CN116749560A - Repairing method for impact damage defect of composite honeycomb sandwich panel - Google Patents
Repairing method for impact damage defect of composite honeycomb sandwich panel Download PDFInfo
- Publication number
- CN116749560A CN116749560A CN202310685939.5A CN202310685939A CN116749560A CN 116749560 A CN116749560 A CN 116749560A CN 202310685939 A CN202310685939 A CN 202310685939A CN 116749560 A CN116749560 A CN 116749560A
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- Prior art keywords
- repairing
- honeycomb core
- skin
- honeycomb
- sandwich panel
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- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 30
- 230000006378 damage Effects 0.000 title claims abstract description 24
- 230000007547 defect Effects 0.000 title claims abstract description 17
- 239000002131 composite material Substances 0.000 title claims abstract description 16
- 230000008439 repair process Effects 0.000 claims abstract description 25
- 238000005498 polishing Methods 0.000 claims abstract description 19
- 239000003292 glue Substances 0.000 claims abstract description 13
- 238000004519 manufacturing process Methods 0.000 claims abstract description 10
- 230000008569 process Effects 0.000 claims abstract description 7
- 238000005520 cutting process Methods 0.000 claims abstract description 6
- 238000009659 non-destructive testing Methods 0.000 claims abstract description 4
- 239000010410 layer Substances 0.000 claims description 43
- 239000004744 fabric Substances 0.000 claims description 15
- 238000010438 heat treatment Methods 0.000 claims description 11
- 238000009966 trimming Methods 0.000 claims description 8
- 239000002313 adhesive film Substances 0.000 claims description 7
- 238000001816 cooling Methods 0.000 claims description 7
- 238000003825 pressing Methods 0.000 claims description 7
- 230000007480 spreading Effects 0.000 claims description 6
- 238000003892 spreading Methods 0.000 claims description 6
- 239000011521 glass Substances 0.000 claims description 5
- 238000004321 preservation Methods 0.000 claims description 4
- 239000011241 protective layer Substances 0.000 claims description 4
- 229920001821 foam rubber Polymers 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 210000001503 joint Anatomy 0.000 claims description 2
- 238000007517 polishing process Methods 0.000 claims 1
- 238000007493 shaping process Methods 0.000 claims 1
- 238000002347 injection Methods 0.000 abstract description 7
- 239000007924 injection Substances 0.000 abstract description 7
- 238000000465 moulding Methods 0.000 abstract description 2
- 238000001723 curing Methods 0.000 description 12
- 239000002344 surface layer Substances 0.000 description 8
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 4
- 239000004917 carbon fiber Substances 0.000 description 4
- 238000004140 cleaning Methods 0.000 description 4
- 239000006260 foam Substances 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- DBGIVFWFUFKIQN-UHFFFAOYSA-N (+-)-Fenfluramine Chemical compound CCNC(C)CC1=CC=CC(C(F)(F)F)=C1 DBGIVFWFUFKIQN-UHFFFAOYSA-N 0.000 description 3
- 208000027418 Wounds and injury Diseases 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 208000014674 injury Diseases 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 229920001971 elastomer Polymers 0.000 description 2
- 239000000565 sealant Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 229920006335 epoxy glue Polymers 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000037380 skin damage Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
-
- 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
- B29C73/04—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 using preformed elements
- B29C73/10—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 using preformed elements using patches sealing on the surface of the article
- B29C73/12—Apparatus therefor, e.g. for applying
-
- 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
- B29C73/245—Apparatus or accessories not otherwise provided for for removing the element having caused the damage
-
- 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
- B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
-
- 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
- B29C73/30—Apparatus or accessories not otherwise provided for for local pressing or local heating
- B29C73/32—Apparatus or accessories not otherwise provided for for local pressing or local heating using an elastic element, e.g. inflatable bag
-
- 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
- B29C73/30—Apparatus or accessories not otherwise provided for for local pressing or local heating
- B29C73/34—Apparatus or accessories not otherwise provided for for local pressing or local heating for local heating
-
- 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
- B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
- B29C2073/262—Apparatus or accessories not otherwise provided for for mechanical pretreatment for polishing, roughening, buffing or sanding the area to be repaired
-
- 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
- B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
- B29C2073/264—Apparatus or accessories not otherwise provided for for mechanical pretreatment for cutting out or grooving the area to be repaired
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/60—Multitubular or multicompartmented articles, e.g. honeycomb
- B29L2031/608—Honeycomb structures
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention provides a repair method for impact damage defects of a composite honeycomb sandwich panel, which mainly comprises the processes of cutting and removing damaged skins and honeycomb cores, polishing the skins of cut circumferences, manufacturing and installing honeycomb core repair blocks, molding and curing the honeycomb cores, repairing the skins, secondarily bagging, curing the skins, carrying out nondestructive testing and the like, and has the advantages of high part repair precision and high strength, and solves the problems of overweight parts, unbalanced weights and the like which are easy to occur in the traditional glue injection repair method due to large glue injection quantity.
Description
Technical Field
The invention relates to the field of composite material repair, in particular to the field of repair of impact damage defects of composite material honeycomb sandwich panels.
Background
The composite honeycomb sandwich panel structure is formed by bonding an upper skin, a lower skin and a honeycomb core through adhesive films, has the advantages of light weight, high specific strength, excellent vibration damping performance and the like, and is widely applied to manufacturing of various military and civil aircraft and aerospace products. In the production, use and transportation processes of the parts, the parts are often damaged by impact due to the reasons of collision, collision injury and the like, such as the problems of skin damage, honeycomb core tearing, collapse and the like of the honeycomb sandwich panel, and serious potential safety hazards are brought to the use of the parts.
At present, a common repairing method for the honeycomb sandwich panel is mainly a glue injection method, repair glue is injected into a honeycomb area, and after the glue solution is solidified, epoxy glue is adopted to scrape the defect area. Because the honeycomb sandwich panel is generally thicker, the glue injection amount is large, when the damage area is larger, the problems of overweight parts, unbalanced weight and the like are caused, and the service life and the use safety of the product are affected. In order to solve the defects of the traditional repairing method, development of a novel reliable repairing method is needed.
Disclosure of Invention
The invention aims to provide a repairing method for impact damage defects of a composite honeycomb sandwich panel, which is used for solving the problems of large glue injection amount, unbalanced counterweight and the like in the traditional method.
The aim of the invention is realized by the following technical scheme:
a repairing method for the impact damage defect of a composite honeycomb sandwich panel specifically comprises the following steps:
1) Excision injury: and cleaning the damaged area, and cutting to remove the damaged skin and the honeycomb core.
2) Polishing a skin: polishing the peripheral ring skin of the notch, and polishing the skin around the notch in a multi-ring step-shaped bevel angle manner, wherein the distance between the outer ring skin and the adjacent inner ring skin is 10-15 mm.
3) Manufacturing a honeycomb core repairing block: the repair block is 2-5 mm higher than the original honeycomb core, the other dimensions are the same as those of the original damage removal honeycomb core area, and the direction of the repair block core strip is the same as that of the original honeycomb core strip.
4) Installing a honeycomb core repair block: and paving a layer of adhesive film on the surface layer with the undamaged notch cavity, mounting the honeycomb core repairing block at the notch cavity position, wherein the direction of the core strip is the same as that of the original honeycomb core strip, and filling foam adhesive at the butt joint position of the honeycomb core repairing block and the original honeycomb core.
5) And (3) bag making: and (3) manufacturing vacuum bags on the upper surface and the lower surface of the repairing area, repairing by adopting a repairing instrument, paving a layer of nonporous isolating film on the repairing block of the honeycomb core during bag manufacturing, placing a heating blanket and a breathable fabric on the nonporous surface of the repairing area, placing a uniform pressing plate and the breathable fabric on the unbroken surface of the repairing area, connecting a thermocouple and a vacuum nozzle in the repairing diagonal margin area, and communicating the upper vacuum bag with the lower vacuum bag.
6) And (3) molding and curing the honeycomb core: and vacuumizing the whole process during curing, wherein the vacuum pressure is not lower than 0.08MPa, the heating rate is not higher than 2 ℃/min, preserving heat after the temperature is raised to the required curing temperature of the foam adhesive, cooling after the heat preservation is finished, and closing the repairing instrument when the cooling rate is not higher than 3 ℃/min and the temperature is lowered to below 60 ℃.
7) Trimming the honeycomb core: and removing the vacuum bag, polishing and trimming the honeycomb core repairing block, and polishing to the same height as the honeycomb core around the notch.
8) Repairing the skin: spreading a layer of adhesive film on the whole upper surface of the polished honeycomb core and the polished skin around the honeycomb core, spreading prepreg patches according to the number of layers, the size and the appearance of the polished skin around the cut, wherein each layer of prepreg patches is sequentially and circularly spread at 0 degrees, +45 degrees, -45 degrees and 90 degrees, and after all prepreg patches are spread, spreading an additional layer of glass cloth on the outermost layer.
9) And (5) secondary bag making: and (3) manufacturing vacuum bags on the upper surface and the lower surface of the repairing area, repairing by adopting a repairing instrument, paving a layer of strippable protective layer on a prepreg patch during bag manufacturing, sequentially placing a hole isolating film, a glue sucking layer, a non-hole isolating film, a uniform pressing plate, a heating blanket and a breathable fabric, placing the uniform pressing plate and the breathable fabric on the unbroken surface of the repairing area, connecting a thermocouple and a vacuum nozzle in the repairing diagonal margin area, and communicating the upper vacuum bag and the lower vacuum bag.
10 Skin curing: and vacuumizing the whole curing process, wherein the vacuum pressure is not lower than 0.08MPa, the heating rate is not higher than 2 ℃/min, the temperature is kept after the temperature is raised to the curing temperature required by the prepreg, the temperature is reduced after the temperature is kept, the cooling rate is not higher than 3 ℃/min, and the repairing instrument is closed when the temperature is reduced to below 60 ℃.
11 Trimming: and removing the vacuum bag, polishing and trimming the repaired area, and removing burrs and redundant rubber stems.
12 Non-destructive testing): nondestructive testing is carried out on the repair area to check whether the problems of layering, debonding, honeycomb core tearing and the like exist.
13 Repairing and delivering qualified products.
The invention has the beneficial effects that:
(1) The original damaged honeycomb core is replaced by adopting the repair method, so that the problems of large glue injection amount and unbalanced counterweight in the traditional glue injection repair method are solved.
(2) The repairing adopts a secondary curing method, firstly, the honeycomb core repairing block is cured and molded, then the repairing block is polished and repaired, and then the skin prepreg patch is paved and pasted, so that the repairing skin is cured, and the part repairing precision is improved.
(3) The glass cloth is paved on the outermost layer of the repairing skin, has the advantages of corrosion resistance, high temperature resistance, high strength and the like, and prolongs the service life of the repairing area.
(4) The repair area surface layer skin is polished in a multi-layer stepped oblique angle polishing mode, and the size from the innermost layer skin to the outermost layer skin is gradually increased when the repair area surface layer skin is paved and pasted, so that the bonding strength of the prepreg patch and the original skin is improved.
(5) And vacuum bags are arranged on the upper surface and the lower surface of the repairing area, the vacuum bags are communicated, the upper surface and the lower surface are pressurized simultaneously when vacuumizing, the vacuum pressure is the same, and the problem of part deformation caused by single-side pressurization and unbalanced pressure is avoided.
Drawings
FIG. 1 is a flow chart for repairing honeycomb sandwich panel impact damage defects
FIG. 2 is a schematic illustration of a multi-turn stepped bevel sanding repair for a honeycomb sandwich panel
FIG. 3 is a schematic illustration of a honeycomb sandwich panel repair lay-up
FIG. 4 is a schematic illustration of a honeycomb core repair block bag making
FIG. 5 is a schematic illustration of a skin prepreg patch bagging
The numbering in the figures illustrates: 1-face layer, 2-honeycomb core, 3-honeycomb core repair block, 4-adhesive film, 5-foam, 6-prepreg patch, 7-additional layer, 8-repair zone, 9-thermocouple, 10-strippable protective layer, 11-porous barrier film, 12-suction layer, 13-non-porous barrier film, 14-leveling plate, 15-heating blanket, 16-ventilation fabric, 17-vacuum bag, 18-vacuum nozzle, 19-sealing tape
Detailed Description
The invention is further described below with reference to examples of embodiments and the accompanying drawings.
Implementation example 1: repair of impact damage to certain type of support rib plate
Injury condition: the support rib plate of a certain model is of a carbon fiber honeycomb sandwich structure, the upper surface layer and the lower surface layer are formed by solidifying 4 layers of M40J carbon fiber unidirectional tapes, REDUX 312UL is adopted for bonding the surface layer and a honeycomb core, the brand number of the honeycomb core is BC1.8-3/8P, and the thickness of the honeycomb core is 15mm. The damage area of the support rib plate is a circular pit with the diameter phi of 170mm, the damage is caused by improper handling, the upper skin is damaged due to impact, and the honeycomb core is torn.
And (3) repairing measures:
(1) The part to be repaired is wiped by clean rag dipped with acetone, and the damaged area of the surface layer 1 and the honeycomb core 2 is cut off, wherein the diameter phi of the damaged area is 170mm. And cleaning the cavity area formed after the cutting, and removing residual glue stems, scraps and the like.
(2) Polishing the peripheral ring skin of the notch, polishing the skin around the notch in a multi-layer step-shaped bevel angle, wherein the distance between the outer ring skin and the adjacent inner ring skin is 13mm, the polishing size phi 170mm of the innermost layer, and the polishing sizes of the rest 3 layers are 196mm, 222mm and 248mm in sequence.
(3) The honeycomb core repairing block 3 is manufactured, the diameter phi of the repairing block 3 is 170mm, and the height of the repairing block is 3mm higher than that of the original honeycomb core and is 18mm.
(4) And paving a REDUX 312UL adhesive film 4 on a surface layer with an undamaged notch cavity, mounting the honeycomb core repair block 3 at the position of the notch cavity, wherein the direction of a core strip is the same as that of an original honeycomb core strip, and filling foam rubber 5 at the joint of the honeycomb core repair block 3 and the original honeycomb core, wherein the brand of the foam rubber 5 is FM490.
(5) A vacuum bag 17 is manufactured in the installation area of the honeycomb core repairing block 3, a layer of non-porous isolating film 13 is paved on the honeycomb core, a heating blanket 15 and a breathable fabric 16 are placed on the non-porous isolating film, a uniform pressing plate 14 and the breathable fabric 16 are placed on the lower skin, a thermocouple 9 and a vacuum nozzle 18 are connected in the diagonal margin area of the repairing area, the vacuum bag 17 is sealed by adopting sealant 19, and the upper surface and the lower surface of the vacuum bag 17 are communicated.
(6) And vacuumizing the whole curing process, wherein the vacuum pressure is 0.085MPa plus or minus 0.02MPa, the heating rate is 2 ℃/min, the temperature is raised to the curing temperature required by the FM490 foam adhesive 5, then the temperature is preserved according to the required curing time, the temperature is reduced after the heat preservation is finished, the cooling rate is 3 ℃/min, and the repairing instrument is closed when the temperature is reduced to below 60 ℃.
(7) And removing the vacuum bag 17, polishing and trimming the honeycomb core repairing block 3 to the same height as surrounding cores, cleaning redundant substances such as scraps generated after polishing by using equipment such as a dust collector, cleaning a polished area by using acetone, and ensuring that the area to be repaired is clean and pollution-free.
(8) Cutting four layers of prepreg patches 6, wherein the material is a carbon fiber unidirectional tape M40J, and the cutting sizes of all layers are respectively phi 170mm, phi 196mm, phi 222mm and phi 248mm. Finally, an additional layer 7 is cut, the material is EW100 glass cloth, the diameter phi 274 of the material sheet is 45 degrees.
(9) And paving a REDUX 312UL adhesive film 4 on the whole upper surface of the polished honeycomb core and the polished skin around the honeycomb core, and then paving a prepreg patch 6. The sizes and angles of the prepreg patches 6 paved on each layer are respectively as follows: the first layer phi is 170mm, and the layering angle is 0 degree; the second layer phi 196mm, the angle of lay is 45 degrees; a third layer phi 222mm, wherein the layering angle is-45 degrees; the fourth layer phi 248mm, the lay-up angle 90 deg.. After the prepreg patch 6 is paved, an EW100 glass cloth additional layer 7 is paved on the outermost layer, and the paving angle is 45 degrees.
(10) The upper and lower layers of the repairing area are provided with vacuum bags 17, a layer of strippable protective layer 10 is paved on the prepreg patch, then a hole isolating film 11, a glue sucking layer 12, a non-hole isolating film 13, a uniform pressing plate 14, a heating blanket 15 and a breathable fabric 16 are sequentially arranged, the lower layer is provided with the uniform pressing plate 14 and the breathable fabric 16, the diagonal margin area of the repairing area is connected with a thermocouple 9 and a vacuum nozzle 18, the vacuum bags 17 are sealed by adopting sealant 19, and the upper and lower vacuum bags 17 are communicated.
(11) And vacuumizing the whole process during curing, wherein the vacuum pressure is 0.085 MPa+/-0.02 MPa, the heating rate is 2 ℃/min, the temperature is kept after the temperature is raised to the curing temperature required by the carbon fiber unidirectional tape M40J, the temperature is reduced after the heat preservation is finished, the cooling rate is 2 ℃/min, and the repairing instrument is closed when the temperature is reduced to below 60 ℃.
(12) And removing the vacuum bag 17, polishing and trimming the repair area 8, and removing burrs and redundant rubber stems.
(13) And carrying out ultrasonic detection and X-ray detection on the repairing area, wherein the repairing area has no layering and debonding problems, the honeycomb core is intact, and the nondestructive detection is qualified.
(14) And (5) delivering.
It should be noted that the above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, but any modifications, equivalents, improvements, etc. within the principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. The repairing method of the composite honeycomb sandwich panel impact damage defect is characterized by comprising the following steps of: 1) Cutting to remove damaged skin and honeycomb core; 2) Polishing the incision circumference skin; 3) Manufacturing a honeycomb core repair block; 4) Installing a honeycomb core repair block; 5) Making bags; 6) Shaping and solidifying the honeycomb core; 7) Trimming the honeycomb core; 8) Repairing the skin; 9) Secondary bag making; 10 Curing the skin; 11 Finishing the skin; 12 Non-destructive testing; 13 Repairing and delivering qualified products.
2. The method for repairing composite honeycomb sandwich panel impact damage defects according to claim 1, wherein the skin polishing process in step 2) is as follows: and after removing the damaged skin and the honeycomb core, polishing the formed incision peripheral ring skin, polishing the skin around the incision by multi-ring-layer step-shaped bevel angles, wherein the distance between the outer ring of skin and the adjacent inner ring of skin is 10-15 mm.
3. The method for repairing the impact damage defect of the composite honeycomb sandwich panel according to claim 1, wherein in the step 3), the height of the honeycomb core repairing block is 2-5 mm higher than that of an original honeycomb core, the rest dimension is the same as that of an original damage removing honeycomb core region, and the direction of a repairing block core strip is the same as that of the original honeycomb core strip.
4. The method for repairing an impact damage defect of a composite honeycomb sandwich panel according to claim 1, wherein the honeycomb core installation method in the step 4) is as follows: and (3) mounting the honeycomb core repairing block at the position of the notch cavity, wherein the direction of the core strip is the same as that of the original honeycomb core strip, and filling foam rubber at the butt joint position of the honeycomb core repairing block and the original honeycomb core.
5. The method for repairing an impact damage defect of a composite honeycomb sandwich panel according to claim 1, wherein the honeycomb core repairing method in the step 7) is as follows: and (5) polishing and trimming the honeycomb core repairing block until the honeycomb core repairing block is polished to be the same as the honeycomb core around the notch.
6. The method for repairing composite honeycomb sandwich panel impact damage defects according to claim 1, wherein the paving mode in the step 8) is as follows: spreading a layer of adhesive film on the whole upper surface of the polished honeycomb core and the polished skin around the honeycomb core, spreading prepreg patches according to the number of layers, the size and the appearance of the polished skin around the cut, wherein each layer of prepreg patches is sequentially and circularly spread at 0 degrees, +45 degrees, -45 degrees and 90 degrees, and after all prepreg patches are spread, spreading an additional layer of glass cloth on the outermost layer.
7. The method for repairing composite honeycomb sandwich panel impact damage defects according to claim 1, wherein the secondary bagging mode in the step 9) is as follows: and (3) vacuum bags are manufactured on the upper surface and the lower surface of the repairing area, a layer of strippable protective layer is paved on the prepreg patch during bag manufacturing, and then a porous isolating film, a glue absorbing layer, a non-porous isolating film, a uniform pressing plate, a heating blanket and a breathable fabric are sequentially arranged, so that the upper surface and the lower surface of the repairing area are communicated with each other.
8. The method for repairing composite honeycomb sandwich panel impact damage defects according to claim 1, wherein the curing modes in the step 6) and the step 10) are as follows: and vacuumizing the whole process during curing, wherein the vacuum pressure is not lower than 0.08MPa, the heating rate is not higher than 2 ℃/min, cooling after the heat preservation stage is finished, the cooling rate is not higher than 3 ℃/min, and closing the repairing instrument when the temperature is reduced to below 60 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310685939.5A CN116749560A (en) | 2023-06-09 | 2023-06-09 | Repairing method for impact damage defect of composite honeycomb sandwich panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310685939.5A CN116749560A (en) | 2023-06-09 | 2023-06-09 | Repairing method for impact damage defect of composite honeycomb sandwich panel |
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| Publication Number | Publication Date |
|---|---|
| CN116749560A true CN116749560A (en) | 2023-09-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310685939.5A Pending CN116749560A (en) | 2023-06-09 | 2023-06-09 | Repairing method for impact damage defect of composite honeycomb sandwich panel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116749560A (en) |
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2023
- 2023-06-09 CN CN202310685939.5A patent/CN116749560A/en active Pending
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