CN115091795A - Repairing method for metal honeycomb sandwich structural member composite material by patching, gluing and repairing - Google Patents
Repairing method for metal honeycomb sandwich structural member composite material by patching, gluing and repairing Download PDFInfo
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- CN115091795A CN115091795A CN202210607939.9A CN202210607939A CN115091795A CN 115091795 A CN115091795 A CN 115091795A CN 202210607939 A CN202210607939 A CN 202210607939A CN 115091795 A CN115091795 A CN 115091795A
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- metal honeycomb
- honeycomb sandwich
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/16—Auto-repairing or self-sealing arrangements or agents
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/24—Apparatus or accessories not otherwise provided for
Abstract
The invention relates to the field of repairing of a metal honeycomb sandwich, in particular to a repairing method for repairing a composite material of a metal honeycomb sandwich structural member by means of patching and bonding, which comprises the following specific steps: s1, marking; s2, removing the loss part; s3, chamfering; s4, sanding; s5, removing residues; s6, cleaning; s7, repairing damage; s8, heating; s9, repairing and leveling; s10, paving; s11, the number of patches; s12, repairing the ratio; s13, repairing the size; s14, repairing the layer; s15, an isolation layer; s16, compacting; s17, vacuumizing; s18, heating and curing; s19, repeating the steps; the repairing process for the metal honeycomb sandwich structure composite material by the patching and bonding does not need to make holes on the original structure, does not damage the original structure, does not generate secondary damage, and does not increase a new stress concentration fatigue crack initiation source; the metal reinforcing sheet does not need to be connected through a fastening piece, and the composite material repairing sheet is light in weight, high in strength and small in weight increment of an original structure.
Description
Technical Field
The invention relates to the field of repairing of metal honeycomb interlayers, in particular to a repairing method for repairing a composite material of a metal honeycomb interlayer structural member by means of patching and gluing.
Background
The metal honeycomb sandwich structure is a sandwich structure formed by bonding metal panels at two sides and a metal honeycomb core in the middle, the panel of the structure is thin, a bonding interface exists between the panel and the core, plate-core debonding is easy to occur, the metal honeycomb core is impacted, corrosion collapse and other semi-through hole and through hole damages are easy to occur, the existing repair mode mainly comprises part replacement or metal reinforcing sheet mechanical connection reinforcement, and both the parts 1 and 5 in the figures are embedded repair sheets as shown in figures 7-10; 2. 6 are all metal reinforcing sheets; 3, repairing the honeycomb; 4, the fastener is low in part renewal difficulty and simple to operate, but the metal honeycomb sandwich structure is complex in forming process, and the part renewal cost is high; the metal reinforcing plate mechanical connection reinforcement repair generally comprises the following steps: (1) removing the damaged metal honeycomb core; (2) cleaning the honeycomb core removing part, and bonding and repairing the honeycomb core; (3) bonding a panel repairing sheet; (4) mechanically connecting the metal reinforcing sheet. The reinforcement mode has strong reliability, can well restore the rigidity and the strength of an original structure, but needs to be drilled on the original structure for mechanical connection reinforcement, easily causes secondary damage of the original structure, a connecting hole is easy to become a new stress concentration part and becomes a new hidden danger source for fatigue damage, and in the mechanical connection reinforcement repair of the metal reinforcement piece, the reinforcement piece is generally externally attached to the surface of a metal honeycomb sandwich structure, obvious bulges are caused, the appearance of the original structure is influenced, and when the requirement of the maintenance structure on the pneumatic appearance of the outer surface is higher, the mechanical connection repair mode of the externally attached reinforcement piece cannot be applied.
Disclosure of Invention
In order to solve the problems, the invention provides a repairing method for a metal honeycomb sandwich structural member composite material through patching, gluing and repairing.
A method for repairing a metal honeycomb sandwich structural member by using a composite material through patching and gluing comprises the following specific steps:
s1, identification: determining the damage range of the metal honeycomb sandwich structure through knocking or ray inspection and identifying;
s2, removing loss part: removing the damaged honeycomb core and the panel of the metal honeycomb sandwich piece by using a hole scribing device;
s3, chamfering: using 80-120-mesh sand paper to perform bevel chamfering and polishing on the periphery of the metal honeycomb sandwich structure removing panel, wherein the chamfer width delta d/t is (10-30), and t is the thickness of the metal honeycomb sandwich panel;
s4, sanding treatment: the panel within the range of 5 mm-10 mm (d0) of the periphery of the chamfer is subjected to sanding treatment, and a surface coating and an oxidation layer of the panel can be removed by adopting 80-120-mesh abrasive paper;
s5, removing residues: trimming the residual honeycomb aluminum foil after the metal honeycomb is removed by the interlayer structural member with scissors, tweezers and rotary file tools;
s6, cleaning: cleaning the damage removal area, the chamfering area and the panel frosting area by using solvents such as acetone, alcohol and the like, and then airing or drying the metal honeycomb sandwich piece in an oven;
s7, repairing damage: paving a layer of glass cloth or resin film containing glue on the bottom panel of the dug metal honeycomb sandwich structure, wrapping a circle of foaming glue around the repaired metal honeycomb, and filling the repaired honeycomb into the damage of the metal honeycomb sandwich structure through holes;
s8, heating: heating the repaired honeycomb area by using heating equipment such as an oven, an electric blanket and a hot air blower according to the adopted foaming glue curing process to foam and cure the foaming glue and finish the bonding of the repaired honeycomb;
s9, repairing and leveling: after the foaming adhesive is cured, trimming the repaired honeycomb by using a grinding machine or a file, removing the raised nodules to enable the repaired metal honeycomb to be flush with the original honeycomb, and cleaning and drying;
s10, paving: preparing a multilayer composite carbon fiber prepreg repairing sheet or a glue-containing carbon fiber fabric wet repairing sheet according to the size of the damaged area;
s11, number of patches: when the carbon fiber prepreg is adopted for repairing the patch, the number N of the patch is t/(0.1-0.15); when the carbon fiber fabric containing the glue is adopted for repairing the patch, the number N of the patch is t/(0.2-0.25);
s12, repairing ratio: when the carbon fiber fabric repairing sheet containing the glue is adopted, the weight ratio of the glue contained in the repairing sheet is controlled to be (50 +/-5)%;
s13, repairing size: the size of each layer of patch is determined according to the perforation damage range and the panel chamfering range; wherein the minimum repair patch outline dimension D1 is equal to the metal honeycomb perforation damage outline dimension D0, and the rest repair patch outline dimensions Dn are D0+ delta D/(N-1) x (N-1) x 2;
s14, repairing layer: manufacturing an additional repairing layer DN +1, wherein the outline size DN +1 of the additional repairing layer is DN +2d 0;
s15, isolating layer: manufacturing a layer of glue-containing glass cloth for isolating the metal honeycomb panel from the carbon fiber maintenance patch to prevent galvanic corrosion caused by direct contact between the metal panel and the carbon fiber;
s16, compacting: paving and sticking a glass cloth DE containing glue above the repaired honeycomb of the metal honeycomb sandwich structural member, paving and sticking D1-DN +1 repaired carbon fiber patches layer by layer, and strickling and compacting;
s17, vacuumizing: packaging a vacuum bag in the repair area, and vacuumizing;
s18, heating and curing: heating and curing the repair area of the metal honeycomb sandwich structure by utilizing heating equipment such as an electric blanket, an oven, a hot air blower, a hot pressing tank and the like according to the curing process requirement of using the adhesive;
s19, repeating the steps: and (4) finishing curing, polishing the repair area of the metal honeycomb sandwich structure and recovering paint layers and coatings on the surface, namely completing the repairing, gluing and repairing of the semi-perforation damage composite material of the metal honeycomb sandwich structure, and repeating the steps S10-S19 on the other side panel during repairing of the perforation damage.
The damaged honeycomb core and the damaged panel in the step S2 are specifically a damaged honeycomb core and a side panel removed by half-through-hole damage, and a damaged honeycomb core and two side panels removed by through-hole damage.
The foaming glue of the step S7 can be SY-P9 or J-118.
And S10, paving anticorrosive glass cloth DE above the metal honeycomb sandwich structural member repairing honeycomb, paving carbon fiber repairing patches D1-D4 layer by layer, and finally paving an additional layer D5, wherein each layer is scraped and compacted when being paved.
Both patches of step S11 are rounded.
The weight ratio of the rubber contained in the glass cloth of the step S15 should be controlled to be (50 ± 5)%, and the overall dimension DE of the glass fiber insulation cloth is DN + 1.
The invention has the beneficial effects that: the repairing process for the metal honeycomb sandwich structure composite material by the patching and bonding does not need to make holes on the original structure, does not damage the original structure, does not generate secondary damage, and does not increase a new stress concentration fatigue crack initiation source; the metal reinforcing sheet does not need to be connected through a fastening piece, and the composite material repairing sheet is light in weight, high in strength and small in weight increment of an original structure; after the composite material is subjected to patching, gluing and repairing, the repairing area of the metal honeycomb sandwich structure is flat and smooth to be connected, the surface has no step bulge, and the pneumatic appearance is excellent in recovery.
Drawings
The invention is further illustrated by the following examples in conjunction with the drawings.
FIG. 1 is a first schematic view of a repair process of the present invention;
FIG. 2 is a schematic view of a repair process flow diagram of the present invention;
FIG. 3 is a third schematic view of a repair process of the present invention;
FIG. 4 is a fourth schematic view of the repair process of the present invention;
FIG. 5 is a schematic view of a repair process flow diagram of the present invention;
FIG. 6 is a sixth schematic view of a repair process flow of the present invention;
FIG. 7 is a first schematic diagram illustrating semi-perforation damage repair according to the background of the invention;
FIG. 8 is a second schematic diagram of repairing a semi-perforation damage according to the background art of the present invention;
FIG. 9 is a first schematic view of the puncture damage repair of the background of the invention;
FIG. 10 is a first schematic view of repairing damage to a via hole according to the background art of the present invention;
reference numerals: 1. a metal panel; 2. a metal honeycomb; 3. repairing the honeycomb; 4. foaming glue; 5. glass cloth containing glue or epoxy glue film; 6. a carbon fiber prepreg repair sheet or a carbon fiber fabric repair sheet containing glue; 7. the glass cloth contains glue.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below.
As shown in fig. 1 to 6, a repairing method for repairing a metal honeycomb sandwich structural member by using a composite material through patching and bonding comprises the following specific steps:
s1, identification: determining the damage range of the metal honeycomb sandwich structure through knocking or ray inspection and marking, as shown in the attached figure 2;
s2, removing loss part: removing the damaged honeycomb core and the panel of the metal honeycomb sandwich piece by using a hole scribing device;
s3, chamfering: using 80-120-mesh sand paper to perform bevel chamfering and polishing on the periphery of the metal honeycomb sandwich structure removing panel, wherein the chamfer width delta d/t is (10-30), and t is the thickness of the metal honeycomb sandwich panel, as shown in the attached figure 4;
s4, sanding treatment: the panel within the range of 5 mm-10 mm (d0) of the periphery of the chamfer is subjected to sanding treatment, and a surface coating and an oxidation layer of the panel can be removed by sanding with 80-120-mesh sand paper, as shown in figure 4;
s5, removing residues: trimming the residual honeycomb aluminum foil after the metal honeycomb is removed by the interlayer structural member with scissors, tweezers and rotary file tools;
s6, cleaning: cleaning the damage removal area, the chamfering area and the panel frosting area by using solvents such as acetone, alcohol and the like, and then airing or drying the metal honeycomb sandwich piece in an oven;
s7, repairing damage: paving a layer of glass cloth or resin film containing glue on the bottom panel of the excavated damaged metal honeycomb sandwich structure, wrapping a circle of foaming glue around the repaired metal honeycomb, and filling the repaired honeycomb into the damaged perforated metal honeycomb sandwich structure, as shown in figure 5;
s8, heating: heating the repaired honeycomb area by using heating equipment such as an oven, an electric blanket and a hot air blower according to the adopted foaming glue curing process to foam and cure the foaming glue and finish the bonding of the repaired honeycomb;
s9, repairing and leveling: after the foaming adhesive is cured, trimming and repairing the honeycomb by using a grinding machine or a file, removing raised adhesive nodules, enabling the repaired metal honeycomb to be flush with the honeycomb with the original structure, and cleaning and drying the repaired metal honeycomb, wherein the dimension DE of the glass cloth is 70mm which is D5 mm, the glass cloth is EW100 glass cloth, the adhesive is SY-49 adhesive, and the adhesive content is 50%;
s10, paving: preparing a plurality of layers of composite carbon fiber prepreg repairing patches or glue-containing carbon fiber fabric wet repairing patches according to the size of a damaged area, paving anticorrosive glass cloth DE above the repairing honeycomb of the metal honeycomb sandwich structural member, paving carbon fiber repairing patches D1-D4 layer by layer, and finally paving an additional layer D5, and scraping and compacting when each layer is paved;
s11, number of patches: when the carbon fiber prepreg is adopted for repairing the patch, the number N of the patch is t/(0.1-0.15); when the carbon fiber fabric containing the glue is adopted for repairing the patch, the number N of the patch is t/(0.2-0.25);
s12, repairing ratio: when the repairing piece of the carbon fiber fabric containing the glue is adopted, the weight ratio of the glue contained in the repairing piece is controlled to be (50 +/-5)%;
s13, repairing size: the size of each layer of repairing sheet is determined according to the perforation damage range and the panel chamfering range; wherein the minimum repair patch outline dimension D1 is equal to the metal honeycomb perforation damage outline dimension D0, and the rest repair patch outline dimensions Dn are D0+ delta D/(N-1) x (N-1) x 2;
s14, repairing layer: manufacturing an additional repairing layer DN +1, wherein the outline size DN +1 of the additional repairing layer is DN +2d 0;
s15, isolating layer: manufacturing a layer of glass cloth containing glue for isolating the metal honeycomb panel from the carbon fiber maintenance patch to prevent galvanic corrosion caused by direct contact between the metal panel and the carbon fiber;
s16, compacting: paving a glued glass cloth DE above the repaired honeycomb of the metal honeycomb sandwich structural member, paving D1-DN + 1 repaired carbon fiber patches layer by layer, and strickling and compacting, as shown in figure 6;
s17, vacuumizing: packaging a vacuum bag in the repair area, and vacuumizing;
s18, heating and curing: heating and curing the repair area of the metal honeycomb sandwich structure by using heating equipment such as an electric blanket, an oven, a hot air blower, an autoclave and the like according to the curing process requirement of the adhesive, specifically, putting the repair part into the oven to perform heating and curing according to the curing process requirement of SY-49 adhesive, polishing and grinding the repair area after curing is finished, and recovering a surface coating and a paint layer;
s19, repeating the steps: and (4) finishing curing, polishing the repair area of the metal honeycomb sandwich structure and recovering paint layers and coatings on the surface, namely completing the repairing, gluing and repairing of the semi-perforation damage composite material of the metal honeycomb sandwich structure, and repeating the steps S10-S19 on the other side panel during repairing of the perforation damage.
The repairing process for the metal honeycomb sandwich structure composite material by the patching and bonding does not need to make holes on the original structure, does not damage the original structure, does not generate secondary damage, and does not increase a new stress concentration fatigue crack initiation source; the metal reinforcing sheet does not need to be connected through a fastening piece, and the composite material repairing sheet is light in weight, high in strength and small in weight increment of an original structure; after the composite material is subjected to patching, gluing and repairing, the repairing area of the metal honeycomb sandwich structure is flat and smooth to be connected, the surface has no step bulge, and the pneumatic appearance is excellent in recovery.
The damaged honeycomb core and the damaged panel in the step S2 are specifically a damaged honeycomb core and a damaged side panel removed by a half-through-hole damage, the damaged honeycomb core and the damaged side panels removed by a through-hole damage, the damaged panel and the honeycomb on one side of the metal honeycomb sandwich structure can be removed by using a punch with a diameter of 30mm, and the bottom panel in the hole is polished to be flat, as shown in fig. 3.
In the step S3, the panel chamfer width Δ d directly affects the bonding area of the composite material repair patch and the structural strength after bonding, when Δ d is small, the bonding area is small and the strength is insufficient, and when Δ d is too large, the original structure is ground in a larger range, and the invention is verified by system tests and actual products that Δ d/t is (10-30), the repairing bonding effect is optimal.
In step S4, 80-mesh sand paper is used to perform chamfer grinding on the panel in the repair area, and the chamfer grinding area Δ d is controlled to be 15mm (18.75 × t), so that the chamfer grinding area should be in smooth transition.
In the step S4, the chamfer peripheral frosted range d0 determines the sizes of the anti-galvanic corrosion glass cloth DE and the additional layer DN +1 during the repair of the composite material by patching and gluing, and directly influences the anti-galvanic corrosion performance and the gluing strength of the metal honeycomb sandwich structure repair area, and the patching and gluing effect is optimal when the d0 is (5 mm-10 mm) through system tests and practical product verification.
The additional layer adhesive surface frosting treatment of step S5 of the present invention: the panel was sanded with 80-mesh sandpaper within a range of 5mm from the chamfered periphery d0, and the honeycomb aluminum foil remaining in the hole after the damage was removed was trimmed with scissors.
The foaming glue of the step S7 can be SY-P9 or J-118.
And S7, paving a layer of EW100 glass cloth containing SY-49 adhesive on the bottom panel of the dug metal honeycomb sandwich structure.
The step S8 is to put the repair piece into the oven to heat according to SY-P9 foaming glue curing process, so that the foaming glue is foamed and cured.
In the step 10, the selection of the repair material directly influences the structural strength and the process operability after repair, and the invention firstly proposes that the repair patch of the composite material carbon fiber prepreg or the glue-containing carbon fiber fabric wet patch is adopted to carry out patching, gluing and repairing on the damaged panel of the metal honeycomb sandwich structure, belonging to key innovation content.
In the step 11, reasonably determining the number of the patches as a key link for repairing the damage of the metal honeycomb sandwich structure, wherein when the patches are repaired by using the carbon fiber prepreg through system tests and actual product verification, the number N of the patches is t/(0.1-0.15); when the carbon fiber fabric containing glue is adopted for repairing the patch, the patching and gluing effect is optimal when the number N of the patches is t/(0.2-0.25).
Both patches of step S11 are rounded.
In the step S12 and the step S15, the glue content of the carbon fiber fabric wet patch and the corrosion-resistant glass cloth directly influences whether the defects of poor glue and rich glue are generated after the carbon fiber fabric wet patch and the corrosion-resistant glass cloth are cured, and the repairing effect is optimal when the glue weight ratio is controlled to be (50 +/-5)% through system tests and actual product verification.
In the step S13, the size of the outline dimension of each layer of carbon fiber repair patch determines the lapping amount between each layer of carbon fiber repair patch, and the lapping amount between the patches directly affects the repair bonding interface strength, and through system tests and actual product verification, the invention adopts the calculation strategy provided in the step S13 to determine the size of each layer of patch, so that the repair effect is optimal, namely: the minimum repair patch outline dimension D1 is equal to the metal honeycomb perforation damage outline dimension D0, and the rest repair patch outline dimensions Dn are D0+ delta D/(N-1) x (N-1) x 2.
The weight ratio of the rubber contained in the glass cloth of the step S15 should be controlled to be (50 ± 5)%, and the overall dimension DE of the glass fiber insulation cloth is DN + 1.
In the step S15, because the potential difference between the aluminum alloy metal and the carbon fiber is large, galvanic corrosion may occur when different materials are directly contacted, and the product structure is damaged.
Based on a repairing and bonding repair process, the characteristics of high specific strength and high specific modulus of composite carbon fiber are utilized, after damage to the metal honeycomb sandwich structure is removed, the composite carbon fiber prepreg or fabric wet cloth is adopted to perform oblique bonding repair on the metal honeycomb sandwich structure, and a layer of glass fiber cloth containing glue is added on a bonding interface of the carbon fiber and the metal structure to perform electrical insulation, so that galvanic corrosion caused by direct contact of metal and the carbon fiber is prevented.
The repairing method for the metal honeycomb sandwich structure composite material by the patching and gluing only needs to perform simple surface treatment after removing the damage of the original structure, does not need to make holes again, does not damage the original structure, does not generate a new stress concentration source after repairing, effectively reduces the risk of fatigue damage, has no bulge on the repaired surface, ensures that the repaired area is smoothly connected with the original structure, and can better keep the original structure appearance.
The foregoing shows and describes the general principles, principal features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. A method for repairing a metal honeycomb sandwich structural member by using a composite material through patching and gluing is characterized by comprising the following steps of: the method comprises the following specific steps:
s1, identification: determining the damage range of the metal honeycomb sandwich structure through knocking or ray inspection and identifying;
s2, removing loss part: removing the damaged honeycomb core and panel of the metal honeycomb sandwich by using a hole scratching device;
s3, chamfering: performing bevel chamfering and polishing on the periphery of the metal honeycomb sandwich structure removing panel;
s4, sanding;
s5, removing residues: trimming the residual honeycomb aluminum foil after the metal honeycomb is removed by the interlayer structural member with scissors, tweezers and rotary file tools;
s6, cleaning: cleaning the damage removal area, the chamfering area and the panel frosting area by using solvents such as acetone, alcohol and the like, and then airing or drying the metal honeycomb sandwich piece in an oven;
s7, repairing damage: paving a layer of glass cloth or resin film containing glue on the bottom panel of the dug metal honeycomb sandwich structure, wrapping a circle of foaming glue around the repaired metal honeycomb, and filling the repaired honeycomb into the damage of the metal honeycomb sandwich structure through holes;
s8, heating: heating the repaired honeycomb area by using heating equipment such as an oven, an electric blanket and a hot air blower according to the adopted foaming glue curing process to foam and cure the foaming glue and finish the bonding of the repaired honeycomb;
s9, repairing and leveling: after the foaming adhesive is cured, trimming the repaired honeycomb by using a grinding machine or a file, removing raised nodules to enable the repaired metal honeycomb to be flush with the original honeycomb structure, and cleaning and drying;
s10, paving: preparing a multilayer composite carbon fiber prepreg repair sheet or a glue-containing carbon fiber fabric wet repair sheet according to the size of the damaged area;
s11, determining the number of patches;
s12, repair ratio: when the carbon fiber fabric repairing sheet containing the glue is adopted, the weight ratio of the glue contained in the repairing sheet is controlled to be (50 +/-5)%;
s13, repairing size: the size of each layer of repairing sheet is determined according to the perforation damage range and the panel chamfering range;
s14, repairing layer: manufacturing an additional repairing layer DN +1, wherein the outline size DN +1 of the additional repairing layer is DN +2d 0;
s15, isolating layer: manufacturing a layer of glue-containing glass cloth for isolating the metal honeycomb panel from the carbon fiber maintenance patch to prevent galvanic corrosion caused by direct contact between the metal panel and the carbon fiber;
s16, compacting: paving and sticking a glass cloth DE containing glue above the repaired honeycomb of the metal honeycomb sandwich structural member, paving and sticking D1-DN +1 repaired carbon fiber patches layer by layer, and strickling and compacting;
s17, vacuumizing: packaging a vacuum bag in the repair area, and vacuumizing;
s18, heating and curing: according to the curing process requirement of using the adhesive, heating equipment such as an electric blanket, an oven, a hot air blower, a hot pressing tank and the like is used for heating and curing the repair area of the metal honeycomb sandwich structure;
s19, repeating the steps: and (4) finishing curing, polishing the repair area of the metal honeycomb sandwich structure and recovering paint layers and coatings on the surface, namely completing the repairing, gluing and repairing of the semi-perforation damage composite material of the metal honeycomb sandwich structure, and repeating the steps S10-S19 on the other side panel during repairing of the perforation damage.
2. The method for repairing the metal honeycomb sandwich structure composite material by the repair of the repair glue of the metal honeycomb sandwich structure composite material, according to claim 1, is characterized in that: the damaged honeycomb core and the damaged panel in the step S2 are specifically a damaged honeycomb core and a side panel removed by half-through-hole damage, and a damaged honeycomb core and two side panels removed by through-hole damage.
3. The method for repairing the metal honeycomb sandwich structure composite material by the repair bonding according to claim 1, wherein the method comprises the following steps: the foaming glue of the step S7 can be SY-P9 or J-118.
4. The method for repairing the metal honeycomb sandwich structure composite material by the repair bonding according to claim 1, wherein the method comprises the following steps: and S10, paving anticorrosive glass cloth DE above the metal honeycomb sandwich structural member repairing honeycomb, paving carbon fiber repairing patches D1-D4 layer by layer, and finally paving an additional layer D5, wherein each layer is scraped and compacted when being paved.
5. The method for repairing the metal honeycomb sandwich structure composite material by the repair of the repair glue of the metal honeycomb sandwich structure composite material, according to claim 1, is characterized in that: both patches of step S11 are rounded.
6. The method for repairing the metal honeycomb sandwich structure composite material by the repair of the repair glue of the metal honeycomb sandwich structure composite material, according to claim 1, is characterized in that: the weight ratio of the glue contained in the glass cloth in the step S15 is controlled to be (50 +/-5)%, and the overall dimension DE of the glass fiber isolation cloth is DN + 1.
7. The method for repairing the metal honeycomb sandwich structure composite material by the repair of the repair glue of the metal honeycomb sandwich structure composite material, according to claim 1, is characterized in that: in the step S3, 80-120-mesh sand paper is used to perform bevel chamfering and polishing on the periphery of the metal honeycomb sandwich structure removing panel, where the chamfer width Δ d/t is 10-30, and t is the thickness of the metal honeycomb sandwich panel.
8. The method for repairing the metal honeycomb sandwich structure composite material by the repair of the repair glue of the metal honeycomb sandwich structure composite material, according to claim 1, is characterized in that: in the step S4, the panel within a range of 5mm to 10mm of the periphery of the chamfer is subjected to a sanding treatment, and a surface coating and an oxide layer of the panel can be removed by sanding with 80-120-mesh sand paper.
9. The method for repairing the metal honeycomb sandwich structure composite material by the repair of the repair glue of the metal honeycomb sandwich structure composite material, according to claim 1, is characterized in that: in the step S13, the minimum repair patch dimension D1 is equal to the damage dimension D0 of the metal honeycomb through hole, and the remaining repair patch dimensions Dn are D0+ Δ D/(N-1) × 2.
10. The method for repairing the metal honeycomb sandwich structure composite material by the repair bonding according to claim 1, wherein the method comprises the following steps: in step S11, when the carbon fiber prepreg patch is used for repairing the patch, the number N of the patch is t/(0.1-0.15); when the carbon fiber fabric containing the glue is adopted for repairing the patch, the number N of the patch is t/(0.2-0.25).
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