Special tool design for in-situ repair of plane of aircraft floor

Abstract

The invention discloses a special tool design for in-situ repair of an aircraft floor plane, and belongs to the technical field of aviation maintenance engineering. Through an integrated electrode system and closed solution circulation design, the in-situ rapid repairing possibility of the plane of the aircraft floor is achieved, the repairing process period is greatly shortened, the efficiency is improved, by means of simulation and tool design, the bad problems that the aircraft floor cannot be repaired after being damaged, the film thickness of an oxidation layer is uneven, and the performance is poor are solved, and the service life of the aircraft floor is prolonged. And the product quality is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation maintenance engineering, and in particular relates to a special tool design for in-situ repair of aircraft floor planes. Background Art

[0002] As a key load-bearing component in the aircraft structure, aircraft floors are subject to long-term human movement, cargo loads, and environmental erosion. Their surfaces usually need to be oxidized to form a high-hardness, high-wear-resistant oxide film to extend their service life.

[0003] However, in actual operation, aircraft floors are prone to damage such as scratches, corrosion, and cracks, seriously affecting flight safety. The repair technologies currently used in the industry have many drawbacks: While the traditional method of applying an oxidant locally is simple to operate, the bond strength between the repaired oxide layer and the substrate is insufficient, the film thickness uniformity is difficult to control, and it is prone to peeling under alternating loads. There is also a significant performance difference between the repaired area and the original oxide layer, making it unable to meet the high standards of aircraft maintenance. While disassembly and resurfacing can ensure repair quality, it requires the entire floor to be disassembled and sent to a specialized workshop for processing. This not only results in a maintenance cycle of several weeks, but also incurs high labor and transportation costs. Frequent disassembly can also cause secondary damage to the aircraft structure, seriously affecting the aircraft's availability.

[0004] More seriously, existing repair processes generally lack effective solution recovery systems, resulting in spillage of oxidizing fluid and contamination of other parts of the aircraft. This poses a safety hazard and does not meet the environmental requirements of modern aviation maintenance. These technical shortcomings severely restrict the efficiency and reliability of aircraft floor repairs, necessitating the development of a new solution that can achieve in-situ repair while ensuring quality. Summary of the Invention

[0005] The purpose of the present invention is to overcome the defects of the prior art and provide a special tool design for in-situ repair of aircraft floor planes.

[0006] The purpose of the present invention can be achieved by the following technical solution: a special tool design for in-situ repair of aircraft floor plane, comprising the following steps:

[0007] S1. Connect the workpiece, power supply and liquid storage tank device, and ensure that the electrode wires are conductive and the pipe connections are sealed;

[0008] S2. Set process parameters according to the area to be repaired and the degree of damage;

[0009] S3, set the peristaltic pump speed;

[0010] S4. Turn on the power switch. After power is turned on, the peristaltic pump starts working, so that the repair solution is evenly covered on the work surface from the liquid storage tank through the liquid inlet; an oxidation reaction occurs between the electrode and the workpiece, forming an oxide film on the workpiece surface. By observing whether there is gas generated in the pipeline, it is confirmed that the reaction is proceeding normally;

[0011] S5. The reaction ends, the power is automatically cut off, and the repair is completed.

[0012] As a further technical solution, the area of ​​the repaired area in step S2 is less than 10cm 2 , the voltage range is 15-25V; the area of ​​the repair area is 10cm 2 -100cm 2 , voltage range is 25V-40V; the area of ​​the repair area is greater than 100cm 2 , the voltage range is 40V-50V.

[0013] As a further technical solution, when the damage degree in step S2 is superficial damage, the current density is 1A / dm 2 -2A / dm 2 When the damage degree is moderate, the current density is 2A / dm 2 -3A / dm 2 When the damage degree is deep damage, the current density is 3A / dm 2 -5A / dm 2 .

[0014] As a further technical solution, the rotation speed of the peristaltic pump in step S3 is 30 ml / min-50 ml / min.

[0015] As a further technical solution, the power-on time in step S4 is 10-60 minutes.

[0016] As a further technical solution, the thickness of the oxide film in step S4 is 10 μm-25 μm.

[0017] Beneficial effects of the present invention:

[0018] 1. The integrated tooling design integrates the electrode system and the tank liquid circulation system on the tooling body to ensure uniform electric field intensity, consistent solution concentration and temperature on the repair working surface.

[0019] 2. Optimization of the tool body: The tool body is made of Teflon, which is resistant to acid and alkali, high and low temperatures, and can be applied to most repair scenarios.

[0020] 3. Electrode system optimization: The electrode system adopts a non-tight-fit structure. According to actual site needs, titanium alloy, graphite, and stainless steel electrodes can be switched at will. During operation, the electrodes are always facing the repair work surface, ensuring consistent electric field strength during the repair process.

[0021] 4. Optimization of the tank liquid circulation system: The present invention has specially designed a closed tank liquid circulation and recovery system. Compared with the traditional open tank liquid system, it has the characteristics of safety, environmental protection, high efficiency and low cost. The tank liquid inlet and outlet are integrated on the tooling body, and a peristaltic pump is used for quantitative and precise delivery and recovery. The tank liquid inlet passes through the liquid inlet channel of the tooling body, and then through the electrode center channel to reach the repair working surface. The tank liquid is evenly dispersed on the working surface for reaction; the tank liquid outlet is evenly distributed around the tooling body, and the reacted tank liquid is recovered to the liquid storage tank through the return liquid channel; by adjusting the speed of the peristaltic pump, the ion concentration and temperature of the working interface can be relatively stable. All interfaces are connected with Teflon-coated hoses to ensure that the tank liquid circulation is always circulating in the tube.

[0022] 5. Optimization of the negative pressure recovery system: A fluororubber seal is installed around the tooling body, ensuring good contact with the workpiece surface. The recovery peristaltic pump operates at a higher speed than the imported peristaltic pump, ensuring a negative pressure environment within the work area, allowing the reaction solution to be promptly pumped away. The entire operation is free of liquid leakage.

[0023] In summary, the present invention, through its integrated electrode system and closed solution circulation design, enables rapid in-situ repair of aircraft floor surfaces, significantly shortening the repair process cycle and improving efficiency. By leveraging simulation and tooling design, it addresses issues such as the inability to repair damaged aircraft floors, uneven oxide film thickness, and poor performance, thereby improving product quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The present invention will be further described below with reference to the accompanying drawings.

[0025] Figure 1 It is a schematic diagram of the three-dimensional structure of the tooling body of the present invention.

[0026] Figure 2 It is a structural schematic diagram of the electrode system and liquid inlet and outlet of the present invention.

[0027] Figure 3 Schematic diagram of aircraft floor plane repair according to the present invention DETAILED DESCRIPTION

[0028] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0029] Example 1

[0030] S1. According to Figure 3 Connect the workpiece, power supply and liquid storage tank device, and ensure that the electrode wires are conductive and the pipeline connections are sealed properly;

[0031] S2, according to the area of ​​the area to be repaired and the degree of damage (the repair area of ​​the workpiece is 5cm 2 , the damage degree is superficial damage), the process parameters are set as voltage of 15V and current density of 1A / dm 2 ;

[0032] S3. Set the speed of the peristaltic pump to 30 ml / min;

[0033] S4. Turn on the power switch. After power is turned on, the peristaltic pump starts working, so that the repair solution is evenly covered on the work surface from the liquid storage tank through the liquid inlet; an oxidation reaction occurs between the electrode and the workpiece, forming a 10μm thick oxide film on the workpiece surface. By observing whether there is gas generated in the pipeline, it is confirmed that the reaction is proceeding normally;

[0034] S5. After 10 minutes of power on, the reaction ends, the power is automatically cut off, and the repair is completed.

[0035] Example 2

[0036] S1. According to Figure 3 Connect the workpiece, power supply and liquid storage tank device, and ensure that the electrode wires are conductive and the pipeline connections are sealed properly;

[0037] S2, according to the area of ​​the area to be repaired and the degree of damage (the repair area of ​​the workpiece is 50cm 2 , the damage degree is moderate damage), the process parameters are set as voltage 30V, current density 3A / dm 2 ;

[0038] S3. Set the speed of the peristaltic pump to 40 ml / min;

[0039] S4. Turn on the power switch. After power is turned on, the peristaltic pump starts working, so that the repair solution is evenly covered from the liquid storage tank to the work surface through the liquid inlet; an oxidation reaction occurs between the electrode and the workpiece, forming a 12μm thick oxide film on the workpiece surface. By observing whether there is gas generated in the pipeline, it is confirmed that the reaction is proceeding normally;

[0040] S5. After 20 minutes of power-on, the reaction ends, the power is automatically cut off, and the repair is completed.

[0041] Example 3

[0042] S1. According to Figure 3 Connect the workpiece, power supply and liquid storage tank device, and ensure that the electrode wires are conductive and the pipeline connections are sealed properly;

[0043] S2, according to the area of ​​the area to be repaired and the degree of damage (the repair area of ​​the workpiece is 110cm 2 , the damage degree is deep damage), the process parameters are set as voltage of 45V and current density of 5A / dm 2 ;

[0044] S3, set the speed of the peristaltic pump to 50ml / min;

[0045] S4. Turn on the power switch. After power is turned on, the peristaltic pump starts working, so that the repair solution is evenly covered from the liquid storage tank to the work surface through the liquid inlet; an oxidation reaction occurs between the electrode and the workpiece, forming a 25μm thick oxide film on the workpiece surface. By observing whether there is gas generated in the pipeline, it is confirmed that the reaction is proceeding normally;

[0046] S5. After 60 minutes of power on, the reaction ends, the power is automatically cut off, and the repair is completed.

[0047] Comparative Example 1

[0048] Repair workpieces using traditional hand-brushed oxidizing agents.

[0049] Comparative Example 2

[0050] Use disassembly workshop anodizing to repair workpieces.

[0051] The performance of Example 2 and Comparative Examples 1 and 2 were tested, and the results are shown in Table 1:

[0052] Table 1

[0053]

[0054] As can be seen from the above table, the present invention greatly shortens the repair process cycle, improves efficiency, and has good oxide layer film performance. Therefore, the present invention has important application value in the field of aviation maintenance engineering technology.

[0055] Throughout the specification, references to terms such as "one embodiment," "example," or "specific example" indicate that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0056] The above contents are merely examples and explanations of the present invention. Those skilled in the art may make various modifications or additions to the described specific embodiments or replace them in similar ways. As long as they do not deviate from the invention or exceed the scope defined by the claims, they should all fall within the scope of protection of the present invention.

Claims

1. A special tool design for in-situ repair of aircraft floor planes, characterized by: The following steps are involved: S1. Connect the workpiece, power supply and liquid storage tank device, and ensure that the electrode wires are conductive and the pipe connections are sealed; S2. Set process parameters according to the area to be repaired and the degree of damage; S3, set the peristaltic pump speed; S4. Turn on the power switch. After power is turned on, the peristaltic pump starts working, so that the repair solution is evenly covered on the work surface from the liquid storage tank through the liquid inlet; an oxidation reaction occurs between the electrode and the workpiece, forming an oxide film on the workpiece surface; S5. The reaction ends, the power is automatically cut off, and the repair is completed.

2. The design of a special tool for in-situ repair of aircraft floor plane according to claim 1, characterized in that: The area of ​​the repaired area in step S2 is less than 10cm 2 , the voltage range is 15-25V; the area of ​​the repair area is 10cm 2 -100cm 2 , voltage range is 25V-40V; the area of ​​the repair area is greater than 100cm 2 , the voltage range is 40V-50V.

3. The design of a special tool for in-situ repair of aircraft floor plane according to claim 1 is characterized in that: When the damage degree in step S2 is superficial damage, the current density is 1A / dm 2 -2A / dm 2 When the damage degree is moderate, the current density is 2A / dm 2 -3A / dm 2 When the damage degree is deep damage, the current density is 3A / dm 2 -5A / dm 2 .

4. The design of a special tool for in-situ repair of aircraft floor plane according to claim 1, characterized in that: In step S3, the peristaltic pump speed is 30 ml / min-50 ml / min.

5. The design of a special tool for in-situ repair of aircraft floor plane according to claim 1 is characterized in that: The power-on time in step S4 is 10-60 minutes.

6. The design of a special tool for in-situ repair of aircraft floor plane according to claim 1, characterized in that: The thickness of the oxide film in step S4 is 10 μm-25 μm.

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