CN115255804A - Rapid repairing method for aircraft fuel tank skin hole fault - Google Patents
Rapid repairing method for aircraft fuel tank skin hole fault Download PDFInfo
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- CN115255804A CN115255804A CN202210932681.XA CN202210932681A CN115255804A CN 115255804 A CN115255804 A CN 115255804A CN 202210932681 A CN202210932681 A CN 202210932681A CN 115255804 A CN115255804 A CN 115255804A
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- Prior art keywords
- tank skin
- hole
- patch
- prefabricated
- repairing
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- 238000000034 method Methods 0.000 title claims abstract description 61
- 239000002828 fuel tank Substances 0.000 title abstract description 21
- 238000010288 cold spraying Methods 0.000 claims abstract description 28
- 238000005507 spraying Methods 0.000 claims abstract description 27
- 230000008569 process Effects 0.000 claims abstract description 25
- 239000000463 material Substances 0.000 claims abstract description 23
- 230000008439 repair process Effects 0.000 claims abstract description 20
- 239000011248 coating agent Substances 0.000 claims description 17
- 238000000576 coating method Methods 0.000 claims description 17
- 239000000654 additive Substances 0.000 claims description 10
- 230000000996 additive effect Effects 0.000 claims description 10
- 229910000838 Al alloy Inorganic materials 0.000 claims description 5
- 238000005498 polishing Methods 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 2
- 239000007921 spray Substances 0.000 claims 1
- 238000003466 welding Methods 0.000 abstract description 21
- 238000005516 engineering process Methods 0.000 abstract description 3
- 230000008646 thermal stress Effects 0.000 abstract description 3
- 238000007789 sealing Methods 0.000 description 10
- 230000009471 action Effects 0.000 description 3
- 230000008021 deposition Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
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- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 2
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- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 210000001503 joint Anatomy 0.000 description 1
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Images
Classifications
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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
- B23P6/00—Restoring or reconditioning objects
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention relates to a method for quickly repairing a hole fault of an aircraft fuel tank skin, which comprises the following steps: cutting the prefabricated patch according to the shape and the size of the hole of the oil tank skin; riveting the pre-fabricated patch to the outside of the hole using a blind rivet; and spraying and material increasing are carried out on the joint area of the prefabricated patch and the oil tank skin by adopting a cold spraying process, so that the repair is completed. Repair after riveting to the hole position through with prefabricated patch, the process is simple, weak point consuming time, and repair high quality can guarantee the intensity of the hole department after restoreing, and the bearing capacity is strong after restoreing, and utilizes cold spray coating technology to repair, need not to carry out high temperature treatment to the oil tank covering, and residual thermal stress is little, has avoided welding deformation and incomplete problem of welding.
Description
Technical Field
The invention relates to the field of aircraft part repair, in particular to a method for quickly repairing a hole fault of an aircraft fuel tank skin.
Background
The aircraft fuel tank skin is the surface of aircraft fuel tank, probably because of being punctured by the foreign matter and appearing the hole at the flight in-process, leads to the oil leak of fuel tank, seriously threatens flight safety and leads to the accident.
In the related art, there are two main repairing methods for the hole fault of the aircraft tank skin: and patch welding and composite material patch bonding. The patch welding needs to completely cover the hole with a repair metal sheet and weld the repair metal sheet on the surface of the fuel tank skin so as to repair the hole. Firstly, washing an airplane oil tank shell by using a washing liquid; repeatedly washing for 5-6 times, and drying for 10-20 min by using a dryer; then introducing protective gas argon into the oil tank; polishing and decontaminating before welding; polishing the oil tank after welding repair welding to ensure that the oil tank is flush with the original plane; and finally, performing visual inspection and x-ray detection, covering the surface of the hole by using a specific material in the bonding method, and bonding the hole to the surface of the oil tank skin by using special glue. The sticking of the patch requires that firstly, the part to be treated of the oil tank is pretreated (502 glue and plastic film are temporarily stopped leakage), secondly, the surface of the part to be repaired is treated, and finally, the patch is used for example; the GY-280 anaerobic adhesive is used with epoxy-polysulfide adhesive (+ glass cloth) for sealing.
However, the patch welding method has the defects of easy occurrence of welding leakage or welding burning holes on the thin-wall skin, high repairing difficulty and poor effect, the bonding process of the patch bonding method consumes long time, and the surface compressive strength after repairing is low.
Disclosure of Invention
The embodiment of the invention provides a method for quickly repairing a hole fault of an aircraft fuel tank skin, which aims to solve the problems of high repairing difficulty, poor effect, long time consumption of a bonding process and low surface compressive strength after repairing, which are caused by easy occurrence of welding leakage or welding burning holes in the related technology.
In a first aspect, a method for quickly repairing a hole fault of an aircraft tank skin is provided, which includes: cutting the prefabricated patch according to the shape and the size of the hole of the oil tank skin; riveting the pre-fabricated patch to the outside of the hole using a blind rivet; and spraying and material increasing are carried out on the joint area of the prefabricated patch and the oil tank skin by adopting a cold spraying process, so that the repair is completed.
In some embodiments, the pre-fabricated patch is 20-30mm in size extending from the aperture.
In some embodiments, the blind rivet is located 8-12mm inward of the outer edge of the pre-formed patch.
In some embodiments, the blind rivets are spaced around the outside of the hole.
In some embodiments, the distance between two adjacent blind rivets is 4-10mm.
In some embodiments, the performing additive spraying on the joint area between the prefabricated patch and the fuel tank skin by using a cold spraying process, and completing repair further includes: and spraying additive materials on the riveting area of the prefabricated patch and the blind rivet.
In some embodiments, the performing, by using a cold spraying process, additive spraying on the joint area between the prefabricated patch and the fuel tank skin to complete the repair further includes: and spraying additive on the surface of the prefabricated patch.
In some embodiments, the performing, by using a cold spraying process, additive spraying on the joint area between the prefabricated patch and the fuel tank skin to complete the repair further includes: and (4) performing spraying additive along the area extending by 20-25mm from the outer edge of the prefabricated patch.
In some embodiments, after the spraying additive to the seam area of the prefabricated patch and the tank skin, the method further includes: and polishing the surface of the repaired cold spraying coating.
In some embodiments, the pre-fabricated patch is made of an aluminum alloy.
The technical scheme provided by the invention has the beneficial effects that:
the embodiment of the invention provides a method for quickly repairing the hole fault of an aircraft fuel tank skin, which is characterized in that a prefabricated patch is riveted to a hole position and then repaired, so that the method is simple in process, short in time consumption and high in repairing quality, the strength of the repaired hole can be ensured, the bearing capacity is high after repair, the repair is carried out by using a cold spraying process, the fuel tank skin does not need to be subjected to high-temperature treatment, the residual thermal stress is small, and the problems of welding deformation and incomplete welding are solved.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a flowchart of a method for quickly repairing a hole fault in an aircraft tank skin according to an embodiment of the present invention;
fig. 2 is a schematic diagram of step 1 of a method for rapidly repairing a hole fault of an aircraft tank skin according to an embodiment of the present invention;
fig. 3 is a schematic diagram of step 2 of a method for rapidly repairing a hole fault of an aircraft tank skin according to an embodiment of the present invention;
fig. 4 is a schematic diagram of step 3 of a method for quickly repairing a hole fault in an aircraft tank skin according to an embodiment of the present invention.
Reference numbers in the figures:
1. covering the oil tank; 2. a hole; 3. prefabricating a patch; 4. blind rivets; 5. and (5) cold spraying the coating.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
The embodiment of the invention provides a method for quickly repairing a hole fault of an aircraft fuel tank skin, which can solve the problems of high repairing difficulty, poor repairing effect, long time consumption of a bonding process and low surface compressive strength after repairing, which are caused by easy occurrence of welding leakage or welding burning holes in the related technology.
Referring to fig. 1, fig. 2, fig. 3 and fig. 4, a method for quickly repairing an aircraft tank skin hole fault provided in an embodiment of the present invention may include:
Referring to fig. 3, in some embodiments, the size of the prefabricated patch 3 may be 20-30mm from the outside of the hole 2, in this embodiment, the size of the prefabricated patch 3 is larger than that of the hole 2, so as to ensure that the hole 2 is completely covered, and the prefabricated patch 3 extends from the outside of the hole 2 for a certain distance, so as to increase the contact area between the prefabricated patch 3 and the tank skin 1, and when cold spraying is subsequently performed, the width of the cold spraying coating 5 may be increased, the seam edge and the rivet hole are covered, so as to ensure the sealing performance at the seam between the repaired hole 2 and the prefabricated patch 3, and the coating thickness is preferably not less than 1mm. In other embodiments, the size of the pre-fabricated patch 3 may also be extended by other distances from the hole 2, or may be just equal to the hole 2.
Referring to fig. 3, in some embodiments, the blind rivet 4 may be located 8-12mm inward from the outer edge of the pre-formed patch 3, and in this embodiment, since the size of the pre-formed patch 3 is 20-30mm outward from the hole 2, the blind rivet 4 may be pushed out to be located approximately in the middle between the pre-formed patch 3 and the hole 2, so that the pre-formed patch 3 can be just attached to the surface of the hole 2 and the surface of the fuel tank skin 1 at the same time, the gap is prevented from being too large, and the sealing performance after spraying is further ensured. In other embodiments, the blind rivet 4 may be riveted to the prefabricated patch 3 at other locations as desired.
Referring to fig. 3, preferably, the blind rivets 4 may be arranged at intervals around the outer circumference of the hole 2, and in this embodiment, the blind rivets 4 are arranged at intervals around the circumference of the hole 2, so that a gap between the prefabricated patch 3 and the fuel tank skin 1 can be further reduced, the sealing performance is ensured, and the strength after repair can also be ensured. In other embodiments, the blind rivets 4 may be arranged in a straight line or in a distributed arrangement.
Referring to fig. 3, preferably, the distance between two adjacent blind rivets 4 may be 4-10mm, and in this embodiment, the distance between the blind rivets 4 may be set to minimize the damage of the blind rivets 4 to the fuel tank skin 1 on the basis of ensuring the sealing performance of the fuel tank skin 1 and the strength of the repaired fuel tank skin at the holes 2. In other embodiments, the spacing between the blind rivets 4 may be set at other distances as desired.
Referring to fig. 4, preferably, the spraying and material increasing of the joint area between the prefabricated patch 3 and the tank skin 1 by using a cold spraying process may further include: and spraying and material increasing are carried out on the riveting area of the prefabricated patch 3 and the blind rivet 4, in the embodiment, the riveting area is an area between the outer wall of the blind rivet 4 and the prefabricated patch 3, and coating powder is shot to the riveting area through a cold spraying process, so that a compact coating is formed by connecting the blind rivet 4 and the prefabricated patch 3, and the phenomenon that the riveting area generates a gap to influence the subsequent use of the oil tank skin 1 is avoided.
Referring to fig. 4, preferably, the spraying and material increasing of the joint area between the prefabricated patch 3 and the tank skin 1 by using a cold spraying process may further include: in the embodiment, the surface of the prefabricated patch 3 is sprayed and subjected to material increase, so that the coating on the surface of the prefabricated patch 3, the coating on the riveting area of the prefabricated patch 3 and the blind rivet 4 and the coating on the seam area of the prefabricated patch 3 and the oil tank skin 1 are connected into a whole, the strength of the coating after cold spraying is further increased, and the sealing property is improved. Wherein, the coating on the surface of the prefabricated patch 3 can be annular, and the prefabricated patch 3 can be covered completely.
Referring to fig. 4, preferably, the spraying and material increasing of the joint area between the prefabricated patch 3 and the tank skin 1 by using a cold spraying process may further include: and spraying and material increasing are carried out along the area which is 20-25mm away from the outer edge of the prefabricated patch 3, in the embodiment, the prefabricated patch 3 is sprayed along the outer edge of the prefabricated patch 3, so that a gap between the prefabricated patch 3 and the oil tank skin 1 is avoided, and the sealing property is further improved.
Referring to fig. 4, after the spraying of the additive material to the seam area of the prefabricated patch 3 and the tank skin 1, it may further include: the surface of the repaired cold spraying coating 5 is polished, in the embodiment, the surface of the cold spraying coating 5 is polished, so that the surface of the cold spraying coating 5 is smoother, and the roughness of the surface of a workpiece is reduced.
As shown in fig. 3, preferably, the prefabricated patch 3 is made of an aluminum alloy material, and the aluminum alloy has good strength and rigidity, so that after the hole 2 is repaired by the prefabricated patch 3, the repaired part has higher strength and better bearing capacity.
The principle of the rapid repairing method for the hole fault of the aircraft fuel tank skin provided by the embodiment of the invention is as follows:
through adopting 3 riveting restoration oil tank skin structural strength of prefabricated patch, guaranteed joint strength and structural stability between prefabricated patch 3 and oil tank skin 1, through adopting cold spraying vibration material disk to restore oil tank skin 1's leakproofness, realized oil tank skin 1's sealing treatment, further strengthened structural strength, realized the rush repair of aircraft wing oil tank skin.
In the description of the present invention, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present invention. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly and encompass, for example, both fixed and removable coupling as well as integral coupling; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
It is to be noted that, in the present invention, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrases "comprising one of 8230; \8230;" 8230; "does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
The foregoing are merely exemplary embodiments of the present invention, which enable those skilled in the art to understand or practice the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A method for quickly repairing a hole fault of an aircraft tank skin is characterized by comprising the following steps:
cutting the prefabricated patch (3) according to the shape and the size of the hole (2) of the oil tank skin (1);
riveting the pre-fabricated patch (3) to the outside of the hole (2) using a blind rivet (4);
and (3) spraying and material increasing are carried out on the joint area of the prefabricated patch (3) and the oil tank skin (1) by adopting a cold spraying process, so that the repair is completed.
2. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 1, wherein:
the size of the prefabricated patch (3) is 20-30mm extended from the hole (2).
3. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 1, wherein:
the blind rivet (4) is positioned at the position 8-12mm inward of the outer edge of the prefabricated patch (3).
4. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 1, wherein:
the blind rivets (4) are arranged around the outer side of the hole (2) at intervals.
5. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 1, wherein:
the distance between two adjacent blind rivets (4) is 4-10mm.
6. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 1, wherein the cold spraying process is adopted to perform spraying material increase on the joint area of the prefabricated patch (3) and the tank skin (1), and the repairing is completed further by:
and spraying additive materials on the riveting area of the prefabricated patch (3) and the blind rivet (4).
7. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 6, wherein the cold spraying process is adopted to perform spraying material addition on the joint area of the prefabricated patch (3) and the tank skin (1), and the repairing is completed further by:
and (4) spraying additive on the surface of the prefabricated patch (3).
8. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 7, wherein the cold spraying process is adopted to spray and add materials to the seam area between the prefabricated patch (3) and the tank skin (1), and the repairing is completed by further comprising:
and (4) performing spraying material increase along the area extending by 20-25mm from the outer edge of the prefabricated patch (3).
9. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 1, characterized in that after the spraying and the material adding of the joint area of the prefabricated patch (3) and the tank skin (1), the method further comprises the following steps:
and (4) polishing the surface of the repaired cold spraying coating (5).
10. The method for rapidly repairing the hole fault of the aircraft tank skin according to claim 1, wherein:
the prefabricated patch (3) is made of an aluminum alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210932681.XA CN115255804A (en) | 2022-08-04 | 2022-08-04 | Rapid repairing method for aircraft fuel tank skin hole fault |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210932681.XA CN115255804A (en) | 2022-08-04 | 2022-08-04 | Rapid repairing method for aircraft fuel tank skin hole fault |
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| Publication Number | Publication Date |
|---|---|
| CN115255804A true CN115255804A (en) | 2022-11-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210932681.XA Pending CN115255804A (en) | 2022-08-04 | 2022-08-04 | Rapid repairing method for aircraft fuel tank skin hole fault |
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1731566A1 (en) * | 1990-12-25 | 1992-05-07 | Харьковский авиационный институт им.Н.Е.Жуковского | Method for repairs of cracked skin |
| DE102006057255A1 (en) * | 2006-12-05 | 2008-06-19 | Airbus Deutschland Gmbh | Method for repairing damage in aircraft skin using patches applied from inside the hull and with outer flush filling |
| CA2772838A1 (en) * | 2012-03-29 | 2013-09-29 | Rosebank Engineering Pty Ltd | Methods for treating aircraft structures |
| US20140017037A1 (en) * | 2011-02-25 | 2014-01-16 | Airbus Operations Gmbh | Method for producing a connector, connector and aircraft or spacecraft |
| FR2999974A1 (en) * | 2012-12-20 | 2014-06-27 | Airbus Operations Sas | System for applying repair kit to face of structure to be repaired e.g. fuselage panel of aircraft, has backpressure device with surface arranged in opposite to goldbeater's skin, and connection units that connects device to frame |
| CN203740116U (en) * | 2014-01-21 | 2014-07-30 | 中国民航大学 | Glue-rivet mixed repair structure of composite material fuselage skin |
| CN204802103U (en) * | 2015-06-08 | 2015-11-25 | 曹启武 | Combined material covering sew up repair structure |
| CN204802067U (en) * | 2015-06-08 | 2015-11-25 | 曹启武 | Glue line of combined material covering mixes repair structure |
| CN111703587A (en) * | 2020-06-08 | 2020-09-25 | 国营四达机械制造公司 | Method for repairing crack corrosion fault of airplane electric heating front edge skin |
| CN113335556A (en) * | 2021-05-25 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Skin repairing method and repairing structure thereof |
| CN114318323A (en) * | 2021-12-10 | 2022-04-12 | 国营芜湖机械厂 | Method for repairing local damage of aircraft skin surface in situ through cold spraying |
-
2022
- 2022-08-04 CN CN202210932681.XA patent/CN115255804A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1731566A1 (en) * | 1990-12-25 | 1992-05-07 | Харьковский авиационный институт им.Н.Е.Жуковского | Method for repairs of cracked skin |
| DE102006057255A1 (en) * | 2006-12-05 | 2008-06-19 | Airbus Deutschland Gmbh | Method for repairing damage in aircraft skin using patches applied from inside the hull and with outer flush filling |
| US20140017037A1 (en) * | 2011-02-25 | 2014-01-16 | Airbus Operations Gmbh | Method for producing a connector, connector and aircraft or spacecraft |
| CA2772838A1 (en) * | 2012-03-29 | 2013-09-29 | Rosebank Engineering Pty Ltd | Methods for treating aircraft structures |
| FR2999974A1 (en) * | 2012-12-20 | 2014-06-27 | Airbus Operations Sas | System for applying repair kit to face of structure to be repaired e.g. fuselage panel of aircraft, has backpressure device with surface arranged in opposite to goldbeater's skin, and connection units that connects device to frame |
| CN203740116U (en) * | 2014-01-21 | 2014-07-30 | 中国民航大学 | Glue-rivet mixed repair structure of composite material fuselage skin |
| CN204802103U (en) * | 2015-06-08 | 2015-11-25 | 曹启武 | Combined material covering sew up repair structure |
| CN204802067U (en) * | 2015-06-08 | 2015-11-25 | 曹启武 | Glue line of combined material covering mixes repair structure |
| CN111703587A (en) * | 2020-06-08 | 2020-09-25 | 国营四达机械制造公司 | Method for repairing crack corrosion fault of airplane electric heating front edge skin |
| CN113335556A (en) * | 2021-05-25 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Skin repairing method and repairing structure thereof |
| CN114318323A (en) * | 2021-12-10 | 2022-04-12 | 国营芜湖机械厂 | Method for repairing local damage of aircraft skin surface in situ through cold spraying |
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