CN109570902B - Bonding repair method for crack composite material of aluminum alloy main bearing part of airplane structure oil tank - Google Patents
Bonding repair method for crack composite material of aluminum alloy main bearing part of airplane structure oil tank Download PDFInfo
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- CN109570902B CN109570902B CN201811407831.5A CN201811407831A CN109570902B CN 109570902 B CN109570902 B CN 109570902B CN 201811407831 A CN201811407831 A CN 201811407831A CN 109570902 B CN109570902 B CN 109570902B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
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- B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
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Abstract
The invention relates to a method for repairing cracks of an aluminum alloy main bearing part of an airplane structure oil tank by gluing by using a composite material, which comprises the following steps: s1: dismantling the accessories on the gluing repair path, preliminarily cleaning the interior of the repair area by using acetone, and removing oil stains; s2: filling holes in the repair area with an adhesive tape for comprehensive protection; s3: checking and installing the pre-cured composite material patch to ensure that the shape is attached to the adhesive surface; s4: polishing the bonding repair area by using sand paper, and carefully cleaning the bonding area of the aluminum alloy and the composite material by using acetone; s5: heating and curing the bonding area by blowing hot air, and fixing and pressurizing the composite material by a magnetic pressurizing method; s6: and after the solidification is finished, cleaning the repair area, and coating HM109 sealant on the possible area of the structural adhesive and the fuel contact area for isolation and sealing. The invention has small structural weight increment; a new stress concentration source cannot be formed, so that secondary damage is avoided; the repair designability can be improved; short repairing time and low cost.
Description
Technical Field
The invention relates to the technical field of airplane repair, in particular to a glue joint repair method for a crack composite material of an aluminum alloy main bearing part of an airplane structure oil tank.
Background
The key bearing structural member of a certain airplane is made of 7B04 high-strength aluminum alloy, cracks of the bearing structural members of a plurality of airplanes are found after the airplane is in service for a period of time, and the key bearing structural member is used as a key bearing structural member for single force transmission of the airplane, mainly bears the supporting load of the main landing gear on the airplane and is used for installing and fixing the main landing gear. Due to maintenance costs, the structural member is not exchangeable, and cracks are scrapped without being repaired. At present, for repairing crack faults of an aluminum alloy structural part of an airplane, a metal reinforcing part mechanical connection method is generally adopted for repairing, but for the interior of an oil tank area with a narrow structural space, the metal reinforcing part mechanical connection method has the problems that the repair quality is difficult to guarantee, a structural part is easy to damage, stress concentration at the edge of a newly-manufactured hole is easy to occur, and the like, and cannot be implemented, and if the key structural part cannot be repaired and replaced, the service life of the whole airplane is shortened, and huge loss is caused.
Disclosure of Invention
In order to avoid and solve the technical problems, the invention provides a method for repairing cracks of an aluminum alloy main bearing part of an airplane structure oil tank by bonding composite materials.
The technical problem to be solved by the invention is realized by adopting the following technical scheme:
the method for repairing the crack composite material of the aluminum alloy main bearing part of the airplane structure oil tank by gluing comprises the following steps:
s1: dismantling the accessories on the gluing repair path, preliminarily cleaning the interior of the repair area by using acetone, and removing oil stains;
s2: filling holes in the repair area with an adhesive tape for comprehensive protection;
s3: checking and installing the pre-cured composite material patch to ensure that the shape is attached to the adhesive surface;
s4: polishing the bonding repair area by using sand paper, and carefully cleaning the bonding area of the aluminum alloy and the composite material by using acetone;
s5: heating and curing the bonding area by using temperature-controllable heating equipment through hot air blowing, and fixing and pressurizing the composite material by using a magnetic pressurizing method;
s6: and after the solidification is finished, cleaning the repair area, and coating HM109 sealant on the possible area of the structural adhesive and the fuel contact area for isolation and sealing.
Further, in S3, the composite patch is chamfered around the edges after the test is completed.
Further, in the step S5, the temperature rising and reducing rate is controlled to be 1.5-2 ℃/min, and after the temperature rises to 80 ℃, the temperature is kept for 3 hours.
The invention has the beneficial effects that: compared with the traditional metal reinforcing part mechanical connection repair, the invention has the following advantages: 1. the weight of the structure is small; 2. the patching glue joint does not need to open holes on the original structure, and a new stress concentration source cannot be formed, so that secondary damage is completely avoided; 3. the repair designability can be improved; 4. the method has the advantages of short repairing time and low cost, and can solve the problem that the mechanical connection repairing of the metal reinforcing part cannot be implemented due to small space.
Drawings
The invention is further illustrated with reference to the following figures and examples.
Fig. 1 is a front view of a main bearing member in the embodiment of the invention;
fig. 2 is a rear view of a main bearing member in an embodiment of the invention;
FIG. 3 is a schematic structural diagram of a test piece in effect verification according to an embodiment of the present invention;
FIG. 4 is a front view of a composite patch in an embodiment of the present invention;
FIG. 5 is a top view of a composite patch in an embodiment of the present invention.
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 5, the method for repairing the crack composite material of the aluminum alloy main bearing part of the airplane structure fuel tank by gluing comprises the following steps:
s1: dismantling the accessories on the gluing repair path, preliminarily cleaning the interior of the repair area by using acetone, and removing oil stains;
s2: filling holes in the repair area with an adhesive tape for comprehensive protection;
s3: checking and installing the pre-cured composite patch 1 to ensure that the shape is attached to the gluing surface, and chamfering the edges of the periphery of the composite patch 1 after checking and installing are finished;
s4: polishing the bonding repair area by using sand paper, and carefully cleaning the bonding area of the aluminum alloy and the composite material by using acetone;
s5: heating and curing the glued joint area by using temperature-controllable heating equipment through hot air blowing, and fixing and pressurizing the composite material by using a magnetic pressurizing method, wherein the magnetic pressurizing method comprises the steps of placing a magnet on one side of a repair area where a composite material patch 1 is placed, placing a steel plate on the other side of the repair area, compacting the composite material patch 1 through mutual attraction of the magnet and the steel plate, controlling the temperature rising and reducing rate to be 1.5-2 ℃/min, and preserving heat for 3 hours after the temperature rises to 80 ℃;
s6: and after the solidification is finished, cleaning the repair area, and coating HM109 sealant on the possible area of the structural adhesive and the fuel contact area for isolation and sealing.
The method for verifying the effect before repairing comprises the following steps: the test piece 3 was machined from the same 7B04 material as the aircraft structural component, and was notched on one side for crack 2 initiation. In order to verify the repairing effect, after the test piece 3 naturally forms the crack 2 on the test piece 3 in a loading mode of a testing machine, the cold composite material patch 1 is subjected to glue joint repairing, and static force comparison tests (shown in a table 1) and tensile fatigue comparison tests (shown in a table 2 and a table 3) after non-repairing and repairing are carried out. The tensile fatigue comparison test is carried out by combining oil immersion and high and low temperature environment tests, and the influence of the aviation kerosene on the structural adhesive and the influence of the structural adhesive on the aviation kerosene are further analyzed. The test results in the table show that: after the composite material is subjected to cementing repair, the static strength is 1.52 times that of the non-repaired composite material; the high-low temperature oil immersion basically has no influence on the fatigue life of the repair test piece 3, and the structural adhesive also has no influence on the aviation kerosene; after the composite bond repair, the fatigue life was 17 times that of the no-repair test piece 3 and the crack 2 propagation rate was 8% of that of the no-repair test piece 3 at a given load.
TABLE 1 static Strength test data
TABLE 2 fatigue Life of unrepairable test pieces
TABLE 3 fatigue life of composite repair test piece
In conclusion, the invention innovatively uses a composite material bonding repair technology for an aluminum alloy main bearing part in an oil tank, and epoxy structural adhesives are respectively used for bonding the pre-cured composite material patches 1 on two surfaces of the main bearing part to reinforce matrix cracks 2, reduce the stress level of the cracks 2 and prolong the service life of an airplane, and meanwhile, the composite material bonding repair method solves the problem of cracks 2 at the key part of the airplane, ensures the safety of the airplane and has high economic benefit.
The foregoing shows and describes the general principles, essential 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 (3)
1. The method for repairing the aluminum alloy main bearing part crack composite material of the airplane structure oil tank by gluing is characterized in that: the method comprises the following steps:
s1: dismantling the accessories on the gluing repair path, preliminarily cleaning the interior of the repair area by using acetone, and removing oil stains;
s2: filling holes in the repair area with an adhesive tape for comprehensive protection;
s3: checking and installing the pre-cured composite material patch to ensure that the shape is attached to the adhesive surface;
s4: polishing the bonding repair area by using sand paper, and carefully cleaning the bonding area of the aluminum alloy and the composite material by using acetone;
s5: heating and curing the bonding area by using temperature-controllable heating equipment through hot air blowing, and fixing and pressurizing the composite material by using a magnetic pressurizing method;
s6: after the solidification is finished, cleaning a repair area, and isolating and sealing the structural adhesive and the area possibly contacted with the fuel oil by coating HM109 sealant;
the magnetic force pressurizing method comprises the steps that a magnet is placed on one side, where a composite material patch is placed, of a repair area, a steel plate is placed on the other side of the repair area, and the composite material patch is tightly pressed through mutual attraction of the magnet and the steel plate; the effect verification is carried out before the cementing repair, and the effect verification method comprises the following steps: the test piece is processed by adopting a 7B04 material which is the same as the aircraft structural member, a groove is formed in one side of the test piece and used for generating cracks, after the test piece naturally forms the cracks on the test piece in a loading mode of a testing machine, bonding repair of the cold composite material patch is carried out, and a static test and a tensile fatigue test after repair are carried out.
2. The aircraft structure fuel tank aluminum alloy main bearing part crack composite material gluing repair method as claimed in claim 1, wherein: in the step S3, after the test is completed, the edges of the composite material patch are chamfered.
3. The aircraft structure fuel tank aluminum alloy main bearing part crack composite material gluing repair method as claimed in claim 1, wherein: and in the S5, the heating and cooling rates are controlled to be 1.5-2 ℃/min, and the temperature is kept for 3h after being heated to 80 ℃.
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| CN110552942A (en) * | 2019-07-26 | 2019-12-10 | 中国航空工业集团公司济南特种结构研究所 | Bonding and curing method for large-load static test radome tension and compression pads |
| CN110566554A (en) * | 2019-07-26 | 2019-12-13 | 中国航空工业集团公司济南特种结构研究所 | Large-curvature large-load radar cover tension and compression pad full-filling type bonding method |
| CN110480254B (en) * | 2019-08-03 | 2021-02-19 | 国营芜湖机械厂 | Method for repairing casting defects of aluminum-silicon alloy shell of aircraft fuel system |
| CN112014473B (en) * | 2020-07-27 | 2022-10-21 | 国营芜湖机械厂 | Wet-process glue-joint repairing method for solving cracks of complex metal profile structure of airplane |
| CN111958331B (en) * | 2020-08-06 | 2021-12-24 | 国营芜湖机械厂 | Method for repairing damage of large-size hole of complex metal structure |
| CN113146142A (en) * | 2021-04-14 | 2021-07-23 | 芜湖创联新材料科技有限公司 | Device and method for rapidly repairing cracks on hole edge of metal skin of airplane by using composite material |
| CN114749867A (en) * | 2022-05-04 | 2022-07-15 | 国营芜湖机械厂 | Repair method suitable for high-temperature titanium alloy structure cracks |
| CN114888521B (en) * | 2022-05-07 | 2023-05-05 | 国营芜湖机械厂 | Composite metal fatigue crack inhibition method |
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| US7858897B2 (en) * | 2006-10-27 | 2010-12-28 | United Technologies Corporation | Insert weld repair |
| CN102335804A (en) * | 2010-07-21 | 2012-02-01 | 贵州贵航无人机有限责任公司 | Method for repairing metal skin by using composite material |
| CN104741864B (en) * | 2013-12-31 | 2017-09-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of structural damage fast repairing method |
| CN107984868A (en) * | 2017-12-26 | 2018-05-04 | 珠海格力电器股份有限公司 | Pressure device and pressing method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103872264A (en) * | 2012-12-11 | 2014-06-18 | 上海大学 | Inflation pressure-controllable packaging system for manufacturing organic electroluminescent devices |
| CN105365251A (en) * | 2014-08-06 | 2016-03-02 | 天津航天瑞莱科技有限公司 | A hot press device for high temperature adhesive curing |
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