39 results about "Composite skin" patented technology

The application discloses a flexible metal composite skin structure capable of regulating local out-of-plane deformation and belongs to the technical field of metal skin structures. The application introduces a paper-cut structure on the surface of a metal skin, regulates mechanical response by changing characteristic parameters such as a paper-cut pattern and a metal skin thickness, so that the structure has high ductility and small plastic deformation characteristics, and the structure can recover to original deformation after the expansion of a protrusion of a driving device, thereby ensuring the continuity of a wing aerodynamic shape. The application meets the basic requirements of application to a flexible skin of a deformation wing, provides a feasible selection for the fusion of a gasbag anti-icing mechanism and a deformation wing, and is expected to be widely applied in the fields of aircraft deicing, spacecraft deicing and deformation wings.

The application provides a carbon-glass hybrid composite material skin for an aircraft and a preparation process thereof, and relates to the technical field of aircraft accessories.A carbon-glass hybrid composite material skin for an aircraft, the material of the skin is a mixture of carbon fibers, glass fibers and resin, and the skin is an integrally formed structure; the mass percentage of the mixture of carbon fibers and glass fibers ranges from 60% to 70%, and the mass percentage of the resin ranges from 40% to 30%; the skin is provided with a non-thickened area and a thickened area.The application solves the technical problems of the prior art, such as the heavy weight of the aircraft skin made of metal material, the complex structure design, the poor impact resistance and stability of the product during use.The material of the skin is a mixture of carbon fibers, glass fibers and resin, and the skin is integrally formed, so that the weight is light and the overall structural strength is improved.

This invention relates to a semi-mounted composite skin frame hull structure. A first, second, third, fourth, and fifth lower arc frame are all located below the left and right main beams and are fixedly connected to them. These lower arc frames are arranged sequentially from the front docking frame to the rear docking frame. A first, second, third, fourth, and fifth upper arc frame are all located above the left and right main beams and are fixedly connected to them. These upper arc frames are arranged sequentially from the front docking frame to the rear docking frame. This invention provides a clear force transmission path, ensuring the hull structure meets strength and rigidity requirements under various working conditions and loads, enabling rapid installation of the warhead, while simultaneously meeting design weight requirements.

The invention discloses a flexible metal composite material skin structure capable of regulating and controlling local out-of-plane deformation, and belongs to the technical field of metal skin structures. The paper-cut structure is introduced to the surface of the metal skin, the mechanical response of the paper-cut structure is regulated and controlled by changing characteristic parameters such as a paper-cut pattern and the thickness of the metal skin, so that the structure has the characteristics of high ductility and small plastic deformation, and the structure can recover to original deformation along with retraction of the driving device after expanding and protruding along with the driving device; and the aerodynamic configuration continuity of the wing is ensured. Basic requirements of flexible skin applied to the deformable wing are met, a feasible choice is provided for fusion of an air bag anti-icing and deicing mechanism and the deformable wing, and the method is expected to be widely applied to the fields of aviation, spacecraft deicing, deformable wings and the like.

The invention discloses a large-size rotary cylinder which comprises an outer wall and an inner wall of a cylindrical structure with a wing-shaped section, and two groups of corresponding ends of the outer wall and the inner wall are connected; the outer wall is defined by sequentially connecting a plurality of outer wall sections, the inner wall is defined by sequentially connecting a plurality of inner wall sections, and the outer wall sections and the inner wall sections are both of a sandwich structure formed by wrapping a foam core material with composite skin; and a first parting surface between the two outer wall sections and a second parting surface between the two inner wall sections are staggered from each other. The composite material barrel is applied to the field of composite material barrels, so that the barrel has higher structural strength and axial deformation resistance, other auxiliary supporting devices are not needed except that the bottom of the barrel needs to be supported by a fixed base, the occupied space is greatly saved, and the assembly difficulty is reduced.

The application discloses a kind of composite skin care active raw materials and preparation method thereof, belong to cosmetic raw material technical field.The composite skin care active raw material includes by mass percentage: anti-sugar active component 1.0%-10.0%, firming and lifting active component 0.5%-8.0%, antioxidant active component 1.0%-4.0%, penetration promoting component 0.5%-2.0%, and the balance is cosmetic grade solvent.The application realizes the four synergistic effects of anti-sugar, firming, antioxidant and penetration promotion by compounding multiple active components at a specific ratio, the system is stable, not delaminated, not discolored, skin feels fresh, the preparation process is mild and simple, easy to industrial production, and can be widely used in essence, emulsion, cream, mask and other skin care products.

The present application relates to a kind of preparation methods of low odor low VOC composite skin, mainly solve the problem of existing technology in the composite skin of automobile interior smell, VOC is high.The present application is by using a kind of preparation method of low odor low VOC composite skin, including the following steps:1) gas and air after drying respectively into gas buffer tank, air buffer tank;2) from the gas buffer tank of gas after pressure control into mixer;3) from the air buffer tank of air after pressure control into mixer;4) control gas and air flow rate adjust the volume ratio of gas and air in mixer, obtain uniform mixed gas;5) mixed gas enters the gas purification device with molecular sieve type adsorbent, obtain purified mixed gas;6) purified mixed gas enters flame compound machine and carries out flame compound, obtain the technical scheme of low odor low VOC composite skin, preferably solve the problem, can be used in the industrial production of automobile interior composite skin.

Stretchable shape-memory polymer composite skin with a Poisson's ratio of zero, comprising the following parts: a main body made of conductive fibers; several metal frames made of metallic aluminium material, arranged under the main body, from which the electrical power is transferred to the main body; and a multitude of reinforcing elements made of synthetic resin or plastic material, each connected at intervals to the lower part of the main body by the several metal frames, the temperature in the main body can change based on the electrical power transmitted by the multiple metal frames.

The invention relates to a laminated structure multi-partition electric heating composite material skin and a preparation method thereof. The preparation method of the laminated structure multi-partition electric heating composite material skin comprises the steps that a layer of resin film is laid on the surface of a heating assembly, the resin film adopts a resin system the same as that of the skin, vacuum prepressing is conducted for 10-60 min at the temperature of 60-80 DEG C, and a heating film is obtained; the heating films of all the partitions are laid and pre-compacted on different side faces of a layer of standard prepreg, and an integrated multi-partition prefabricated heating layer with the determined position relation is formed; wave-transparent bearing skin prepreg, the prefabricated heating layer and outer-layer wave-transparent skin prepreg are laid on a mold in sequence, co-curing is conducted through a vacuum bag-autoclave system, and the overall skin structure is formed. The technical problems that in the prior art, three-dimensional projection positioning is not accurate, the relative positions of heating partitions are not accurate due to the fact that accumulated errors of layer-by-layer paving are large, gaps or overlapping exist in heating covering, and molded surfaces protrude due to electrode overlapping can be solved.

This invention relates to a method for connecting a composite material skin to a truss; a prefabricated component for connection to the truss is fabricated, the prefabricated component including a connecting part and a locating part, the connecting part including a first connecting segment and a second connecting segment; a fiber-reinforced fabric is cut according to the cross-sectional area of ​​the connecting part and laid on the truss to form a first composite material skin; a second connecting segment passes through the first composite material skin and is fixed to the truss; a fiber-reinforced fabric is cut according to the shape of the locating part and laid on the first composite material skin to form a second composite material skin; a third composite material skin and a fourth composite material skin are laid on the second composite material skin and cured to complete the connection between the composite material skin and the truss; by integrally molding the composite material skin with the prefabricated component, the technical problems of fastening the composite material skin to the truss with screws or rivets, requiring hole machining, resulting in deformation in local areas of the skin, failure of related connections under overload, and skin detachment are solved.

The invention discloses a bionic polypeptide nano-composite skin permeation carrier and a preparation method thereof. According to the carrier, a biodegradable high polymer material is used as a nano core, hydrophobic active ingredients are loaded, and a nano composite system with a bifunctional bionic shell is formed through covalent immobilization of bionic cell-penetrating peptide and biological adhesion peptide. The preparation method comprises three steps of oil / water emulsification volatilization nucleation, peptide coupling modification and freeze drying. The obtained carrier has the characteristics of actively penetrating a skin barrier and long-acting residence, the encapsulation efficiency reaches 85% or above, the steady-state transdermal rate is increased to 3.7 micrograms / cm < 3 > / h, and the drug leakage rate is lower than 7% after the carrier is stored for 30 days. By simulating the natural mechanism of skin permeation and adhesion, efficient encapsulation, steady-state release and deep delivery of active ingredients are realized, and the preparation method is suitable for the fields of transdermal drug delivery, skin repair, beauty and the like, and has good application prospects and industrialization potential.

In a method for manufacturing an aircraft panel that has a composite skin with integrated components (stringers / frames) having unsupported slots, a male tool with the integrated component is obtained. The composite skin is laid up directly over the unsupported slots of the integrated component with an automated fiber placement, AFP machine that provides tow deposition The integrated components lack auxiliary support tools. A force applied to the tow with the AFP machine is adjusted during deposition over the unsupported slots to compensate the lack of auxiliary support tools.

The utility model discloses a composite material stringer which is fixed on a fuselage wall plate, the stringer is made of carbon fiber reinforced epoxy resin composite materials, the cross section of the stringer is of a cap-shaped structure, the cap-shaped stringer cross section is provided with four corners, and the four corners comprise two lower stringer internal corners and two upper stringer external corners. A plurality of triangular reinforcing ribs are arranged on the inner sides of the two stringer external corners at intervals, no triangular reinforcing ribs are arranged on the inner sides of the two stringer internal corners, and a pre-deformation area is formed between the stringer internal corners and the fuselage wall plate. The triangular reinforcing rib is designed on the inner side of the external corner of the stringer, and the pre-deformation area is formed between the internal corner of the stringer and the fuselage wall plate, so that the bending rigidity of the fuselage wall plate in the width direction can be increased, and the bending deformation of the composite material skin in the width direction is limited in the curing forming process; and the deformation resistance of the fuselage wall plate in the width direction in use is improved.

The utility model discloses a small unmanned aerial vehicle composite skin forming tool, and relates to the technical field of aviation. The small unmanned aerial vehicle composite skin forming tool comprises a frame, a template and a connecting cushion block are installed on the frame, and the template and the frame are connected through the connecting cushion block, so that different models of templates can be installed on the frame, and the template and the frame are convenient to assemble and disassemble; the shape of the connecting cushion block can be correspondingly adjusted according to the shapes of the templates of different models, so that the novel template can be conveniently connected with the frame. According to the composite skin forming tool for the small unmanned aerial vehicle, the bottom frame and the template are connected through the connecting cushion blocks, so that after the structure of the small unmanned aerial vehicle is changed, it can be guaranteed that the bottom frame and the template are convenient to disassemble and assemble, the frame can be directly connected with a newly-manufactured template, only a small number of connecting cushion blocks need to be manufactured, and good economical efficiency is achieved; the movable insert is arranged on the template, so that the product can be smoothly demoulded when a negative angle exists.

The invention relates to a method for manufacturing an aircraft panel and an aircraft panel. The invention relates to a method for manufacturing an aircraft panel comprising a composite skin (240) and a one-piece component (220) (stringer / frame) having an unsupported slot (220a), the method comprising: obtaining (110) a male tool having the one-piece component (220); laying (120) the composite skin directly over the unsupported slots of the one-piece component (220) using an automatic fiber placement, i.e., AFP machine, that provides tow deposition, where the one-piece component (220) is free of auxiliary support tools; and adjusting (130) a force applied to the tow with the AFP machine during deposition over the unsupported tank to compensate for the absence of the auxiliary support tool.

The present application relates to the technical field of skin bag material, and particularly relates to a weather-resistant elastic composite skin bag material and a preparation method thereof, which is prepared from the following components: 65-85 parts of elastic matrix resin, 10-20 parts of elastic reinforcing agent, 4-9 parts of weather-resistant agent, 1-4 parts of plasticizer, 0.5-2.0 parts of antioxidant, and 0.3-1.0 parts of lubricant. The present application designs a multi-component synergistic composite weather-resistant agent to achieve all-round weather resistance: abandoning the single action mode of traditional small-molecule weather-resistant agents, adopting bentonite, boron nitride and nano-silicon carbide as physical barrier phases, lanthanum oxide as a chemical stable phase, chitosan and sodium silicate as interface compatible phases, and nano-cellulose agent as a dispersion reinforcing phase.

The embodiment of the invention provides a vehicle body and a rail vehicle, the vehicle body comprises a vehicle roof assembly and side walls, the side walls are located at the two ends of the vehicle roof assembly in the transverse direction, the vehicle roof assembly and the side walls are each provided with a skin layer, and the skin layers are formed by laying prepreg in a preset mold layer by layer; the roof side rail is used for connecting the roof assembly and the side wall, the roof side rail is wrapped in the skin layer of one of the roof assembly and the side wall to be integrally formed, and the skin layer of the other one of the roof assembly and the side wall is fixed to the roof side rail. The roof side rail is wrapped in the skin layer of one of the roof assembly and the side wall to be jointly solidified and connected to ensure that the roof assembly and the side wall are tightly combined, and a high-strength overall frame is formed; due to the fact that the continuous fiber structure of the composite material skin layer can effectively distribute stress along a load transmission path, stress concentration is avoided, and the connecting portion can bear larger loads while light weight is guaranteed. Meanwhile, connecting joints of large components between the roof assembly / side wall and the roof side rail are reduced, and the reliability is improved.

The present application relates to the field of rail vehicle body roof forming, and particularly discloses a grid wallboard composite roof structure based on automatic fiber placement process, a rail vehicle and a manufacturing method thereof. The process realizes accurate placement of continuous fibers on a complex curved surface through an automatic fiber placement device, and forms a large integrated roof part with a grid reinforcing structure. The grid wallboard composite roof structure comprises a composite skin layer and a fiber foam sandwich layer. The fiber foam sandwich layer comprises hoop grid ribs, transverse grid ribs and longitudinal grid ribs. The transverse grid ribs and the longitudinal grid ribs are arranged in the hoop grid ribs, and the hoop grid ribs, the transverse grid ribs and the longitudinal grid ribs are connected to form a continuous closed placement path grid. High-density foam is arranged in the grid intersection node area, and low-density foam is arranged in the grid unit area. Large-size grids are arranged in the central area of the roof, and small-size grids are arranged in the edge and connecting area of the roof. The present application is particularly suitable for batch manufacturing of large roof parts of high-speed rail, subway and light rail.

The invention discloses an automatic gluing assembly for a composite skin plate and edge sealing equipment and a method, belongs to the field of plate processing equipment, and aims to solve the problems that existing gluing equipment is uneven in gluing, insufficient in glue feeding into plate gaps and low in operation efficiency, the automatic gluing assembly comprises a glue box arranged at the bottom of a bottom frame, and the surface of the bottom frame is rotationally connected with a second gluing roller; the middle of the second glue coating roller is located in the glue box, the bottom of the second glue coating roller makes contact with glue, sliding ways are arranged on the two sides of the glue box, first sliding blocks are slidably connected into the sliding ways, a penetrating first glue coating roller is rotationally connected between the two first sliding blocks, and the first glue coating roller and the second glue coating roller are the same in height; the top of the glue box is fixedly connected with two symmetrically-arranged rails, second sliding blocks are slidably connected into the two rails, and a second mounting frame is slidably connected between the second sliding blocks. The automatic gluing device is used for edge sealing and automatic gluing of composite skin plates, glue can be brushed into gaps, and the gluing quality and efficiency are improved.

The application provides a three-dimensional bulging structure, a control method and a system for an airfoil. The three-dimensional bulging structure comprises: a composite skin, first driving members and second driving members, the first driving members and the second driving members are arranged in a thickness direction of the composite skin in a laminated manner, wherein the first driving members and the second driving members each comprise a plurality of shape memory alloy (SMA) wires and a plurality of composite round rods, the SMA wires and the composite round rods of the first driving members are arranged in a first direction, and the SMA wires and the composite round rods of the second driving members are arranged in a second direction; and a temperature control assembly comprising heating wires connected with the SMA wires, the heating wires are used for heating the SMA wires to trigger the SMA wires to generate deformation, drive the composite round rods to be pressed and bent outward, and further drive the composite skin to form a three-dimensional bulging curved surface.

The invention relates to the technical field of bionic robots, and discloses a wearable modular bionic robot composite skin and a preparation method thereof. The composite skin comprises, from outside to inside, a thermal shrinkage surface layer wrapping the whole body of the bionic robot, a reinforced supporting layer distributed at the stress or bending part of the bionic robot, a pressure-sensitive sensing layer distributed at the interaction sensing part of the bionic robot, and a base body layer wrapping the whole body of the bionic robot. A layered composite structure is adopted, and each layer is composed of a standardized material system; the thermal shrinkage surface layer is in thermal shrinkage connection through an overlapping area of the wearable forming part, so that seamless full coverage of the whole body is realized; the supporting layer and the pressure-sensitive sensing layer are selectively assembled, so that redundant assembly of unnecessary parts is avoided; the base body layer is fixedly connected with the bionic robot body and provides stable support for other layers. The standardized material and the wearable forming structure are matched with all parts of the bionic robot, the robot can be matched with various bionic robots through size adjustment and selective assembly, the large-scale production difficulty is low, and the application range is wide.

The invention discloses a humanoid robot face composite skin preparation method, which comprises: S1, preparing a flexible substrate, adopting a silica gel injection molding process to prepare the flexible substrate, and reserving a channel penetrating through the inner surface and the outer surface of the flexible substrate in the preset position of the flexible substrate during the molding process; s2, preparing surface skin, namely preparing the surface skin by adopting a silica gel injection molding process for later use; s3, preparing a wire, and printing on the inner surface of the flexible substrate through a 3D printing process to form a conductive circuit; s4, preparing an electrode plate, and forming the electrode plate on the outer surface of the flexible substrate through a hot pressing process or a conductive ink direct writing process; s5, a conductive connecting piece is embedded in the channel in the S1, one end of the conductive connecting piece is electrically connected with the wire, and the other end of the conductive connecting piece is electrically connected with the electrode plate; s6, the flexible substrate and the surface skin are compounded into a whole. The wires and the electrode plates are specially arranged, and it can be ensured that the skin accurately responds to driving signals.

The invention discloses a composite skinning agent for repairing a gobi gravel curtain layer, a preparation method and a repairing method, and belongs to the technical field of ecological repairing. The composite skinning agent comprises modified plant fibers, gas-solid reaction mineral components, biological polysaccharide, organic acid and microorganism induction factors; the modified plant fibers are plant fibers which are subjected to carbonization and oxidation activation treatment and have carboxyl and hydroxyl active sites on the surfaces; the gas-solid reaction mineral component is calcium oxide and / or magnesium oxide. The crust layer obtained by the invention has a continuous fiber-mineral composite network, so that the stability is improved, the reaction system can be cured under a low-moisture condition, and the method is beneficial to application in an arid gobi environment.

The invention discloses a lightweight train body co-molded by a composite material and a mold and a molding method thereof, and relates to the technical field of rail transit, and the train body structure comprises a 3D printing chopped fiber reinforced thermoplastic polymer core layer, a continuous fiber reinforced resin matrix composite material skeleton, a composite material outer skin and a composite material inner skin. The 3D printing chopped fiber reinforced thermoplastic composite material polymer has the advantages of high strength, light weight, high temperature resistance, complex molding and the like; the 3D printing dot matrix core layer is combined with the traditional composite material grating and the composite material skin, so that the overall weight of the train is further reduced, the use of various connecting pieces is reduced, the workload of train body assembly is reduced, and the economical efficiency of train operation is improved.

The present application relates to a kind of moisturizing, oil control and soothing plant composite skin care composition and its preparation method, application, belong to cosmetic raw material technical field.The moisturizing, oil control and soothing plant composite skin care composition is composed of white white lily flower extract, honeysuckle flower extract and hamamelis virginiana extract with weight ratio (4-6) : (2-3) : (1-3) ;The extraction process and matching ratio of raw materials in the composition of the present application are optimized, and the composition is endowed with excellent skin moisturizing, oil control and skin soothing effect, and has good application effect in cosmetics.

The present application relates to the technical field of non-destructive characterization of composite material interface, and provides a method for characterizing fracture toughness of aircraft composite bonding structure based on nonlinear guided waves, which comprises applying nonlinear guided wave excitation to the bonding structure of the aircraft composite skin and shell to be tested, collecting the first-arriving guided wave signals propagating along the bonding interface in each bonding sample to be tested; performing frequency domain analysis on the first-arriving guided wave signals on each propagation path, extracting the amplitudes of the fundamental frequency component, the second harmonic component and the third harmonic component, calculating the corresponding nonlinear parameters and the normalized nonlinear parameters; solving the corresponding interface evolution index by using the constructed bonding interface fracture toughness characterization model; converting the obtained interface evolution index into interface fracture toughness according to the mapping relationship between the interface evolution index and the type I interface fracture toughness established by experiments, and realizing the non-destructive fracture toughness characterization of the bonding sample to be tested.

The invention relates to the technical field of batteries, in particular to a composite battery box with high safety, low cost, light weight and standardization. Comprising a composite material inner container and a metal frame wrapping the periphery of the side wall of the composite material inner container. The metal frame is of a split structure and is formed by connecting a front section, a rear section, a left section and a right section of independent section bar frames through plug connectors and fasteners, and the metal frame and the outer side wall of the composite material inner container are bonded and fixed through structural adhesive; the composite material inner container is of a sandwich structure and comprises an upper-layer composite material skin, a lower-layer composite material skin and a sandwich layer located between the upper-layer composite material skin and the lower-layer composite material skin. By adopting the innovative scheme of the sandwich composite material liner and the split metal frame, the safety of the battery box body is remarkably improved, the cost is reduced, the light weight is realized, and the maintainability and adaptability of the product are enhanced through the standardized and modular design.

The application discloses a flanging forming method of a composite skin bowl, and comprises the following steps: realizing the bending of the top of the outer framework of the composite skin bowl to the horizontal state through the flanging forming die to tightly press the top of the inner framework, and realizing the flanging and rolling process. By using the upper die plate with different inclined contact surfaces in the flanging forming die, the top of the outer framework is gradually bent to the horizontal state through multiple contact and pressure to tightly press the top of the inner framework, so that the problem that the top of the erected outer framework cannot be bent to the horizontal state to tightly press the top of the inner framework in the prior art is solved.

The application discloses a kind of production high-end noodle equipment of toughness, it is related to noodle processing production technical field, it solves the noodle production equipment of prior art, to improve the taste of noodle, generally increase curing time and the number of calender roll, above-mentioned mode tends to increase very high cost, it is easy to lead to the effect of noodle internal quality is not good, reduces noodle production efficiency technical problem;Including several racks, cutting knife assembly and be set on rack conveyor one, conveyor two, conveyor three, conveyor four, electric slide rail and PLC control system and inductor group;Wherein, electric slide rail and PLC control system are connected;The application adopts the method of analog composite skin calendering, increases dough thickness, reaches to improve dough internal toughness, to improve the taste of noodle, not only can reach to improve the effect of noodle internal quality, while reducing processing and manufacturing cost, simple structure is convenient for installation, simplifies maintenance in later use process.

The application discloses a kind of composite stiffened panel integral forming methods;Including: S1, the composite material prepreg needed for forming composite skin is laid to form composite skin preform;S2, the composite material prepreg is laid to form composite stringer preform A;S3, the two ends of stringer on composite stringer preform A are cut to form bevel, obtain composite stringer preform;S4, composite stringer preform is fixed on composite skin preform, then again on composite stringer preform Laid composite material prepreg with stringer via hole, obtain stiffened panel preform;S5, after heating and curing, composite stiffened panel is prepared.The stiffened panel prepared by the application is the integrated structure of stringer and skin, and the stiffened panel formed by layer combination of the application avoids the risk of degumming compared with the panel manufactured by the existing process, and improves the structural stability and strength of the panel.