107 results about "Composite skin" patented technology

The invention discloses a multifunctional aircraft skin bionic heterostructure and a preparation method thereof, belongs to the technical field of aerospace, and aims to solve the problem that a traditional aircraft skin structure is difficult to synergistically realize impact resistance, sound absorption, noise reduction and electromagnetic shielding, and a multifunctional composite skin protection structure is designed in a breakthrough manner. Through collaborative innovation of a bionic framework and a functional material, triple optimization of mechanical-acoustic-electromagnetic characteristics is realized. A bionic skeleton structure with outstanding mechanical properties is obtained through a layered annular structure of a glass sponge skeleton and a hierarchical structure design of a thighbone, and the bionic skeleton structure is combined with modified polyurethane foam with excellent sound absorption performance and electromagnetic shielding performance to obtain a multifunctional heterostructure with impact resistance, noise reduction and electromagnetic shielding.

The invention relates to the technical field of functional composite probe material preparation, in particular to a three-core spinning technology-based bio-compatible gel probe and a preparation method thereof, and the three-core spinning technology-based bio-compatible gel probe comprises a composite skin layer and three functional core layers; the composite skin layer is composed of a sodium alginate-polydopamine-chitosan grafted copolymer in a mass ratio of 2: 1: 0.5, and contains # imgabs 0 # chondroitin sulfate and # imgabs 1 # polyoxyethylene; the three core layers are respectively a carbon nanotube-polyaniline # imgabs2 # hybrid material, a graphene-polypyrrole-boron nitride hybrid material and a # imgabs3 # polythiophene-hydroxyapatite hybrid material, and the mass ratio of the carbon material to the conductive polymer to the newly added nano material in each core layer is 1: 2: 0.3; and the diameter ratio of the skin layer to the three core layers is 1: 0.28: 0.22: 0.17. According to the invention, multichannel signal transmission is realized, the impedance is reduced by the hybrid material, and the conductivity is improved; the composite skin layer is matched with soft tissue mechanical properties, and interface bonding is stable; and the biocompatible component reduces inflammation, is suitable for acquiring nerve electrophysiological signals, and is easy for large-scale production.

The invention provides a notebook keyboard composite skin-touch paint film and a preparation process thereof. The notebook keyboard composite skin-touch paint film comprises a primer layer, a middle paint layer and a UV skin-touch finish paint layer which are sequentially arranged on the surface of a notebook keyboard base material, the primer layer is prepared from the following components in percentage by weight: 20 to 30 percent of hydroxy acrylic resin, 15 to 25 percent of modified epoxy acrylate, 5 to 10 percent of vinyl modified fumed silica, 5 to 10 percent of fluorosilicone resin, 5 to 10 percent of epoxy phosphate, 5 to 10 percent of filler, 15 to 25 percent of solvent A, 2 to 4 percent of curing agent, 0.1 to 0.3 percent of flatting agent and 0.1 to 0.3 percent of defoaming agent; the middle paint layer is prepared from the following components: 40 to 50 percent of acrylic polyurethane resin, 12 to 16 percent of filler, 1 to 3 percent of cerium oxide, 7 to 12 percent of laser carving toner, 1 to 3 percent of dispersing agent, 20 to 30 percent of solvent B, 0.1 to 0.3 percent of plasticizer, 0.1 to 0.3 percent of flatting agent and 0.1 to 0.3 percent of defoaming agent; the UV skin-touch finish paint layer is prepared from the following components: 52 to 55 percent of polyurethane acrylate resin, 15 to 25 percent of reactive diluent, 2 to 4 percent of photoinitiator, 10 to 15 percent of skin-touch additive, 5 to 10 percent of filler, 0.1 to 0.3 percent of flatting agent and 0.1 to 0.3 percent of antioxidant. The paint film provided by the invention has the advantages of favorable wear resistance, favorable adhesive force and favorable hand feeling.

The invention provides a wing panel stringer skin accurate butt joint device and a use method. According to the method, the actual space pose of the skin is determined through a composite skin forming mold, and then the theoretical space pose of the stringer is calculated; space attitude adjustment is conducted on the stringers to be in butt joint through the numerical control attitude adjusting and positioning structure, the stringer accurate positioning device grabs and positions the stringers and accurately moves the stringers in the X direction and the Y direction, finally the stringers are accurately positioned and pressed on the composite material skin, and accurate butt joint of the stringers and the skin of the composite material wing wall plate is achieved.

The invention provides a sandwich structure battery pack bottom guard plate energy absorption evaluation method and system based on strain energy analysis, and relates to the technical field of power battery pack protection, and the method comprises the steps: preparing a laminated sandwich structure bottom guard plate; calculating strain energy per unit volume of the composite material skin, the foam core material and the embedded steel plate; determining a deformation area volume based on a Hertz contact theory; the total absorption energy is obtained through superposition integration; and optimal structure parameters meeting energy absorption requirements and deformation constraint conditions are determined through gradient optimization. According to the invention, the energy absorption performance of the battery pack bottom guard plate can be effectively evaluated, lightweight design is realized, and the safety of the battery pack is improved.

A composite airfoil assembly has a composite airfoil, a spar, and a wrap. The composite airfoil has an outer wall and a composite skin. The outer wall extends between a root and a tip. The outer wall defines an interior. The composite skin at least partially defines the outer wall. The spar having a spar centerline axis, a stem, a base, and a transition interconnecting the base and the stem.

The invention provides a power generation and energy storage flexible composite skin assembly, which comprises a flexible solar cell, a flexible energy storage cell and a flexible insulating substrate, and is characterized in that the flexible solar cell is arranged on the front surface of the flexible insulating substrate, and the flexible energy storage cell is arranged on the back surface of the flexible insulating substrate. The beneficial effects of the invention are that the flexible solar cell, the flexible energy storage cell, the flexible insulating substrate, the packaging layer and the management circuit are integrated in the skin structure, the advantages of light weight, flexibility, high integration and the like are realized, power supply and electric energy storage are realized, the output of the overall electrical performance of the skin assembly is improved, and the cost is reduced. The maximum power output is kept in the electrical performance output process, and the environmental adaptability and cruising ability of the unmanned aerial vehicle can be greatly improved.

The invention discloses an aircraft skin drilling tool and a use method thereof, and discloses a high-precision bidirectional rotary aircraft skin drilling tool. According to the tool, the rotation control assemblies at the two ends of the base drive the mold positioning platform to achieve 0-180-degree two-way precise rotation, and the angle locking error is smaller than or equal to 0.5 degree. The mold positioning platform is provided with a profiling rib plate supporting plate and an adjustable rib plate fastening device, and skin curved surface self-adaptive positioning is achieved in cooperation with a transversely-arranged appearance clamping plate assembly. A hard alloy titanium-plated drill bushing is arranged on the clamping plate assembly and is axially perpendicular to the surface of the skin, hole positions accurately correspond to drawing coordinates, and automatic drilling is completed in cooperation with a mechanical arm controlled by an industrial control box and a drilling driving assembly. By means of multi-dimensional positioning of rotary adjustment, profiling supporting and the sliding clamping plate, the problems of position precision and efficiency of machining of rivet holes of the skin with the complex curvature are solved, and the machining device is particularly suitable for meeting the high-standard machining requirement of aviation composite skin.

The utility model belongs to the technical field of automobile wrapping parts, and particularly relates to a geometric texture wrapping structure which comprises a framework and a composite skin, the outer side wall of the framework comprises a texture feature area and a non-texture feature area, the composite skin covers the outer side wall of the framework, and the composite skin is arranged on the outer side wall of the framework. Geometric texture features and non-geometric texture features are formed between the texture feature region and the non-texture feature region through pressing, the geometric texture features correspond to the texture feature region, and the non-geometric texture features correspond to the non-texture feature region. The texture feature area is arranged on the outer side wall of the framework, the composite skin is wrapped, and the composite skin is shaped and wrapped in a hot-pressing and cold-pressing mode, so that geometric texture features are formed, geometric textures are more stereoscopic, and the comfort level of the composite skin in use is improved.

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 invention relates to a composite material component (20) for turbomachinery, particularly aircraft turbomachinery, comprising: - a composite skin (22) having an inner face (28) and an outer face (26), the composite skin comprising continuous fibers; and - at least one element (24) extending along a respective extension direction (X), each element (24) comprising a body (30) extending from the inner face (28) of the skin to a free end (32) along an elevation direction (Z) distinct from the extension direction, each body (30) being connected to the inner face by at least one fillet (36, 36'), the body being made of a composite material comprising mainly discontinuous fibers; characterized in that the component (20) further comprises an additional skin (40) of continuous fibers covering at least one fillet of the body to the inner face of the skin. Figure for the abstract: Figure 3

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 belongs to the technical field of cosmetics, and provides a moisturizing, whitening and cleaning type white mud mask and a preparation method thereof.The white mud mask is prepared from, by weight, 35-45 parts of purified water, 15-20 parts of a moisturizing agent, 15-18 parts of Amazon white mud, 6-9 parts of kaolin, 6-9 parts of bentonite, 6-13 parts of an emollient, 4-7 parts of a skin whitening agent and 2-4 parts of a stabilizer. The composition is prepared from the following raw materials in parts by weight: 1 to 3 parts of lecithin, 0.1 to 0.8 part of xanthan gum, 0.1 to 0.5 part of allantoin, 0.1 to 0.3 part of phenoxyethanol, 0.1 to 0.3 part of ethylhexylglycerin and 0.1 to 0.3 part of bisabolol. Wherein the humectant is prepared from a moisture absorbent, a moisturizing active ingredient and a water locking agent. The white mud mask disclosed by the invention is safe in components and comfortable in body feeling, not only has an efficient skin cleaning effect, but also has the effects of whitening, moisturizing and controlling oil, can improve the activity of skin cells and accelerate the metabolism of the skin cells at the same time, achieves the multifunctional composite skin nourishing effect of a single product, reduces the irritation, and can be suitable for various types of skins.

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 present invention proposes a method for laying a metal mesh composite film and a method for characterizing the state of a composite part using the texture of the metal mesh composite film. The laying method includes: pre-setting a metal mesh composite film on the surface of the part to be formed; wherein the parts to be formed include: parts to be co-cured and parts to be co-glued, and the metal mesh composite film is composed of a glue film and a ductile metal mesh; performing different laying treatments on composite skins of different configurations; packaging the laid parts in a vacuum bag, evacuating them, and performing vacuum value testing to form a complete vacuum state; and curing them according to the curing cycle of the metal mesh composite film and prepreg material resin system to generate a composite part. For the design verification and process verification required for large composite parts, the present invention provides a method for rapidly characterizing the internal state of composite parts.

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.

The utility model discloses a multi-layer damping skin structure and an integrated test cabinet skin in the technical field of composite products, the multi-layer damping skin structure comprises an outer skin layer, a damping layer and an inner skin layer, the outer skin layer and the inner skin layer are both formed by paving carbon fiber reinforced epoxy resin prepreg, the damping layer is formed by paving damping rubber, and the integrated test cabinet skin comprises a composite skin which is in a box body shape, the bottom of the composite skin is an opening, two sides of the composite skin are provided with side openings, and the top of the composite skin is provided with a top opening; the skin side cover is in a flat plate shape and is mounted on the side opening of the composite skin; and the skin top cover is in a flat plate shape and is arranged on the top opening of the composite material skin. According to the utility model, the purpose of reducing the weight of the test cabinet is realized.

The utility model relates to a double-layer composite skin-care cotton piece, which belongs to the technical field of skin-care cotton pieces and comprises an upper cotton piece body and a lower cotton piece body, blocking protrusions are arranged on the outer surface of the upper cotton piece body and the outer surface of the lower cotton piece body, and a reinforcing mechanism used for improving the strength of the skin-care cotton piece is arranged on the upper surface of the upper cotton piece body. The lower surface of the lower cotton piece body is provided with a comfortable mechanism used for improving the skin-friendly effect of the skin care cotton piece. The reinforcing mechanism comprises a moisturizing layer, a water locking layer, a tensile layer and a wrinkle layer, the moisturizing layer is arranged on the upper surface of the upper cotton piece body, and the water locking layer is arranged on the upper surface of the moisturizing layer. According to the double-layer composite skin-care cotton piece, the blocking protrusions are arranged on the outer surfaces of the upper cotton piece body and the lower cotton piece body and can be used for preventing liquid on the surface of the skin-care cotton piece from dripping, so that the liquid is left on the skin-care cotton piece, and the formed air holes can be used for improving the air permeability of membrane cloth; and the arranged reinforcing mechanism can be used for improving the tensile and moisturizing effects of the film cloth.

The utility model discloses a biomass fire grate driving sealing device which comprises two flange bodies, the opposite sides of the two flange bodies are fixedly connected with fixing pipes, the ends, away from the flange bodies, of the fixing pipes are fixedly connected with fixing discs, and fixing grooves are formed in the outer walls of the fixing discs. A fluororubber composite skin is movably connected between the two fixing discs, a metal expansion joint is fixedly connected between the two fixing discs, displacement such as thermal expansion and cold contraction caused by temperature change and the like of a pipeline can be compensated through the metal expansion joint, and the composite skin generally has the characteristics of certain flexibility, corrosion resistance and the like. The metal expansion joint can be protected, good sealing performance is achieved, the screw rod is in threaded connection with the moving block in cooperation with rotation of the screw rod, so that the moving block drives the connecting block and the locking column to be disengaged from a locking groove in the positioning block, the fluororubber composite skin is conveniently and rapidly replaced, the convenience is improved, and meanwhile the service life of the fluororubber composite skin is prolonged. And the sealing performance and the service life of the sealing device are improved.

The invention relates to a part (20) made of composite material for a turbomachine, in particular an aircraft, comprising:- a composite skin (22) having an inner face (28) and an outer face (26), the composite skin comprising continuous fibers; and- at least one element (24) extending in a respective direction of extension (X), each element (24) comprising a body (30) extending from the inner face (28) of the skin to a free end (32) in an elevation direction (Z) distinct from the direction of extension, each body (30) being connected to the inner face by at least one fillet (36, 36'), the body is made of composite material comprising mainly discontinuous fibers; characterized in that the part (20) further comprises an additional skin (40) of continuous fibers covering at least the at least one fillet connecting the body to the inner face of the skin. Figure for abstract: Figure 3

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 discloses a light missile wing which comprises a metal wing handle, a main beam, an auxiliary beam, an end rib, a filling core material and a composite material skin wrapping the outer layer. The wing handles, the main beams, the auxiliary beams, the end ribs and the filling core materials are bonded through adhesive films to form a missile wing body. The composite material skin is laid on the surface of the missile wing body and then is subjected to mold pressing co-curing and integrated forming to form the clear-edge missile wing. According to the light missile wing, the composite material is mainly selected, the advantages of low density and high strength of the composite material are utilized, the structural strength and rigidity can be guaranteed, the overall structure is light, the structural efficiency is high, and the range and the effective load of a missile are increased; the structural design is simple, the working hours can be reduced, the production cost is reduced, the production efficiency is greatly improved, in addition, the high-strength barium phenolic glass fiber fabric prepreg is laid on the standard layer, and the thermal protection performance of the surface layer of the missile wing is greatly improved.

The invention relates to an aviation composite material skin grounding network, which comprises a plurality of metal flow guide strips fixed on a composite material plate through bonding hoops and connecting conductors for realizing connection and conduction between the metal flow guide strips, and at least one metal guide strip is further connected and conducted with the metal beam web through a connecting conductor. The grounding network provides a low-impedance path for the composite material airplane, and the problem that the composite material airplane cannot realize original grounding and protection functions is solved; compared with a grounding loop formed by a traditional metal structure, the grounding network has the advantage of being light in weight and has the advantage in economical efficiency. The grounding network metal diversion strips can be detached and replaced, and the maintainability is good.

Provided are a skin material of an insulating material, an insulating material comprising the skin material, and a manufacturing method therefor, the skin material comprising a composite skin material sequentially including a first nonwoven fabric layer, a kraft paper layer, and a second nonwoven fabric layer, wherein the basis weight of the second non-woven fabric layer is 40 g / ㎡ to 60 g / ㎡ and the permeability from the second non-woven fabric layer toward the first non-woven fabric layer in the composite skin layer at 100 Pa is 2 L / min·㎠ to 8 L / min·㎠.

The invention discloses a high-elastic wear-resistant short-plush warm-keeping textile fabric and a preparation method thereof, and relates to the field of textile fabrics, the high-elastic wear-resistant short-plush warm-keeping textile fabric comprises a short-plush outer layer and a skin-friendly inner layer, the short-plush outer layer is obtained by weaving composite short-plush yarns and composite phase-change yarns, and the skin-friendly inner layer is obtained by weaving composite skin-friendly yarns and composite high-elastic yarns; the skin-friendly inner layer comprises an elastic grid structure, and the elastic grid structure comprises a circumferential expansion grid structure or / and an oblique deformation grid structure. By arranging the double-layer structure, the skin-friendly comfort of the textile fabric is improved, meanwhile, the good heat preservation effect is achieved, the #-shaped patterns are formed in the spinning process of the skin-friendly inner layer, the heat preservation fabric is provided with tiny breathable meshes, and then the breathability of the fabric is improved; and a circumferential expansion grid structure or an inclined expansion grid structure is arranged in the skin-friendly inner layer, so that the short plush thermal fabric has a better stretching effect and a better rebound effect when being used at different stress parts, and the application range of the thermal fabric is widened.

The present application relates to the technical field of functional composite probe material preparation, in particular to a biocompatible gel probe based on three-core spinning technology and a preparation method thereof, which comprises a composite skin layer and three-layer functional core layers; the composite skin layer is composed of sodium alginate-polydopamine-chitosan graft copolymer with a mass ratio of 2:1:0.5, and contains chondroitin sulfate and polyethylene oxide; the three-layer core layers are carbon nanotube-polyaniline, graphene-polyazole-boron nitride and polythiophene-hydroxyapatite hybrid materials respectively, and the mass ratio of carbon materials, conductive polymers and new nano materials in each core layer is 1:2:0.3; the diameter ratio of the skin layer to the three-layer core layers is 1:0.28:0.22:0.17. The present application realizes multi-channel signal transmission, reduces impedance and improves conductivity by using hybrid materials; the composite skin layer matches the mechanical properties of soft tissues, and the interface combination is stable; the biocompatible components reduce inflammation, are suitable for nerve electrophysiological signal acquisition, and the process is easy to scale.

A method for forming a composite sandwich structure by compression molding is disclosed. The method includes: placing a stack of two composite skins (13a, 13b) separated by a non-adherent layer (13c) in a compression molding tool (10); compression molding the stack of composite skins and non-adherent layer while applying heat to the tool, wherein compression molding of the stack is carried out until each composite skin conforms to and adhere to the molding surface adjacent to it but the thermoset resin in each composite skin is not fully cure; opening the compression molding tool, wherein each composite skin remains adhered to the adjacent molding surface; removing the non-adherent layer from the compression molding tool; placing a core layer (14) in the compression molding tool; and compression molding until the core layer is bonded to the composite skins, thereby forming a shaped sandwich structure (15).