62 results about "Composite skin" patented technology

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.

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 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 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).

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 belongs to the technical field of composite material processing, and provides a composite material skin forming method based on a glue blocking measure, which comprises the following steps: preparing a mold; composite material laying: laying the prepreg on a mold according to a certain laying sequence and angle, and compacting after laying each layer; designing and mounting a glue blocking structure: designing the glue blocking structure according to the shape and the size of the skin and the predicted glue flowing direction, and mounting the glue blocking structure along the edge of the mold or the predicted region where the glue is easy to lose; vacuum bag packaging: covering the surface of the laminated composite material with an isolating membrane and a breathable material, sealing the edge of the vacuum bag with a sealing tape, and connecting a vacuum pipeline; vacuumizing, heating and curing; and demolding and post-processing. The technical problem that resin glue liquid flows during composite material skin forming is solved, the phenomenon of uneven glue liquid loss is reduced, and the composite material skin forming quality and the product percent of pass are improved.

To provide a composite skin material excellent in designability, and durability of design.SOLUTION: A composite skin material 1 includes a sheet material 2 having gloss, and a skin material 3 laminated on the sheet material 2 having gloss, where the skin material 3 has a plurality of open holes 4. A pore diameter (L) of the open holes and a thickness (d) of the skin material satisfy the relation of L≥1.03×d, and a visible angle is 70° or wider.SELECTED DRAWING: Figure 1

The present application belongs to the technical field of composite material component manufacturing, and particularly relates to a high-quality integrated manufacturing method for a composite material skin-metal web. The present application reduces residual stress caused by the difference in thermal expansion coefficient through methods such as segmented processing of the metal web, splicing forming and surface structure design, improves the positioning accuracy of the metal web and the internal quality of the overall structure through the design application of the positioning template, and realizes high-quality and high-efficiency integrated manufacturing of the composite material skin and the metal web through process optimization, thereby laying a technical foundation for the manufacturing of composite material-metal stiffened structure components of dissimilar materials and composite processes.

The invention discloses a truck frame light-weight skin fixing structure and method and a vehicle, and the truck frame light-weight skin fixing structure comprises a fastening connecting assembly which comprises a rivet nut and a fastening bolt, the outer side of a composite skin is coated with a skin pressing plate, the outer side of a truck frame is coated and fixed with the composite skin through the fastening connecting assembly, and the rivet nut is provided with a first gasket; a thickening cushion block and a second gasket are arranged on the fastening bolt; the fastening connection assembly locks the skin pressing plate and the composite skin along the first locking path to form a skin fixing structure; the anti-vibration and anti-loosening effects are effectively improved, the fixed bolt is not prone to loosening under the long-time vibration operation working condition, the maintenance frequency and the maintenance cost are reduced, and the operation reliability of the whole vehicle is improved; the outer side of the composite skin is coated with the skin pressing plate, the fastening bolt is provided with the thickening cushion block and the wedged lock washer, the probability of abrasion or crushing of the composite skin in the installation process is reduced, waste generated in the production process is reduced, and the one-time assembly completion rate is increased.

The application provides a sandwich structure battery pack bottom protection plate energy absorption evaluation method and system based on strain energy analysis, relates to the power battery pack protection technical field, and comprises the following steps: preparing a laminated sandwich structure bottom protection plate; calculating the unit volume strain energy of a composite skin, a foam core material and an embedded steel plate; determining the deformation region volume based on the Hertz contact theory; obtaining the total absorption energy through superposition integration; and determining the optimal structure parameters under the energy absorption requirements and deformation constraint conditions by using gradient optimization. The application can effectively evaluate the energy absorption performance of the battery pack bottom protection plate, realize lightweight design, and improve the safety of the battery pack.

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 the field of sponges, and discloses a medical skin-friendly sponge and a preparation method thereof.The medical skin-friendly sponge is prepared from, by weight, 100 parts of composite polyether polyol, 42-48 parts of 4, 4 '-dicyclohexylmethane diisocyanate, 10.5-21.5 parts of a composite skin-friendly modifier, 3-5 parts of an antibacterial agent, 4-6 parts of deionized water and 0.2-0.5 part of a catalyst. And 0.4 to 0.8 part of a surface active agent. The composite skin-friendly modifier is prepared from 10 to 20 parts of polyethylene glycol and 0.5 to 1.5 parts of hyaluronic acid; the composite polyether polyol is composed of polyether triol and polyether glycol according to a mass ratio of 1: (3-5). Through a multi-component synergistic raw material system and multi-performance accurate regulation and control, the synergistic standard reaching of low hardness, fine surface, high water absorption and water retention and strong antibacterial property of the medical skin-friendly sponge is realized, the medical skin-friendly sponge can be widely adapted to various medical scenes, and technical upgrading of the field of medical sponges is promoted.

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 invention provides a gradient woven continuous ceramic fiber reinforced titanium-based composite skin structure and a preparation method thereof.According to the method, through the composite pressing and degreasing-sintering process of a Ti65 alloy thin plate and continuous ceramic fiber cloth, fibers and a titanium plate are pre-tightened under the room-temperature cold pressing condition, and fiber displacement is reduced; a gradient heating and pressurizing technology is adopted, flowing and interface diffusion bonding of the binder are promoted, meanwhile, under the degreasing-sintering synergistic effect, organic matter in the binder is removed step by step in two steps, and residual carbonization is avoided; in the final sintering process, the titanium alloy matrix and the fibers are firmly combined, and the pressure and the temperature are accurately controlled, so that grain coarsening is inhibited, and high-temperature carbonization of the fibers is prevented. Therefore, the prepared composite skin structure has higher density, excellent high-temperature mechanical property and excellent thermal shock resistance, and is particularly suitable for application in extreme environments.

The utility model relates to the field of process equipment, in particular to a composite skin forming tool. The tool comprises a plurality of die body blocks, a glue joint positioning clamping plate, an upper flange edge, a lower flange edge, an upper flange support, a lower flange support and a frame. Wherein the plurality of die body sub-blocks are of special-shaped cylindrical structures, the molded surface of a structure formed by the plurality of die body sub-blocks has multiple curvatures and multiple bends, the upper flange edge is fixed on the upper flange support, the lower flange edge is fixed on the lower flange support, one end of the glue joint positioning clamping plate is connected with the plurality of die body sub-blocks, and the other end of the glue joint positioning clamping plate is connected with the die body sub-blocks. The other end of the glue joint positioning clamping plate is connected with the frame, one ends of the mold body sub-blocks are connected with the upper flange edge, the other ends of the mold body sub-blocks are connected with the lower flange edge, and the problems that in the prior art, a special-shaped pipeline structure skin is difficult to demold and difficult to lay are solved.

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.