CN110453213A - A kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure - Google Patents
A kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure Download PDFInfo
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- CN110453213A CN110453213A CN201910722197.2A CN201910722197A CN110453213A CN 110453213 A CN110453213 A CN 110453213A CN 201910722197 A CN201910722197 A CN 201910722197A CN 110453213 A CN110453213 A CN 110453213A
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- piston rod
- crackle
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- aircraft
- melting coating
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
Abstract
The present invention relates to a kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedures, the following steps are included: determining laser repairing process parameter step 1: testing by the stretching, impact and fatigue behaviour of simulation piston rod, while determining that the groove type of laser melting coating reparation is V-type；Step 2: choosing simulating piece before reparation, simulating piece fatigue test is carried out, evaluation test is as a result, determine final laser cladding repair technique；Step 3: carrying out laser repairing to piston rod crackle；Step 4: being detected to piston rod restoring area, it is desirable that flawless and incomplete fusion defect after the completion of repairing；Step 5: processing restoring area, resizing meet drawing or matching requirements.The present invention carries out fatigue test to piston rod simulating piece, determines final renovation technique, guarantees that piston rod is not in crackle in long-time use process, uses requirement safely to ensure aircraft in lifetime.
Description
Technical field
The present invention relates to piston rods to repair field, specifically a kind of aircraft 300M steel undercarriage piston rod lip crackle
Laser melting coating restorative procedure.
Background technique
It is easy to produce fatigue crack in constitutional details such as undercarriage outer cylinder, piston rod, body part, connector and axis,
Traditional argon arc welding heat affecting is big, and easily-deformable, residual stress is big, and reparation reliability is low, is unable to satisfy repairing and requires.With aircraft
Active time extends undercarriage part for a long time by shock loading, and under corrosive environment, and fatigue damage probability is increasingly
Greatly, especially undercarriage piston rod value is high, and single-piece, which is scrapped, will lead to a full set of landing gear and scrap, and economic loss is very big.
Carry out damage and remanufacture reparation, and assessment characterization is carried out to its fatigue behaviour, to ensure to repair feasibility and reliability, can solve
It produces spare part problem, save a large amount of repair costs, while guaranteeing that safe handling requires in the Aircraft life phase.
Poor mechanical property is repaired for traditional argon arc welding, the low problem of reliability utilizes laser melting and coating technique dimensional accuracy
The features such as height, heat affected area is small, workpiece deflection is very small, even tissue, stable mechanical property, proposes a kind of undercarriage piston
The laser cladding repair technique method of bar crackle.
As application number CN201710785371.9 unimach rises and falls the electromagnetic agitation laser melting coating reparation side of frame member
Method, comprising the following steps: (1) prepare laser melting coating repair materials, (2) repair front surface cleaning, (3) electromagnetic agitation auxiliary laser
Cladding reparation, (4) machining, (5) non-destructive testing, (6) stress relief annealing are completed to repair, and the patent is before reparation not to rising and falling
Frame carries out simulated performance test, is unable to ensure the reliability of the technique.
Summary of the invention
Now in order to solve the above-mentioned technical problem, the invention proposes a kind of aircraft 300M steel undercarriage piston rod lip crackles
Laser melting coating restorative procedure.The technical problems to be solved by the invention are realized using following technical scheme:
A kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure, comprising the following steps:
Laser repairing process parameter is determined step 1: testing by the stretching, impact and fatigue behaviour of simulation piston rod, together
When determine laser melting coating reparation groove type be V-type；
Step 2: choosing simulating piece before reparation, simulating piece fatigue test is carried out, evaluation test is as a result, determine final sharp
Light cladding repair technique；
Step 3: carrying out laser repairing to piston rod crackle；
Step 4: being detected to piston rod restoring area, it is desirable that flawless and incomplete fusion defect after the completion of repairing；
Step 5: processing restoring area, resizing meet drawing or matching requirements.
Steps are as follows for the simulating piece fatigue test:
Step 1: simulating piece is fixed on testing stand fixture, and apply the vertically concentrated force with simulating piece axis；
Step 2: first 100 times are tested the zone of action that crackle is in loading spectrum concentrated force；
Step 3: simulating piece is rotated by 90 ° and is applying concentrated force by rear 100 tests；
Step 4: collecting test data, evaluation test result.
Laser repairing process parameter experiment in the first step the following steps are included:
Step 1: carrying out the processing and test of room temperature tensile sample according to HB 5143-96；
Step 2: carrying out the processing and test of room temperature impact sample according to HB 5144-96；
Step 3: carrying out the processing and test of fatigue behaviour sample according to HB 5287-96；
Step 4: collecting test data, evaluation test result determines laser repairing process parameter.
The laser repairing process parameter is as follows:
Power: 400W~600W；
Speed: 500mm/min~700mm/min；
Powder feeding revolving speed: 3.5r/min~25.0rpm；
Pipette tips protect gas: 15L/min；
Carry powder gas: 5L/min.
The simulating piece needs to be heat-treated completely before bevel and shot peening strengthening.
The processing needs to carry out stress relief annealing to piston rod before repairing.
The beneficial effects of the present invention are: laser melting and coating technique is applied to undercarriage piston rod lip crackle by the present invention
It repairs, safe handling in the Aircraft life phase is met after reparation and is required, aircraft key part crack fault is able to solve, has very high
Economic benefit；The present invention carries out fatigue test to piston rod simulating piece, determines final renovation technique, guarantees piston rod in length
Be not in crackle in time use process, use requirement safely to ensure aircraft in lifetime.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples.
Fig. 1 is workflow schematic diagram of the present invention.
Specific embodiment
In order to make those skilled in the art better understand technical solution of the present invention, below in conjunction in embodiment
Attached drawing, the present invention is become apparent from, it is more complete illustrate, certain described embodiment be a part of the invention rather than
All, it is based on the present embodiment, those skilled in the art are obtained other real without any creative labor
Example is applied, is within the scope of the invention.
As shown in Figure 1, a kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure, including it is following
Step:
Laser repairing process parameter is determined step 1: testing by the stretching, impact and fatigue behaviour of simulation piston rod, together
When determine laser melting coating reparation groove type be V-type；；Before determining laser repairing process parameter, using visual and lossless inspection
Survey method carries out inspection and statistic of classification to the size of crack position, distribution and the form of expression；
Step 2: choosing simulating piece before reparation, simulating piece fatigue test is carried out, evaluation test is as a result, determine final sharp
Light cladding repair technique；
Step 3: carrying out laser repairing to piston rod crackle；It is molten as laser using 6KW optical-fiber laser Three-dimension process system
Prosthetic appliance and XF-G01 metal powder are covered as laser cladding of material；
Step 4: being detected to piston rod restoring area, it is desirable that flawless and incomplete fusion defect after the completion of repairing；Benefit
Laser repairing region is detected with fluorescence and X-ray detection technology, while repairing area and upper axis using vernier caliper measurement
Lip flange inner diameter size at cooperation is covered, measurement data is recorded；
Step 5: processing restoring area, resizing meet drawing or matching requirements；It is repaired using lathe or by hand throwing
Manufacturing process processes restoring area.
Before piston rod simulating piece fatigue test, bevel is carried out to simulating piece, carries out laser melting coating, it is then molten to laser
Simulating piece after covering is machined, and simulating piece is made to restore drawing size.
Steps are as follows for the simulating piece fatigue test:
Step 1: simulating piece is fixed on testing stand fixture, and apply the vertically concentrated force with simulating piece axis；
Step 2: first 100 times are tested the zone of action that crackle is in loading spectrum concentrated force；
Step 3: simulating piece is rotated by 90 ° and is applying concentrated force by rear 100 tests；
Step 4: collecting test data, evaluation test result.
Laser repairing process parameter experiment in the first step the following steps are included:
Step 1: carrying out the processing and test of room temperature tensile sample according to HB 5143-96；
Step 2: carrying out the processing and test of room temperature impact sample according to HB 5144-96；
Step 3: carrying out the processing and test of fatigue behaviour sample according to HB 5287-96；
Step 4: collecting test data, evaluation test result determines laser repairing process parameter.
The laser repairing process parameter is as follows:
Power: 400W~600W；
Speed: 500mm/min~700mm/min；
Powder feeding revolving speed: 3.5r/min~25.0rpm；
Pipette tips protect gas: 15L/min；
Carry powder gas: 5L/min；It is verified by room temperature tensile, room temperature impact and fatigue test, shows that room temperature impact is tough mild-natured
Equal 81.2J/cm2, it has been more than the 56.3J/cm of base material2；Room temperature tensile intensity is averaged 1601MPa, is 81.7% (base material of base material
Tensile strength is 1960MPa), 300M steel laser weld joint fatigue life is about the 61% of base material, the above test data surface
Meet safe handling in the Aircraft life phase after 300M steel undercarriage piston rod crackle laser melting coating reparation to require.
The simulating piece needs to be heat-treated completely before bevel and shot peening strengthening.
The processing needs to carry out stress relief annealing to piston rod before repairing；Heat while selecting by ceramic heat band
Temperature controller observing and controlling temperature.
The basic principles, main features and advantages of the present invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and what is described in the above embodiment and the description is only the present invention
Principle, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these variation and
Improvement is both fallen in claimed invention.The claimed scope of the invention is by appended claims and its equivalent circle
It is fixed.
Claims (6)
1. a kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure, it is characterised in that: including following
Step:
Laser repairing process parameter is determined step 1: testing by the stretching, impact and fatigue behaviour of simulation piston rod, while really
The groove type for determining laser melting coating reparation is V-type；
Step 2: choosing simulating piece before reparation, simulating piece fatigue test is carried out, evaluation test is as a result, determine that final laser is molten
Cover renovation technique；
Step 3: carrying out laser repairing to piston rod crackle；
Step 4: being detected to piston rod restoring area, it is desirable that flawless and incomplete fusion defect after the completion of repairing；
Step 5: processing restoring area, resizing meet drawing or matching requirements.
2. a kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure according to claim 1:
It is characterized by: steps are as follows for the simulating piece fatigue test:
Step 1: simulating piece is fixed on testing stand fixture, and apply the vertically concentrated force with simulating piece axis；
Step 2: first 100 times are tested the zone of action that crackle is in loading spectrum concentrated force；
Step 3: simulating piece is rotated by 90 ° and is applying concentrated force by rear 100 tests；
Step 4: collecting test data, evaluation test result.
3. a kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure according to claim 1:
It is characterized by: in the first step laser repairing process parameter experiment the following steps are included:
Step 1: carrying out the processing and test of room temperature tensile sample according to HB 5143-96；
Step 2: carrying out the processing and test of room temperature impact sample according to HB 5144-96；
Step 3: carrying out the processing and test of fatigue behaviour sample according to HB 5287-96；
Step 4: collecting test data, evaluation test result determines laser repairing process parameter.
4. a kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure according to claim 1:
It is characterized by: the laser repairing process parameter is as follows:
Power: 400W~600W；
Speed: 500mm/min~700mm/min；
Powder feeding revolving speed: 3.5r/min~25.0rpm；
Pipette tips protect gas: 15L/min；
Carry powder gas: 5L/min.
5. a kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure according to claim 1:
It is characterized by: the simulating piece needs to be heat-treated completely before bevel and shot peening strengthening.
6. a kind of aircraft 300M steel undercarriage piston rod lip crackle laser melting coating restorative procedure according to claim 1:
It is characterized by: the processing needs to carry out stress relief annealing to piston rod before repairing.
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Cited By (6)
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| CN110926975A (en) * | 2019-12-09 | 2020-03-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Detection method for three-dimensional additive repair quality |
| CN111992977A (en) * | 2020-07-17 | 2020-11-27 | 国营芜湖机械厂 | Preventive repair research method for stress corrosion damage of main bearing structure of airplane |
| CN112461648A (en) * | 2020-10-06 | 2021-03-09 | 湖北超卓航空科技股份有限公司 | Testing device for fatigue performance detection of sample piece |
| CN113245551A (en) * | 2021-06-10 | 2021-08-13 | 北京煜鼎增材制造研究院有限公司 | Laser additive repair method for 300M steel aircraft landing gear |
| CN113500351A (en) * | 2021-05-27 | 2021-10-15 | 沈阳北方飞机维修有限公司 | Maintenance method for corrosion cracks on main wheel of airplane |
| CN115386873A (en) * | 2022-09-06 | 2022-11-25 | 北京航星机器制造有限公司 | Defect repairing method for TA15 titanium alloy part formed by selective laser melting |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110926975A (en) * | 2019-12-09 | 2020-03-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Detection method for three-dimensional additive repair quality |
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| CN111992977A (en) * | 2020-07-17 | 2020-11-27 | 国营芜湖机械厂 | Preventive repair research method for stress corrosion damage of main bearing structure of airplane |
| CN111992977B (en) * | 2020-07-17 | 2022-05-24 | 国营芜湖机械厂 | Preventive repair research method for stress corrosion damage of main bearing structure of airplane |
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| CN113500351A (en) * | 2021-05-27 | 2021-10-15 | 沈阳北方飞机维修有限公司 | Maintenance method for corrosion cracks on main wheel of airplane |
| CN113245551A (en) * | 2021-06-10 | 2021-08-13 | 北京煜鼎增材制造研究院有限公司 | Laser additive repair method for 300M steel aircraft landing gear |
| CN113245551B (en) * | 2021-06-10 | 2021-10-01 | 北京煜鼎增材制造研究院有限公司 | Laser additive repair method for 300M steel aircraft landing gear |
| CN115386873A (en) * | 2022-09-06 | 2022-11-25 | 北京航星机器制造有限公司 | Defect repairing method for TA15 titanium alloy part formed by selective laser melting |
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