9results about How to "High damage tolerance" patented technology

The application discloses a kind of laminated composite intercalation repair methods, belong to laminated composite maintenance technical field.The application uses the way of multilayer intercalation reinforcement patch, significantly increase the bonding area of patch and original laminated laminated composite material, can effectively improve the bonding strength of repair area, so that repair area will not become laminated laminated composite material / member dangerous area;The bonding surface is composed of multiple planes, and adjacent bonding surfaces bear tensile or shear load respectively, and after debonding or damage of a certain bonding surface, the crack will not spread to other bonding surfaces, significantly enhance the damage tolerance of repair bonding area, and further improve the mechanical properties of repair material / member.

This application discloses a method for preparing a double-needle stitched reinforced wall panel structure, relating to the field of fiber composite material reinforcement technology. The method includes the following steps: designing and machining a digital model of a double-needle stitching mold based on the reinforced wall panel structure; creating oblique grooves along the stitching direction in the double-needle stitching mold, the depth and width of which are adapted to the movement trajectory of the double needles; cutting carbon fiber cloth as reinforcing layer and skin layer according to the reinforced wall panel structure; stacking the reinforcing layer and skin layer on the double-needle stitching mold in a predetermined order and fixing them; using a double-needle stitching device, simultaneously stitching the flanges of the reinforcing layer and skin layer along the stitching path to form a double-stitch preform; impregnating the double-stitch preform with resin using a vacuum-assisted liquid molding process, and curing it to obtain the reinforced wall panel structure. This application is the first to apply double-needle synchronous stitching technology to mainstream reinforced structures without foam cores, solving the problem of insufficient interlayer strength in traditional adhesive / co-curing processes, and can cover most reinforced wall panel structural forms in the aerospace field.

This invention discloses a design method for composite material shells of deep-sea pressure-resistant devices and its application. The design method selects four key parameters: initial out-of-roundness amplitude, wall thickness deviation coefficient, hybrid fiber ratio, and difference in elastic modulus between inner and outer fibers. Combining nonlinear finite element analysis and response surface regression techniques, a quantitative prediction model of nonlinear buckling load with respect to the above parameters is established. Based on this, the buckling resistance advantages and performance-cost marginal benefit relationship of hybrid ply configuration are systematically explained from the two dimensions of structural mechanics mechanism and engineering economy.

This invention relates to a one-piece molded Whipple's Shield impact protection structure textile composite material and its preparation method. The product comprises, from top to bottom, an impact-facing fabric layer, a spacer fabric layer, and a back fabric layer. The impact-facing fabric layer is a single-layer or multi-layer fabric, with adjacent layers bonded together by resin. The spacer fabric layer is a hollow multi-layer structure consisting of a top layer, a bottom layer, and a spacer layer. The back fabric layer is also a multi-layer fabric, with adjacent layers bonded together by resin. The spaces between the impact-facing fabric layer and the top layer of the spacer fabric layer, as well as between the bottom layer of the spacer fabric layer and the back fabric layer, are filled with resin. Resin is impregnated between the back fabric layer, the spacer fabric layer, and the impact-facing fabric layer using a vacuum-assisted resin transfer molding process. After impregnation, the vacuum is removed, and the product is cured and demolded to obtain the final product. This invention features a simple preparation method; the product has high energy absorption, low specific gravity, high damage tolerance, and good impact protection performance.

The invention relates to the technical field of fiber reinforced composite materials, and discloses a field-assisted additive manufacturing bionic composite material interface structure and a preparation method and application thereof. The invention discloses a bionic composite material interface structure for field-assisted additive manufacturing. The bionic composite material interface structure comprises a fiber reinforced composite material substrate and a bionic middle layer. According to the method, an arthropod exoskeleton cuticle Belii gang arrangement toughening mechanism and a slit receptor micro-stress sensing mechanism are used for reference, and field-assisted additive manufacturing and magnetic field orientation regulation and control technologies are combined, so that crack deflection is induced through a spiral Belii gang structure, external energy is dissipated, and the mechanical property of the spiral Belii gang structure is improved; interlayer anti-layering toughening and damage tolerance improvement of the fiber reinforced composite material are realized, micro-deformation of a base body can be converted into resistance electric signal sudden change by virtue of a stress concentration seam, and layering damage inhibition and real-time accurate monitoring of structural health are synchronously completed; the method is suitable for mechanical property optimization and on-line micro-stress damage detection scenes of the fiber reinforced composite material.

The invention belongs to the technical field of superconducting, and relates to an insulation enhanced superconducting cable and a preparation method thereof. The method comprises the following steps: firstly, reinforcing a superconducting wire rod through a NiCoCr / Cu composite matrix, and carrying out multi-channel coating and on-line monitoring by adopting BN modified polyimide paint to form a uniform insulating layer; and then wrapping and hot pressing are carried out by using a B-stage epoxy-impregnated aromatic polyamide tape to construct an insulation enhanced structure. Stranded cable forming is carried out through tension control and a numerical control positioning die, and the composite cable is formed by combining the core wire and the multiple layers of insulation reinforced wires. Finally, through secondary wrapping and pretension braiding protection, the superconducting cable with the coverage area larger than or equal to 99.9% and the void ratio smaller than 1% is obtained, the withstand voltage between strands is larger than 5000V, the withstand voltage between cables is larger than 7000V, the mechanical stability and the thermal management performance are remarkably improved, and the superconducting cable is suitable for being applied to high-field magnets and fast pulses.

The application discloses a manufacturing method of aileron bonding parts in the technical field of aerial unmanned planes, and comprises the following steps: S1, preparing laminated plate parts and edge strip parts; S2, pretreating a bonding tool; S3, pretreating bonding surfaces of the laminated plate parts and the edge strip parts; S4, preparing a honeycomb core and a foam core, laying a rubber film or foaming rubber on a preset bonding surface, positioning a lower skin on the bonding tool, and sequentially assembling a preformed framework to be subjected to pre-foaming treatment. By adopting a carbon fiber composite laminated structure, a composite layout of a foam sandwich and a honeycomb sandwich, and an integrated structure design of a single beam and multiple ribs, the application greatly reduces the number of independent parts and standard parts, significantly reduces the overall weight of the aileron bonding parts, effectively improves the flight maneuvering flexibility and endurance of the unmanned plane, and simultaneously reduces flight energy consumption and manufacturing cost.

The invention provides a carbon fiber composite material battery shell as well as a preparation method and application thereof. The carbon fiber composite material battery shell comprises an upper cover and a box body; the box body is provided with side walls and an internal reinforcing beam; a skin of the box body is formed by compression molding of a plurality of layers of biaxial warp-knitted carbon fiber cloth; the internal reinforcing beam is a prefabricated carbon plate; the prefabricated carbon plate is embedded and fused in the skin of the box body in the compression molding process of the box body to form an integrated structure; when the maximum height-width ratio H / L of the side walls is larger than 0.2, the included angle between the main fiber guiding direction and the length direction of the box body ranges from + / -55 degrees to + / -65 degrees. When the maximum height-width ratio H / L of the side walls is smaller than or equal to 0.2, the included angle between the main fiber guiding direction and the length direction of the box body ranges from + / -30 degrees to + / -50 degrees. The weight is reduced, the consumption of the carbon fibers is reduced, meanwhile, the mechanical property is kept unchanged, the material can be applied to new energy electric vehicles, and the cost is reduced.

The application discloses a silicon carbide fiber turbine rotor blade preform and a preparation method thereof, and belongs to the field of material science and engineering. The method comprises the following steps: preparing by using low-buckling silicon carbide fiber cloth, preparing by dividing the turbine rotor blade into an inner core and an outer layer, and using the integral layer forming method for the inner core and the outer layer, so that the blade body and the tenon in the inner core are an integral whole, and the carrying capacity and the stability of the blade are greatly improved; and the low-buckling silicon carbide fiber cloth has low buckling, good in-plane performance, and the yarn is easier to deform and keep the original mechanical properties of the fiber in the forming process of the blade; compared with the blade prepared by the traditional method, the blade prepared by combining the satin silicon carbide fiber cloth and the integral layer forming has better oxidation resistance, creep resistance, higher damage tolerance and energy absorption performance.