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A preparation method for coating material for strengthening and repairing aircraft landing gear

A technology for aircraft landing gear and coating materials, which is applied in the direction of coating and metal material coating technology, and can solve the problems of corrosion failure of landing gear and its components, and failure of landing gear retraction and deployment.

Active Publication Date: 2017-08-25
BEIJING UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, because the aircraft landing gear is often exposed to the changeable marine corrosion environment and is also affected by various operational factors, it is easy to cause corrosion failure of the landing gear and its components; There will be friction between them, so the wear of the landing gear and its components is also faster, especially at the journal of the outer cylinder of the pillar, its wear often leads to failure of landing gear retraction

Method used

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  • A preparation method for coating material for strengthening and repairing aircraft landing gear
  • A preparation method for coating material for strengthening and repairing aircraft landing gear
  • A preparation method for coating material for strengthening and repairing aircraft landing gear

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0014] Including the following steps:

[0015] (1) The components of the alloy powder are designed according to mass percentage: C: 1.45wt%; Co: 6.93wt%; Cr: 10.27wt%; Ni: 5.53wt%; Mo: 5.64wt%; W: 5.74wt% ; Mn: 0.99wt%, Nb: 1.15wt%; V: 1.11wt%; Ti: 1.45wt%; Fe: 59.74wt%. Weigh the proportioned single-element powder according to the mass percentage of the above components, mix the powder in a ball mill for 1.5 hours, and obtain a uniform powder after mixing;

[0016] (2) Dry the powder in a drying oven for 2.5 hours at a drying temperature of 100 degrees Celsius;

[0017] (3) Clean and wipe the area of ​​the Aermet100 high-strength steel landing gear with a diameter of 200mm to be repaired with acetone to remove oil and impurities on the surface;

[0018] (4) A semiconductor laser is used to prepare an alloy cladding layer on the surface of the Aermet100 material. The laser cladding process parameters are: the conveyed powder beam and the laser beam are at 55°, the powder bea...

Embodiment 2

[0027] Including the following steps:

[0028] (1) The components of the alloy powder are designed according to mass percentage: C: 0.75wt%; Co: 6.53wt%; Cr: 10.05wt%; Ni: 5.25wt%; Mo: 5.34wt%; W: 5.52wt% ; Mn: 0.89wt%, Nb: 1.05wt%; V: 1.01wt%; Ti: 1.35wt%; Fe: 62.26wt%. Weigh the proportioned single element powder according to the mass percentage of the above components, mix the powder in a ball mill for 3 hours, and obtain a uniform powder after mixing;

[0029] (2) Dry the powder in a drying oven for 3 hours at a drying temperature of 110 degrees Celsius;

[0030] (3) Clean and wipe the 300M high-strength steel undercarriage area with a diameter of 170mm to be repaired with acetone to remove oil and impurities on the surface;

[0031] (4) A fiber laser is used to prepare an alloy cladding layer on the surface of the landing gear with a material of 300M. The process parameters of the laser cladding preparation process are: the conveyed powder beam and the laser beam are at...

Embodiment 3

[0040] (1) The components of the alloy powder are designed according to mass percentage: C: 0.65wt%; Co: 5.24wt%; Cr: 8.72wt%; Ni: 4.02wt%; Mo: 4.11wt%; W: 4.31wt% ; Mn: 0.79wt%, Nb: 0.95wt%; V: 0.91wt%; Ti: 1.25wt%; Fe: 69.05wt%. Weigh the proportioned single-element powder according to the mass percentage of the above components, mix the powder in a ball mill for 4.5 hours, and obtain a uniform powder after mixing;

[0041] (2) Dry the powder in a drying oven for 3.5 hours at a drying temperature of 120 degrees Celsius;

[0042] (3) Clean and wipe the area of ​​the AF1410 high-strength steel landing gear with a diameter of 150mm to be repaired with acetone to remove oil and impurities on the surface;

[0043] (4) Using CO 2 The laser prepares the Ni-based alloy cladding layer on the surface of the AF1410 landing gear material. The process parameters of the laser cladding preparation process are: the delivered powder beam and the laser beam are at an angle of 45°, the powder ...

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Abstract

The invention discloses a method for preparing a coating material for strengthening and repairing aircraft landing gear, which belongs to the field of surface coating. The mass percentage of the material is as follows: C: 0.65-1.45wt%; Co: 5.24-6.93wt%; Cr: 8.72-10.27wt%; Ni: 4.02-5.53wt%; Mo: 4.11-5.64wt%; W: 4.31-5.74 wt%; Mn: 0.79-0.99wt%, Nb: 0.95-1.15wt%; V: 0.91-1.11wt%; Ti: 1.25-1.45wt%; Fe: 59.74-69.05wt%. The preparation method includes the following steps: on the area to be repaired, an alloy coating with a thickness of 0.3-0.6mm is prepared, the laser power is 5000-6000W, the scanning rate is 750-950mm / min, the overlapping rate is 20%-30%, and the powder feeding rate is 35- 45g / min, the angle between the powder beam and the laser beam is 45°~55°, the spot diameter is 3‑6mm, and it is carried out under the protection of argon. The invention forms a wear-resistant and corrosion-resistant alloy coating with a certain thickness on the surface of the base material without defects such as pores and cracks, and with good metallurgical quality.

Description

technical field [0001] The invention relates to a method for preparing a coating material, in particular to a method for preparing a wear-resistant and corrosion-resistant coating material on a high-strength steel area of ​​an aircraft landing gear to be repaired. Background technique [0002] Ultra-high-strength steel is widely used in aircraft landing gear because of its unique high strength, high modulus of elasticity, modulus of rigidity and other excellent properties. However, because the aircraft landing gear is often exposed to the changeable marine corrosion environment and is also affected by various operational factors, it is easy to cause corrosion failure of the landing gear and its components; There will be friction between them, so the wear of the landing gear and its components is also faster, especially at the journal of the outer cylinder of the pillar, its wear and tear often leads to the failure of landing gear retraction. Corrosion and wear problems seri...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C24/10C22C38/52
Inventor 杨胶溪张健全王艳芳常万庆
Owner BEIJING UNIV OF TECH