Aircraft sealing end face insulation resistance test tool

Abstract

This invention provides a tool for testing the insulation resistance of a sealed end face of an aircraft, including a contact panel, a handle, a multimeter, a first test lead, and a second test lead. The contact panel includes a first contact surface and a second contact surface. The first contact surface is attached to the lower surface of the sealed end face, and the second contact surface is connected to the handle. One end of the first test lead is connected to the second contact surface, and the other end is connected to the multimeter. One end of the second test lead is connected to the upper surface of the sealed end face, and the other end is also connected to the multimeter. One end of the first test lead connected to the second contact surface includes multiple first mounting contact points, and one end of the second test lead connected to the sealed end face includes multiple second mounting contact points. By having the contact panel parallel to the sealed end face being measured, compared to the testing method using a test pen, the contact panel fully covers the sealed end face being measured during the test, improving the accuracy of the measurement data and reducing the potential risk of the test pen damaging the sealed end face.

Description

Technical Field

[0001] This utility model relates to insulation testing technology in the field of aerospace vehicle assembly and testing, specifically, to a tool for testing the insulation resistance of a sealed end face of a spacecraft. Background Technology

[0002] Spacecraft are supporting products for space station construction, and the reliability of their sealing performance is directly related to the safety of astronauts. Meanwhile, exposed components are exposed to the cold, dark background of space for extended periods, and frequent exposure to and exposure to light causes rapid temperature cycling, with a temperature change rate as high as 40-50°C / min. This high temperature change rate and repeated thermal cycling can cause material peeling and surface coating detachment from the substrate. Therefore, the quality of the sealing surface is one of the key factors determining the product's on-orbit lifespan. Improving the surface quality of the sealing end face is a key technical challenge in spacecraft manufacturing. Furthermore, spacecraft are mostly mechatronic products, with numerous different sealing end faces having insulation performance requirements. Based on the sealing element and contact position, seals can be divided into circumferential seals and end face seals. End face seals are also known as mechanical seals. Taking end face seal insulation testing as an example, during the testing process, if one end of the test lead is installed on the upper surface of the sealing end face, it is an exposed surface of the product, not the sealing end face, reducing potential quality risks to the sealing end face when installing the test lead.

[0003] Chinese Patent CN215116607U discloses an insulation testing device and system for testing the insulation performance of a device under test (DUT). The system includes a main body, contacts that contact the DUT, a verification module, a measurement module for measuring the insulation performance of the DUT, and a switching module. The advantages of this invention are that by setting up a measurement module, a verification module, contacts, and a switching module, where the switching module switches between the verification module and the measurement module, the verification module verifies whether the contacts are correctly contacting the DUT, and the measurement module tests the insulation performance of the DUT, the problem of determining whether the probe is making good contact with the DUT is solved. If the contact is poor, the verification module can verify the DUT, ensuring that the measurement module can correctly test the insulation performance of the DUT, thereby improving the yield rate of the DUT after it leaves the factory.

[0004] Conventional end-face insulation performance testing mainly uses a multimeter test probe to select measurement points. This method has drawbacks such as the test probe tip damaging the surface quality of the sealed end face during testing and the incomplete coverage of the selected measurement points. This poses a potential risk of inaccurate judgment of the overall quality of the aircraft. In addition, the method of selecting measurement points is inefficient. Utility Model Content

[0005] In view of the deficiencies in the existing technology, the purpose of this utility model is to provide a tool for testing the insulation resistance of the sealed end face of an aircraft.

[0006] According to the present invention, a test tool for the insulation resistance of the sealed end face of an aircraft is provided, comprising a contact panel, a handle, a multimeter, a first test lead, and a second test lead;

[0007] The contact panel includes a first contact surface and a second contact surface, the first contact surface is in contact with the lower surface of the sealing end face, and the second contact surface is connected to the handle;

[0008] One end of the first test lead is connected to the second contact surface, and the other end of the first test lead is connected to a multimeter. One end of the second test lead is connected to the upper surface of the sealing end face, and the other end of the second test lead is connected to a multimeter.

[0009] One end of the first test lead connected to the second contact surface includes multiple first mounting contact points, and one end of the second test lead connected to the sealed end face includes multiple second mounting contact points.

[0010] Preferably, the first contact surface and the second contact surface comprise mutually parallel planes.

[0011] Preferably, the flatness of both the first contact surface and the second contact surface is 0.01 mm.

[0012] Preferably, both the first contact surface and the second contact surface have chamfered edges.

[0013] Preferably, the contact panel comprises a contact panel forged from aluminum alloy LD10CS.

[0014] Preferably, the first test lead is connected to the multimeter via a banana plug, and the first mounting contact point is fixed to the second contact surface via a copper lug.

[0015] Preferably, the second test lead is connected to the multimeter via a banana plug, and the second mounting contact point is fixed to the upper surface of the sealing end face via a copper lug.

[0016] Preferably, the plurality of first mounting contact points are connected to a first solder joint by welding, and the plurality of second mounting contact points are connected to a second solder joint by welding.

[0017] Preferably, both the first mounting contact point and the second mounting contact point include two.

[0018] Preferably, the insulation value of the handle is greater than 500 megohms.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] 1. This utility model significantly increases the testing area compared to the testing method of a test pen by using a contact panel that is parallel to the sealed end face being measured. This is beneficial for the contact panel to fully cover the sealed end face of the aircraft during the testing process, which greatly improves the accuracy of the measurement data and reduces the potential quality risk of the test pen damaging the sealed end face.

[0021] 2. This utility model achieves full coverage by having the contact panel parallel to the sealed end face being measured and by installing multiple test points, which is beneficial to the effectiveness and accuracy of the measured insulation resistance data.

[0022] 3. This utility model improves the accuracy of test data by expanding the coverage of measurement points through the parallel contact panel that is attached to the sealed end face being measured. While taking into account testing efficiency, the testing tool has a simple structure and low manufacturing cost. Attached Figure Description

[0023] Other features, objects, and advantages of this invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0024] Figure 1 This utility model mainly illustrates the use of a tool for testing the insulation resistance of the sealed end face of an aircraft.

[0025] Figure 2 This is a schematic diagram illustrating the structure of the contact panel, which is the main feature of this utility model.

[0026] Figure 3 This is a schematic diagram showing the structure of the handle, which is the main feature of this utility model.

[0027] In the picture:

[0028] Contact panel 1, Contact handle 202, Second test lead 4

[0029] First contact surface 101, through hole 203, second mounting contact point 401

[0030] Second contact surface 102, first test line 3, second solder joint 402

[0031] Handle 2 First mounting contact point 301 Multimeter 5

[0032] Rod handle 201 First weld point 302 Detailed Implementation

[0033] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0034] like Figure 1 As shown, a test tool for the insulation resistance of a sealed end face of an aircraft according to this utility model includes a contact panel 1, a handle 2, a multimeter 5, a first test lead 3, and a second test lead 4. The contact panel 1 includes a first contact surface 101 and a second contact surface 102. The first contact surface 101 is attached to the lower surface of the sealed end face, and the second contact surface 102 is connected to the handle 2. One end of the first test lead 3 is connected to the second contact surface 102, and the other end of the first test lead 3 is connected to the multimeter 5. One end of the second test lead 4 is connected to the upper surface of the sealed end face, and the other end of the second test lead 4 is connected to the multimeter 5. One end of the first test lead 3 connected to the second contact surface 102 includes a plurality of first mounting contact points 301, and one end of the second test lead 4 connected to the sealed end face includes a plurality of second mounting contact points 401.

[0035] This utility model relates to a sealing end face insulation resistance testing tool, which is used to quickly and efficiently complete the overall insulation resistance measurement of a large area sealing end face. At the same time, the full coverage and multiple test point installation methods can effectively ensure the validity and accuracy of the measured insulation resistance data.

[0036] Specifically, the first test lead 3 is connected to the multimeter 5 via a banana plug, and the first mounting contact point 301 is fixed to the second contact surface 102 via a copper lug. The second test lead 4 is connected to the multimeter 5 via a banana plug, and the second mounting contact point 401 is fixed to the upper surface of the sealing end face via a copper lug. Multiple first mounting contacts 301 are welded to a first solder joint 302, and multiple second mounting contacts 401 are welded to a second solder joint 402. Preferably, there are two first mounting contacts 301 and two second mounting contacts 401. One feasible implementation is that the copper lug of the dual mounting points of the first test lead 3 is mounted on the back of the contact panel 1 with screws, serving as a fixed component that does not require disassembly. The other end of the first test lead 3 is connected to the multimeter 5 via a banana plug. The copper lugs of the second test lead 4 with dual mounting points are installed on the upper surface of the sealed end face of the aircraft with screws. The other end of the second test lead 4 is connected to the multimeter 5 via a banana plug. The first test lead 3, contact panel 1, and handle 2 are the tool's own fixing components. Before testing, the resistance between the dual mounting points of the first test lead 3 and the second test lead 4 and the banana plug must be measured. The dual mounting point structure can improve the accuracy of the insulation test data.

[0037] One end of the copper nose of the first test lead 3 with dual mounting points can be fixed to the handle 2 using a wire harness, preventing external tension from affecting the accuracy of the measurement data. One end of the copper nose of the second test lead 4 with dual mounting points can be fixed to the tested sealing surface using a wire harness or positioning clamp, preventing external tension from affecting the accuracy of the measurement data. One end of the second test lead 4 is mounted on the upper surface of the sealing surface, which is an exposed surface rather than the sealed surface itself, reducing potential quality risks to the sealing surface during test lead installation.

[0038] The contact panel 1 of this invention has no surface treatment that affects the insulation measurement performance. The second contact surface 102 can be anodized for corrosion protection. Before the corrosion protection treatment, the copper nose contact surface and the mounting threaded hole must be protected to ensure that there is no surface treatment on the copper nose contact surface and the mounting threaded hole that would affect the resistance test data. The contact panel minimizes potential quality risks to the sealing end face by improving the smoothness of the contact surface and using a handheld control measurement method. Figure 2 As shown, the contact panel 1 is made of forged aluminum alloy LD10CS. The contact panel 1 includes a first contact surface 101 and a second contact surface 102. The flatness of both the first contact surface 101 and the second contact surface 102 is within 0.01 mm. The first contact surface 101 and the second contact surface 102 are parallel planes, and both the first contact surface 101 and the second contact surface 102 have chamfered edges for smooth transition. The contact panel 1 and the handle 2 are fastened together using screws.

[0039] Specifically, such as Figure 3 As shown, the handle 2 is made of PA66 (nylon) with resistive insulation properties, and the insulation value is greater than 500 megohms. Alternatively, the handle 2 can be made of PTFE (polytetrafluoroethylene) or MDF (bakelite) with insulating properties. One design of the handle 2 is as follows: the handle 2 includes a handle 201 and a contact handle 202, which are integrally connected or fixedly connected. The contact handle 202 is attached to the contact panel 1, preferably fastened to the contact panel 1 with screws, serving as a fixing component for the tool itself. A through hole 203 is provided in the handle 201 near the contact handle 202. One end of the first test lead 3 passes through and exits the through hole 203 and is then mounted on the contact panel 1 via a copper lug. This facilitates the arrangement and installation of the first test lead 3.

[0040] The testing method for the sealing end face insulation resistance testing tool of this utility model is as follows:

[0041] Clean the contact panel 1 and the sealed end face under test. Connect the banana plugs of the first test lead 3 and the second test lead 4 to the multimeter 5. The copper lugs of the second test lead 4 with double mounting points are installed on the upper surface of the aircraft's sealed end face using screws. Before testing, the resistance between the double mounting points of the first test lead 3 and the second test lead 4 and the banana plugs needs to be measured. Holding the handle 2 of the testing tool, place the contact panel 1 parallel to the sealed end face under test and read and record the insulation resistance data. Depending on the area of ​​the sealed end face, and assuming full coverage of the measurement points, change the measurement position and repeat the above method. The data record corresponds to the quadrant of the measurement position. During the test, using the full coverage of the aircraft's sealed end face under test by the contact panel 1 as the standard, repeat the above work in a certain order, and the data record corresponds to the quadrant of the measurement position.

[0042] The spacecraft sealing end face insulation resistance testing tool provided by this utility model can achieve low-cost manufacturing, simple structure and convenient operation. The method of parallel contact panel 1 to the sealing end face to be measured greatly increases the test area compared with the test pen method, so as to ensure that the contact panel 1 fully covers the sealing end face of the spacecraft to be measured during the test. By repeating the above work in a certain order, the accuracy of the measurement data can be greatly improved, providing a new test scheme for sealing end face insulation resistance testing in the field of spacecraft assembly and testing.

[0043] The purpose of this invention is to provide a test tool for the insulation resistance of the sealed end face of an aircraft, in order to solve the potential quality risk of damage to the sealed end face by the measuring pen during the measurement of the insulation resistance of the sealed end face in the field of aerospace vehicle assembly and testing. By expanding the coverage of the measurement points, the accuracy of the test data is improved. While taking into account the test efficiency, the test device has the advantages of simple structure and low manufacturing cost.

[0044] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0045] The specific embodiments of this utility model have been described above. It should be understood that this utility model is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the substantive content of this utility model. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. An aircraft seal face insulation resistance value testing tool, characterized by, Includes a contact panel (1), a handle (2), a multimeter (5), a first test lead (3), and a second test lead (4); The contact panel (1) includes a first contact surface (101) and a second contact surface (102). The first contact surface (101) is in contact with the lower surface of the sealing end face, and the second contact surface (102) is connected to the handle (2). One end of the first test lead (3) is connected to the second contact surface (102), and the other end of the first test lead (3) is connected to the multimeter (5). One end of the second test lead (4) is connected to the upper surface of the sealing end face, and the other end of the second test lead (4) is connected to the multimeter (5). One end of the first test line (3) connected to the second contact surface (102) includes a plurality of first mounting contact points (301), and one end of the second test line (4) connected to the sealing end face includes a plurality of second mounting contact points (401).

2. The aircraft sealed face insulator resistance value testing tool of Claim 1, wherein, The first contact surface (101) and the second contact surface (102) comprise mutually parallel planes.

3. The aircraft sealing end face insulation resistance testing tool as described in claim 1, characterized in that, The flatness of both the first contact surface (101) and the second contact surface (102) is 0.01 mm.

4. The aircraft sealing end face insulation resistance testing tool as described in claim 1, characterized in that, Both the first contact surface (101) and the second contact surface (102) have chamfers around their perimeters.

5. The aircraft sealing end face insulation resistance testing tool as described in claim 1, characterized in that, The contact panel (1) comprises a contact panel forged from aluminum alloy LD10CS.

6. The aircraft sealing end face insulation resistance testing tool as described in claim 1, characterized in that, The first test lead (3) is connected to the multimeter (5) via a banana plug, and the first mounting contact point (301) is fixed on the second contact surface (102) via a copper lug.

7. The aircraft sealing end face insulation resistance testing tool as described in claim 1, characterized in that, The second test lead (4) is connected to the multimeter (5) via a banana plug, and the second mounting contact point (401) is fixed to the upper surface of the sealing end face via a copper lug.

8. The aircraft sealing end face insulation resistance testing tool as described in claim 1, characterized in that, Multiple first mounting contacts (301) are welded to a first solder joint (302), and multiple second mounting contacts (401) are welded to a second solder joint (402).

9. The aircraft sealing end face insulation resistance testing tool as described in claim 1, characterized in that, The first mounting contact point (301) and the second mounting contact point (401) each include two.

10. The aircraft sealing end face insulation resistance testing tool as described in claim 1, characterized in that, The insulation value of the handle (2) is greater than 500 megohms.

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