Bus bar detection device, bus bar assembly and airplane windshield glass

Abstract

The utility model provides a bus bar detection device, a bus bar assembly and airplane windshield glass. The bus bar detection device comprises a detection circuit and a moisture invasion tracing layer which are connected with the inner side of the outer-layer airplane windshield glass. The detection circuit is arranged below the bus bar, and the detection circuit is provided with a detection port; and the moisture invasion tracing layer is arranged below the detection circuit. The bus bar detection device provided by the utility model can be connected with external equipment to monitor the resistance value of the detection circuit, so that the health state of the bus bar is judged, the hidden danger that the bus bar possibly has faults can be judged earlier and more accurately, and the situation that windshield glass is broken due to the faults of the bus bar in the flying process is avoided.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aviation safety technology, concretely relates to a busbar detection device. In addition, the utility model also relates to a busbar assembly containing the aforementioned busbar detection device and a plane windshield glass containing the aforementioned busbar detection device. BACKGROUND

[0002] The plane windshield glass is one of the most important components on the plane, which not only protects the pilot from the external environment, but also can withstand the huge pressure difference brought by high-speed flight and the impact of possible bird strikes. Modern plane windshield glasses are usually made of composite materials, which contain multiple layers of different materials to meet the requirements of strength, light transmission and durability. The following are some existing technical characteristics of the plane windshield glass: 1) adopt multi-layer composite structure design, the plane windshield glass is usually composed of several layers of different materials. The outer layer of the plane windshield glass is usually a material with strong wear resistance, the middle layer of the plane windshield glass may have PVB (polyvinyl butyral) or other types of interlayer, and the inner layer of the plane windshield glass is a relatively thick tempered glass layer to ensure the strength of the entire plane windshield glass and prevent the plane windshield glass from breaking. 2) use sodium-potassium system molten salt for ion exchange strengthening, which can significantly improve the strength of the plane windshield glass. 3) In order to ensure the best vision of the pilot, the plane windshield glass needs to have high light transmission and reduce visual distortion.

[0003] In addition to the aforementioned three technical characteristics, in order to ensure the pilot's clear vision in bad weather conditions, the plane windshield glass is usually equipped with a heating system to prevent the plane windshield glass from icing or remove the ice on the plane windshield glass. For example, in order to ensure that the pilot can still have a clear vision under complex weather conditions, the windshield glass of existing large passenger planes is equipped with a heating system to provide anti-icing and defogging functions. The main purpose of this heating system is to prevent frost formation and quickly remove the formed frost when necessary. Its working principle includes the following parts: first, resistance heating, the most common way of heating is to embed a layer of resistance wire or conductive film inside the windshield glass. When electric current passes through these resistance materials, they will generate heat and transfer heat to the surface of the windshield glass. Second, automatic control, the heating system is usually connected to the automatic control system of the plane, which can automatically start or adjust the heating intensity according to the changes of external temperature and humidity. Third, manual control, the pilot can also manually turn on or off the heating system or adjust the heating level through the control panel in the cockpit. For safety reasons, the heating system has the following safety designs. Fourth, overheat protection, the heating system is usually equipped with overheat protection devices to prevent safety hazards caused by overheating of the heating elements. Fifth, redundancy design, in order to improve the reliability and safety of the system, sometimes redundant heating elements or backup circuits are added in the design.

[0004] The busbar is a key component connecting the aircraft windshield heating system and the aircraft windshield heating film, also known as a heating busbar. The heating busbar of the aircraft windshield glass is generally attached to the inner side of the outer aircraft windshield glass, i.e. between the outer aircraft windshield glass and the rubber layer. The heating busbar of the aircraft windshield glass is generally in the form of a strip, which can be composed of a series of small resistance wires, and the series of small resistance wires are usually embedded in a transparent film. The heating busbar of the aircraft windshield glass can also be a conductive coating printed directly on the glass, and the typical installation method is to print a conductive material (such as silver paste) on the surface of the aircraft windshield glass, and then solidify the conductive material at high temperature to form a conductive coating, and the formed conductive coating is the heating busbar; this installation method can not only achieve the purpose of heating, but also maintain the transparency of the aircraft windshield glass. However, this installation method also has some disadvantages. Under extreme conditions, the heating busbar can locally overheat or corrode, causing the resistance between the conductive coating solidified by the silver paste to be too large, resulting in local arc discharge. This local discharge phenomenon can easily cause the heating film to break, and the arc can spread along the crack of the heating film, further inducing arc expansion and cracking of the aircraft windshield heating film, and even inducing breakage of the aircraft windshield glass.

[0005] In the active civil aviation passenger aircraft fleet, the failure of the aircraft windshield glass busbar is a problem that deserves attention, because it directly affects flight safety. For example, the right front windshield glass of the 3U8633 flight of Sichuan Airlines suddenly broke and fell when it normally climbed to an altitude of 9800 meters. As shown in the existing cases, busbar failure can generally cause an arc and cause the outer layer of the aircraft windshield glass to break, seriously affecting the safety of the aircraft. The busbar of a typical civil aviation passenger aircraft is located at the edge of the windshield glass, and the corresponding position can be observed, and the busbar is generally visually inspected. However, moisture intrusion can easily cause corrosion and aging of the busbar, leading to busbar failure, and further causing an arc and causing the outer layer of the aircraft windshield glass to break, and moisture intrusion cannot be easily detected by visual inspection alone.

[0006] Therefore, in order to enhance the safety of the operation of the aircraft windshield glass, developing a busbar detection device to improve the in-service detection capability and reliability of the busbar has become a problem that needs to be solved by those skilled in the art. Practical new type content

[0007] The utility model discloses a busbar detection device, a busbar assembly and an aircraft windshield glass, wherein the busbar detection device is arranged at a position where moisture intrusion is likely to occur. The busbar detection device helps users to timely detect busbar failure, and more accurately judges the potential risks of busbar failure, so as to replace the glass in advance and avoid windshield glass breakage caused by busbar failure during flight.

[0008] One of the purposes of the utility model is to provide a busbar detection device, including:

[0009] Detection circuit, be located below busbar;The detection circuit is connected with the inner side of the outer layer aircraft windshield glass;The detection circuit is equipped with detection port;

[0010] Moisture intrusion tracer layer, be located below the detection circuit;The moisture intrusion tracer layer is connected with the inner side of the outer layer aircraft windshield glass.

[0011] In a preferred embodiment of the utility model,

[0012] The detection circuit is strip-shaped;And / or,

[0013] The moisture intrusion tracer layer is strip-shaped;

[0014] Preferably,

[0015] The detection circuit is parallel with the busbar;And / or,

[0016] The moisture intrusion tracer layer is parallel with the busbar.

[0017] In a preferred embodiment of the utility model,

[0018] The length of the detection circuit is not less than the length of the busbar;And / or,

[0019] The length of the moisture intrusion tracer layer is not less than the length of the busbar.

[0020] In a preferred embodiment of the utility model,

[0021] The detection circuit is made of copper or aluminum, or is made of silver paste high-temperature solidification;And / or,

[0022] The moisture intrusion tracer layer is made of humidity indicator material.

[0023] In a preferred embodiment of the utility model,

[0024] The detection circuit is further provided with lead-out end, and the lead-out end is connected with lead-out end wire.

[0025] The second purpose of the utility model is to provide a busbar assembly, including upper busbar, lower busbar and the busbar detection device of the first purpose of the utility model;The upper busbar and the lower busbar are connected with the inner side of the outer layer aircraft windshield glass;The busbar detection device is located below the lower busbar and is connected with the inner side of the outer layer aircraft windshield glass.

[0026] In an optimal embodiment of the utility model, the busbar assembly further comprises a moisture barrier layer; the moisture barrier layer is arranged below the moisture intrusion tracer layer, and the moisture barrier layer is connected to the inner side of the outer aircraft windshield.

[0027] In an optimal embodiment of the utility model,

[0028] The length of the moisture barrier layer is not less than the length of the busbar; and / or,

[0029] The width of the moisture barrier layer is 3-20 mm, preferably 3-5 mm; and / or,

[0030] The bottom of the moisture barrier layer is at the same vertical height as the bottom of the outer aircraft windshield.

[0031] In an optimal embodiment of the utility model, the moisture barrier layer is any one of a copper plating layer and an aluminum plating layer.

[0032] The utility model discloses a kind of aircraft windshields, including

[0033] Outer aircraft windshield;

[0034] Busbar, with the inner side of the outer aircraft windshield is connected;Including upper and lower arrangement upper busbar and lower busbar;

[0035] Aircraft windshield heating film, is arranged between the upper busbar and the lower busbar;The aircraft windshield heating film is connected to the inner side of the outer aircraft windshield;The aircraft windshield heating film is electrically connected with the busbar;

[0036] Aircraft windshield heating system, electrically connected with the busbar;

[0037] The busbar detection device of one of the purposes of the utility model is arranged below the lower busbar and is connected to the inner side of the outer aircraft windshield;

[0038] Preferably,

[0039] The aircraft windshield further comprises a moisture barrier layer;The moisture barrier layer is arranged below the moisture intrusion tracer layer, and the moisture barrier layer is connected to the inner side of the outer aircraft windshield.

[0040] Compared with prior art, the utility model has the beneficial effects that:

[0041] 1. The busbar detection device of this utility model can be connected to external equipment to monitor the resistance value of the detection circuit, thereby judging the health status of the busbar, and judging the potential faults of the busbar earlier and more accurately, so as to avoid the windshield cracking caused by busbar failure during flight.

[0042] 2. The busbar detection device of this utility model can help determine the corrosion and aging status of the busbar by setting a moisture intrusion tracer layer, and further help determine the health status of the busbar. It can identify potential faults in the busbar earlier and more accurately, and avoid windshield breakage caused by busbar failure during flight.

[0043] 3. The manifold assembly of this utility model can block the passage of water vapor by setting a moisture barrier layer, thereby preventing water vapor from entering the vicinity of the manifold and causing corrosion and aging of the manifold. On the one hand, it can extend the actual service life of the aircraft windshield, and on the other hand, it can avoid the outer layer of the aircraft windshield from cracking due to manifold failure. Attached Figure Description

[0044] Figure 1 This is a three-dimensional schematic diagram of the busbar detection device, busbar, and aircraft windshield of this utility model;

[0045] Figure 2 This is a partial perspective view of the busbar detection device, busbar, and aircraft windshield of this utility model.

[0046] In the diagram, 1-detection circuit; 2-moisture intrusion tracer layer; 3-moisture barrier layer; 4-busbar; 41-lower busbar; 5-outer aircraft windshield glass; 6-aircraft windshield heating film. Detailed Implementation

[0047] The present invention will now be described in further detail with reference to the accompanying drawings:

[0048] Example 1

[0049] like Figures 1-2 As shown, this utility model provides a busbar detection device, including a detection circuit 1 and a moisture intrusion tracer layer 2. Those skilled in the art know that the outer layer of an aircraft windshield typically includes two busbars 4 arranged vertically, respectively installed on the inner side of the outer aircraft windshield 5 near the top and near the bottom. Figure 1As shown, the upper busbar is installed at the position close to the top of the inner side of the outer aircraft windshield 5, and the lower busbar 41 is installed at the position close to the bottom of the inner side of the outer aircraft windshield 5. The detection circuit 1 in the busbar detection device is arranged below the busbar, specifically below the lower busbar 41; the detection circuit 1 is connected to the inner side of the outer aircraft windshield 5. Preferably, the detection circuit 1 is in the form of a strip as a whole, which is parallel to the busbar 4, that is, the axis of the detection circuit 1 is parallel to the axis of the busbar 4. In actual application, the axis of the busbar 4 inside the cockpit is generally parallel to the ground, so the axis of the detection circuit 1 is also parallel to the ground. The length of the detection circuit 1 is not less than the length of the busbar 4.

[0050] Preferably, the detection circuit 1 is made of copper foil or aluminum foil, or made of silver paste high-temperature curing. Such material makes the detection circuit 1 oxidized when encountering water vapor, resulting in an increase in its resistance. By connecting the external circuit with the detection circuit 1, the change in the resistance value of the detection circuit 1 can be monitored, and then it can be judged whether water vapor intrusion has occurred, so as to achieve the purpose of monitoring the health status of the busbar 4. The detection circuit 1 is the circuit closest to the busbar area, and in the working state of this area, there is no obvious current passing through. The detection circuit 1 is provided with detection ports (two), when it is necessary to detect the busbar 4, a multimeter or resistance measuring device is connected to the detection port of the detection circuit 1, and then the resistance value of the detection circuit 1 is detected. Exemplarily, the detection circuit 1 is a continuous wire, both ends of which are provided with detection ports, which can be arranged at or near the socket position of the busbar 4. When the aircraft is in service after the flight, the detection port can be connected to the test equipment (such as a multimeter or a resistance measuring device), and the test equipment tests the resistance value at both ends of the detection circuit 1, and then judges whether water vapor intrusion has occurred through the measured resistance value.

[0051] In a preferred embodiment of the utility model, the detection circuit 1 is also provided with a lead-out end, the lead-out end is connected with a lead-out end wire, the other end of the lead-out end wire can be connected with a junction box, and then the resistance value of the detection circuit 1 can be directly detected through the junction box. The other end of the lead-out end wire can also be connected to the outer side of the windshield, and the resistance value of the detection circuit 1 is detected through other interfaces.

[0052] The moisture intrusion tracer layer 2 is arranged below the detection circuit 1, and the moisture intrusion tracer layer 2 is connected to the inner side of the outer aircraft windshield glass 5, so as to facilitate line engineering inspection, especially monitoring of the busbar 4. The moisture intrusion tracer layer 2 is in the form of a strip as a whole, and is made of a moisture-sensitive indicator material. The moisture-sensitive indicator material is a material capable of reacting to the change of moisture content in the surrounding environment, and the reaction is usually a color change. Preferably, the moisture-sensitive indicator material can be combined to the inner side of the outer aircraft windshield glass 5 by any one of chemical transfer, sputtering, spraying and coating. More preferably, the moisture-sensitive indicator material is combined to the inner side of the outer aircraft windshield glass 5 by chemical transfer. Most preferably, the moisture intrusion tracer layer 2 is parallel to the busbar 4, that is, the axis of the moisture intrusion tracer layer 2 is parallel to the axis of the busbar 4. In actual application, the axis of the busbar 4 in the cockpit is generally parallel to the ground, so the axis of the moisture intrusion tracer layer 2 is also parallel to the ground. The length of the moisture intrusion tracer layer 2 is not less than the length of the busbar.

[0053] In a preferred embodiment of the utility model, the moisture-sensitive indicator material includes at least one of cobalt chloride, phenolphthalein, silica gel particles, methyl red, bromocresol green, phenol red, crystal violet, color-changing silica gel, phenolic compounds or other organic dyes, and more preferably includes at least one of cobalt chloride, phenolphthalein and silica gel particles. The color change of these moisture-sensitive indicator materials is relatively obvious, and can be easily found by on-site maintenance personnel. The moisture-sensitive indicator material is an existing material, and a person skilled in the art can select a suitable moisture-sensitive indicator material according to the requirement, which will not be described here.

[0054] The utility model also provides a busbar assembly which comprises the busbar detection device, the upper busbar and the lower busbar 41. That is, the busbar assembly comprises the detection circuit 1, the moisture intrusion tracer layer 2, the upper busbar and the lower busbar 41. Specifically, the detection circuit 1 is arranged below the lower busbar 41. The moisture intrusion tracer layer 2 is arranged below the detection circuit 1.

[0055] In the preferred embodiment of the utility model, the busbar assembly further comprises a moisture barrier layer 3. The moisture barrier layer 3 is arranged below the moisture intrusion tracer layer 2, and the moisture barrier layer 3 is connected to the inner side of the outer aircraft windshield glass 5 to prevent the passage of water vapor, thereby preventing water vapor from entering the vicinity of the busbar 4 and causing corrosion and aging of the busbar 4. On the one hand, it can prolong the actual service life of the aircraft windshield glass, and on the other hand, it can avoid the breakage of the outer layer of the aircraft windshield glass caused by the failure of the busbar 4. Preferably, the moisture barrier layer 3 is parallel to the busbar 4, that is, the axis of the moisture barrier layer 3 is parallel to the axis of the busbar 4. In actual application, the axis of the busbar 4 inside the cockpit is generally parallel to the ground, so the axis of the moisture barrier layer 3 is also parallel to the ground. The length of the moisture barrier layer 3 is not less than the length of the busbar.

[0056] In the preferred embodiment of the utility model, the moisture barrier layer 3 is a plating layer, which is made of a material capable of blocking moisture intrusion. More preferably, the moisture barrier layer 3 is any one of a copper plating layer and an aluminum plating layer, further enhancing its performance in blocking moisture intrusion. In another preferred embodiment of the utility model, the width of the moisture barrier layer 3 is 3-20 mm, preferably 3-5 mm. Most preferably, the bottom of the moisture barrier layer 3 is at the same vertical height as the bottom of the outer aircraft windshield glass 5.

[0057] The utility model also provides an aircraft windshield, including outer aircraft windshield 5, busbar 4, aircraft windshield heating film 6, aircraft windshield heating system and preceding busbar detection device. That is, the aircraft windshield includes the detection circuit 1, the moisture intrusion tracer layer 2, the busbar 4, the moisture barrier layer 3, outer aircraft windshield 5, the aircraft windshield heating film 6 and aircraft windshield heating system. More specifically, busbar 4 is connected with the inner side of outer aircraft windshield 5, including upper busbar and lower busbar 41 arranged upwards and downwards, the upper busbar is installed at the position near the top of the inner side of outer aircraft windshield 5, and the lower busbar 41 is installed at the position near the bottom of the inner side of outer aircraft windshield 5;The aircraft windshield heating film 6 is located between the upper busbar and the lower busbar 41, and the aircraft windshield heating film 6 is connected with the inner side of the outer aircraft windshield 5;The aircraft windshield heating system is electrically connected with the busbar 4, and the aircraft windshield heating film 6 is also electrically connected with the busbar 4, so that the current of the aircraft windshield heating system enters the busbar 4 and then enters the aircraft windshield heating film 6 to generate heat, thereby heating the outer aircraft windshield 5 to realize the anti-icing and defogging of the outer aircraft windshield 5;The busbar detection device is located below the lower busbar 41 and is connected with the inner side of the outer aircraft windshield 5, the detection circuit 1 is located below the lower busbar 41 and is connected with the inner side of the outer aircraft windshield 5, and the moisture intrusion tracer layer 2 is located below the lower busbar 41 and is connected with the inner side of the outer aircraft windshield 5.

[0058] In the description of the utility model, it is to explain that, unless otherwise explicitly provided and limited, the term "connected" "connection" should be broad sense understanding, for example, can be fixed connection, also can be detachable connection, or integrally connected;Can be mechanical connection, also can be electrical connection;It can be directly connected, also can be indirectly connected through the intermediate medium. For ordinary skilled in the art, the specific meaning of the above-mentioned terms in the utility model can be understood according to specific circumstances.

[0059] In the description of the utility model, unless otherwise stated, the orientation or position relationship indicated by the terms "upper", "lower", "left", "right", "inner", "outer" and the like is based on the orientation or position relationship shown in the drawing, which is only for the convenience of describing the utility model and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, so it cannot be understood as a limitation on the utility model.

[0060] The technical scheme is only one implementation manner of the utility model, and for the person skilled in the art, on the basis of the disclosed principle, various types of improvements or deformations can be easily made, and are not limited to the technical scheme described in the above specific embodiments of the utility model, therefore, the above description is only preferred, and does not have a limiting meaning.

Claims

1. A busbar detection device, characterized in that, include: The detection circuit is located below the busbar; the detection circuit is connected to the inner side of the outer layer of the aircraft windshield. The detection circuit is equipped with a detection port; A moisture intrusion tracer layer is disposed below the detection circuit; the moisture intrusion tracer layer is connected to the inner side of the outer aircraft windshield.

2. The busbar detection device according to claim 1, characterized in that, The detection circuit is strip-shaped; and / or, The moisture intrusion tracer layer is strip-shaped.

3. The busbar detection device according to claim 2, characterized in that, The detection circuit is parallel to the busbar; and / or, The moisture intrusion tracer layer is parallel to the busbar.

4. The busbar detection device according to claim 1, characterized in that, The length of the detection circuit is not less than the length of the busbar; and / or, The length of the moisture intrusion tracer layer is not less than the length of the busbar.

5. The busbar detection device according to claim 1, characterized in that, The detection circuit is made of copper or aluminum, or of silver paste cured at high temperature; and / or, The moisture intrusion tracer layer is made of a moisture-sensitive indicator material.

6. The busbar detection device according to claim 1, characterized in that, The detection circuit is also provided with a lead-out terminal, which is connected to a lead-out terminal wire.

7. A busbar assembly, characterized in that, The device includes an upper busbar, a lower busbar, and a busbar detection device according to any one of claims 1 to 6; both the upper busbar and the lower busbar are connected to the inner side of the outer layer of the aircraft windshield; the busbar detection device is located below the lower busbar and is connected to the inner side of the outer layer of the aircraft windshield.

8. The busbar assembly according to claim 7, characterized in that, The busbar assembly also includes a moisture barrier layer; the moisture barrier layer is disposed below the moisture intrusion tracer layer and is connected to the inner side of the outer aircraft windshield.

9. The busbar assembly according to claim 8, characterized in that, The length of the moisture barrier layer is not less than the length of the manifold; and / or, The width of the moisture barrier layer is 3~20mm; and / or, The bottom of the moisture barrier layer is at the same vertical height as the bottom of the outer aircraft windshield.

10. The busbar assembly according to claim 8, characterized in that, The moisture barrier layer can be either a copper plating or an aluminum plating.

11. An aircraft windshield, characterized in that, include Outer layer of aircraft windshield; The busbar connects to the inner side of the outer aircraft windshield; it includes an upper busbar and a lower busbar arranged vertically. An aircraft windshield heating film is disposed between the upper busbar and the lower busbar; the aircraft windshield heating film is connected to the inner side of the outer layer of the aircraft windshield glass; the aircraft windshield heating film is electrically connected to the busbar; The aircraft windshield heating system is electrically connected to the busbar. The busbar detection device according to any one of claims 1 to 6 is disposed below the lower busbar and connected to the inner side of the outer aircraft windshield.

12. The aircraft windshield according to claim 11, characterized in that, The aircraft windshield also includes a moisture barrier layer; the moisture barrier layer is disposed below the moisture intrusion tracer layer, and the moisture barrier layer is connected to the inner side of the outer aircraft windshield.

Images