CN114671045A - In-situ repairing and reinforcing method for cracks of main landing gear beam joint of airplane - Google Patents
In-situ repairing and reinforcing method for cracks of main landing gear beam joint of airplane Download PDFInfo
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- CN114671045A CN114671045A CN202210208572.3A CN202210208572A CN114671045A CN 114671045 A CN114671045 A CN 114671045A CN 202210208572 A CN202210208572 A CN 202210208572A CN 114671045 A CN114671045 A CN 114671045A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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Abstract
The invention relates to the field of material processing technology and surface engineering, in particular to an in-situ repairing and reinforcing method for cracks of a main landing gear beam joint of an airplane, which comprises the following specific steps: step one, forming a laser high-energy beam in-situ repair and reinforcement expert system; secondly, preprocessing the surface of the landing gear beam joint; step three, accurately identifying and processing a crack damage area; step four, generating a crack damage repair area model; step five, laser additive repair; sixthly, finishing the surface of the repair layer; seventhly, performing laser shot peening; step eight, surface protection; according to the invention, the crack damage identification processing system, the laser additive repair system and the laser shot peening system are integrated on the mobile platform, so that accurate removal, additive repair and post-treatment strengthening processes of a crack damage region can be realized simultaneously, the service performance requirement after repair is ensured, related technologies can be implemented in situ, and series problems about in-situ high-performance repair of the landing gear beam joint are overcome.
Description
Technical Field
The invention relates to the field of material processing technology and surface engineering, in particular to an in-situ repairing and reinforcing method for cracks of a main landing gear beam joint of an airplane.
Background
The landing gear beam joint is mainly used for connecting landing gear struts, transfers landing gear load to the landing gear beam, and is an important connecting component between a body structure and a landing gear. The maximum load born by the airplane in the taking-off and landing process can reach more than +/-1.0 multiplied by 107N, the airplane plays an important role in the key flight processes of taking-off and landing and the like, the crack damage of the part can seriously affect the flight safety, and the part can not be disassembled and replaced. Therefore, whether the in-situ repair and the reinforcement of the cracks of the landing gear beam joint in the aircraft maintenance process are realized directly determines whether the aircraft can be continuously in service.
In the field of aviation maintenance, technologies such as laser additive repair and laser shot peening are mature and applied. However, there are still many difficulties in applying it to crack repair of landing gear beam joints. Firstly, the landing gear beam joint cannot be disassembled, in-situ repair is required, and series of technologies such as crack identification, treatment, repair, reinforcement and the like must be implemented on site; secondly, the landing gear beam joint is a key important load-bearing and transmission component, the requirements on the performances of load bearing, fatigue and the like are extremely strict, and the service performance requirements of the landing gear beam joint cannot be met by a single repair technology.
By adopting the surface repairing and reinforcing technology which can be carried out in situ, the accurate identification treatment of a crack damage area, the high-performance repairing and the preparation of a reinforcing layer are simultaneously realized, and the method is a basic technical path for realizing the service efficiency recovery of the landing gear beam joint.
Regarding in-situ repair and reinforcement of important airplane components, chinese patent application No. 111036520a discloses an in-situ reinforcement repair method for airplane landing gear beam cracks, which directly deposits a cold spray coating with a certain size on the landing gear beam crack area by using a cold spray technology to realize reinforcement of the damaged area. The cold spraying coating prepared by the method has low bonding strength, and is not suitable for parts bearing alternating heavy load, such as lifting frame beam joints (tensile and compressive loads can reach +/-1.0 multiplied by 107N), and the like. As another example, a mobile increase and decrease composite processing system disclosed in chinese patent No. 109202289B can realize large-scale movement of laser additive repair space, thereby realizing in-situ implementation of repair process, but the system only integrates additive and subtractive units, and has no laser shot peening system, but only can realize size recovery and partial performance recovery of key components, and is not suitable for components with extremely high repair performance such as landing gear beam joints, and the like, and further enters a manufacturing method of laser manufacturing composite steel pipes in chinese patent application No. 201911339717.8, by adding a pretreatment step before the surface coating manufacturing step, oil stains on the surface can be cleaned, and the surface is rusted and polished by a motor sander or shot peening, and then the surface on which the coating material is clad by a laser cladding technology, thereby obtaining a composite material, the original capabilities on a certain aspect, such as corrosion resistance, wear resistance, high temperature resistance and the like, are improved through the combination, but the method is not suitable for in-situ repair of cracks of the main landing gear beam joint of the airplane due to the fact that the method is not based on long-term laser additive repair and laser shot peening strengthening actual production experience data and is combined with the process characteristics of an in-situ repair system.
Disclosure of Invention
In order to solve the problems, the invention provides an in-situ repairing and reinforcing method for cracks of a main landing gear beam joint of an airplane.
An in-situ repairing and reinforcing method for cracks of a main landing gear beam joint of an airplane comprises the following specific steps:
step one, forming a laser high-energy beam in-situ repair and reinforcement expert system: forming a set of high-energy laser beam in-situ repair and reinforcement expert system, and integrating the expert system on a control computer;
step two, undercarriage beam joint surface pretreatment: the main work is paint stripping and removal of a surface protective layer;
step three, accurately identifying and processing a crack damage area: identifying a crack damage area on the surface, determining a polishing range, monitoring the change of the damage area in real time by an image identification processing system during polishing, feeding back and controlling a polishing unit in time, and determining that the crack damage area is completely removed;
step four, generating a crack damage repair area model: scanning the polished landing gear beam joint by a system 3D scanning module, and comparing the polished landing gear beam joint with a standard part in the system to generate a crack damage repair area model;
step five, laser additive repair: introducing the crack damage repair area model generated in the step four, calling the matched repair material and process in the expert system to carry out laser material increase repair, adjusting the repair process according to actual needs, and ensuring the performance and size recovery of the repair layer;
Step six, repairing the surface finish of the layer: calling a system polishing control unit, matching a proper polishing head based on the surface state of the repair layer, and performing surface finishing;
seventhly, laser shot peening reinforcement: calling a laser shot peening process in the strengthening expert system, determining process parameters such as a constraint layer, an absorption layer and laser frequency, and performing laser shot peening strengthening on the surface of the repair layer;
and step eight, surface protection.
The system in the first step is formed based on long-term laser additive repair and laser shot peening practical production experience data and combined with the process characteristics of an in-situ repair system.
And in the third step, the crack damage area on the surface is identified by coloring and displaying the crack damage characteristic.
And step five, monitoring the state of a molten pool and the size recovery state in the repair process and immediately adjusting the repair process.
And the surface protection in the step eight is brushing a surface protection layer and a paint layer.
The invention has the beneficial effects that: according to the invention, the crack damage identification processing system, the laser additive repair system and the laser shot peening system are integrated on the mobile platform, so that accurate removal, additive repair and post-treatment strengthening processes of a crack damage region can be realized simultaneously, the service performance requirement after repair is ensured, related technologies can be implemented in situ, and series problems about in-situ high-performance repair of the landing gear beam joint are overcome.
Drawings
The invention is further illustrated by the following examples in conjunction with the drawings.
FIG. 1 is a schematic structural diagram of a crack damage identification processing procedure of the present invention;
FIG. 2 is a schematic flow diagram of an in situ repair and enhancement procedure of the present invention;
figure 3 is a schematic view of the structure of the region of the landing gear beam joint where crack damage occurs according to the present invention.
Detailed Description
The present invention will be further described in order to make the technical means, the creation characteristics, the achievement purposes and the effects of the present invention easy to understand.
As shown in fig. 1 to 3, an in-situ repairing and reinforcing method for cracks of a main landing gear beam joint of an aircraft comprises the following specific steps:
step one, forming a laser high-energy beam in-situ repair and reinforcement expert system: forming a set of high-energy laser beam in-situ repair and reinforcement expert system, and integrating the expert system on a control computer;
step two, undercarriage beam joint surface pretreatment: the method mainly comprises the steps of removing paint and a surface protective layer;
step three, accurately identifying and processing a crack damage area: identifying a crack damage area on the surface, determining a polishing range, monitoring the change of the damage area in real time by an image identification processing system during polishing, feeding back and controlling a polishing unit in time, and determining that the crack damage area is completely removed;
Step four, generating a crack damage repair area model: scanning the polished landing gear beam joint by a system 3D scanning module, and comparing the polished landing gear beam joint with a standard part in the system to generate a crack damage repair area model;
step five, laser additive repair: introducing the crack damage repair area model generated in the step four, calling the matched repair material and process in the expert system to carry out laser material increase repair, adjusting the repair process according to actual needs, and ensuring the performance and size recovery of the repair layer;
step six, repairing the surface finish of the layer: calling a system polishing control unit, matching a proper polishing head based on the surface state of the repair layer, and performing surface finishing;
seventhly, laser shot peening reinforcement: calling a laser shot peening process in the strengthening expert system, determining technological parameters of a constraint layer, an absorption layer and a laser frequency class, and carrying out laser shot peening strengthening on the surface of the repair layer;
and step eight, surface protection.
According to the invention, the crack damage identification processing system, the laser additive repair system and the laser shot peening system are integrated on the mobile platform, so that accurate removal, additive repair and post-treatment strengthening processes of a crack damage region can be realized simultaneously, the service performance requirement after repair is ensured, related technologies can be implemented in situ, and series problems about in-situ high-performance repair of the landing gear beam joint are overcome.
The system in the first step is formed based on long-term laser additive repair and laser shot peening practical production experience data and combined with the process characteristics of an in-situ repair system.
As shown in fig. 3, the starting position of the landing gear beam joint after the 3D scanning module scans and polishes is marked at positions a and B, and the crack damage occurrence region is marked at position C.
The invention adopts an integrated mode of in-situ repair and enhancement system, comprising: the system comprises a mobile platform, a crack damage identification and processing system, a laser additive repair system, a laser shot peening system and a mechanical arm of a control system of the laser shot peening system.
And in the third step, the crack damage area on the surface is identified by coloring and displaying the crack damage characteristic.
And step five, monitoring the state of a molten pool and the size recovery state in the repair process and immediately adjusting the repair process.
And the surface protection in the step eight is brushing a surface protection layer and a paint layer.
The landing gear beam joint in-situ repair and enhancement process, comprising: the method comprises a crack damage area identification processing technology, a laser material increase repairing technology, a laser shot peening strengthening technology, and a matching mode and a sequence among the technologies in the technology implementation process.
The foregoing shows and describes the general principles, principal 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 (8)
1. An in-situ repairing and reinforcing method for cracks of a main landing gear beam joint of an airplane is characterized by comprising the following steps: the method comprises the following specific steps:
step one, forming a laser high-energy beam in-situ repair and reinforcement expert system: forming a set of high-energy laser beam in-situ repair and reinforcement expert system, and integrating the expert system on a control computer;
step two, undercarriage beam joint surface pretreatment: the method mainly comprises the steps of removing paint and a surface protective layer;
step three, accurately identifying and processing a crack damage area: identifying a crack damage area on the surface and determining a polishing range;
generating a crack damage repair area model;
Step five, laser additive repair: introducing the crack damage repair area model generated in the step four, calling the matched repair material and process in the expert system to carry out laser material increase repair, adjusting the repair process according to actual needs, and ensuring the performance and size recovery of the repair layer;
sixthly, finishing the surface of the repair layer;
seventhly, laser shot peening: calling a laser shot peening process in the strengthening expert system, determining technological parameters of a constraint layer, an absorption layer and a laser frequency class, and carrying out laser shot peening strengthening on the surface of the repair layer;
and step eight, surface protection.
2. The method of in situ repair and reinforcement of cracks in an aircraft main landing gear beam joint of claim 1, wherein: the system in the first step is formed based on long-term laser additive repair and laser shot peening practical production experience data and combined with the process characteristics of an in-situ repair system.
3. The method of in situ repair and reinforcement of cracks in an aircraft main landing gear beam joint of claim 1, wherein: and in the third step, the image recognition processing system monitors the change of the damaged area in real time while polishing, and feeds back and controls the polishing unit in time to determine that the crack damaged area is completely removed.
4. The method of in situ repair and reinforcement of aircraft main landing gear beam joint cracks as claimed in claim 3, wherein: and in the third step, the crack damage area on the surface is identified by coloring and displaying the crack damage characteristic.
5. The method of in situ repair and reinforcement of aircraft main landing gear beam joint cracks as claimed in claim 1, wherein: in the fourth step, the 3D scanning module of the system is used for scanning the polished landing gear beam joint, and the polished landing gear beam joint is compared with a standard part in the system to generate a crack damage repair area model.
6. The method of in situ repair and reinforcement of aircraft main landing gear beam joint cracks as claimed in claim 1, wherein: and step five, monitoring the state of a molten pool and the size recovery state in the repair process and immediately adjusting the repair process.
7. The method of in situ repair and reinforcement of aircraft main landing gear beam joint cracks as claimed in claim 1, wherein: in the sixth step, the method specifically comprises the following steps: and calling a system polishing control unit, matching a proper polishing head based on the surface state of the repair layer, and performing surface finishing.
8. The method of in situ repair and reinforcement of cracks in an aircraft main landing gear beam joint of claim 1, wherein: and the surface protection in the step eight is brushing a surface protection layer and a paint layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210208572.3A CN114671045A (en) | 2022-03-03 | 2022-03-03 | In-situ repairing and reinforcing method for cracks of main landing gear beam joint of airplane |
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| CN202210208572.3A CN114671045A (en) | 2022-03-03 | 2022-03-03 | In-situ repairing and reinforcing method for cracks of main landing gear beam joint of airplane |
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| CN114671045A true CN114671045A (en) | 2022-06-28 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115070061A (en) * | 2022-07-20 | 2022-09-20 | 西安空天机电智能制造有限公司 | Laser repairing method for undercarriage cracks |
| CN115142702A (en) * | 2022-07-18 | 2022-10-04 | 华南理工大学 | Method for repairing earthquake damage beam-column bolted joint based on laser material increase technology |
-
2022
- 2022-03-03 CN CN202210208572.3A patent/CN114671045A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115142702A (en) * | 2022-07-18 | 2022-10-04 | 华南理工大学 | Method for repairing earthquake damage beam-column bolted joint based on laser material increase technology |
| CN115142702B (en) * | 2022-07-18 | 2023-07-18 | 华南理工大学 | Method for repairing shock damage Liang Zhushuan welded node based on laser material-increasing technology |
| CN115070061A (en) * | 2022-07-20 | 2022-09-20 | 西安空天机电智能制造有限公司 | Laser repairing method for undercarriage cracks |
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