Device for laser-plasma composite deposition of aircraft landing gear coating

Abstract

The utility model relates to a device for laser-plasma composite deposition of an aircraft landing gear coating. According to the device, laser and plasma technologies are combined, so that high-quality coating preparation of the shock strut of the aircraft landing gear is realized. The device mainly comprises a powder feeding system, a plasma control system, a laser control system, a manipulator, a dust removal system, a chuck, a heat insulation sleeve, a sliding baffle and the like. The heat insulation sleeve, the dust removal cover, the sliding baffle and the chuck are made of heat insulation ceramic fibers, heat stress and residual stress can be effectively relieved through the heat insulation sealing experiment environment, crack sensitivity is reduced, and the technological parameter range can be further expanded. The powder material is accurately impacted to the surface of the substrate by accurately controlling the angle and synchronization action of the laser beam and the plasma beam to form metallurgical bonding, improve the bonding strength and density of the coating and optimize the microstructure of the coating, so that the forming quality and wear resistance of the coating are remarkably improved, and the service life of an aircraft landing gear is remarkably prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of the aviation industry, in particular to a device for laser-plasma composite deposition of an aircraft landing gear coating. Background Art

[0002] Among the components of aerospace, the shock absorber strut of an aircraft landing gear is a key component to ensure the safe operation of the aircraft. During the takeoff and landing of the aircraft, it will be impacted by hard particles in the environment, resulting in wear. Therefore, its material is mostly ultra-high-strength steel, which enables it to withstand the huge impact load generated during the takeoff and landing of the aircraft. Although it has advantages such as high strength, good transverse plasticity, and excellent fracture toughness, its wear resistance is still insufficient. Therefore, in order to further improve its wear resistance and self-lubrication performance, extend its service life, and reduce maintenance costs, surface protection is required. The plasma spraying technology has the advantages of a wide range of spraying materials, little heat affected on the substrate, and a wide range of applications, and plays an increasingly important role in modern manufacturing. However, for the coating prepared by the plasma spraying technology, in terms of the bonding between the coating and the metal substrate, it mainly relies on mechanical bonding, and this bonding method is relatively weak, resulting in limited bonding strength. At the same time, since the laser is in the form of rapid heating and rapid cooling during the coating preparation process, there are many pores and fine cracks inside the coating. These factors jointly affect the denseness and wear resistance of the coating, making the actual service life of the coating fail to fully reach the theoretical expectation. Therefore, there is still a large room for improvement in the overall performance of the coating, and a new preparation device is needed to prepare high-performance coatings.

[0003] This technology designs a device for laser-plasma composite deposition of an aircraft landing gear coating. This device can not only reduce the thermal stress and residual stress through the heat insulation device, so as to improve the preparation effect of the aircraft landing gear, but also improve the wear resistance of the coating to extend its service life. Summary of the Utility Model

[0004] The utility model provides a device for laser-plasma composite deposition of an aircraft landing gear coating. It overcomes the problems faced in the coating preparation on the aircraft landing gear, mainly aiming at the cracks and wear resistance of the coating. The purpose is to improve the coating preparation quality, wear resistance, and service life of the shock absorber strut of the aircraft landing gear, while reducing maintenance costs and ensuring the safe operation of the aircraft.

[0005] This device can realize the preparation of high-quality coatings for landing gear products, and it includes a baffle controller, a powder feeding system, a plasma control system, a laser control system, a dust removal system, a manipulator, a laser nozzle, a plasma gun, a dust removal pipeline, a chuck, a heat insulation sleeve, a dust removal cover, a workpiece to be processed, and a sliding baffle.

[0006] The powder feeding system is used to transport the powder material to the laser and plasma processing areas through the protective gas;

[0007] A plasma control system, connected to a plasma gun, for controlling the operating parameters of the plasma gun, including power, powder feeding rate, spraying distance, and carrier gas flow rate;

[0008] A laser control system, connected to a laser nozzle, for controlling the operating parameters of the laser nozzle, including laser power, scanning speed, spot diameter, and argon gas flow rate;

[0009] A manipulator for precisely moving the plasma gun and the laser nozzle to a specified position on the workpiece substrate; ensuring that the laser beam is at 90° - 100° to the part surface, the plasma spraying beam is at 70° - 90° to the part surface, and the plasma beam is coaxial with the powder beam.

[0010] A dust removal system, connected to a dust removal pipeline, and the pipeline is connected to a dust hood for dust removal to prevent dust from polluting the experimental environment;

[0011] A chuck, in direct contact with the workpiece to be processed and the right end of the dust hood, for firmly fixing the workpiece substrate;

[0012] A heat insulation sleeve, with the left side of the cylindrical heat insulation sleeve being an integral structure with the equipment, and the dust hood at the right end of the heat insulation sleeve being also integral. The hollow structure is used to place the landing gear workpiece.

[0013] Connected to a sliding baffle and a baffle controller, the sliding baffle is controlled by the baffle controller and opens and closes with the operation of the laser nozzle and the plasma gun.

[0014] The heat insulation sleeve, dust hood, sliding baffle, and chuck of the present utility model are made of ceramic fiber material. Ceramic fiber is a lightweight, high-temperature resistant, corrosion-resistant, and good thermal stability inorganic fiber material. It has good heat insulation performance and can effectively prevent heat transfer. Since the working environment of the overall landing gear workpiece is carried out in a sealed and heat-insulated environment, after the coating receives high heat input, it cannot dissipate heat in time, reducing the residual stress during the coating preparation process and alleviating the crack sensitivity. At the same time, laser-plasma hybrid deposition is the combined action of a laser beam and a plasma beam, precisely impacting the powder onto the substrate surface, and softening, deforming, or slightly melting the powder and the substrate material at high temperature to form a metallurgical bond. In addition, the laser energy also performs secondary heating on the deposited coating, promoting the tight combination between powder particles and optimizing the coating microstructure. It solves the problem that the coating and the substrate in traditional plasma spraying are mostly mechanically bonded, significantly improving the bonding strength and density of the coating. The processing environment of the present utility model is a sealed environment, and the setting of the dust removal system can handle the spatter generated by powder gasification, further reducing the experimental error. Through this device, a crack-free coating can be effectively prepared. At the same time, adding hard phases and lubricating phases to the powder can further improve the wear resistance, realizing the effective preparation of high-quality and high-performance coatings for aircraft landing gears. Brief Description of the Drawings

[0015] Figure 1 It is a schematic structural diagram of a laser-plasma composite deposition device for aircraft landing gear coatings

[0016] Figure 2 It is a schematic structural diagram of the heat insulation sleeve part of the laser-plasma composite deposition device for aircraft landing gear coatings

[0017] Figure 3 It is the SEM scanning image in Example 1

[0018] Figure 4 It is the hardness distribution diagram in Example 1

[0019] Figure 5 It is the wear rate of the coating in Example 1

[0020] Figure 1 In, there are baffle controller (1), powder feeding system (2), plasma control system (3), laser control system (4), dust removal system (5), manipulator (6), laser nozzle (7), plasma gun (8), dust removal duct (9), chuck (10), heat insulation sleeve (11), dust removal hood (12), workpiece (13) and sliding baffle (14).

[0021] Figure 2 In, there are baffle controller (1), dust removal duct (9), heat insulation sleeve (11), dust removal hood (12), workpiece (13) and sliding baffle (14). Detailed Description of the Preferred Embodiments

[0022] The following will further describe the present invention in detail in conjunction with the embodiments and the drawings, but the embodiments of the present invention are not limited thereto. Attached Figure 1 and attached Figure 2 What is shown is a schematic diagram of a specific embodiment of the present invention. It should be emphasized that this embodiment is only a form of manifestation of the present invention and does not represent all possible embodiments of the present invention.

[0023] The specific technical solutions involved in the present invention have broad flexibility and applicability, and can be appropriately adjusted and optimized according to actual needs to meet the usage requirements in different situations and conditions. The core of the present invention lies in its unique technical concept and innovation points, and these elements are specifically embodied and demonstrated through this embodiment, but should not be limited to the specific form and details of this embodiment.

[0024] The following will combine attached Figure 1 and attached Figure 2 to introduce a specific device provided by the embodiment of the present invention.

[0025] Such asFigure 1 Shown is a schematic structural diagram of a device for laser-plasma composite deposition of an aircraft landing gear coating. The device includes a baffle controller (1), a powder feeding system (2), a plasma control system (3), a laser control system (4), a dust removal system (5), a manipulator (6), a laser nozzle (7), a plasma gun (8), a dust removal duct (9), a chuck (10), a heat insulation sleeve (11), a dust removal hood (12), a workpiece (13), and a sliding baffle (14). Among them Figure 2 Shown is a schematic structural diagram of the heat insulation sleeve part of a laser-plasma composite deposition aircraft landing gear coating device. The device includes a baffle controller (1), a dust removal duct (9), a heat insulation sleeve (11), a dust removal hood (12), a workpiece (13), and a sliding baffle (14).

[0026] The powder feeding system (2), which is designed to accurately transport powder materials to the core area of laser and plasma processing on the workpiece (13) through a shielding gas.

[0027] The plasma control system (3), connected to the plasma gun (8), is responsible for regulating various operating parameters of the plasma gun, such as power, powder supply rate, spraying distance, and shielding gas flow rate.

[0028] The laser control system (4), connected to the laser nozzle (7).

[0029] The manipulator (6), used to precisely position and move the plasma gun (8) and the laser nozzle (7) on the workpiece substrate.

[0030] The dust removal system (5), which removes dust by connecting the dust removal duct (9) and the dust removal hood (12).

[0031] The chuck (10), which is in direct contact with the workpiece (13) to be processed and the right end of the dust removal hood (12).

[0032] The heat insulation sleeve (11), the left side of the cylindrical heat insulation sleeve is an integral structure with the device, and the dust removal hood at the right end of the heat insulation sleeve is also of the same integral structure. The hollow structure is used to place the landing gear workpiece.

[0033] The sliding baffle (14) is connected to the baffle controller (1).

[0034] The heat insulation sleeve (11), the dust removal hood (12), the sliding baffle (14), and the chuck (10) are made of ceramic fiber heat insulation materials.

[0035] Example 1

[0036] The method of the embodiment of the present utility model may include the following contents:

[0037] The shock absorber strut of the aircraft landing gear is made of 300M ultra-high-strength steel. The yield strength of 300M steel can reach 1930 MPa, and the tensile strength can reach 2070 MPa, which enables it to withstand the huge impact load generated during aircraft takeoff and landing. The specific steps are as follows:

[0038] Step 1, before the experiment, the landing gear workpiece is treated by sandblasting to remove surface oil stains and increase roughness. Place the landing gear (13) in the heat insulation sleeve (11). The right end is fitted on the chuck (10), and ensure that it is firmly fixed on the chuck (10).

[0039] Step 2, set up the sliding baffle (14) at the upper end, and control the opening and closing of the sliding baffle with the baffle controller (1) as the laser nozzle (7) and the plasma gun (8) work to achieve the effects of sealing and heat insulation. At the same time, turn on the dust removal system (5), absorb through the dust hood (12), and enter the dust removal pipeline (9) to prevent dust from polluting the experimental environment.

[0040] Step 3, mix the coating powder materials: Ni 45wt%, Cr 20wt%, Mo 2wt%, Si 3wt%, with the balance of Fe as the main body, with MoS2 2wt%, Cr3C2 6wt% and Cr3C2 9wt% respectively, and set them as C1 and C2. Put them into the powder feeding system (2) respectively.

[0041] Step 4, adjust the equipment layout, align the laser beam (7) with the surface of the workpiece (13), and set the angle within the range of 90° to 100°. At the same time, adjust the plasma spraying beam (8) so that it forms an angle of 70° to 90° with the surface of the workpiece (13). Ensure that the plasma beam and the powder beam are coaxial, and the two work together in the common area of the laser beam on the workpiece surface.

[0042] Step 5, process parameter setting: Start the laser control system (4) and the plasma control system (3) equipment, and set the coating process parameters. Plasma spraying equipment parameters: (power 30 kW; powder feeding rate 40 g / min, spraying distance 250 mm, carrier gas flow rate 4.2 L / min; laser parameters: laser power 800 W, scanning speed 480 mm / s, spot diameter 4.2 mm, argon gas flow rate 10 L / min, overlap rate 0.65).

[0043] Step 6, coating deposition: Start the powder feeding system (2) and the plasma control system (3), and start the light output program of the laser (4) after the plasma gun (8) beam becomes stable. Scan 10 layers with a thickness of 200 μm using the set coating parameters.

[0044] Step 7, conduct relevant test data feedback such as SEM on the two specimens after cooling, and characterize the microstructure of the coating. The microstructure pictures are as Figure 3As shown in the figure. For the detection of related mechanical properties such as hardness, the average hardness of the coating prepared from the composite powder of 89 wt.% Ni45 + 2 wt.% MoS2 + 9 wt.% Cr3C2 can reach 599.4 HV 0.5 . The hardness distribution of the coating is as shown in Figure 4 . For the characterization of wear performance, wear performance data are obtained. The wear rate is as shown in Figure 5 .

Claims

1. A device for laser-plasma composite deposition of aircraft landing gear coatings, characterized in that: Powder feeding system (2), plasma control system (3), laser control system (4), dust removal system (5), manipulator (6), laser nozzle (7), plasma gun (8), dust removal duct (9), chuck (10), heat insulation sleeve (11), dust removal hood (12), workpiece (13); The plasma control system (3) is connected to the plasma gun (8); the laser control system (4) is connected to the laser nozzle (7); It further includes a manipulator (6) for controlling the plasma gun (8) and the laser nozzle (7); the dust removal system (5) is connected to the dust removal hood (12) through the dust removal duct (9); The chuck (10) is connected to the workpiece (13); the chuck (10) is in contact with one end of the dust removal hood (12); the heat insulation sleeve (11) is integrated with the dust removal hood at the right end of the heat insulation sleeve.

2. The device for laser-plasma composite deposition of aircraft landing gear coatings according to claim 1, characterized in that: The sliding baffle (14) is connected to the baffle controller (1); the sliding baffle (14) is arranged above the heat insulation sleeve (11).

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