducting deep drawing on the trimmed pre-drawing part, and a deep drawing part is obtained; and S6, the deep drawing part is machined, and the thin-wall guide sleeve is obtained. The parts machined through the method are better in consistency and higher in quality, the one-time machining qualification rate of the parts is guaranteed, and the forming efficiency of the thin-wall guide sleeve parts is greatly improved.

The invention relates to the technical field of alloys, in particular to a high-strength and high-toughness aluminum alloy and a preparation method thereof. The aluminum alloy is prepared from, by mass, 7.6%-8.2% of Zn, 1.9%-2.4% of Mg, 1.6%-2.4% of Cu, 0.10%-0.25% of Mn, 0.08%-0.18% of Zr, 0.01%-0.06% of Sc and the balance Al. The preparation method comprises the steps of ingredient smelting, combination of two-stage homogenization treatment and intermediate thermal deformation, hot rolling, solution treatment, cryogenic treatment, high-temperature treatment, re-water quenching, low-temperature pre-aging, pre-stretching, graded aging and the like in sequence. By optimizing microalloying elements and a composite heat treatment process, recrystallization coarsening and grain boundary continuous precipitation are effectively inhibited, the fracture toughness and stress corrosion resistance of the aluminum alloy are remarkably improved while high strength is kept, and the aluminum alloy is suitable for force-bearing components such as aerospace components.

Method for monitoring a thermoforming process designed to form a large number of articles in a single layer of material (10), the method comprising: Recording at least two measured values ​​at at least two mold cavities (160, 160a, 160b, 160c), wherein at least one measured value is recorded at each of the at least two mold cavities (160, 160a, 160b, 160c), which indicates a stretching force or stretching energy to be applied when pre-stretching the material layer (10) into the respective mold cavity (160, 160a, 160b, 160c); and Comparing the measured values ​​recorded at the at least two forming cavities (160, 160a, 160b, 160c) to obtain a comparative result, the comparative result being an indicator of the homogeneity of the thermoforming process.

The present application relates to the technical field of machining, and discloses a segmented type bundling and stretching forming equipment for large-curvature roller coating hyperbolic aluminum plate, which comprises the following steps: establishing a distributed material gene library, designing a material parameter verification and correction mechanism, calibrating parameters, and triggering model retraining when continuous abnormalities occur; establishing an environmental influence coefficient matrix, calculating actual yield strength, strain threshold and pre-stretching force; collecting aluminum plate surface images in real time; dynamically adjusting stretching parameters, optimizing stretching speed to control stretching force loading; reconstructing a strain field in real time, and designing a self-adaptive termination mechanism; inputting material and strain parameters to predict critical curvature, calculating square tube structure parameters, calculating initial pressure and optimizing pressure; designing a multi-stage stretching and pressure maintaining process, and reducing pressure of a corresponding area if local strain exceeds a limit; controlling progressive unloading by using an exponential decay curve, detecting residual stress, performing full-size detection, analyzing deformation deviation, solving optimal parameters, and updating a parameter library.

The invention discloses a method for pre-stress fatigue reinforcement of a steel structure through a local additive and subtractive Fe-SMA component, firstly, the position, needing to be reinforced, of the steel structure is subjected to surface treatment, then the Fe-SMA component is installed, and the Fe-SMA component comprises a Fe-SMA component and additive parts which are arranged at the two ends of the component and used for being connected with the surface of the steel structure or an anchoring assembly in a matched mode. The Fe-SMA components can be pre-stretched to reach preset strain, and active prestress is applied to the to-be-reinforced structure in a thermal excitation mode by utilizing the shape memory effect of the Fe-SMA materials. And the novel intelligent material Fe-SMA is used, so that the fatigue performance of the structure is improved. And meanwhile, the shape memory effect of Fe-SMA can be utilized, prestress can be applied to the to-be-reinforced structure in a thermal excitation mode, and the safety of the to-be-reinforced structure is greatly improved.

The invention provides a 7xxx series aluminum alloy plate strip for anodic oxidation with a high recovery ratio and a preparation method of the 7xxx series aluminum alloy plate strip. The 7xxx series aluminum alloy plate strip comprises the following elements of 0.06%-0.12% of Si element, 0.10%-0.25% of Fe element, 4.5%-5.5% of Zn element, 2.0%-3.0% of Mg element, 1.2%-2.0% of Cu element, 0.05%-0.15% of Mn element, 0.10%-0.15% of Er element, 0.10%-0.12% of Zr element, 0%-0.03% of Ti element and the balance aluminum element. The aluminum alloy plate strip is prepared through the steps of reclaimed material grading pretreatment, low-liquid-level semi-continuous casting, multi-stage homogenizing heat treatment, hot rolling, cold rolling, solid solution, pre-stretching, two-stage aging and the like. Through joint optimization of material components and the process, the finished plate strip has excellent mechanical performance, an oxidation film is uniform in color and luster, and salt mist resistance, friction resistance and the like are achieved.

The multi-force-source progressive die is used for machining a material sheet into a flexible gear blank, the flexible gear blank comprises a barrel and a flange, a barrel opening in one end of the barrel is connected with the flange, a feeding channel is formed between an upper die base and a lower die base, and when the upper die base and the lower die base are closed, the feeding channel is connected with the flange. The first female die assembly and the first male die assembly pre-stretch a material sheet to form a boss, the second female die assembly and the second male die assembly conduct contour shaping on the boss formed through pre-stretching, and the third female die assembly and the third male die assembly punch a center hole in the boss subjected to contour shaping. The multi-force-source male die assembly and the multi-force-source female die assembly apply shearing force and drawing force which are opposite to each other to a material piece with a punched center hole, a flange is punched through the shearing force to achieve blanking, and a boss with the center hole is drawn into a cylinder through the drawing force. According to the scheme, through the synergistic effect of multiple force sources, die abrasion is reduced, the service life is prolonged, and the size precision and shape precision of the flexible gear blank can be guaranteed.

The invention relates to a screw transmission structure suitable for a vertical shaft, and its pre-stretching process, and belongs to the technical field of machine tool screw structures. Its structure is: an upper bearing seat and a lower bearing seat are coaxially arranged above and below the mounting base; the upper bearing seat and the lower bearing seat are jointly connected to the screw, the bottom thread of the screw is connected to the lower locking nut, the lower end face of the lower bearing group is limited to the upper surface of the lower sealing sleeve, and the lower surface of the lower sealing sleeve is supported on the lower locking nut; the upper end of the lower bearing group is coaxially matched with the screw through a sealing adjustment device, and is connected and positioned with the lower bearing seat at the same time. This structure not only ensures the sealing performance of the lower bearing, but also improves the rigidity of the upper bearing seat, and optimizes the vertical shaft transmission structure as a whole.

The invention relates to a forming process of an automobile hinge support. The forming process comprises the steps of material shearing, five-time pre-stretching, first-time shaping, edge cutting, flanging shaping, punching, second-time shaping and inspection and warehousing. According to the forming process of the automobile hinge support, the standard production requirement is met after multiple times of stretching and shaping, the quality of produced products is stable, the percent of pass reaches 99.2%, and the production efficiency is high.

The invention discloses a strengthening method and a preparation process of a high-strength corrosion-resistant aluminum alloy, and relates to the technical field of aluminum alloy materials.The strengthening method comprises the following steps that 1-3% pre-stretching treatment is conducted on a 7-series aluminum alloy profile obtained after solid solution quenching, and a dislocation network with the dislocation density larger than or equal to 10 < 14 > m <-2 > is introduced; by controlling specific chemical components of the 7-series aluminum alloy, a foundation is laid for high performance of the material, by means of a pre-stretching-aging synergistic process, residual stress is released through plastic deformation in pre-stretching, follow-up machining deformation and stress corrosion cracking risks are reduced, a dislocation network formed by pre-stretching provides a large number of uniform nucleation points for a strengthening phase, and the stress corrosion cracking risk is reduced. By combining two-stage aging and stretching regulation, uniform dispersed precipitation of a nanoscale eta'phase is promoted, generation of a thick eta phase is inhibited, meanwhile, the nucleation tendency of a strengthening phase at a grain boundary is reduced, a fine discontinuous grain boundary precipitated phase and a narrow lean solute region are formed, intergranular corrosion resistance and exfoliation corrosion resistance are remarkably improved, and balance of strength, toughness and corrosion resistance is achieved.

The invention relates to the technical field of steel plate wall manufacturing, in particular to anti-deformation steel plate wall manufacturing equipment which comprises a bottom frame, a moving assembly and the like. A plurality of moving assemblies are fixedly connected to the bottom frame. A steel plate is transversely stretched through the four electromagnets, meanwhile, the two electromagnets on the upper portion and the two electromagnets on the lower portion move oppositely, and therefore the steel plate is longitudinally stretched through the four electromagnets, two-way pre-stretching is achieved, controllable and uniform pre-stretching stress is applied to the steel plate, and the steel plate can be subjected to two-way pre-stretching. The steel plate is in a slightly tensioned elastic state and then is welded until the steel plate is welded on the keel frame of the wall body, so that the wall body is manufactured, the correction procedure is greatly reduced or even eliminated, the efficiency is effectively improved, the manufacturing cost is reduced, and the production efficiency is improved. And the manufactured wall is low in residual stress, high in size precision and high in flatness, and the safety and reliability of the whole structure are improved.

The application discloses a kind of rotor cup machine shell bearing chamber bearing hole periphery R angle forming local material thickening process, by pre-stretching, main stretching, pre-punching bearing hole, back to mound and shrinkage back mound, final stretching finishing these six steps are completed.The application process optimizes the distribution regulation and control of metal flow in the plastic deformation process of stretching forming material and controls the quantitative flow of material, realizes the integral thickening of the material in the bearing chamber area, realizes the accurate control of material flow, thereby realizes the directional thickening of local material, and the shell product prepared is locally increased in thickness by more than one time of the original material thickness at the bearing hole periphery R angle of bearing chamber, while ensuring that the wall thickness of bearing chamber is only slightly thinned, to ensure that the rotor cup machine shell is completed and the forming quality is improved, and the product reaches higher mechanical strength, dimensional accuracy and surface quality.

The utility model discloses a lead screw cold and hot prestretching device for a numerical control machine tool, which relates to the technical field of numerical control machine tools and comprises a base, two groups of sliding rails are arranged on the outer surface of the upper end of the base, two groups of sliding blocks are arranged at the upper ends of the two groups of sliding rails, and fixing blocks are arranged at the upper ends of the two groups of sliding blocks. Threaded rods are arranged on the two sides of the upper ends of the two sets of fixing blocks correspondingly, a movable plate is arranged at the upper ends of the threaded rods, driven gears are arranged at the positions, in the movable plate, of the upper ends of the two sets of threaded rods correspondingly, a driving gear is arranged between the driven gears, and a motor is arranged at the upper end of the movable plate. And a threaded groove is formed between the movable plate and the fixed block. According to the lead screw cold and hot pre-stretching device for the numerical control machine tool, the distance between the movable plate and the fixed block can be adjusted, lead screws with different diameters can be fixed conveniently, and the lead screws are fixed more stably in the pre-stretching process.

The invention discloses a preparation method of a high-zinc small-wall-thickness aluminum alloy profile for aviation, and belongs to the technical field of material science. Preparation: preparing a high-zinc aluminum alloy cast ingot; after two-stage homogenizing annealing, saw cutting and turning are conducted, and after heating, extrusion forming is conducted; and after two-stage solid solution quenching treatment, pre-stretching is conducted, then two-stage aging treatment is conducted, and a T76511-state profile, namely the high-zinc small-wall-thickness aluminum alloy profile for aviation, is obtained. According to the method, the two-stage homogenizing annealing and two-stage solid solution heat treatment processes are adopted, so that the structure property of the profile is more uniform and stable, and it is guaranteed that all properties of a final product meet standard requirements. The prepared high-zinc small-wall-thickness aluminum alloy profile has the advantages of being high in strength, good in corrosion resistance, resistant to corrosion and the like, the average tensile strength of the high-zinc small-wall-thickness aluminum alloy profile is 635 MPa which is 21 MPa higher than the product standard requirement, the average yield strength of the high-zinc small-wall-thickness aluminum alloy profile can reach 610 MPa which is 24 MPa higher than the product standard requirement, the requirement of amphibious aircrafts of special models for high-performance aluminum alloy materials is met, and the high-zinc small-wall-thickness aluminum alloy profile can be widely applied to the field of aerospace.

The utility model discloses a double-oil-cylinder straightening machine with a pre-stretching function. The double-oil-cylinder straightening machine comprises a fixed straightening head and a movable straightening head. The fixed straightening head and the movable straightening head run on the same ground rail; the movable straightening head clamps one end of an aluminum profile to be stretched and moves towards the end, away from the fixed straightening head, of the ground rail, and when the movable straightening head moves to the designated position, the position of the movable straightening head is locked through a tail clamp. The other end of the aluminum profile to be stretched is clamped by the fixed straightening head; the fixed straightening head is provided with a pre-stretching oil cylinder which is used for pre-stretching the bent and deformed aluminum profile to be stretched; the fixed straightening head is further provided with a main stretching oil cylinder, and the pre-stretched aluminum profile is stretched to the set length. According to the double-oil-cylinder straightening machine with the pre-stretching function, the pre-stretching oil cylinders are additionally arranged, and the pre-stretching step is added, so that the stress state of a metal material can be effectively improved, and better conditions are created for subsequent straightening operation.

The utility model discloses a kind of thin permanent magnet brake, including by flange, armature, inner magnetic pole, permanent magnet, magnetic shell coaxial setting composition brake body, the flange is equipped with pre-stretching elastic element between armature, the elastic element continuously pulls armature and moves to flange direction;Permanent magnet and coil are equipped with magnetic shell, the coil diameter is greater than permanent magnet diameter, the permanent magnet is placed inside coil;The permanent magnet is also fixedly connected inner magnetic pole, the inner magnetic pole, permanent magnet, magnetic shell form accommodating groove, the coil is equipped in accommodating groove, the inner magnetic pole and magnetic shell are equipped with at least one gap. The utility model does not destroy the appearance size of brake geometric body, can greatly compress brake thickness, output brake force is big, and performance is more stable.

This utility model relates to the technical field of pre-stretching devices, and discloses a simulated pre-stretching device for enameled wire winding. It includes a base plate, a platform fixedly connected to the top of the base plate, load-bearing components on the left and right sides of the top of the platform, a stretching component between the load-bearing components, and a tension adjustment component at the bottom of the stretching component. The tension adjustment component includes a fixed plate, fixed columns fixedly connected to the left and right sides of the top of the fixed plate, a movable plate on the top of the fixed plate, and multiple buffer springs on the top of the movable plate. Threaded rods are threaded to the four corners inside the fixed plate. In this utility model, when matching the tension threshold of enameled wires of different diameters, the length of the buffer springs is adjusted by rotating the threaded rods. During pre-stretching, the buffer springs absorb tension fluctuations through deformation, avoiding cracking of the enamel layer caused by rigid stretching. This solves the problem of uneven tension easily damaging the wire, improving the pre-stretching quality and yield of the enameled wire.

The invention belongs to the field of aluminum alloy processing, and relates to a method for rapidly reducing quenching residual stress of an aluminum alloy plate, which comprises the following steps: S1, carrying out solid solution quenching treatment on the aluminum alloy plate; s2, the aluminum alloy plate is subjected to primary flattening treatment; and S3, the aluminum alloy plate subjected to primary flattening treatment is subjected to primary cold pressing machining. And S4, the first-pass cold pressing plate is rotated by 85-95 degrees, second-pass cold pressing machining is conducted, and the multi-direction cold pressing plate is obtained. The total deformation amount of the cold pressing processing is 4-5%. And S5, secondary flattening treatment is conducted, and a flattened plate is obtained. And S6, the flat plate is subjected to stepped aging treatment, and the stress-eliminated aluminum alloy plate is obtained. The method for eliminating the quenching residual stress of the aluminum alloy plate is efficient, high in precision and low in cost, solves the problem of low production efficiency of a pre-stretching method in the prior art, and has a wide industrial application prospect.

A bottle blank structure conducive to stretch blow molding comprises an integrally injection-molded bottle blank, wherein the bottle blank comprises a bottle mouth, a bottleneck, a blank body and a blank bottom which are connected in sequence, and the blank bottom is arranged as an upper bottom and a lower bottom which are connected, and the bottom end of the lower bottom is lower than the convergence point formed by the extension line of the upper bottom generatrix curve segment I, so that the blank bottom forms a downwardly protruding lower bottom on the basis of the upper bottom molding, and the lower bottom serves as a pre-stretching structure of the blank bottom, so that the blank bottom is fully expanded during the stretch blow molding process, so that serious material accumulation at the bottle bottom is avoided, and more material is distributed to the rest of the bottom of the bottle blank, so that when designing the bottle blank, the blank bottom wall thickness can be designed to be thinner, so as to achieve the purpose of lightweighting.