Annular electrode airplane structure coating monitoring sensing probe

Abstract

The invention discloses an annular electrode aircraft structure coating monitoring sensing probe which comprises a hollow metal support, an annular electrode is fixed in a through hole in the metal support, a working area metal base body is fixed in an inner hole of the annular electrode, a cylindrical electrode is fixed in a center hole of the working area metal base body, and an annular electrode is fixed in a center hole of the cylindrical electrode. The outer wall, where the annular electrode is located, of the metal support is coated with an anti-corrosion coating. The probe can monitor the corrosion condition of the surface coating of the metal matrix in the working area between the cylindrical electrode and the annular electrode in all directions.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft structure corrosion degree monitoring, and particularly relates to a monitoring sensing probe for aircraft structure coating with a ring electrode. Background Art

[0002] When an aircraft is used in coastal areas, it will be subjected to extreme marine environments such as high and low temperatures, humidity, salt spray, light, chemical pollution, rain, snow, fog, and seawater sputtering, which can easily cause corrosion of its airframe structure, systems, electronic equipment, and accessories, seriously affecting the structural integrity and functionality of the aircraft. In order to slow down and control corrosion, it is necessary to monitor and repair the corrosion of the aircraft. The corrosion maintenance of traditional aircraft often adopts the method of regular maintenance, mainly formulating the best detection time and corrosion protection and repair according to experience, for the corrosion damage monitoring of aircraft structure coatings and formulating repair methods. Its main drawback is that there will be premature and lagging phenomena in maintenance projects. Premature maintenance will cause huge waste of human, material, and time costs, and at the same time reduce the service life of equipment and facilities, while lagging will lead to further deterioration of the corrosion situation, and untimely maintenance will further reduce the service life, safety, and reliability of the aircraft. Therefore, the corrosion condition-based maintenance strategy is introduced. The successful implementation of this strategy mainly depends on a corrosion real-time online monitoring sensing probe with advanced technology and reliable performance, providing reference for condition-based maintenance, determining the best maintenance time and maintenance plan, and avoiding the drawbacks of premature maintenance and maintenance lag. Summary of the Invention

[0003] Object of the Invention

[0004] Aiming at the problem that the prior art cannot achieve early corrosion monitoring of aircraft structures, the present invention provides a monitoring sensing probe for aircraft structure coating with a ring electrode.

[0005] Technical Solution of the Invention

[0006] A monitoring sensing probe for aircraft structure coating with a ring electrode includes a hollow metal support. A ring electrode is fixed in the through hole on the metal support. A working area metal matrix is fixed in the inner hole of the ring electrode. A cylindrical electrode is fixed in the central hole of the working area metal matrix. An anti-corrosion coating is applied on the outer wall of the metal support where the ring electrode is located.

[0007] Preferably, the material of the metal support is the same as that of the metal base material in the monitoring area.

[0008] Preferably, the material of the working area metal matrix is the same as that of the metal base material in the monitoring area.

[0009] Preferably, the anti-corrosion coating is the same as the surface coating in the monitoring area.

[0010] Preferably, the outer circle of the ring electrode is in clearance fit with the through hole on the metal support.

[0011] Preferably, the metal matrix in the working area is circular, and there is a clearance fit between the inner hole of the annular electrode and the outer circle of the metal matrix in the working area.

[0012] Preferably, there is a clearance fit between the central hole of the metal matrix in the working area and the outer circle of the cylindrical electrode.

[0013] Preferably, the metal support and the annular electrode, the annular electrode and the metal matrix in the working area, and the metal matrix in the working area and the cylindrical electrode are all connected by epoxy resin potting adhesive.

[0014] Preferably, both the annular electrode and the cylindrical electrode are connected to the excitation signal through connecting wires.

[0015] Preferably, one end of the connecting wire is connected to the annular electrode and the cylindrical electrode at one end inside the cavity of the metal support, and the other end of the connecting wire passes through the nozzle on the metal support, and the cavity of the metal support is filled with epoxy resin potting adhesive.

[0016] Advantages of the present invention:

[0017] (1) It can comprehensively monitor the corrosion condition of the surface coating of the metal matrix in the working area between the cylindrical electrode and the annular electrode;

[0018] (2) When the probe monitors, it does not need to be in direct contact with the metal structure and coating of the aircraft body. Instead, it uses the same materials as the metal structure of the body and its surface coating, indirectly reflecting the aging and failure conditions of the body surface coating;

[0019] (3) When the probe monitors, no electrolyte solution is required;

[0020] (4) The cylindrical electrode and the annular electrode of the probe are located at the interface between the coating and the metal body, and can accurately monitor the performance changes at the interface between the coating and the metal body, so as to accurately evaluate the corrosion failure condition of the coating. Description of the Drawings

[0021] Figure 1 is a schematic external view of a monitoring and sensing probe for aircraft structure coatings with an annular electrode according to the present invention.

[0022] Figure 2 is a schematic structural view of a monitoring and sensing probe for aircraft structure coatings with an annular electrode according to the present invention.

[0023] Figure 3 is a test result diagram of a monitoring and sensing probe for aircraft structure coatings with an annular electrode according to the present invention.

[0024] In the figure, 1 is the metal support, 2 is the metal matrix in the working area, 3 is the anti-corrosion coating, 4 is the cylindrical electrode, 5 is the annular electrode, 6 is the epoxy resin potting adhesive, and 7 is the connecting wire. Detailed Embodiments

[0025] The present invention is realized through the following technical solutions.

[0026] A ring electrode aircraft structure coating monitoring sensing probe, comprising a metal support 1, a working area metal matrix 2, an anti-corrosion coating 3, a cylindrical electrode 4, a ring electrode 5, an epoxy resin potting adhesive 6, and a connecting wire 7.

[0027] The metal support 1 of the probe is a hollow structure. The lower part of the metal support 1 has two fixed lugs. The top of the metal support 1 is provided with a through hole. The side of the metal support 1 has a nozzle. In this embodiment, it has a cube cavity with a width of 20 mm, and the diameter of the opening at the top is 16 mm. The material of the metal support 1 is the same as that of the metal base material in the monitoring area.

[0028] The working area metal matrix 2 is arranged in the through hole on the top surface of the metal support 1. A circular plate with a central hole is provided on the working area metal matrix 2. In this embodiment, the diameter of the central hole of the working area metal matrix 2 is 1.5 mm, the diameter of the circular plate is 12 mm, and the material of the working area metal matrix 2 is the same as that of the metal base material in the monitoring area.

[0029] The top surface of the metal support 1 is coated with an anti-corrosion coating 3. The anti-corrosion coating 3 is a commonly used coating in aviation, composed of a primer and a topcoat. The aging degree of its surface coating reflects the corrosion states such as the aging and failure of the aircraft body surface coating.

[0030] The diameter of the cylindrical electrode 4 is 1 mm. The electrode material is copper or platinum, with good electrical conductivity. The cylindrical electrode 4 penetrates into the central hole of the working area metal matrix, and the hole gap between the cylindrical electrode 4 and the working area metal matrix 2 is isolated by the epoxy resin potting adhesive 6.

[0031] The ring electrode 5 is arranged in the through hole at the top of the metal support 1 and is located outside the working area metal matrix 2. In this embodiment, the inner diameter of the ring electrode 5 is 13 mm, the outer diameter is 15 mm. The electrode material is copper or platinum, with good electrical conductivity. The through hole gap between the ring electrode 5 and the working area metal matrix 2 and the gap with the metal support 1 are both isolated by the epoxy resin potting adhesive 6.

[0032] The main functions of the epoxy resin potting adhesive 6 are sealing holes for isolation and fixing wires.

[0033] The connecting wire 7 is used to connect the cylindrical electrode 4 and the ring electrode 5, mainly playing the role of connecting and conducting electricity.

[0034] Using the above-designed probe for coating protection performance verification, a hard film corrosion inhibitor and a polyurethane coating are respectively coated on the surface of the probe. Figure 3Test results of the verification example of the coating monitoring sensing probe for the annular electrode aircraft structure. After 11 months, the monitoring results show that the impedance value of the polyurethane coating has basically not changed and the protection performance is good, while the impedance value of the hard film inhibitor has decreased significantly and the protection performance has deteriorated.

[0035] The scope of protection of the present invention is not limited to the above embodiments. Obviously, those skilled in the art can make various changes and deformations to the present invention without departing from the scope of the present invention. If these changes and deformations fall within the scope of the claims of the present invention and its equivalent technologies, the intention of the present invention also includes these changes and deformations.

Claims

1. A ring electrode aircraft structure coating monitoring sensor probe, characterized in that: The invention comprises a hollow metal support (1), a ring electrode (5) is fixed in a through hole on the metal support (1), a working area metal substrate (2) is fixed in the inner hole of the ring electrode (5), a cylindrical electrode (4) is fixed in the central hole of the working area metal substrate (2), and an outer wall of the metal support 1 where the ring electrode (5) is located is coated with an anti-corrosion coating (3).

2. The ring electrode aircraft structure coating monitoring sensor probe according to claim 1, characterized in that: The material of the metal support (1) is the same as the metal substrate of the monitoring area.

3. The ring electrode aircraft structure coating monitoring sensor probe according to claim 2, characterized in that: The material of the metal substrate (2) in the working area is the same as that of the metal substrate in the monitoring area.

4. The ring electrode aircraft structure coating monitoring sensor probe according to claim 2, characterized in that: The anti-corrosion coating (3) is the same as the surface coating of the monitoring area.

5. The ring electrode aircraft structure coating monitoring sensor probe according to claim 1, characterized in that: The outer circle of the annular electrode (5) is gap-matched with the through hole on the metal support (1).

6. The ring electrode aircraft structure coating monitoring sensor probe according to claim 1, characterized in that: The working area metal substrate (2) is circular, and the inner hole of the annular electrode (5) is gap-matched with the outer circle of the working area metal substrate (2).

7. The ring electrode aircraft structure coating monitoring sensor probe according to claim 1, characterized in that: The central hole of the metal substrate (2) in the working area is gap-matched with the outer circle of the cylindrical electrode (4).

8. The ring electrode aircraft structure coating monitoring sensor probe according to claim 1, characterized in that: The metal support (1) and the annular electrode (5), the annular electrode (5) and the working area metal matrix (2), and the working area metal matrix (2) and the cylindrical electrode (4) are all connected via epoxy resin potting glue (6).

9. The ring electrode aircraft structure coating monitoring sensor probe according to claim 1, characterized in that: The annular electrode (5) and the cylindrical electrode (4) are both connected to the excitation signal via a connecting wire (7).

10. The ring electrode aircraft structure coating monitoring sensor probe according to claim 9, characterized in that: One end of the connecting wire (7) connects the annular electrode (5) and the cylindrical electrode (4) located at one end of the inner cavity of the metal support (1), and the other end of the connecting wire (7) passes through the nozzle on the metal support (1), and the inner cavity of the metal support (1) is filled with epoxy resin potting glue (6).

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