CN108928050B - Preparation method, equipment and structure of honeycomb sandwich structure containing micro-perforated panel - Google Patents

Preparation method, equipment and structure of honeycomb sandwich structure containing micro-perforated panel Download PDF

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CN108928050B
CN108928050B CN201711339151.XA CN201711339151A CN108928050B CN 108928050 B CN108928050 B CN 108928050B CN 201711339151 A CN201711339151 A CN 201711339151A CN 108928050 B CN108928050 B CN 108928050B
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honeycomb
adhesive film
micro
panel
needle
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CN108928050A (en
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纪双英
史湘宁
刘杰
许健翔
郝巍
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AVIC Composite Corp Ltd
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AVIC Composite Corp Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B26—HAND CUTTING TOOLS; CUTTING; SEVERING
    • B26F—PERFORATING; PUNCHING; CUTTING-OUT; STAMPING-OUT; SEVERING BY MEANS OTHER THAN CUTTING
    • B26F1/00—Perforating; Punching; Cutting-out; Stamping-out; Apparatus therefor
    • B26F1/24—Perforating by needles or pins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/12—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of paper or cardboard
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
    • B32B37/1284—Application of adhesive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
    • B32B37/144—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers using layers with different mechanical or chemical conditions or properties, e.g. layers with different thermal shrinkage, layers under tension during bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
    • B32B37/146—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers whereby one or more of the layers is a honeycomb structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/04—Punching, slitting or perforating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/04—Punching, slitting or perforating
    • B32B2038/047—Perforating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/02—Synthetic macromolecular fibres
    • B32B2262/0261—Polyamide fibres
    • B32B2262/0269—Aromatic polyamide fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/06—Vegetal fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/10—Properties of the layers or laminate having particular acoustical properties
    • B32B2307/102—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Forests & Forestry (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

The invention discloses a preparation method and equipment of a honeycomb sandwich structure containing a micro-perforated panel. Belonging to the field of composite material sandwich structure manufacture. The method comprises the following steps: selecting a honeycomb substrate, selecting a glue film, preparing a micro-perforated panel and a rigid back plate, preparing a special needle roller, pre-perforating, combining, curing and the like before the glue film is used, and obtaining a final sandwich structure. The micro-perforated panel sandwich structure prepared by the technical scheme of the invention can be used in the field of noise elimination. The invention ensures the bonding quality and simultaneously avoids the blockage of the micropores of the panel by the glue film.

Description

Preparation method, equipment and structure of honeycomb sandwich structure containing micro-perforated panel
Technical Field
The invention belongs to the technology of manufacturing functional honeycombs, and relates to a method, equipment and a structure for manufacturing a honeycomb sandwich structure with a micro-perforated panel.
Background
In order to reduce the noise of an aircraft engine structure, the existing noise reduction technology mostly adopts a sandwich material noise reduction structure prepared by micro-perforated panel/honeycomb composite, and is characterized in that the honeycomb is bonded with a micro-perforated plate and matched with a rigid back plate to form a composite structure. The noise elimination principle is that external sound waves are absorbed and transmitted into the honeycomb structure through holes regularly distributed on the panel, the sound waves are reflected, refracted, penetrated and absorbed in the honeycomb, and are not transmitted out through the entering holes, and therefore the purpose of structural noise reduction is achieved. The silencing honeycomb technology is characterized in that holes are formed in a panel through a special gang drill machine, and a composite sandwich structure is formed by a glue film and a honeycomb material. The method adapts to different noise environments through the design of the perforated panel, the change of the size of the honeycomb structure, the design of the number of sandwich layers and the like.
The biggest difficulty in the preparation of the structure is to avoid the micro-pores from being blocked in the bonding process. The traditional honeycomb sandwich structure preparation method is to bond the panel and the honeycomb core by adopting the adhesive film, and specifically comprises the steps of laying the adhesive film and the panel at two ends of the honeycomb in sequence respectively, and then carrying out high-temperature treatment on the combined structure to obtain the integral sandwich structure.
In order to avoid the blocking of the micro-perforations by the adhesive film, it is a common practice to puncture the adhesive film at the corresponding position of the perforation before curing, and blow the adhesive film under and around the perforation with hot air. In order to improve the efficiency, the method usually needs to prepare a special hole breaking tool, and once the specification of the perforated panel is changed, the hole breaking tool needs to be manufactured again, so that the cost is higher.
Disclosure of Invention
The object of the present invention is to solve the above problems in the art and to provide a method and an apparatus for manufacturing a honeycomb sandwich structure comprising a microperforated panel, which method ensures the quality of the bonding and avoids the clogging of the microperforated panel.
In order to achieve the technical purpose, the technical scheme of the invention is as follows:
a method of making a sandwich structure of a panel including microperforations, comprising the steps of:
1) selecting a honeycomb matrix: the honeycomb matrix is selected from aramid paper honeycomb, glass cloth honeycomb, aluminum honeycomb or plant fiber honeycomb, the depth h of the honeycomb is 5-500 mm, and the side length L of the honeycomb cell is 2-8 mm;
2) selecting an adhesive film: the adhesive film can be an epoxy adhesive film, a bismaleimide adhesive film or a polyimide adhesive film, and the thickness t of the adhesive film is 0.02mm-0.15 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting or preparing a panel and a rigid back plate with the thickness of 0.2mm-10mm respectively, and processing the panel into a micro-perforated front panel in a laser drilling or mechanical drilling mode, wherein the diameter of each micro-hole is 0.1mm-3mm, and the perforation rate is 2% -20%;
4) preparing a special needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between the needles is 1.732 times of the side length of the honeycomb cell, the diameter of each needle is 0.1mm-0.5mm, the length of each needle is more than 10mm, and the front end of each needle is in a sharp needle shape;
5) pre-breaking holes before using the adhesive film: perforating the surface of the adhesive film by adopting the needle roller in the step 4), wherein the interval between the needles is determined by the side length of the honeycomb cells, and the adhesive film after pre-hole breaking is laid on the honeycomb by taking the center of each cell as the standard; then, breaking the honeycomb paved with the adhesive film at the temperature of 150-250 ℃ for 20-60 s;
6) and combining and curing the honeycomb matrix, the micro-perforated front panel and the rigid back panel to obtain the final sandwich structure.
Preferably, the honeycomb laid with the adhesive film in the step 5) is subjected to hole breaking in an oven.
The special equipment for pre-breaking holes is in a needle roller type, needles used in the needle roller are arranged in a regular triangle, and the distance between every two needles is 1.732 times of the length of a honeycomb cell side. The diameter of the needle is 0.1mm-0.5mm, the length is more than 10mm, and the front end is in a sharp needle shape.
A sandwich structure of a panel containing micro-perforations prepared by the method comprises a micro-perforated front panel, a honeycomb matrix and a rigid back panel.
The invention has the beneficial effects that: the sandwich structure comprising the micro-perforated panel is mainly used as a sound-damping structure, so the micro-perforations on the panel are functional perforations, and the micro-perforations are not allowed to be blocked in the preparation process. The invention utilizes the hollow structure of the honeycomb and the thermal shrinkage characteristic of the adhesive film to shrink the adhesive film to the honeycomb wall for gluing, thereby ensuring that the micro-perforation is not blocked and avoiding the defects of time and labor waste and high cost of the traditional method.
Drawings
FIG. 1 is a schematic flow diagram of a method of making a honeycomb sandwich structure including a microperforated face sheet in accordance with the present invention;
FIG. 2 is a honeycomb substrate with pre-perforated adhesive films laid thereon according to a method for manufacturing a honeycomb sandwich structure with a micro-perforated panel;
FIG. 3 shows a rubber film and a honeycomb substrate after hole breaking in a method for manufacturing a honeycomb sandwich structure with a micro-perforated panel according to the present invention;
the reference numbers in the figures are as follows: 11-pre-hole-broken glue film, 12-hole-broken glue film, 2-honeycomb substrate, and 3-pre-hole-broken.
Detailed Description
In order that the invention may be more clearly understood, the following detailed description of the embodiments of the invention is given with reference to the accompanying drawings and examples.
A method of making a sandwich structure of a panel containing microperforations as shown in figure 1, comprising the steps of:
1) selecting a honeycomb matrix: the honeycomb matrix is selected from aramid paper honeycomb, glass cloth honeycomb, aluminum honeycomb or plant fiber honeycomb, the depth h of the honeycomb is 5-500 mm, and the side length L of the honeycomb cell is 2-8 mm;
2) selecting an adhesive film: the adhesive film can be an epoxy adhesive film, a bismaleimide adhesive film or a polyimide adhesive film, and the thickness t of the adhesive film is 0.02mm-0.15 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting or preparing a panel and a rigid back plate with the thickness of 0.2mm-10mm respectively, and processing the panel into a micro-perforated front panel in a laser drilling or mechanical drilling mode, wherein the diameter of each micro-hole is 0.1mm-3mm, and the perforation rate is 2% -20%;
4) preparing a special needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between the needles is 1.732 times of the side length of the honeycomb cell, the diameter of each needle is 0.1mm-0.5mm, the length of each needle is more than 10mm, and the front end of each needle is in a sharp needle shape;
5) pre-breaking holes before using the adhesive film: as shown in fig. 2 and 3, perforating the surface of the adhesive film by using the needle roller in the step 4), wherein the interval between the needles is determined by the side length of the honeycomb cells, and the adhesive film after pre-breaking is laid on the honeycomb by taking the center of each cell as a standard; then, breaking the honeycomb paved with the adhesive film at the temperature of 150-250 ℃ for 20-60 s; FIG. 2 is a honeycomb substrate 2 with pre-perforated adhesive films 11 laid thereon according to the method for preparing a honeycomb sandwich structure with a micro-perforated panel, wherein pre-perforated holes 3 are distributed on the pre-perforated adhesive films 11; fig. 3 shows a perforated film 12 and a honeycomb substrate 2.
6) And combining and curing the honeycomb matrix, the micro-perforated front panel and the rigid back panel to obtain the final sandwich structure.
And (5) breaking the holes of the honeycomb paved with the adhesive film in the oven.
One special device for pre-breaking holes mentioned in the above steps is in the form of a needle roller, needles used in the needle roller are arranged in a regular triangle, and the distance between the needles is 1.732 times the length of the honeycomb cell side. The diameter of the needle is 0.1mm-0.5mm, the length is more than 10mm, and the front end is in a sharp needle shape.
The sandwich structure of the panel containing the micro-perforations prepared by the method comprises a micro-perforated front panel, a honeycomb matrix and a rigid back panel.
Example 1:
1) selecting a honeycomb matrix: selecting one piece of an aramid fiber paper honeycomb core with the height of 40mm and NH-5.5-48 produced by the medium aircraft composite material for later use.
2) Selecting an adhesive film: selecting a J-116 epoxy adhesive film produced by Heilongjiang petrochemical research institute, wherein the thickness t of the adhesive film is 0.4 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting two glass steel plates with the thickness of 0.5mm, wherein one glass steel plate is used as a rigid back plate, and the other glass steel plate is processed into a micro-perforated front panel by mechanical drilling, the perforation rate is 5%, and the aperture is 1.0 mm;
4) preparing a special needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between every two needles is 9.526mm, the diameter of each needle is 0.2mm, and the length of each needle is 15 mm;
5) breaking holes in the glue film: and pre-breaking the adhesive film by using a needle roller, laying the adhesive film on the honeycomb, and enabling the pre-broken hole on the adhesive film to be positioned at the center of the honeycomb cell as much as possible during laying. Then, the honeycomb paved with the adhesive film is placed at a high temperature for hole breaking, the hole breaking temperature is 150 ℃, and the hole breaking time is 30 s;
6) and (3) combining the honeycomb, the micro-perforated front panel and the rigid plate, and curing at 130 ℃ for 2 hours to obtain the final sandwich structure.
Example 2:
1) selecting a honeycomb matrix: selecting one piece of aramid paper honeycomb core with the height of 20mm and NRH-5-48 produced by the medium aircraft composite material for later use.
2) Selecting an adhesive film: selecting a J-154 epoxy adhesive film produced by Heilongjiang petrochemical research institute, wherein the thickness t of the adhesive film is 0.3 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting two glass steel plates with the thickness of 1.0mm, wherein one glass steel plate is used as a rigid back plate, and the other glass steel plate is processed into a micro-perforated front panel by mechanical drilling, the perforation rate is 5%, and the aperture is 1.0 mm;
4) preparing a special needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between every two needles is 8.66mm, the diameter of each needle is 0.2mm, and the length of each needle is 15 mm;
5) breaking holes in the glue film: and pre-breaking the adhesive film by using a needle roller, laying the adhesive film on the honeycomb, and enabling the pre-broken hole on the adhesive film to be positioned at the center of the honeycomb cell as much as possible during laying. Then, the honeycomb paved with the adhesive film is placed at a high temperature for hole breaking, the hole breaking temperature is 150 ℃, and the hole breaking time is 30 s;
6) and (3) combining the honeycomb, the micro-perforated front panel and the rigid plate, and curing at 130 ℃ for 2 hours to obtain the final sandwich structure.
Example 3:
1) selecting a honeycomb matrix: selecting one piece of aramid paper honeycomb core with the height of 20mm and NRH-5-48 produced by the medium aircraft composite material for later use.
2) Selecting an adhesive film: selecting a SY-14M high-temperature epoxy adhesive film produced by Beijing aviation material research institute, wherein the thickness t of the adhesive film is 0.3 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting two glass steel plates with the thickness of 1.0mm, wherein one glass steel plate is used as a rigid back plate, and the other glass steel plate is processed into a micro-perforated front panel by mechanical drilling, the perforation rate is 5%, and the aperture is 1.0 mm;
4) preparing a special needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between every two needles is 8.66mm, the diameter of each needle is 0.2mm, and the length of each needle is 15 mm;
5) breaking holes in the glue film: and pre-breaking the adhesive film by using a needle roller, laying the adhesive film on the honeycomb, and enabling the pre-broken hole on the adhesive film to be positioned at the center of the honeycomb cell as much as possible during laying. Then, the honeycomb paved with the adhesive film is placed at a high temperature for hole breaking, the hole breaking temperature is 220 ℃, and the hole breaking time is 60 s;
6) and (3) combining the honeycomb, the micro-perforated front panel and the rigid plate, and curing at 180 ℃ for 2 hours to obtain the final sandwich structure.
Example 4:
1) selecting a honeycomb matrix: selecting one aluminum honeycomb core with the cell size of 6mm and the height of 20mm for production of the medium aviation composite material for later use;
2) selecting an adhesive film: selecting a SY-24C high-temperature epoxy adhesive film produced by Beijing aviation material research institute, wherein the thickness t of the adhesive film is 0.3 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting two carbon fiber plates with the thickness of 1.0mm, wherein one carbon fiber plate is used as a rigid back plate, and the other carbon fiber plate is processed into a micro-perforated front panel by mechanical drilling, the perforation rate is 10 percent, and the aperture is 0.8 mm;
4) preparing a special needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between every two needles is 10.392mm, the diameter of each needle is 0.5mm, and the length of each needle is 15 mm;
5) breaking holes in the glue film: and pre-breaking the adhesive film by using a needle roller, laying the adhesive film on the honeycomb, and enabling the pre-broken hole on the adhesive film to be positioned at the center of the honeycomb cell as much as possible during laying. Then, the honeycomb paved with the adhesive film is put at a high temperature for hole breaking, the hole breaking temperature is 160 ℃, and the hole breaking time is 30 s;
6) and (3) combining the honeycomb, the micro-perforated front panel and the rigid plate, and curing at 130 ℃ for 2 hours to obtain the final sandwich structure.
Example 5:
1) selecting a honeycomb matrix: selecting one plant honeycomb core with the cell size of 4.5mm and the height of 30mm for production of the middle aviation composite material for later use;
2) selecting an adhesive film: selecting a J-154 medium-temperature epoxy adhesive film produced by Heilongjiang petrochemical research institute, wherein the thickness t of the adhesive film is 0.2 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting two carbon fiber plates with the thickness of 0.8mm, wherein one carbon fiber plate is used as a rigid back plate, and the other carbon fiber plate is processed into a micro-perforated front panel by mechanical drilling, the perforation rate is 6 percent, and the aperture is 1.2 mm;
4) preparing a special needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between every two needles is 7.794mm, the diameter of each needle is 0.3mm, and the length of each needle is 12 mm;
5) breaking holes in the glue film: and pre-breaking the adhesive film by using a needle roller, laying the adhesive film on the honeycomb, and enabling the pre-broken hole on the adhesive film to be positioned at the center of the honeycomb cell as much as possible during laying. Then, the honeycomb paved with the adhesive film is put at a high temperature for hole breaking, the hole breaking temperature is 160 ℃, and the hole breaking time is 40 s;
6) and (3) combining the honeycomb, the micro-perforated front panel and the rigid plate, and curing at 130 ℃ for 2 hours to obtain the final sandwich structure.
Example 6:
1) selecting a honeycomb matrix: selecting one aluminum honeycomb core with the cell size of 6mm and the height of 20mm for production of the medium aviation composite material for later use;
2) selecting an adhesive film: selecting a J-299 high-toughness bismaleimide film produced by Heilongjiang petrochemical research institute, wherein the thickness t of the bismaleimide film is 0.35 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting two carbon fiber plates with the thickness of 1.0mm, wherein one carbon fiber plate is used as a rigid back plate, and the other carbon fiber plate is processed into a micro-perforated front panel by mechanical drilling, the perforation rate is 6 percent, and the aperture is 0.5 mm;
4) preparing a special needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between every two needles is 10.392mm, the diameter of each needle is 0.5mm, and the length of each needle is 15 mm;
5) breaking holes in the glue film: and pre-breaking the adhesive film by using a needle roller, laying the adhesive film on the honeycomb, and enabling the pre-broken hole on the adhesive film to be positioned at the center of the honeycomb cell as much as possible during laying. Then, the honeycomb paved with the adhesive film is placed at a high temperature for hole breaking, the hole breaking temperature is 250 ℃, and the hole breaking time is 30 s;
6) and (3) combining the honeycomb, the micro-perforated front panel and the rigid plate, and curing at 200 ℃ for 3 hours to obtain the final sandwich structure.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.

Claims (3)

1. A method for preparing a sandwich structure of a panel containing micro-perforations is characterized by comprising the following steps:
1) selecting a honeycomb matrix: the honeycomb substrate is selected from aramid paper honeycomb, glass cloth honeycomb, aluminum honeycomb or plant fiber honeycomb, the depth h of the honeycomb is =5 mm-500 mm, and the side length L of the honeycomb cell is =2 mm-8 mm;
2) selecting an adhesive film: the adhesive film is an epoxy adhesive film, a bismaleimide adhesive film or a polyimide adhesive film, and the thickness t =0.02mm-0.15 mm;
3) preparing a micro-perforated front panel and a rigid back panel: selecting or preparing a panel and a rigid back plate with the thickness of 0.2mm-10mm respectively, and processing the panel into a micro-perforated front panel in a laser drilling or mechanical drilling mode, wherein the diameter of each micro-hole is 0.1mm-3mm, and the perforation rate is 2% -20%;
4) preparing a needle roller: the needles in the needle roller are arranged in a regular triangle, the distance between the needles is 1.732 times of the side length of the honeycomb cell, the diameter of each needle is 0.1mm-0.5mm, the length of each needle is more than 10mm, and the front end of each needle is in a sharp needle shape;
5) pre-breaking holes before using the adhesive film: perforating the surface of the adhesive film by adopting the needle roller in the step 4), wherein the interval between the needles is determined by the side length of the honeycomb cells, and the adhesive film after pre-hole breaking is laid on the honeycomb by taking the center of each cell as the standard; then, breaking the honeycomb paved with the adhesive film at the temperature of 150-250 ℃ for 20-60 s;
6) and combining and curing the honeycomb matrix, the micro-perforated front panel and the rigid back panel to obtain the final sandwich structure.
2. The method of claim 1 for making a sandwich construction of a microperforated face sheet, comprising:
and (5) breaking the holes of the honeycomb paved with the adhesive film in the oven.
3. A sandwich structure comprising a microperforated face sheet made by the process of claim 1 comprising a microperforated front sheet, a honeycomb matrix and a rigid back sheet.
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