171results about How to "High specific stiffness" patented technology

The invention provides a high-plasticity aluminum-based composite material containing TiB2 particles and a preparation method thereof, and relates to an aluminum-based composite material and a preparation method thereof. The invention solves the problems of the prior art, such as poor plasticity and toughness and difficulty in secondary processing. The composite material contains (by volume) titanium diboride reinforcement particles 10-25 percent, aluminum particles 25-35 percent, and aluminum alloy matrix in balance. The preparation method comprises: (1) weighing titanium diboride reinforcement particles, aluminum particles and aluminum alloy matrix; (2) mixing by mechanical dry method to obtain a reinforcement powder; (3) placing the reinforcement powder in a die and compression-molding; (4) heating the die; (5) melting aluminum alloy and casting in the die; (6) applying a pressure on the die with molten aluminum and maintaining the pressure for a period of time and cooling; (7) demoulding and taking the cast ingot, that is reinforced aluminum-based composite material. The inventive aluminum-based composite material has high plasticity and good wear resistance and is adapted to secondary processing and machining.

A manufacturing method of a carbon fiber metal composite laminated plate relates to a manufacturing method of a fiber metal composite laminated plate. The method aims at solving the problems that no manufacturing methods for manufacturing aircraft structural material with high specific stiffness, high specific strength, tenacity and workability exist in China. The method comprises the following steps of: carrying out surface treatment to three pieces of metal plates; winding a carbon fiber composite material layer which is soaked in liquid cement on one of the metal plates, wherein, the liquid cement is prepared by epoxy resin, a metaphenylene diamine curing agent and an anhydrous alcohol solvent according to the mass ratio of 1:0.1 to 0.18:0.15 to 0.2; fixedly arranging another two metal plates on the upper surface and the lower surface of the carbon fiber composite material layer so as to be integrally put into a mould, and then treated with mould assembling, drying, solidification by adopting the method of gradient temperature increasing, and demoulding. The manufacturing method of the invention is simple and is easy for operation. The carbon fiber metal composite laminated plate manufactured by the method of the invention has the advantages of high specific stiffness, high specific strength, also high tenacity and workability of metal material, good fatigue property, and good damage tolerance capability.

The invention provides a sandwich energy-absorbing device which comprises an upper panel, a lower panel, lateral plates and a core plate layer, wherein the core plate layer is fed in a closed space formed by enclosing the upper panel, the lower panel and the lateral plates, and the core plate layer comprises core materials and a shear thickening fluid material fed between the core materials and/or fed between the core materials and the closed space. When an energy-absorbing device suffers from an action an external impact, structures of the upper panel, the lower panel, the lateral plates and the core materials rapidly deform, so that a quick shear action is applied to the shear thickening fluid material fed in a core plate, the viscosity of the shear thickening fluid material with a relatively high shear strain rate is rapidly improved, and thus impact energy is rapidly dissipated, and relatively high specific strength, specific stiffness and vibration resistance and energy absorption capabilities are achieved.

The invention aims at disclosing a specially-made vacuum smelting furnace and a preparing technology for a SiC particle enhanced aluminum-base composite material. A certain component proportion and a special smelting casting technology are adopted. The vacuum smelting furnace is adopted in the technology, overall closing and vacuum-state charging can be achieved, the inner temperature of melt can be measured in real time, the particles accurately fall into a melt vortex center with a certain speed and are evenly distributed in the melt under powerful stirring, the functions of deoxygenation and degassing can be effectively achieved on the composite material melt, and therefore the composite material uniform in component, low in porosity, high in mechanical performance and excellent in heat-conducting property can be produced through the technology. The crucible lifting type vacuum smelting furnace comprises a crucible composite device and lifting platform system, a stirring device and lifting platform system, a charging device, a vacuum system, a handheld lifting thermocouple, a sealing system and an electric control system.

The invention discloses a light multifunctional composite structure. The composite structure comprises a first outer surface plate, a second surface plate, a metal foam sandwich layer and a honeycomb sandwich layer, wherein the metal foam sandwich layer and the honeycomb sandwich layer are arranged between the first outer surface plate and the second surface plate, and the honeycomb sandwich layer is hexagonal aluminum honeycombs or square aluminum honeycombs. According to the sandwich structure through the composition of metal foams with the hexagonal aluminum honeycombs or the square aluminum honeycombs, the weight can be obviously reduced, and a plurality of functions such as load bearing, sound absorption, sound and heat insulation and shock resistance are provided.

The invention discloses a preparation method for a shell-nacreous-layer-imitating magnesium-based composite material. A SiC particle reinforced magnesium-based composite material of a distinct shell-nacreous-layer structure can be prepared through the preparation method. A shell-nacreous-layer microstructure serves as a model, and a directional freeze thawing ice template method and a laminated hot pressing technique are adopted for preparing a biomimetic SiCp/Mg composite material with distinct shell-nacreous-layer microstructure characteristics and a controllable organizational structure. According to the novel preparation technique for biomimetic metal-based composite materials, the route is unique and the production efficiency is high. Compared with traditional magnesium-based composite materials, the prepared magnesium-based composite material of the shell-nacreous-layer-imitating structure not only has good mechanical properties such as high specific strength, high specific stiffness, good abrasion resistance, but also has good toughness and plasticity.

A mainshaft head mechanism with parallel three shafts for performing multi-direction vertical and horizontal machining is composed of a fixed platform, threerotary sets distributed by 120 deg and connected to said fixed platform, three moving sets respectively linked to the rotay sets, three rod sets respectively linked to three moving sets, three spherical sets respectively linked to three rod sets, movable platform, and mainshaft unit installedon said movable platform. Said mainshaft unit can do longitudinal movement along Z axis and rotations around A axis and B axis.

The invention relates to a truss type ultralight overall wing structure, and belongs to the technical field of aircraft structure design. The truss type ultralight overall wing structure includes a front beam, a back beam, at least two wing ribs, a hard skin and a flexible skin, wherein the front beam and the back beam are in parallel and are arranged in the flight direction; each wing rib includes a front wing rib and a back wing rib, the front wing ribs are arranged between the front beam and the back beam, the back wing ribs are fixed to the front beam and provided with wing-shaped camberedsurfaces, and the wing ribs are in parallel. The hard skin is installed on the windward side between the front beam and the leading edge of a wing. The hard skin is provided with a wing-shaped cambered surface. The flexible skin is installed on the front beam, the back beam and the hard skin in a paved mode to maintain aerodynamic configuration. According to the truss type ultralight overall wingstructure, a novel layout mode of 'thin film skin-sandwich skeleton' is put forward in layout, and strict weight index requirements are met on the basis of meeting requirements of strength and rigidity.

The invention discloses a dot matrix sandwich structure of a wooden engineering composite material. The dot matrix sandwich structure comprises a panel I (1), a core layer (2) and a panel II (3), wherein the panel I (1), the core layer (2) and the panel II (3) are formed by gluing through joggle joint; the core layer (2) comprises a dot matrix structures (4) and fillers filling the dot matrix structures (4); partial enhancement is performed through gluing of an adhesive by using a fiber reinforced material; the dot matrix structures (4) are periodically distributed on the core layer according to reasonable unit specification design. The dot matrix sandwich structure can bear high static load and cyclic load for a long time, is light in weight, high in specific strength and high in specific stiffness, endows the wooden engineering composite material with multifunctional characteristic and can be widely applied to the fields of constructional engineering, vehicle engineering, bridge engineering and the like requiring structure load and multifunction.

The invention discloses a multielement-enhanced heat-resistant corrosion-resistant magnesium alloy and a manufacturing method of the multielement-enhanced heat-resistant corrosion-resistant magnesium alloy. The ingredients of the multielement-enhanced heat-resistant corrosion-resistant magnesium alloy comprise pure magnesium ingots, pure zinc ingots, Mg-Gd alloy, Mg-Y alloy, Mg-Nd alloy, Mg-Ca alloy, Mg-Zr alloy and nanometer-scale NdN particles. The elements in the raw materials comprise, by mass, 3.5-5.0% of Gd, 1.0%-3.0% of Y, 0.5%-0.8% of Nd, 0.8%-1.5% of Zn, 0.3%-0.8% of Ca, 0.3%-0.6% of Zr, 0.5%-1.5% of nanometer-scale NdN particles and the balance Mg. The sequence of the mass percentage contents of the three rare earth elements of the Gd, the Y and the Nd from large to small is Gd>Y>Nd, and the mass percentage of the total addition amount of the three rare earth elements of the Gd, the Y and the Nd does not exceed 10%. The particle size of the nanometer-scale NdN particles is 80-150 nm. The steps of pretreatment and cladding of the NdN particles, preheating of the ingredients, smelting, refining, doping, pouring, sectioned solution treatment and artificial aging treatment are sequentially conducted, and then the fine, dispersive nanometer-precipitated-phase microscopic-structure heat-resistant corrosion-resistant magnesium alloy product is obtained. By the adoption of the multielement-enhanced heat-resistant corrosion-resistant magnesium alloy and the manufacturing method of the multielement-enhanced heat-resistant corrosion-resistant magnesium alloy, the manufacturing cost is low, and the heat resistance and corrosion resistance of the magnesium alloy are excellent.

The invention relates to an aluminum base composite material, in particular to an aluminum base carbon fiber graphite composite material and a preparation method. The method comprises the following steps of: firstly, adopting finely sorted, processed and checked graphite fluoride powder as raw materials for preparing spherical graphite particles through granulation and spheroidization; then, using a stainless steel plate as a cathode and pure aluminum as an anode, filling insert gas between the two electrodes, exerting voltage, soaking the spherical graphite particles by glucose amide containing 0.23 to 0.6 percent of boron, cleaning and baking the spherical graphite particles, placing the spherical graphite particles on a disc between the cathode and the anode, shaking the disc while exerting the voltage, and arranging latticed high-performance carbon fiber in a casting mold at the arrangement density determined according to the intensity requirement of the materials; filling the spherical graphite particles with the diameter between 1 and 5mm in the casting mold, finally, injecting aluminum liquid, applying pressure at the upper part of the mold so that the aluminum liquid can be filled between the spherical graphite particles, and obtaining products after cooling. The composite material is simple to prepare, and has the advantages of high product intensity, light weight, wear resistance, low raw material consumption and high production efficiency.

The invention relates to a metal-based foam-filling low-frequency broad-band-gap elastic metamaterial. The elastic metamaterial adopts a metal material as a matrix sheet material. Multiple round holes are arranged in the matrix sheet material in an array manner. Each round hole is filled with a foamed aluminium material to form a filling unit. Each filling unit is adhered to a local resonance unit. Each local resonance unit comprises two pairs of cylinders which are symmetrically arranged at two edges of the filling unit and are on the same straight line with the center of circle and the filling unit. The elastic metamaterial meets requirements for structural intensity and rigidity. A theoretical model of a prepared test piece has three complete band gaps in a low frequency range of below 500Hz and has a curved vibration band gap with the width of 400Hz. The lower boundary of the band gap is 66Hz. The metamaterial can be used for achieving low frequency broadband vibration noise control of a naval ship structure, and is significant for application of the elastic metamaterial in engineering vibration damping and noise reduction and naval ship acoustic stealth.

The present invention relates to collision-proof safety material, and is especially composite laminated foamed aluminum/resin/aluminum alloy material and its preparation process. The composite material is used in automobile bumper, casing and other parts. The composite material is prepared with type-LY12 aluminum alloy plate and foamed aluminum in the thick ratio of 1 to 3-5 as well as filled PC resin and through hot pressing curing process. The present invention has excellent impact performance, no technological problem of painting on the surface of aluminum alloy, simple technological process, small density, high specific strength, high specific rigidity, high performance/cost ratio and flexible performance design.

Disclosed is a strain-induced semi-solid forming process and die for magnalium mobile phone shells. The process includes cutting a magnalium plate with certain compressive deformation into the suitable size, performing semi-solid heat preservation on the cut magnalium plate, and then putting the obtained magnalium plate with semi-solid characteristics into the preheated die for extrusion forming. The die comprises a mobile phone shell bottom cavity die device, the upper side of the mobile phone shell bottom cavity die device is connected with a mobile phone shell top terrace die device, die guide rods are assembled on the mobile phone shell top terrace die device, a left mobile phone shell core-pulling slider is connected to the left of the mobile phone shell bottom cavity die device, a right mobile phone shell core-pulling slider is connected to the right of the mobile phone shell bottom cavity die device, and mobile phone shell ejection mechanism is connected to the lower side of the same. The magnalium mobile phone shells with superior performance can be produced, and the process and the die have the advantages of simple process, high forming speed, low cost and the like.

The invention provides a hybrid propulsion cabin of a small high-orbit satellite common platform. The hybrid propulsion cabin comprises a platform cabin main force-bearing structure configured to provide an accommodating space, wherein the platform cabin main force-bearing structure comprises a satellite-rocket connecting ring; a plurality of storage tanks which are arranged in the accommodating space and are directly loaded on the satellite-rocket connecting ring; and an air path assembly which is arranged in the accommodating space so that the load of the air path assembly is transmitted tothe satellite-rocket connecting ring through the platform cabin main force bearing structure.

The invention is concerned with the manufacture method of polyester elastomeric foaming plate that is with damping action, the characteristics is: the polyester elastomer is as the material, uses the microcapsule vesicant or the microcapsule vesicant mother grain to make the foaming plate by the extruder and the mould forming.

The invention discloses a foam steel board shear wall structure. The foam steel board shear wall structure comprises steel beams and steel columns, wherein the steel beams and the steel columns are connected through beam column joints; foam steel boards are installed between the adjacent steel beams and the adjacent steel columns to form a shear wall steel board; the two sides of the foam steel boards are connected with the steel beams through horizontal angle iron; the two sides of the foam steel boards are connected with the steel columns through vertical angle iron; the foam steel boards and the horizontal angle steel are fastened and connected through transversely distributed vertical bolts; the horizontal angle steel and the steel beams are connected through transversely distributed parallel bolts; the foam steel boards and the vertical angle steel are connected through vertically distributed perpendicular bolts; the vertical angle steel and the steel columns are connected through vertically distributed parallel bolts. The foam steel board shear wall structure can overcome the defects of an ordinary steel board shear wall, can be prevented from buckling failure, and has the advantages of being large in lateral rigidity, good in anti-seismic property, high in ductility, full in energy consumption hysteresis hoop and the like.

The invention discloses a support method for an aircraft model in a wind tunnel experiment. The method includes the following steps: 1) a wind tunnel and an aircraft model in the wind tunnel are connected and fixed through a spatial rod system, and the wind tunnel is not in direct contact with the aircraft model; and 2) according to requirements of experimental measurement and support system design, the diameter, length, number, material and spatial distribution form of support rods in the spatial rod system are adjusted, thereby realizing optimization of rigidity of an aircraft model supportsystem. By adoption of the support method provided by the invention, the support system further adapts to and meets the requirements of wind tunnel experiment content and measurement, thereby achieving the purpose of improving precision and reliability of pneumatic experiment data, and effectively solving the problems of insufficient rigidity, large flow field interference and complicated system internal force of a support system in a traditional support method, and the support method provided by the invention has obvious advantages and potential of innovative development in the aspect of a wind tunnel experiment, particularly in the aspect of a full-size large-model pneumatic experiment.

The invention belongs to the technical field of aluminum profiles, and particularly relates to an L-shaped edge sealing aluminum profile. The L-shaped edge sealing aluminum profile comprises a fixed bottom plate and a side baffle. The side baffle is fixed to the side of the fixed bottom plate. The L-shaped edge sealing aluminum profile is characterized in that a damping cavity is formed in the fixed bottom plate, and a sandwich layer is inserted into the damping cavity; the sandwich layer adopts a closed-hole foam aluminum material, one end of the sandwich layer is uniformly provided with a plurality of inserting cavities, and inserting cross beams are arranged in the plurality of inserting cavities; the other end of the sandwich layer is uniformly provided with a plurality of inserting blocks, and the inserting blocks are made of foam aluminum materials; the plurality of inserting blocks are correspondingly inserted into the plurality of inserting cavities, sliding clamping grooves are formed in the two sides of the plurality of inserting blocks, and the sliding clamping grooves are in sliding inserting fit with the inserting cross beams; and a stepped hole is formed in the lateral side of the fixed bottom plate; threaded holes are formed in the plurality of inserting cavities; fixing bolts are connected in the threaded holes in a threaded manner; and the rigidity and firmnessof the splicing positions of spliced edge sealing aluminum profiles are improved, and the overall weight of the edge sealing aluminum profiles is reduced.

The invention discloses a reinforcing method for a bonding interface of an MgFe compound casting. The reinforcing method comprises the following steps: (1) preparing a Fe-based dot matrix material onthe bonding surface of a Fe-based material by adopting a selective laser melting technology; (2) processing the surface of the dot matrix material by adopting a chemical deoiling-pickling and passivating-chemical electroless copper plating process; and (3) fixing the Fe-based material in a cast, pouring a magnesium alloy melt in the cast, and carrying out ultrasonic oscillating treatment in the casting process to achieve firm bonding of Mg and Fe. Different from a conventional plane combining mode, the reinforcing method provided by the invention is high in bonding strength, the bonding interface is unlikely to fall, and firm bonding between Mg and Fe is achieved. In addition, no complicated equipment is needed, and parameters are easily controlled.