CN118527947A - Method for repairing damage of aircraft knuckle bearing mounting hole - Google Patents
Method for repairing damage of aircraft knuckle bearing mounting hole Download PDFInfo
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- CN118527947A CN118527947A CN202410826737.2A CN202410826737A CN118527947A CN 118527947 A CN118527947 A CN 118527947A CN 202410826737 A CN202410826737 A CN 202410826737A CN 118527947 A CN118527947 A CN 118527947A
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- bushing
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- hole
- bearing mounting
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 230000003068 static effect Effects 0.000 claims abstract description 36
- 238000012360 testing method Methods 0.000 claims abstract description 25
- 230000008439 repair process Effects 0.000 claims abstract description 19
- 239000000853 adhesive Substances 0.000 claims abstract description 14
- 230000001070 adhesive effect Effects 0.000 claims abstract description 14
- 238000003825 pressing Methods 0.000 claims abstract description 14
- 238000004519 manufacturing process Methods 0.000 claims abstract description 10
- 239000011159 matrix material Substances 0.000 claims abstract description 10
- 230000001680 brushing effect Effects 0.000 claims abstract description 7
- 239000000463 material Substances 0.000 claims abstract description 6
- 238000005520 cutting process Methods 0.000 claims abstract description 5
- 238000013461 design Methods 0.000 claims description 8
- 238000004154 testing of material Methods 0.000 claims description 8
- 238000011179 visual inspection Methods 0.000 claims description 8
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 238000004088 simulation Methods 0.000 claims description 4
- 239000000758 substrate Substances 0.000 claims description 4
- 238000007689 inspection Methods 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 2
- 238000009864 tensile test Methods 0.000 abstract 1
- 238000009736 wetting Methods 0.000 abstract 1
- 239000000654 additive Substances 0.000 description 3
- 230000000996 additive effect Effects 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000004040 coloring Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004372 laser cladding Methods 0.000 description 1
- 238000009659 non-destructive testing Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000011867 re-evaluation Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000007751 thermal spraying Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- 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)
- Sliding-Contact Bearings (AREA)
Abstract
The invention provides a method for repairing damage to an aircraft knuckle bearing mounting hole, which comprises the following steps: annular cutting off the mounting hole to confirm that no crack exists; original state samples A, B and C are manufactured; processing the samples B and C into damaged samples, wherein the damaged samples comprise step holes which can cover damaged areas at damaged bearing mounting holes; carrying out static load tension test on the sample A and the sample B; manufacturing a bushing made of the same material as the joint bearing mounting matrix; pressing the knuckle bearing into a bushing, brushing anaerobic adhesive outside the bushing, and then wetting the bushing into a sample C; carrying out static load tensile test and bearing release force test on the sample C with the bushing; and manufacturing the bushing, and completing the assembly of the knuckle bearing, the bushing and the product. The invention repairs the damaged part of the joint bearing mounting hole by adopting a method of removing the damaged part and wet-mounting and pressing the bushing after brushing anaerobic adhesive, has high bonding strength of parts, small residual stress, and strength and service life meeting the technical requirements of products, and ensures the quality and delivery cycle of the products.
Description
Technical Field
The invention belongs to the technical field of aviation repair, and particularly relates to a method for repairing damage to an aircraft knuckle bearing mounting hole.
Background
In the structural design of an aircraft body, the movable part is ensured to rotate by adopting a mode of press-mounting the joint bearing on a structural member, and the joint bearing and a matching surface of a base body of the joint bearing are easy to wear and damage such as falling blocks under the action of load, so that the assembly and the use of products are affected. There are two conventional repair methods: one is to repair the replacement parts of the bearing, but the replacement parts are difficult to purchase and have long period, so that the product delivery requirement cannot be met; the other is to repair the damaged part by adopting additive repair technologies such as thermal spraying, argon arc welding, laser cladding and the like, but experiments prove that the common part after the additive repair has low bonding strength, large heat affected zone and large residual stress, cannot guarantee the size and repair quality, is extremely easy to damage a machine part, and reduces the strength and service life of the machine part.
Disclosure of Invention
The invention aims to solve the problems that the product delivery cycle requirement cannot be met by adopting a replacement repair mode when the aircraft knuckle bearing mounting hole is damaged and the repair quality cannot be guaranteed by adopting an additive repair technology in the prior art, and provides a method for repairing the aircraft knuckle bearing mounting hole damage.
In order to achieve the above purpose, the technical solution provided by the present invention is:
The method for repairing the damage of the aircraft knuckle bearing mounting hole is characterized by comprising the following steps of:
Step1, performing annular cutting on an aircraft joint bearing mounting hole with damage until the damage is completely removed, then performing visual inspection on the residual matrix to confirm that no crack exists, performing nondestructive inspection on the residual matrix around the joint bearing hole to be repaired after visual inspection, and confirming that no crack exists;
Step 2, three original state samples, namely a sample A, a sample B and a sample C, are manufactured according to design patterns of the joint bearing mounting hole area, wherein the bearing mounting holes of the original state samples are original through holes, the aperture of the original through holes is D 1, and the thickness of the original through holes is H 1;
Step 3, on the premise of ensuring that the hole periphery distance is not smaller than the design technical requirement of a product, the simulation step 1 processes a sample piece B and a sample piece C into a damaged state sample piece, wherein the damaged state sample piece comprises a step hole capable of covering a damaged area at a damaged bearing mounting hole, the step hole comprises a large hole and a small hole, the aperture of the small hole is D 2, the aperture of the large hole is D 3, the thicknesses of the large holes are H 2,D2、D3 and H 2 are determined according to the volume of the damaged area of the product, and the damage of the edge of a base body of the aperture of the product can be eliminated;
step 4, respectively carrying out a static load tension test on the sample A and the sample B on a material testing machine, so as to ensure that the static load tension value of the sample B is not less than 80% of the static load tension value of the sample A;
Step 5, manufacturing a bushing made of the same material as the joint bearing mounting substrate, wherein the bushing comprises a base part and a flange part, the inner diameter of the base part is D 1, the outer diameter of the base part is D 2, the thickness of the base part is H 1-H2, the inner diameter of the flange part is D 1, the outer diameter of the flange part is D 3, the thickness of the flange part is H 2, and the interference fit quantity of the bushing and the step hole meets the tolerance fit requirement;
step 6, pressing the knuckle bearing into a bushing, uniformly brushing a layer of anaerobic adhesive on the outer surface of the bushing, and pressing the bushing into a sample C in a wet manner;
Step 7, after the anaerobic adhesive is naturally cured, carrying out a static load tension test on a sample C with a bushing on a material testing machine, ensuring that the static load tension value is not less than 80% of the static load tension value of the sample A, and carrying out a bearing release force test on a mechanical tension testing machine, thereby ensuring that the release force meets HB 0-37 regulation;
and 8, manufacturing a bushing according to the step 5, and assembling the knuckle bearing, the bushing and the product according to the step 6, thereby completing the repair of the product.
Further, in step 6, TY340 anaerobic glue is selected to brush the outer surface of the liner.
Further, in step 3, when the original state sample is processed into the damaged state sample, the hole peripheral distance is ensured to be not less than 9.5mm.
Further, in step 5, the flange portion of the sleeve is made to further include a radially inwardly projecting boss for preventing the knuckle bearing from backing out of the sleeve.
The invention has the advantages that:
According to the method for repairing the damage of the mounting hole of the aircraft knuckle bearing, an original state sample piece is firstly manufactured when the product is not damaged before being used, then the damaged state sample piece is processed according to a damaged area of the repaired product, then a static load tension test is carried out to ensure that the static load tension of the damaged state sample piece meets the requirement, then a lining matched with the damaged state sample piece is manufactured, the knuckle bearing is pressed into the lining, after being coated with anaerobic adhesive, the lining is wet-packed into the damaged state sample piece, and the static load tension and the axial bearing pressing force are verified to meet the regulation, and then the damaged area of the product to be repaired is removed, and the lining is pressed into the lining. Therefore, the method for removing the damaged part and wet-mounting and pressing the reinforced bushing after brushing anaerobic adhesive is adopted to repair the damaged part of the joint bearing mounting hole, and the static load tension and bearing axial pressure release force test proves that the repairing method is simple and reliable, the machine part bonding strength is high, the residual stress is small, the machine part is not damaged, the machine part strength and the service life meet the product technical requirements, and the product quality and the delivery cycle are ensured.
Drawings
The features and advantages of the present invention will become more readily understood from the following description with reference to the accompanying drawings, which are not drawn to scale, and some features are exaggerated or reduced to show details of particular components, in which:
FIG. 1 is a perspective view of a damaged and removed residual substrate in a method of repairing damage to an aircraft knuckle bearing mounting hole in accordance with the present invention;
FIG. 2 is a cross-sectional view of a bushing in the method of repairing damage to an aircraft knuckle bearing mounting hole of the present invention.
In the figure: 1-large hole, 2-small hole, 3-base, 4-flange and 5-boss.
Detailed Description
The invention will be described in detail below with the aid of exemplary embodiments of the invention with reference to the accompanying drawings. It should be noted that the following detailed description of the present invention is for illustrative purposes only and is not intended to be limiting.
The invention provides a method for repairing damage to an aircraft knuckle bearing mounting hole, which is used for repairing the damaged knuckle bearing mounting hole with abrasion, block dropping and the like, in particular to a product with an elliptical mounting hole.
The method for repairing the damage of the aircraft knuckle bearing mounting hole as an exemplary embodiment of the invention comprises the following steps:
Step S1, as shown in FIG. 1, annular cutting is carried out on an aircraft knuckle bearing mounting hole with damage until the damage part is completely removed, then visual inspection is carried out on the residual matrix (the middle part is in a step hole shape) to confirm that no crack exists, and nondestructive detection is carried out on the residual matrix around the knuckle bearing hole to be repaired after the visual inspection to confirm that no crack exists;
Step S2, three original state samples, namely a sample A, a sample B and a sample C, are manufactured according to design patterns of the joint bearing mounting hole area, wherein the bearing mounting holes of the original state samples are original through holes, the aperture of the original through holes is D 1, and the thickness of the original through holes is H 1;
Step S3, on the premise that the hole periphery distance is not smaller than the design technical requirement of a product, the simulation step S1 processes a sample piece B and a sample piece C in three original state sample pieces into two damaged state sample pieces, the damaged state sample pieces comprise step holes capable of covering a damaged area at a damaged bearing mounting hole, the step holes comprise large holes 1 and small holes 2, the aperture of the small holes is D 2, the aperture of the large holes is D 3, the thicknesses of the large holes are H 2,D2、D3 and H 2 are determined according to the volume of the damaged area of the product, and damage of the edge of a base body of the aperture of the product can be eliminated, and D 3>D2>D1,H2<H1;
S4, respectively carrying out a static load tension test on an original state sample, namely a first damaged state sample in the sample A and two damaged state samples and the sample B on a material testing machine, so as to ensure that the static load tension value of the sample B is not less than 80% of the static load tension value of the sample A;
S5, manufacturing a bushing of the same material as the joint bearing mounting substrate, wherein the bushing has a structure as shown in FIG. 2, is consistent with a damage area cut off in an annular manner, comprises a base part 3 and a flange part 4, wherein the base part 3 is used for being matched with the small hole 2, the inner diameter of the bushing is D 1, the outer diameter of the bushing is D 2, the thickness of the bushing is H 1-H2, the flange part 4 is used for being matched with the large hole 1, the inner diameter of the flange part is D 1, the outer diameter of the flange part is D 3, the thickness of the flange part is H 2, and the interference fit quantity of the bushing and the step hole meets the tolerance fit requirement;
S6, pressing the knuckle bearing into a bushing, uniformly brushing a layer of anaerobic adhesive on the outer surface of the bushing, and pressing the bushing into a second damaged state sample piece and a sample piece C of the two damaged state sample pieces in a wet-packing manner;
S7, after the anaerobic adhesive is naturally cured, carrying out a static load tension test on the sample C with the bushing on a material testing machine, so as to ensure that the static load tension value of the sample C is not less than 80% of the static load tension value of the sample A, and carrying out a bearing release force test on a mechanical tension testing machine, so as to ensure that the release force meets HB 0-37 regulation;
and S8, manufacturing a bushing according to the step S5, and completing the assembly of the knuckle bearing, the bushing and the product shown in FIG. 1 according to the step S6, thereby completing the repair of the product.
In step S1, if the repaired product has a crack and the crack area is large, the repair may not be performed and a re-evaluation is required.
Alternatively, in step S3, when the original state sample is processed into the damaged state sample, the hole peripheral distance may be ensured to be not less than 9.5mm.
In step S4, if the static load tension value of the sample B is less than 80% of the static load tension value of the original sample, it indicates that the load strength of the damaged sample cannot meet the working requirement, and the structural size of the damaged sample needs to be readjusted.
In an exemplary embodiment of the present invention, the flange portion 4 of the manufactured bush further includes a boss 5 protruding radially inward, having an inner diameter smaller than D 1, for preventing the knuckle bearing from coming out of the bush, particularly, from coming out of the bush when the knuckle bearing is press-fitted into the bush, and from coming out of the bearing when the bush with the bearing is press-fitted into the damaged-state sample in step S5.
In step S6, the outer surface of the lining is brushed with TY340 anaerobic adhesive.
In step S7, if the verification result of either the static load pull test or the bearing release force test does not meet the specification, the structural dimensions of the bushing and the damaged condition sample need to be modified again. Only if the specification is satisfied, the structure obtained by the method of processing the damaged product and installing the bushing in the same way as the damaged state sample can meet the requirement, and the repaired product can be repaired by adopting a method of removing the damaged area and pressing the damaged area into the reinforced bushing.
As described above, the method of removing damaged parts and wet-mounting and pressing in after the reinforcement bush is coated with anaerobic adhesive is adopted to repair damaged parts of the joint bearing mounting hole, and the static load tension and bearing axial pressure release force tests prove that the repairing method is simple and reliable, the machine part bonding strength is high, the residual stress is small, the machine part is not damaged, the machine part strength and the service life meet the product technical requirements, and the product quality and the delivery cycle are ensured.
The method for repairing the damage to the mounting hole of the joint bearing of the aircraft provided by the invention is further described below with reference to examples.
Taking damage repair of a mounting hole of a joint bearing (UG 12) mounted on an airplane wing nacelle transition beam as an example, wherein the joint material is LD10, and the minimum hole edge distance is 9.5mm; the nondestructive testing mode adopts coloring inspection and is implemented as follows:
Step S1, annular cutting is carried out on an aircraft joint bearing mounting hole with damage until the damage is completely removed, then visual inspection is carried out on the residual matrix to confirm that no crack exists, and nondestructive detection is carried out on the residual matrix around the joint bearing hole to be repaired after the visual inspection to confirm that no crack exists;
S2, three original state samples, namely a sample A, a sample B and a sample C, are manufactured according to design patterns of a rear joint knuckle bearing mounting hole area, wherein bearing mounting holes of the three samples are original through holes, the aperture of each original through hole is 22mm, and the thickness of each original through hole is 7.2mm;
Step S3, on the premise of ensuring that the hole peripheral distance is not less than 9.5mm, the simulation step S1 processes the sample piece B and the sample piece C into two damaged state sample pieces, wherein the damaged state sample pieces comprise step holes capable of covering a damaged area at the damaged bearing mounting hole, each step hole comprises a large hole and a small hole, the aperture of each small hole is 23.2mm, the aperture of each large hole is 28mm, the thickness of each large hole is 1.5mm, and damage to the edges of a product aperture matrix is eliminated;
S4, respectively carrying out static load tension test on the sample A and the sample B on a material testing machine, wherein the static load tension value of the sample A is 67500N, the static load tension value of the sample B is 63500N, and the static load tension value of the sample A is not less than 80% of the static load tension value of the sample in an original state, so that the sample A meets the specification of technical requirements;
S5, designing and manufacturing a bushing by using a material LD10, wherein the bushing comprises a base part and a flange part, the inner diameter of the base part is 22mm, the outer diameter of the base part is 23.2mm, the thickness of the base part is 5.7mm, the inner diameter of the flange part is 22mm, the outer diameter of the flange part is 28mm, the thickness of the flange part is 1.5mm, and the interference fit of the bushing and the knuckle bearing is 0.005mm according to the requirements of H5800 'tolerance and fit manual';
S6, pressing the knuckle bearing into a bushing, uniformly brushing a layer of TY340 anaerobic adhesive on the outer surface of the bushing, and pressing the bushing into a sample C in a wet manner;
s7, after the anaerobic adhesive is naturally cured, carrying out a static load tension test on a sample C with a bushing on a material testing machine, wherein the static load tension value is 60000N and is not less than 80% of the static load tension value (67500N) of the sample A, the test meets the technical requirement, the bearing release force test is carried out on a mechanical tension testing machine, the release force is 4000N, and the test meets the requirement specified in HB 0-37 technical standard (more than or equal to 1961N);
and S8, manufacturing a bushing according to the step S5, and completing the assembly of the knuckle bearing, the bushing and the product according to the step S6, thereby completing the repair of the product.
Therefore, the above examples verify the effectiveness and reliability of the method of repairing the damage to the aircraft knuckle bearing mounting holes provided by the present invention.
Finally, it should be noted that features mentioned and/or shown in the above description of exemplary embodiments of the invention may be combined in one or more other embodiments in the same or similar way, in combination with or instead of the corresponding features in the other embodiments. Such combined or substituted solutions should also be considered to be included within the scope of the invention.
Claims (4)
1. A method of repairing damage to an aircraft knuckle bearing mounting hole, comprising the steps of:
Step1, performing annular cutting on an aircraft joint bearing mounting hole with damage until the damage is completely removed, then performing visual inspection on the residual matrix to confirm that no crack exists, performing nondestructive inspection on the residual matrix around the joint bearing hole to be repaired after visual inspection, and confirming that no crack exists;
step 2, three original state samples, namely a sample A, a sample B and a sample C, are manufactured according to design patterns of the joint bearing mounting hole area, wherein the bearing mounting holes of the original state samples are original through holes, the aperture of the original through holes is D 1, and the thickness of the original through holes is H 1;
Step 3, on the premise of ensuring that the hole periphery distance is not smaller than the design technical requirement of a product, the simulation step 1 processes a sample piece B and a sample piece C into a damaged state sample piece, wherein the damaged state sample piece comprises a step hole capable of covering a damaged area at a damaged bearing mounting hole, the step hole comprises a large hole and a small hole, the aperture of the small hole is D 2, the aperture of the large hole is D 3, the thicknesses of the large holes are H 2,D2、D3 and H 2 are determined according to the volume of the damaged area of the product, and the damage of the edge of a base body with the aperture of the product can be eliminated, and D 3>D2>D1,H2<H1;
step 4, respectively carrying out a static load tension test on the sample A and the sample B on a material testing machine, so as to ensure that the static load tension value of the sample B is not less than 80% of the static load tension value of the sample A;
step 5, manufacturing a bushing made of the same material as the joint bearing mounting substrate, wherein the bushing comprises a base part and a flange part, the inner diameter of the base part is D 1, the outer diameter of the base part is D 2, the thickness of the base part is H 1-H2, the inner diameter of the flange part is D 1, the outer diameter of the flange part is D 3, the thickness of the flange part is H 2, and the interference fit quantity of the bushing and the step hole meets the tolerance fit requirement;
step 6, pressing the joint bearing into the bushing, uniformly brushing a layer of anaerobic adhesive on the outer surface of the bushing, and pressing the bushing into the sample C in a wet manner;
Step 7, after the anaerobic adhesive is naturally cured, carrying out a static load tension test on a sample C with a bushing on a material testing machine, ensuring that the static load tension value is not less than 80% of the static load tension value of the sample A, and carrying out a bearing release force test on a mechanical tension testing machine, thereby ensuring that the release force meets HB 0-37 regulation;
and 8, manufacturing a bushing according to the step 5, and assembling the knuckle bearing, the bushing and the product according to the step 6, thereby completing the repair of the product.
2. The method of repairing aircraft knuckle bearing mounting hole damage of claim 1, wherein: in the step 6, TY340 anaerobic glue is selected to brush the outer surface of the lining.
3. The method of repairing aircraft knuckle bearing mounting hole damage of claim 1 or 2, wherein: in the step 3, when the original state sample is processed into the damaged state sample, the hole peripheral distance is ensured to be not less than 9.5mm.
4. The method of repairing aircraft knuckle bearing mounting hole damage of claim 1 or 2, wherein: in said step 5, the flange portion of the bushing is made further comprising a radially inwardly protruding boss for preventing the knuckle bearing from backing out of the bushing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410826737.2A CN118527947A (en) | 2024-06-25 | 2024-06-25 | Method for repairing damage of aircraft knuckle bearing mounting hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410826737.2A CN118527947A (en) | 2024-06-25 | 2024-06-25 | Method for repairing damage of aircraft knuckle bearing mounting hole |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118527947A true CN118527947A (en) | 2024-08-23 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410826737.2A Pending CN118527947A (en) | 2024-06-25 | 2024-06-25 | Method for repairing damage of aircraft knuckle bearing mounting hole |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118527947A (en) |
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2024
- 2024-06-25 CN CN202410826737.2A patent/CN118527947A/en active Pending
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