79 results about "Specific strength" patented technology

The invention belongs to the technical field of metal material engineering, and relates to a light high-toughness low-cost aluminum alloy and a preparation method thereof.The alloy comprises, by mass, 7.0%-9.2% of Mg, 2.5%-4.0% of Zn, 0.06%-0.20% of Zr, 0.01%-0.03% of Sb, main impurities including Fe smaller than or equal to 0.15%, Si smaller than or equal to 0.12%, other single impurities smaller than or equal to 0.05%, the total impurity smaller than or equal to 0.15% and the balance Al. Compared with 2xxx series and 7xxx series aluminum alloys, the alloy has certain advantages in the aspects of density, specific strength, ductility, corrosion resistance and the like, and has a remarkable cost advantage compared with a low-density aluminum-lithium alloy, so that the core competitiveness of an alloy product is improved, and the alloy product has the potential of becoming a next-generation commercial aluminum alloy.

The utility model discloses a composite material support with a C-shaped cross section and a negative angle and a forming die thereof, the composite material support comprises a body with a C-shaped cross section, the body comprises an upper plate, a middle plate and a lower plate, one edge of the upper plate is connected with the upper edge of the middle plate into a whole, the lower edge of the middle plate is connected with one edge of the lower plate into a whole, and the lower plate is connected with the lower plate into a whole. A C-shaped structure is defined by the upper plate, the middle plate and the lower plate, an integrated rectangular frame is defined after a C-shaped opening of the body faces outwards, the upper plate on the two opposite edges of the rectangular frame is of a negative angle structure, namely the upper plate inclines outwards and downwards, so that the included angle between the upper plate and the middle plate is an acute angle, and the lower plate and the middle plate form a right angle. The upper plates and the middle plates of the other two opposite frames of the rectangular frame are perpendicular, and the lower plates and the middle plates are perpendicular. The composite material support is low in machining cost and high in specific strength and specific stiffness.

The application belongs to the field of high-entropy alloys, and particularly relates to a preparation method of an ultra-high strength and plasticity product Fe50Mn30Co10Cr10 alloy. Firstly, a cast slab is prepared through vacuum induction melting, then the cast slab is subjected to multi-pass hot rolling with a reduction ratio of 70% to 75%, and after pickling, the cast slab is subjected to multi-pass warm rolling with a reduction ratio of 80%, and finally, high-temperature short-time annealing is carried out at 1050 to 1150 DEG C to obtain a final annealing plate. In the application, the phase transformation behavior in the alloy deformation process is inhibited by controlling the hot rolling and warm rolling temperatures, and the rolling plasticity of the material is improved. Meanwhile, by optimizing the annealing process, the grains are refined as much as possible, and a certain dislocation density is retained, and the strength and plasticity of the alloy are improved through the comprehensive action of multiple strengthening mechanisms. The prepared Fe50Mn30Co10Cr10 alloy has a tensile strength of 1050 to 1280 MPa, an elongation of 35% to 58%, and a strength and plasticity product of 40 to 73 GPa.

The invention discloses a vertical-horizontal mixed enhanced selective laser melting lattice structure based on a face-centered cube (FCC) and a preparation method of the vertical-horizontal mixed enhanced selective laser melting lattice structure. According to the method, starting from a basic FCC lattice unit, firstly, an in-plane enhanced transition lattice structure FCC-H (FCC-Horizon) is formed through a crossed structure of an inclined main rod and an auxiliary rod perpendicular to the main rod; the secondary auxiliary rods are distributed in a radial mode to construct a continuous bridging grid by further optimizing the rod piece connecting mode and the diameter proportion, and finally the vertical-horizontal mixed enhanced FCC-VH (FCC-Vertical Horizon) lattice structure is obtained. According to the structure, through the synergistic effect of the inclined main rods and the auxiliary rods perpendicular to the main rods, the compressive strength, the specific stiffness, the specific strength and the specific energy absorption of the structure are remarkably improved while the light weight is kept. According to an experiment, 316L stainless steel powder is adopted, an FCC-VH lattice structure is prepared through a selective laser melting (SLM) technology, the compression deformation mode of the FCC-VH lattice structure is converted into multi-node cooperative bearing from local buckling of a basic FCC, and the overall compression performance is more remarkably improved.

The invention relates to the technical field of transmission shaft machining, in particular to a kinetic energy transmission shaft body and a machining process integrating pultrusion, weaving, winding and glue injection, the kinetic energy transmission shaft body comprises a shaft body, the shaft body is formed by winding a continuous composite material reinforced thermosetting resin prepreg tape, and a composite material comprises a reinforcing material, a base material, a functional additive and filler; a plurality of limiting grooves are formed in the inner wall of the shaft body, the limiting grooves extend in the axial direction of the shaft body, the length of the limiting grooves is consistent with that of the shaft body, and pultrusion, weaving, winding and glue injection processes are organically integrated, so that the manufactured kinetic energy transmission shaft body has high specific strength, high torsional rigidity, excellent interlayer bonding performance and good dynamic stability; meanwhile, a limiting groove can be precisely machined in the inner wall of the shaft body, the high-precision torque transmission requirement is met, and the defects that a traditional metal shaft body is heavy and prone to corrosion and layers of a single composite material shaft body are prone to layering are overcome.

According to the high-toughness superstructure manufacturing method based on gradient bionic spiral construction, a composite material superstructure with the excellent mechanical property is constructed through the synergistic effect of gradient bionic spiral laying layer design and a Z-pin anchoring technology, in a gradient bionic spiral laying layer, the spiral angle changes in a gradient mode, Z-pin anchoring penetrates through a composite material laminated plate, and the Z-pin anchoring technology is used for anchoring the composite material laminated plate. According to the manufacturing method, a three-dimensional reinforced network is formed, the interlayer strength and impact resistance are remarkably improved, the high-toughness superstructure is manufactured through an autoclave forming process, cooperative reinforcement of gradient bionic spiral construction and a Z-pin anchoring effect is achieved, and the prepared superstructure has high specific strength, high toughness and excellent layering resistance.

The application discloses a high specific strength high-elongation 6-series aluminum alloy anti-collision beam, which comprises a base, the upper side walls of the base are symmetrically fixedly connected with vertical plates, the opposite sides of the two vertical plates are fixedly connected with support plates, the upper side walls of the two support plates are fixedly connected with a smelting furnace, a stirring mechanism is arranged on the smelting furnace, a feeding port is formed in the upper side wall of the smelting furnace, and arc-shaped blocks are arranged on the inner bottom wall of the smelting furnace. The anti-collision beam combines the advantages of 6082 alloy and 7003 alloy, has good extrusion forming performance, the strength is greater than 340 MPa, the elongation is greater than or equal to 15%, and the elongation is improved by more than 10% compared with the 6082 alloy. The rare earth rhenium is added to refine the grains and improve the alloy strength, and the 6-series profile is subjected to double-stage aging strengthening, so that the elongation of the alloy is further improved.

The application discloses a preparation method of a high-temperature / high-strength / high-toughness heterogeneous structure Ti6Al4V alloy, which takes a Ti6Al4V alloy forge piece as a matrix, takes Ti6Al4V alloy powder and Ti6.5Al3,5Mo1,5Zr0.3Si alloy powder as deposition materials, controls the alloy powder output by adjusting the rotating speed of a powder feeding barrel, continuously changes the Ti6.5Al3,5Mo1,5Zr0.3Si mass percentage doped into the Ti6Al4V powder in the thickness direction, and prepares a symmetric gradient heterogeneous structure titanium alloy by laser deposition. The application fully utilizes the high specific strength of the Ti6Al4V alloy and the high-temperature characteristics of the Ti6.5Al3,5Mo1,5Zr0.3Si alloy, and the heterogeneous structure Ti6Al4V alloy prepared by the method has excellent tensile strength and impact toughness. The application is suitable for the preparation process of the 3D printing heterogeneous structure Ti6Al4V alloy which is easy to realize.

The invention discloses a preparation method capable of reducing the grain size and segregation layer of a 6-series alloy, and relates to the technical field of metal material preparation, the preparation method comprises the following specific steps: S100, preparing raw materials; weighing an aluminum ingot, a pure magnesium ingot and a ferrosilicon alloy according to the standard components of the 6-series alloy by using an electronic analytical balance, wherein the weighing error of each raw material is + / -0.01%; through the magnetic field constraint solidification technology, the alternating magnetic field with the specific strength and frequency is applied in the 6-series alloy solidification process, alloy grains are effectively refined, formation of a segregation layer is reduced, limitation of the traditional solidification technology is broken through, uniform distribution of solute atoms is promoted through the magnetic field effect, and the alloy quality is improved. Therefore, the overall uniformity and the mechanical property of the alloy are improved, the precise control and the high uniformity of the magnetic field intensity are ensured by combining the magnetic field constraint solidification with the superconducting magnet, and a reliable means is provided for microstructure optimization of an alloy material.

The invention provides a manufacturing and performance verification method of a spray-formed aluminum alloy forge piece for a helicopter, and the method comprises the following steps: carrying out spray forming on uniformly mixed metal powder to obtain a spray-formed aluminum alloy ingot blank; carrying out extrusion hot processing on the spray-formed aluminum alloy ingot blank; forging the ingot blank subjected to extrusion hot processing; the forged forge piece is subjected to heat treatment; and carrying out performance verification on the forged piece subjected to heat treatment. The spray-formed aluminum alloy forge piece manufactured based on the method can meet the weight reduction design requirements of typical bearing frames and other parts of helicopters, structural weight reduction is achieved, and the development requirements of ultra-light structures and high specific strength are met.

The application discloses an insect exoskeleton morphological layup composite panel, a sandwich structure and a preparation method. The sandwich structure comprises two pieces of bionic layup composite panels and a piece of aramid honeycomb core layer. The bionic layup composite panel draws lessons from the spiral stacking microstructure of the insect exoskeleton, the layup design considers the symmetry and balance requirements of the composite material, a fixed rotation angle is introduced between adjacent fiber layers, and the rotation angle is taken as a period of 180 degrees, and after a plurality of periods are laid and heat-pressed and cured, the bionic layup composite panel is obtained. The bionic layup design effectively reduces the interlaminar shear stress of the composite material, weakens the inherent anisotropy of the composite material, and improves the transverse bearing capacity and impact resistance. The bionic layup composite panel and the aramid honeycomb core layer have the advantages of high specific strength, high specific stiffness, impact energy absorption, vibration and noise reduction, electromagnetic shielding and the like, and a structure and function integrated material with more excellent comprehensive performance is obtained, and the structure and function integrated material is expected to be widely used in main load-bearing structures of various spacecrafts.

The invention discloses a bimodal structure hollow glass bead / epoxy resin floating body material based on a bimodal optimal strength ratio and a preparation method of the bimodal structure hollow glass bead / epoxy resin floating body material. A bimodal optimal strength ratio formula is adopted, and the stress concentration ratio and density distribution of a hollow glass bead / polyether-ether-ketone composite material are optimized; the composite foam material which is high in strength ratio, low in density and complete in structure is achieved, the performance of the composite material is improved, a universal and normative formula is provided for industrial production, the method can be applied to calculation related to various microbead stress relations, the problems of uneven microbead distribution, stress concentration of buoyancy materials and over-high density accumulation are solved, and the application prospect is wide. The stability and durability of the solid buoyancy material are improved, the specific strength of the solid buoyancy material is improved, and a large amount of test cost is saved.

The invention relates to the technical field of composite material manufacturing, in particular to a preparation method and application of a PEEK composite material. The preparation method of the PEEK composite material comprises the following steps: carrying out high-temperature oxidation and silane coupling agent impregnation pretreatment on short carbon fibers, and meanwhile, carrying out dry premixing on polyimide microspheres and nano silicon dioxide; feeding and stirring step by step according to the proportion to form a premix with uniformly distributed components; carbon fibers are supplemented in a lateral feeding mode, and melt blending and granulation are completed in cooperation with precise temperature control; and finally, drying the composite material particles, and carrying out injection molding or compression molding to obtain a finished product. The prepared PEEK composite material has excellent comprehensive performance: the material density is extremely low, and the specific strength is excellent; a multi-scale enhanced network is constructed in the composite material, high rigidity and high toughness are both considered, and the composite material has excellent impact resistance; the composite material has a self-lubricating property and outstanding wear resistance and fatigue resistance.

The invention discloses a high-space-utilization-rate support / mast for a space structure, and belongs to the technical field of aerospace. The stent / mast is of a tubular structure in which material portions of higher strength are arranged on opposite sides of the tubular structure; the thermoplastic resin material part is connected with the edge part of the material part with high specific strength to form a pipe main body structure with a tubular structure; the slotted hole gaps are formed in the positions, opposite to each other, of the material parts with the high specific strength on the two opposite sides. During storage, pipe section parts, located outside the two ends of the slotted hole gap, of the tubular structure are flattened oppositely, flattening creases occur at the thermoplastic resin material parts, the two flattened pipe section parts are wound on the core material, and the wound flattened pipe section parts are restrained through binding belts; and the two coiled and restrained pipe section parts realize the turning direction orthogonal to the flattening direction through the slotted hole gap. The folding folding bed has the advantages of being convenient to store, small in occupied space after being stored and high in structural rigidity after being unfolded.

The application discloses a preparation method of a force-thermal superstructure with light load bearing and laser protection, adopts a double-point lattice structure design of light metal skeleton lattice and ablation type resin matrix composite lattice nested with each other, utilizes a 3D printing forming process, combines new technical advantages of selective forming of various materials, and realizes integrated high-precision forming of the force-thermal superstructure with light load bearing and laser protection by means of finite element numerical simulation and calculation optimization. The superstructure prepared by the method improves the specific strength and specific stiffness of the structure within the design range, and simultaneously has the laser protection function, so that the method has important significance for overall weight reduction and protection.

The invention provides a vibration reduction and sound insulation acoustic material valve and a design method thereof, and belongs to the field of valve design. The valve body is of a valve body structure formed by bonding three basic materials including a metal material, a CFRP material and a damping material instead of an all-metal structure of an original metal valve body, the metal material serves as an inner container, the outer layer of the inner container is coated with the CFRP material to form a CFRP layer, the outer layer of the CFRP is coated with the damping material to form a damping material layer, and the three materials are bonded into a whole through epoxy resin. And materials coated at different positions of the valve body and the thicknesses of the materials are different. The invention further provides a design method of the vibration reduction and sound insulation acoustic material valve. By utilizing the characteristics of high specific strength and high specific modulus of the CFRP material and the vibration reduction and sound insulation performance of the CFRP material and the damping material, the noise reduction and vibration reduction functions of the material can be realized on the premise that the structural weight is not increased and the mechanical property of the material is ensured.

The present application provides a kind of buffering and slow pressure non-woven spacer fabric, its processing device and method, buffering and slow pressure non-woven spacer fabric includes negative Poisson ratio material particles and built-in auxetic structure or adds auxetic particle.Belong to textile material and technical field.The present application passes through built-in auxetic structure in spacer fabric, and the shaped auxetic structure enters in auxetic structure passage, is in the interior of spacer fabric, so that spacer fabric has buffering and slow pressure capacity.Spacer fabric made of auxetic structure material and polyester fiber has the characteristics of high specific strength, large specific stiffness, strong designability, also has the advantages of high negative Poisson ratio structure shear modulus, strong energy absorption capacity, etc., has great development potential in protective clothing, building materials, automotive interiors, sports equipment and other fields.

This invention discloses a method for controlling the stability of ultra-high strength steel welds using a cold-rolled laser welding machine. The method involves: splicing the tail end of a preceding hot-rolled strip with the head end of a following hot-rolled strip and then laser welding them; smoothing the weld and performing a first annealing treatment on the weld area; uniformly covering one side of the weld with a layer of cladding powder, and then laser cladding the cladding powder; using the same cladding powder to laser cladize another side of the weld; performing a second annealing treatment on the clad area; and completing the welding of the hot-rolled strip after cooling. This invention overcomes the technical limitations of conventional annealing by combining a secondary weld heat treatment with a specific strength heterogeneous transition cladding process, fundamentally solving the strip breakage problem during continuous production of ultra-high strength steel. By matching the strength gradient in the weld area, it solves the strength mismatch problem between the weld and the base material in high-carbon equivalent steel, reducing the risk of fracture near the fusion line. This enables stable continuous production of 1800MPa grade hot-formed steel and other steel grades.

The application relates to the technical field of aircraft thermal protection, and particularly discloses a preparation method of a bearing / heat-proof integrated ordered porous sweating composite structure, which comprises the following steps: preparing a three-dimensional fiber preform, phthalonitrile resin pouring, cutting processing and aluminum wire removal; and the bearing / heat-proof integrated ordered porous sweating composite structure comprises an ordered porous sweating structure, a cooling working medium flow cavity and a cooling working medium storage tank, the ordered porous sweating structure is a bearing part of a component main body, and the ordered porous sweating structure is provided with a micropore flow channel for sweating cooling; the ordered porous composite material sweating structure of the application can have higher bearing capacity while the sweating cooling performance is considered, and the specific strength is far higher than that of the commonly-used metal and ceramic sweating materials; the bearing and sweating structure functions are simultaneously realized; the hierarchical structure of the sweating structure can be reduced, the overall thickness of the sweating system is reduced, and the negative weight of the aircraft is greatly reduced.

The invention relates to the technical field of rail transit, and provides a composite material high-speed train head mold and a molding method, and the molding method of the composite material high-speed train head comprises the following steps: S1, raw material preparation, mold and tool preparation; s2, laying a prepreg layer; s3, curing the prepreg; s4, demolding; s5, finishing is conducted; s6, glue joint assembly is carried out; comprising the steps of metal embedded part gluing and gluing of a headstock outer shell and a headstock inner shell. On the basis of reducing the weight of the mold, the air tightness is guaranteed, demolding is facilitated, and the prepared headstock is high in specific strength and specific stiffness, good in designability, excellent in impact resistance, fireproof performance, corrosion resistance and fatigue resistance and suitable for large-scale production. The problems that a metal high-speed train head is poor in corrosion resistance and fatigue resistance, and a head formed through a conventional wet method such as hand lay-up forming is low in strength and poor in thickness and size stability are solved.

The invention discloses a preparation method of an aero-engine composite material fan blade in the technical field of composite material molding, and the preparation method comprises the following steps: S1, providing a carbon fiber reinforced epoxy resin prepreg and cutting to obtain a prepreg sheet; s2, after the blade paving mold is cleaned, the surface of the blade paving mold is coated with a release agent, and mold preparation is completed; and S3, a shape-following pressing mold matched with the molded surface of the upper surface of the blade is manufactured, and the shape-following pressing mold is subjected to layer laying and vacuum compaction and then is cured and formed. The T800-grade high-strength one-way and plain carbon fibers are selected as reinforcements and the high-temperature epoxy resin is selected as a matrix to prepare the prepreg, and the 1500D aramid fiber lines are adopted to carry out X-shaped Z-direction sewing on the laminated blade blank, so that the specific strength, the specific stiffness and the interlayer shear strength of the blade are effectively improved, the problem that a traditional laminated plate is easy to layer is solved, and the production efficiency is improved. And the requirements of light weight and high performance of the blade are met.

The invention discloses a low-density high-specific-strength rare earth aluminum alloy and a preparation method thereof, and belongs to the technical field of aluminum alloy materials. The aluminum alloy is prepared from the following components in percentage by mass: 3 to 5 weight percent of Zn, 3 to 6 weight percent of Mg, 0 to 1.5 weight percent of Cu, 0 to 0.2 weight percent of rare earth element, 0.08 to 0.12 weight percent of Mn, 0.03 to 0.05 weight percent of Cr, 0.05 to 0.07 weight percent of Ti and the balance of Al and inevitable impurities. The preparation method comprises the steps of smelting and casting, hot rolling, solid solution heat treatment, quenching, stretching and subsequent aging heat treatment. The Zn / Mg ratio is cooperatively regulated and controlled to reduce the density, rare earth elements and Zr are introduced for microalloying, grains are refined, a nanoscale dispersed phase is formed, an optimized step solid solution and two-stage aging heat treatment process is adopted, the material density is reduced to 2.69 g / cm < 3 > or below (reduced by about 5% compared with a traditional 7xxx system), meanwhile, the tensile strength is kept at 475-505 MPa, the specific strength is excellent, and the service life is long. And meanwhile, the fracture toughness and corrosion resistance are remarkably improved, and the material is suitable for the fields of aerospace, rail transit and the like for material lightweight and has outstanding practicability and industrialization value.

The invention discloses a preparation method for winding and forming a combined type inclusive casing prepreg in the technical field of composite material forming. The preparation method comprises the following steps: S1, processing a metal casing: processing a molded surface, a mounting edge and an end surface hole in a metal casing blank; s2, prepreg preparation: providing a prepreg prepared from a fiber reinforcement and a resin matrix, and slitting the prepreg into narrow strips; s3, winding and intermediate curing: winding the prepreg narrow strip on the outer surface of the metal casing to form a composite material layer; when the winding thickness reaches a set threshold value, the winding body is subjected to pre-curing treatment; the TC4 titanium alloy is selected as the metal substrate, the Hyplon high-strength high-modulus polyimide fiber and the B2501 bismaleimide resin are used for preparing the composite material layer, a traditional pure titanium alloy structure is replaced, the overall mass of the combined type inclusive case is effectively reduced, meanwhile, the specific strength, the impact resistance and the corrosion resistance of a product are remarkably improved, and the service life of the combined type inclusive case is prolonged. And the dual requirements of light weight and high performance of the aero-engine are perfectly met.

The invention provides an interlayer pressure-resistant shell structure and a processing method thereof, and relates to an underwater vehicle structure, the interlayer pressure-resistant shell structure comprises an inner-layer shell, an outer-layer shell and a middle interlayer located between the inner-layer shell and the outer-layer shell, and the middle interlayer comprises hollow glass beads, reinforced fibers and epoxy resin. The spherical hollow glass beads and the reinforced fibers are uniformly mixed in the epoxy resin, are jointly placed between the inner-layer shell and the outer-layer shell in a flow state form, and are vacuumized and cured to form the buoyancy material between the inner-layer shell and the outer-layer shell; the pressure-resistant shell is used for solving the problems that in the prior art, the bearing capacity of a pressure-resistant shell of an underwater vehicle is not fully exerted, and the specific strength and the specific stiffness are not high.

The utility model provides a kind of carbon fiber roller, including pipe body, inner flange, outer flange, pipe body includes inner end and outer end, inner flange is installed in inner end, and outer flange is installed in outer end;The pipe body is carbon fiber pipe body, and the pipe wall of carbon fiber pipe body is equipped with punching part, and carbon fiber roller realizes significant light weight and high specific strength simultaneously, and the layout of vent hole of punching part is optimized to balance ventilation efficiency and structural strength.

The invention discloses a wave-transparent high-strength ablation-resistant element hybrid branched nano aerogel composite material and a preparation method thereof, the material takes boron / zirconium hybrid branched polysiloxane as a matrix, a sol-gel method is combined with a resin transfer molding process, and an inorganic fiber reinforced part and a nanoscale functional filler are subjected to multi-scale compounding. By regulating and controlling various reaction factors, complete molding of the material under a normal-pressure drying process is realized, a nanoscale porous network structure is successfully constructed, and large-scale production can be realized. The composite material has the following characteristics: the wave transmission performance is excellent, and the dielectric constant in the frequency band of 8-20GHz is less than or equal to 3.0; the extreme ablation resistance is high, and the structural integrity is still kept after the material is ablated by oxyacetylene flame at 1650 DEG C for 30 minutes; the comprehensive performance is outstanding, the density is low, the specific strength is high, and the heat insulation property is excellent.

This invention discloses a method for preparing a high-strength, high-modulus carbon fiber ultrathin prepreg, comprising: spreading high-strength, high-modulus carbon fibers to obtain flat fiber bundles, then stacking and pressing them with a resin film placed above and below them; under the action of temperature and pressure, allowing the resin to fully impregnate the fiber bundles; and then cooling, coating, and winding. The high-strength, high-modulus carbon fiber is one of M40X, M55J, M60J, or higher grade carbon fibers, with a tensile modulus >377 GPa. This invention also discloses the high-strength, high-modulus carbon fiber ultrathin prepreg prepared by the above method and its applications. The spreading roller surface used in this invention is made of polytetrafluoroethylene, and the limiting roller surface is made of ceramic, solving the problems of easy fuzzing and fiber breakage of high-strength, high-modulus carbon fibers, and avoiding corrosion between carbon fibers and metals. The prepreg prepared by this invention has advantages such as high specific strength, high specific modulus, corrosion resistance, and stable structural dimensions, and has broad application prospects in aerospace and other fields.

The embodiment of the invention provides a defect metamaterial and a preparation method thereof, and relates to the technical field of metamaterial manufacturing. The method comprises the following steps: based on an initial TPMS (Tire Pressure Monitor System) structure, constructing an initial triangularization grid limited by a predetermined straight line segment in a tetrahedron; by introducing new vertexes and increasing boundary straight line segments, the defect level of the grid is improved, and a plurality of non-overlapping triangular patches formed by connecting the original vertexes and the new vertexes are formed; performing iterative evolution and Bonnet rotation on the grid according to an energy criterion to obtain a TPMS conjugate surface limited in a tetrahedral cell element; and generating a TPMS unit cell structure along the surface of the basic tetrahedron in a mirror symmetry manner by utilizing the symmetry of the initial structure. According to the method provided by the embodiment of the invention, the specific stiffness and specific strength of the deficient metamaterial under low density are remarkably improved, the industrial problem that the mechanical property of the deficient metamaterial is sharply attenuated along with the reduction of the density is solved, and the process bottleneck that residues such as uncured resin / unsintered powder are difficult to discharge in additive manufacturing is thoroughly solved.

The present application relates to a kind of high specific strength 3D printing aluminum alloy and its preparation method, by adding Mg and Li element not only can reduce the density of aluminum alloy, can also with Mn, Sc, Zr, Ti, Er and Yb element together play the role of strengthening, to improve the specific strength of aluminum alloy.In addition, the present application first prepares near-spherical aluminum alloy powder with low impurity content by gas atomization method, then utilizes the technical advantage that 3D printing rapid solidification can significantly expand the solute element solid solution limit, then cooperates with the advantages of double-stage aging heat treatment of dry ice cooling and combines multi-element microalloying, inhibits the coarsening of incoherent precipitate phase, realizes the step-by-step regulation of nanoscale coherent precipitate phase and submicron incoherent strengthening phase composition and organization, and improves the specific strength of aluminum alloy.

The utility model relates to vehicle technical field discloses a kind of threshold beam structure and carrier, comprising: threshold beam body, along first direction setting, its inside has cavity;Reinforcing member, be located in cavity, and extend along first direction, its material is composite material;Energy-absorbing member, it is circumferentially arranged around reinforcing member, and is located between reinforcing member and threshold beam body, and energy-absorbing member is connected with threshold beam body. Composite material reinforcing member is used instead of traditional threshold beam inside metal reinforcing structure, utilize the characteristics of high specific strength, high specific stiffness of composite material, can be while greatly reducing threshold beam weight, enhance threshold beam structure performance, realize whole car light weight design, improve vehicle endurance, and energy-absorbing member circumferentially arrangement around reinforcing member, when vehicle side collision occurs, collision energy can be effectively absorbed, avoid threshold beam stress to occur serious deformation, guarantee vehicle safety performance, realized to the effective lateral collision protection of passenger cabin and chassis below battery pack.