CN112743880B - Repairing method for large-area damage of honeycomb sandwich structural member - Google Patents
Repairing method for large-area damage of honeycomb sandwich structural member Download PDFInfo
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- CN112743880B CN112743880B CN202011452975.XA CN202011452975A CN112743880B CN 112743880 B CN112743880 B CN 112743880B CN 202011452975 A CN202011452975 A CN 202011452975A CN 112743880 B CN112743880 B CN 112743880B
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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
- B29C73/04—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
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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
- B29C73/04—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
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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
- B29C73/245—Apparatus or accessories not otherwise provided for for removing the element having caused the damage
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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
- 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
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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
- 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
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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The application provides a repairing method for a large-area damage of a honeycomb sandwich structure, which comprises the following steps: dividing the damage region (9) into N parts according to the area of the damage region (9); placing corresponding honeycombs on the N parts of the damaged area (9) in sequence, and curing the honeycombs according to preset curing conditions to form spliced honeycombs; and sequentially placing a structural adhesive film (7) and a patch (8) on the upper surface of the spliced honeycomb from bottom to top, and curing the patch (8) according to a preset curing condition.
Description
Technical Field
The invention relates to the field of aviation composite material hot repair instruments and vacuum pumps, in particular to a repairing method for large-area damage of a honeycomb sandwich structural member.
Background
The honeycomb sandwich structure for aviation is an integral structure which is formed by that an original structure honeycomb (3) with large thickness and small density is clamped between an upper panel (1) and a lower panel (2) with high strength and high modulus, and a structural adhesive film (7) is cured and bonded in a certain temperature and pressure environment. The panel material comprises an aluminum alloy plate or a composite material plate of carbon fiber, glass fiber and aramid fiber, and the honeycomb is an aluminum alloy honeycomb or an aramid paper honeycomb. In the production, use and maintenance processes of the honeycomb sandwich structural member, damage of one or more combinations of scratching and sinking of a panel, collapse and slippage of the honeycomb and the like easily occurs, and damage areas (9) are different and irregular in size.
The repair of defects or damages of the honeycomb sandwich structure is classified into two major categories, cold repair and hot repair, according to the curing temperature of the repair material. The cold repair is a repair method of curing at room temperature after damage is removed, and in order to accelerate curing, reduce curing time and obtain high-quality repair, the curing can be carried out at the temperature of 60-80 ℃ by using heating equipment; hot repairs are typically used in specific areas of a part and can be divided into 120 ℃ cure repairs and 180 ℃ cure repairs. The repair method is classified into a surface scraping method, an external lapping patch gluing method, a honeycomb splicing method, a filler injection method, and the like. The repair methods described above generally allow for repair of smaller area (typically no more than 400mm in diameter) lesions.
Disclosure of Invention
The invention provides a repairing method for a large-area damage of a honeycomb sandwich structure, which can repair the large-area damage of the honeycomb sandwich structure.
The application provides a repairing method for a large-area damage of a honeycomb sandwich structure, which comprises the following steps:
dividing the damage region (9) into N parts according to the area of the damage region (9);
placing corresponding honeycombs on the N parts of the damaged area (9) in sequence, and curing the honeycombs according to preset curing conditions to form spliced honeycombs;
and sequentially placing a structural adhesive film (7) and a patch (8) on the upper surface of the spliced honeycomb from bottom to top, and curing the patch (8) according to a preset curing condition.
Specifically, placing a corresponding honeycomb on a first part of the damaged area (9) specifically includes:
removing the upper panel and the honeycombs of the first part of the damaged area (9), wherein the removed damaged honeycombs are full-height;
a structural adhesive film (7) is placed on the contact surface of the first honeycomb (4) and the lower panel (2), an expansion adhesive film (6) is placed on the butt joint surface of the first honeycomb (4) and the original structural honeycomb (3), and the free end of the first honeycomb (4) is fixed with the honeycomb edge by adopting a putty strip (14);
a thermocouple (10), a ventilated felt (11), a hot-pressing blanket (12), the ventilated felt (11), a putty strip (14) and a vacuum bag (13) are sequentially placed on the outer side of the lower panel (2), and the other end of the thermocouple (10) is connected with a hot patching instrument;
the outer side of the upper panel (1) is sequentially provided with a pressure equalizing plate (15), an air-permeable felt (11), a putty strip (14) and a vacuum bag (13).
Specifically, placing a corresponding honeycomb on the second part of the damaged area (9) specifically includes:
removing the upper panel and the honeycombs of the second part of the damaged area (9), wherein the removed damaged honeycombs are full-height;
a layer of structural adhesive film (7) is placed on the contact surface of the second honeycomb (5) and the lower panel (2), and an expansion adhesive film (6) is respectively placed on the butt joint surface of the second honeycomb (5) and the original structural honeycomb (3) and the butt joint surface of the second honeycomb (5) and the first honeycomb (4).
A thermocouple (10), an air permeable felt (11), a hot-pressing blanket (12), the air permeable felt (11), a putty strip (14) and a vacuum bag (13) are sequentially placed on the outer side of the lower panel (2);
a pressure equalizing plate (15) is arranged on the outer side of the upper panel (1), and then the ventilated felt (11), the putty strips (14) and the vacuum bag (13) are sequentially arranged.
Specifically, the method further comprises:
a thermocouple (10), an air-permeable felt (11), a hot-pressing blanket (12), the air-permeable felt (11), a putty strip (14) and a vacuum bag (13) are sequentially arranged on the outer side of the patch (8).
Specifically, the preset curing condition is that the vacuum pressure is 0.07 +/-0.01 MPa; the heating temperature is 165 +/-5 ℃, or the heating temperature is 110 +/-5 ℃; the heating rate is 2 ℃; the cooling rate is 3 ℃; the constant temperature period was 3 hours.
Specifically, the pressure equalizing plate (15) is an aluminum alloy pressure equalizing plate with the thickness of 0.4 mm.
Specifically, the hot-pressing blanket (12) arranged on the outer side of the patch (8) comprises two parts, each part of the hot-pressing blanket is respectively arranged above the second honeycomb (5) and the first honeycomb (4), and the air-permeable felt (11) is arranged between the two parts of the hot-pressing blankets.
Specifically, an airfelt (11) placed outside the patch (8) covers the entire damaged area (9).
In summary, the invention provides a repairing method for repairing large-area damage of a honeycomb sandwich structure, which adopts a hot-repair instrument (hot-press blanket) for heating, vacuumizing (vacuum pump) for pressurizing, sectionally splicing honeycombs, and curing and molding for multiple times to repair large-area damage of the honeycomb sandwich structure. The invention can solve the problem that the existing repairing method can not repair the panel of the honeycomb sandwich structural member and the honeycomb when the panel and the honeycomb are damaged in large area (950 multiplied by 350 mm); the risk that the honeycomb sandwich structural member must be scrapped due to overlarge damage area is greatly reduced, and secondary damage to an aircraft platform due to replacement of structural large parts can be avoided.
Drawings
FIG. 1 is a schematic view of a honeycomb sandwich structure;
FIG. 2 is a schematic diagram of a first honeycomb splice provided herein;
FIG. 3 is a schematic diagram of a second honeycomb splice provided herein;
FIG. 4 is a schematic illustration of the bonding of a patch provided herein;
FIG. 5 is a schematic illustration of repair of large area ablation damage provided herein;
wherein: 1-upper panel, 2-lower panel, 3-original structure honeycomb, 4-first honeycomb, 5-second honeycomb, 6-expansion glue film, 7-structure glue film, 8-patch, 9-damaged area, 10-thermocouple, 11-air felt, 12-hot press blanket, 13-vacuum bag, 14-putty strip and 15-pressure equalizing plate.
Detailed Description
A repairing method for large-area damage of honeycomb sandwich structure member comprises heating with hot-pressing blanket (hot-patch instrument fitting), wherein the heating temperature is determined according to the forming temperature of original honeycomb sandwich structure member, and the heating temperature is generally 10 deg.C lower than the forming temperature; vacuumizing (pressurizing by a vacuum pump), wherein the vacuum pressure is not lower than 0.06Mpa, and the number of the vacuum pumps is adjusted according to the size of the damaged area so as to ensure that the vacuum pressure meets the requirement; the honeycomb is spliced in sections, and the honeycomb is spliced twice, so that the phenomenon that the adhesive film at the spliced part is not uniformly heated and can not be completely cured due to too large splicing area is avoided; and curing and repairing for many times, curing the spliced honeycomb twice, curing the patch once, curing for three times in total, heating the outer side of the panel bonded with the honeycomb by using an upper vacuum bag and a lower vacuum bag which are arranged on two sides when the spliced honeycomb is cured, avoiding the deformation of the panel, manufacturing the vacuum bag on the outer side of the patch when the patch is cured, and butting and heating by using two hot pressing blankets to ensure that the patch can be cured and molded once.
The repairing method for the large-area damage of the honeycomb sandwich structure comprises the following steps:
the method comprises the following steps: the first honeycomb was cured, as shown in detail in figure 2.
1) And removing the upper panel and the honeycomb of the first part of the damaged area (9), wherein the removed damaged honeycomb is full-height, and the lower panel is not allowed to be damaged in the removing process.
It should be noted that the damaged area (9) is divided into N parts as required, and each part can fill one honeycomb.
2) A layer of structural adhesive film (7) is placed on the contact surface of a first honeycomb (4) and a lower panel (2), a layer of expansion adhesive film (6) is placed on the butt joint surface of the first honeycomb (4) and an original structural honeycomb (3), and a putty strip (14) is adopted at the free end of the first honeycomb (4) to fix a honeycomb edge to prevent honeycomb sliding.
3) A thermocouple (10), an air permeable felt (11), a hot-pressing blanket (12), the air permeable felt (11), a putty strip (14) and a vacuum bag (13) are respectively arranged on the outer side of the lower panel in sequence.
The other end of the thermocouple (10) is connected with a hot patching instrument for heating and vacuumizing.
It should be noted that when the vacuum bag is manufactured, the putty strips are used for sealing all leakage points, the boundary of the vacuum bag is determined according to the size and the placement position of the first honeycomb, and the position of the vacuum nozzle is reasonably arranged, if the area of the first honeycomb is larger, the number of the vacuum pumps and the number of the vacuum nozzles are additionally increased to ensure that the vacuum pressure meets the requirement.
4) A uniform pressure plate (15) made of aluminum alloy with the thickness of 0.4mm is arranged on the outer side of the upper panel (1), and the air-permeable felt (11), the putty strip (14) and the vacuum bag (13) are arranged.
It should be noted that when the vacuum bag is manufactured, the putty strips are used for sealing all leakage points, the boundary of the vacuum bag is determined according to the whole damaged area, the positions of the vacuum nozzles are reasonably arranged, and if the damaged area is large, the number of the vacuum pumps and the number of the vacuum nozzles are additionally increased to ensure that the vacuum pressure meets the requirement.
5) The curing of the first honeycomb is completed according to the vacuum pressure of 0.07 +/-0.01 MPa, the heating temperature of 165 +/-5 ℃ (or 110 +/-5 ℃), the heating rate of 2 ℃, the cooling rate of 3 ℃ and the constant temperature duration of 3 hours.
Step two: the second honeycomb was cured, as shown in detail in figure 3.
1) And removing the residual upper panel and the honeycomb in the damaged area (9), wherein the removed damaged honeycomb is full-height, and the lower panel is not allowed to be damaged in the removing process.
2) A layer of structural adhesive film (7) is placed on the contact surface of the second honeycomb (5) and the lower panel (2), and a layer of expansion adhesive film (6) is placed on the butt joint surface of the second honeycomb (5), the original structural honeycomb (3) and the first honeycomb (4).
3) A thermocouple (10), an air permeable felt (11), a hot-pressing blanket (12), the air permeable felt (11), a putty strip (14) and a vacuum bag are respectively arranged on the outer side of the lower panel in sequence.
It should be noted that when the vacuum bag is manufactured, the putty strips are used for sealing all leakage points, the boundary of the vacuum bag is determined according to the size and the placement position of the first honeycomb, and the position of the vacuum nozzle is reasonably arranged.
4) A uniform pressure plate (15) made of aluminum alloy with the thickness of 0.4mm is arranged on the outer side of the upper panel (1), and the air-permeable felt (11), the putty strip (14) and the vacuum bag are arranged.
It should be noted that when the vacuum bag is manufactured, the putty strips are used for sealing all leakage points, the boundary of the vacuum bag is determined according to the whole damaged area, the positions of the vacuum nozzles are reasonably arranged, and if the damaged area is large, the number of the vacuum pumps and the number of the vacuum nozzles are additionally increased to ensure that the vacuum pressure meets the requirement.
5) And the second honeycomb is cured under the vacuum pressure of 0.07 +/-0.01 MPa, the heating temperature of 165 +/-5 ℃ (or 110 +/-5 ℃), the heating rate of 2 ℃, the cooling rate of 3 ℃ and the constant temperature duration of 3 hours.
Step three: the patch is cured, see figure 4 for details.
1) Placing a structural adhesive film (7) on the upper surface of the spliced honeycomb, and then placing a patch (8);
2) a thermocouple (10), an air-permeable felt (11), a hot-pressing blanket (12), an air-permeable felt (11), a putty strip and a vacuum bag are respectively arranged on the outer side of the patch in sequence.
It should be noted that when the vacuum bag is manufactured, the putty strips are used for sealing all leakage points, the boundary of the vacuum bag is determined according to the size and the placement position of the patch, and the position of the vacuum nozzle is reasonably arranged, if the patch area is larger, the number of the vacuum pumps and the number of the vacuum nozzles are additionally increased to ensure that the vacuum pressure meets the requirement. The butt joint of the two hot-pressing blankets needs to be well coated by a breathable felt and is tightly bound by a high-temperature pressure-sensitive adhesive tape for heat preservation. Test data shows that the temperature of the butt joint of the two hot-pressing blankets is generally lower by about 5 ℃, and the requirement of the curing temperature of the structural adhesive can be met.
3) The curing of the patch is completed according to the vacuum pressure of 0.07 +/-0.01 MPa, the heating temperature of 165 +/-5 ℃ (or 110 +/-5 ℃), the heating rate of 2 ℃, the cooling rate of 3 ℃ and the constant temperature duration of 3 hours.
The first embodiment is as follows:
a certain helicopter tail beam is of a honeycomb sandwich structure, an outer panel is made of aluminum alloy 2024T3 and is 0.4mm thick, an inner panel is made of aluminum alloy 5052H19 and is 0.1mm thick, and a sandwich is made of aramid paper honeycomb DHS251-142 and is 12mm thick. The plastic conduit inside the tail beam is on fire due to power failure, the tail beam is ablated and damaged in a large area, and the damaged area is about 950 mm multiplied by 300 mm. Heating to 165 ℃ by using a hot-pressing instrument (hot-pressing blanket), vacuumizing (vacuum pump) and pressurizing to 0.07Mpa, sequentially curing and splicing two aramid paper honeycombs DHS251-142-12 with the areas of 450 multiplied by 300mm and 500 multiplied by 300mm twice, and finally curing an aluminum alloy patch 5052H19 with the area of 1050 multiplied by 400mm and the thickness of 0.4mm, as shown in figure 5.
As can be seen, the present application:
1) the size limitation of repairing the damage by adopting a conventional honeycomb splicing method is broken through, and the damage with the damage length of up to 1.5m can be repaired by the segmented and fractional curing method;
2) the curing requirement of the adhesive film can be met by adopting a temperature control measure of heating the inside and the outside simultaneously (the honeycomb height is 12mm, if one side is heated by 180 ℃, the temperature of the other side can only reach 120 ℃);
3) the heat preservation measure adopted at the butt joint of the hot-pressing blanket can control the curing temperature error within a theoretical error range, and meet the curing requirement of the adhesive film (if the heat preservation measure is not adopted at the butt joint of the heating blanket, the temperature is about 10 ℃ lower than the normal temperature, and exceeds the theoretical error range; if heat preservation measures are taken, the temperature is only about 5 ℃ lower than the normal temperature, and is within the theoretical error range);
4) the sealing and fixing measures adopted at the free end can meet the vacuum degree requirement of the first honeycomb curing process and avoid honeycomb slippage.
Example two:
a certain type unmanned aerial vehicle oil tank floor is of a honeycomb sandwich structure, an upper panel is made of an aluminum alloy LY12 CZ, the thickness of the upper panel is 0.4mm, a lower panel is made of a LY12 CZ, the thickness of the lower panel is 0.6mm, and a sandwich is made of aramid paper honeycomb NH-1-1.83 and 12 mm. The large-area collapse of the upper panel and the honeycomb and the damage area of 750 multiplied by 350mm are caused by overlarge bolt tightening torque during equipment installation, a hot-repair instrument (hot-press blanket) is adopted to heat to 110 ℃, vacuum pumping (vacuum pump) is adopted to pressurize to 0.07Mpa, two aramid paper honeycombs NH-1-1.83-12 with the areas of 350 multiplied by 350mm and 400 multiplied by 350mm are successively cured and spliced twice, and finally an aluminum alloy patch LY12 CZ with the area of 850 multiplied by 450mm is cured and spliced, wherein the thickness is 0.4 mm.
In conclusion, the invention provides a method for repairing large-area damage of a honeycomb sandwich structural member by heating with a hot-repair instrument (hot-press blanket), vacuumizing (vacuum pump) for pressurizing, splicing honeycombs in sections and curing and molding for multiple times. One purpose is to solve the problem that the damage area of the honeycomb sandwich structure piece exceeds the conventional repair range, and the repair can not be implemented by an external factory; and the second is to reduce the scrapping risk of the honeycomb sandwich structural member due to large damage area, greatly reduce the cost of the aircraft in the whole life cycle, and simultaneously avoid secondary damage to the aircraft platform due to the replacement of structural large parts.
Claims (6)
1. A method for repairing a large area damage to a honeycomb sandwich structure, the method comprising:
dividing the damage region (9) into N parts according to the area of the damage region (9);
placing corresponding honeycombs on the N parts of the damaged area (9) in sequence, and curing the honeycombs according to preset curing conditions to form spliced honeycombs;
sequentially placing a structural adhesive film (7) and a patch (8) on the upper surface of the spliced honeycomb from bottom to top, and curing the patch (8) according to a preset curing condition;
placing a corresponding honeycomb on a first part of the damaged area (9), specifically comprising:
removing the upper panel and the honeycombs of the first part of the damaged area (9), wherein the removed damaged honeycombs are full height;
a structural adhesive film (7) is placed on the contact surface of the first honeycomb (4) and the lower panel (2), an expansion adhesive film (6) is placed on the butt joint surface of the first honeycomb (4) and the original structural honeycomb (3), and the free end of the first honeycomb (4) is fixed with the honeycomb edge by adopting a putty strip (14);
a thermocouple (10), an air permeable felt (11), a hot-pressing blanket (12), the air permeable felt (11), a putty strip (14) and a vacuum bag (13) are sequentially placed on the outer side of the lower panel (2), and the other end of the thermocouple (10) is connected with a hot patching instrument;
a pressure equalizing plate (15), an air permeable felt (11), a putty strip (14) and a vacuum bag (13) are sequentially arranged on the outer side of the upper panel (1);
placing a corresponding honeycomb on a second part of the damaged area (9), specifically comprising:
removing the upper panel and the honeycombs of the second part of the damaged area (9), wherein the removed damaged honeycombs are full-height;
a layer of structural adhesive film (7) is placed on the contact surface of the second honeycomb (5) and the lower panel (2), and an expansion adhesive film (6) is respectively placed on the butt joint surface of the second honeycomb (5) and the original structural honeycomb (3) and the butt joint surface of the second honeycomb (5) and the first honeycomb (4);
a thermocouple (10), an air permeable felt (11), a hot-pressing blanket (12), the air permeable felt (11), a putty strip (14) and a vacuum bag (13) are sequentially placed on the outer side of the lower panel (2);
a pressure equalizing plate (15) is arranged on the outer side of the upper panel (1), and then the air-permeable felt (11), the putty strips (14) and the vacuum bag (13) are sequentially arranged.
2. The repair method of claim 1, further comprising:
a thermocouple (10), an air-permeable felt (11), a hot-pressing blanket (12), the air-permeable felt (11), a putty strip (14) and a vacuum bag (13) are sequentially arranged on the outer side of the patch (8).
3. The repair method of claim 1, wherein the preset curing conditions are a vacuum pressure of 0.07 ± 0.01 MPa; the heating temperature is 165 +/-5 ℃, or the heating temperature is 110 +/-5 ℃; the heating rate is 2 ℃; the cooling rate is 3 ℃; the constant temperature period was 3 hours.
4. Repair method according to claim 1, characterized in that the pressure equalizer plate (15) is a 0.4mm thick aluminum alloy pressure equalizer plate.
5. Repair method according to claim 2, characterized in that the thermo-compression blanket (12) placed outside the patch (8) comprises two parts, each corresponding to the second honeycomb (5) and the first honeycomb (4), between which the airfelt (11) is placed.
6. Repair method according to claim 2, characterized in that the airfelt (11) placed outside the patch (8) covers the whole of the damaged area (9).
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| CN113415005B (en) * | 2021-06-29 | 2023-02-03 | 中国人民解放军61255部队 | Outfield repairing method for debonding and breaking of honeycomb in composite material |
| CN116330680B (en) * | 2023-05-19 | 2023-09-22 | 无锡透平叶片有限公司 | Bonding assembly method for hollow fan outlet guide vane |
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