Preparation method for coating material for strengthening and repairing airplane 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: 2015-09-23
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 compon

Method used

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  • Preparation method for coating material for strengthening and repairing airplane landing gear
  • Preparation method for coating material for strengthening and repairing airplane landing gear
  • Preparation method for coating material for strengthening and repairing airplane landing gear

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0013] Including the following steps:

[0014] (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;

[0015] (2) Dry the powder in a drying oven for 2.5 hours at a drying temperature of 100 degrees Celsius;

[0016] (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;

[0017] (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

[0026] Including the following steps:

[0027] (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;

[0028] (2) Dry the powder in a drying oven for 3 hours at a drying temperature of 110 degrees Celsius;

[0029] (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;

[0030] (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

[0039] (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;

[0040] (2) Dry the powder in a drying oven for 3.5 hours at a drying temperature of 120 degrees Celsius;

[0041] (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;

[0042](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 45°, the powder beam and th...

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Abstract

The invention belongs to the field of surface coating, and particularly relates to a preparation method for a coating material for strengthening and repairing an airplane landing gear. The coating material comprises, by weight, 0.65-1.45% of C, 5.24-6.93% of Co, 8.72-10.27% of Cr, 4.02-5.53% of Ni, 4.11-5.64% of Mo, 4.31-5.74% of W, 0.79-0.99% of Mn, 0.95-1.15% of Nb, 0.91-1.11% of V, 1.25-1.45% of Ti and 59.74-69.05% of Fe. The preparation method comprises the following steps that the alloy coating with the thickness being 0.3-0.6 mm is obtained in an area to be repaired under the protection of argon, the laser power is 5000-6000 W, the scanning rate is 750-950 mm/min, the overlapping rate is 20-30%, the powder feeding rate is 35-45 g/min, the included angle between the powder beam and the laser beam is 45-55 degrees, and the spot diameter is 3-6 mm. The coating material is formed on the surface of a base material, has the certain thickness, does not have the defects of air holes or cracks or the other, and is good in metallurgical quality, and resistant to abrasion and corrosion.

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