15 results about "Sandwich-structured composite" patented technology

The invention belongs to the technical field of composite material processing, and provides a composite material supporting type honeycomb structure edge strengthening method, which comprises the following steps of: extracting characteristics of a honeycomb molded surface to be stabilized; designing and manufacturing a metal male mold matched with the honeycomb molded surface; carrying out process simulation calculation; paving, curing and post-processing the composite material frame; stabilizing a honeycomb slope; checking the honeycomb and the composite material frame; and laying an adhesive film according to a verification result, and curing and forming. The process problems of honeycomb edge slippage shrinkage, in-plane shrinkage, collapse and the like generated in the pressurizing and curing process of the high-chamfer honeycomb sandwich structure composite material part are solved, and stabilization of the high-chamfer honeycomb is achieved.

The invention provides a preparation method of a honeycomb sandwich structure composite material. The preparation method comprises the following steps: S1, paving an inner side skin and an inner side adhesive film on a forming tool; s2, after all the layers of the inner side skin and the inner side adhesive film are laid, the inner surfaces of the inner layer honeycombs are laid on the two sides of the outermost layer of the inner side skin; s3, an outer side skin and an outer side adhesive film are laid and attached to the outer surface of the inner layer honeycomb, and a honeycomb sandwich structure composite material middleware is obtained; wherein the inner layer honeycomb comprises an over-stretched honeycomb and a regular hexagonal honeycomb which are spliced with each other, the regular hexagonal honeycomb is arranged on a smooth section between the inner side skin and the outer side skin, and the over-stretched honeycomb is arranged on a large-curvature section between the inner side skin and the outer side skin; and S4, curing the middleware of the honeycomb sandwich structure composite material to obtain the honeycomb sandwich structure composite material. In this way, at least one of the problems that the honeycomb bonding effect is not ideal, the sunken area is not compensated, and the edge position is debonded can be solved.

The invention belongs to the technical field of composite material structural strength, and provides an adhesive effect-considered honeycomb equivalent modeling method, which comprises the following steps of: obtaining a tensile / compressive elastic modulus of a honeycomb core material, a tensile / compressive elastic modulus of a curing adhesive material and an adhesive thickness; establishing an equivalent relationship among the mechanical properties and structural parameters of the adhesive material, the mechanical properties of the honeycomb core material, the structural parameters of the honeycomb core layer and the mechanical parameters of the honeycomb; and inputting the equivalent relationship into finite element software, and carrying out honeycomb equivalent modeling. According to the method, the technical problem that an analysis result obtained after equivalent modeling is greatly different from a test result is solved, and the requirement for accurate analysis of the mechanical property of the honeycomb sandwich structure composite material is met.

The present invention discloses a potting device and method for a honeycomb sandwich structure composite material part. The potting device includes a honeycomb sandwich structure composite material part to be potted and a potting forming auxiliary tooling; the honeycomb sandwich structure composite material part to be potted is located on the potting forming auxiliary tooling, and the potting forming auxiliary tooling is used to adjust the state of the honeycomb sandwich structure composite material part to be potted, adjust its potting area to be horizontal, prevent the horizontal tolerance deviation of the potting area of the workpiece from being too large and difficult to be completely filled. At the same time, exhaust holes are drilled at the outer edge of the potting area to ensure the discharge of the entrapped air, and a rubber dam is pasted at the outer edge of the opening of the potting area to increase the liquid level height of the potting adhesive and ensure that the potting adhesive is completely filled. The potting method of the present invention can achieve the preparation of large-size honeycomb core parts with high quality and high qualification rate, laying a foundation for the subsequent manufacture of qualified honeycomb sandwich structure composite material parts.

The invention belongs to the technical field of composite material process manufacturing, and discloses a foam sandwich structure composite material forming method, which is characterized in that a lower skin prepreg, a metal connecting piece, a foam core material and an upper skin prepreg are laid in a mold cavity in sequence, so that accurate positioning and effective coating are realized; a cavity is wrapped in the root area of the blade body by utilizing the excellent in-plane mechanical property of the prepreg, a filling agent is injected through a glue injection port, the filling agent is heated to expand in the heating process, the size is remarkably increased, the irregular shape of the root area of the blade and the edge of a metal connecting piece can be automatically filled, and therefore the blade can be manufactured. And the shape follow-up supplement of the root structure is realized. The expanded microspheres form a uniform closed-cell foam structure, so that the thickness of an interlayer is effectively supported, structural collapse or insufficient local compaction is prevented, local accumulation of resin can be inhibited, the thickness consistency and the structural compactness are improved, the layering process is simplified, and the quality control is improved.

The invention discloses an expandable and contractible large-diameter sandwich structure mold and a forming process method, solves the process problem of continuous high-quality forming of inner and outer skins of a super-large-diameter rotary sandwich structure composite material, and belongs to the technical field of advanced manufacturing of structural composite materials. The invention is oriented to the manufacturing of large composite components, breaks through the splicing structure and the sealing method of the modular composite combined die, successfully solves the problem of matching of thermal expansion coefficients of the composite components and the die, and reduces the influence of the die on the dimensional accuracy of the composite component product as much as possible; a space frame structure scheme is adopted, the difficult problem of mold profile rigidity control is solved, a forming mold split airtight system is designed, and the airtight requirement in the composite material sandwich structure barrel forming process is met; the mold can be disassembled and assembled in a split mode and can be repeatedly used, and the manufacturing cost of the component mold is reduced.

A method of the present disclosure includes inserting thermoplastic components into a mold such that at least two or more thermoplastic components are adhered to an inner wall of the mold. The thermoplastic components are substantially hollow and made of a thermoplastic material. The method includes applying pressure onto the thermoplastic components adhered to the inner wall in a direction towards the inner wall of the mold to compress the thermoplastic components. The method includes heating the thermoplastic components concurrently with applying the pressure such that a first portion of the thermoplastic material of the thermoplastic components forms a first sheet on a first side of the thermoplastic components and a second portion of the thermoplastic material of the thermoplastic components forms a second sheet on a second side of the thermoplastic components opposite to the first side. The first sheet connects the plurality of thermoplastic components.

The application discloses a high-temperature energy storage sandwich structure composite material and a preparation method thereof. A polyamide acid precursor solution A with dispersed oxide aerogel is used as insulating layer slurry, a polyamide acid precursor solution B with dispersed BBC is used as polarization layer slurry, the polarization layer and the insulating layer are sequentially and layer by layer cast by adjusting the height of a doctor blade and drying conditions, a sandwich structure is prepared, and after gradient temperature imidization, the sandwich structure is placed in a hot press to make the interlayer polymers undergo thermal fusion by accurately controlling the temperature and time, so that a seamless and thickness-stable sandwich structure is formed.

The application relates to a method for testing the in-plane shear performance of a sandwich structure composite material, comprising the following steps: preparing a test piece with a sandwich structure, wherein the test piece with the sandwich structure comprises a core plate, non-test panels and test panels adhered to upper and lower end surfaces of the core plate; bonding three reinforcing plates on the test panels at intervals along the width, which are respectively a middle reinforcing plate and two side end reinforcing plates, gaps are arranged between the middle reinforcing plate and the corresponding side end reinforcing plates, the middle reinforcing plate and the two side end reinforcing plates extend out of the test panel in opposite directions, wherein a first connecting hole is arranged at the extending end of the middle reinforcing plate, and clamp connecting holes are arranged at the extending ends of the two side end reinforcing plates; saw slits corresponding to the upper and lower gaps of each gap are arranged on the non-test panels, and the depths of the saw slits extend into the test piece; and the problems of a complex test fixture and low test efficiency of a civil aviation cabin floor test are solved through the above design.

The invention relates to the technical field of aircraft composite material manufacturing, in particular to a sandwich structure composite material hole making method. According to the method, a replaceable tool bit with a gradually-changed sawtooth cutting structure is adopted, and a double-positioning system with guide rod positioning and end face attaching to a positioning ring is matched, so that precise locking of the drilling position is achieved; the tool bit is integrated with an inner cooling channel and a spiral flow guide groove, and a cooling medium is synchronously conveyed and chippings are discharged during drilling; an elastic scraping blade is arranged at the tail of the tool bit, and burr cleaning is synchronously completed after hole forming. According to the drilling tool, the tool bit can be replaced quickly through the quick-release structure, and the requirements of different hole diameters are met. The technical problems of layering, hole diameter deviation, untimely heat dissipation and the like in the hole forming process of the sandwich structure composite material are effectively solved, the hole forming process is simplified, the hole forming efficiency and the hole wall quality are improved, the universality is high, and the method is suitable for various sandwich structure hole forming scenes of an aircraft composite material assembly site.

The preparation method comprises the following steps: taking a polyamide acid precursor solution A dispersed with oxide aerogel as insulating layer slurry, and taking a polyamide acid precursor solution B dispersed with BBC as polarization layer slurry; the height of a scraper and drying conditions are adjusted, a polarization layer and an insulating layer are subjected to layer-by-layer tape casting in sequence, a sandwich structure is prepared, the sandwich structure is placed in a hot press after gradient heating imidization, interlayer polymers are subjected to heat fusion by accurately controlling the temperature and time, and the sandwich structure which is seamlessly combined and stable in thickness is formed.

The present application relates to the technical field of aviation composite material manufacturing, in particular to a forming method for a C-shaped rib of a composite material with a honeycomb sandwich structure on the inner side. The forming method comprises the following steps: laying up an inner skin prepreg on a forming tool; covering a first adhesive film on the lower end surface of the honeycomb after cutting, and fixing the first adhesive film on the upper end surface of the inner skin prepreg; covering a second adhesive film on the upper end surface of the fixed honeycomb, and laying up an outer skin on the honeycomb and the inner skin prepreg; and finally, packaging into a tank for co-curing. The forming method for the C-shaped rib of the composite material with the honeycomb sandwich structure on the inner side aims to solve the problem of how to simultaneously improve the internal quality of the C-shaped rib, the positioning accuracy of the honeycomb, and the forming efficiency.

A method for forming a ceramic sandwich-structured composite component includes applying one or more ceramic matrix composite (CMC) plies to a surface of a tool, and positioning a ceramic foam precursor with respect to the tool such that the ceramic foam precursor and the one or more CMC plies is disposed in a sealed interior cavity of the tool. The ceramic foam precursor and the one or more CMC plies are cured within the sealed interior cavity to form a green preform such that the ceramic foam precursor expands within the sealed interior cavity to apply a pressure to the one or more CMC plies to consolidate the one or more CMC plies. The expanded ceramic foam precursor forms a ceramic core of the green preform bonded to the one or more CMC plies. The green preform is removed from the tool and sintered to ceramify the green preform.

The present invention discloses a method for preparing a full-carbon sandwich composite material. Specifically, the method comprises the following steps: preparing a hollow core mold and filling it with foam to prepare a solid lightweight core rod; inserting the lightweight core rod into a three-dimensional woven carbon fiber honeycomb fabric; sewing the carbon fiber fabric onto the upper and lower surfaces of the three-dimensional woven carbon fiber honeycomb fabric inserted into the lightweight core rod to prepare an integrated full-carbon sandwich structure fabric; using a vacuum infusion process to uniformly impregnate the integrated full-carbon sandwich structure fabric with resin; heating the mold to the initial curing temperature of the resin and maintaining the temperature, and then separating and demolding the mold; and reinforcing the upper and lower layers of the full-carbon sandwich structure composite material using an autoclave process to prepare a full-carbon fiber honeycomb sandwich composite material with uniform content and high planar accuracy. The material prepared by this method has the advantages of being lightweight, high-strength, and resistant to delamination and peeling; the demolding method is simple and convenient and does not damage the fibers; and the prepared full-carbon sandwich honeycomb composite material has uniform molding quality and high planar accuracy.

A molded part comprises a sandwich composite structure with a first substrate comprising a first reinforcing fiber attached to the first substrate by a thread. A resin layer is disposed adjacent to the first substrate. A second substrate is disposed adjacent to the resin layer and comprises a second reinforcing fiber attached to the second substrate by a thread. At least one side of the composite sandwich structure is encapsulated with an overmolding resin.