Aircraft power connector with replaceable insertion core

Abstract

The utility model discloses an aircraft power supply connector with a replaceable insertion core, which comprises a shell, an insertion core inner frame is arranged in the shell, the insertion core inner frame is provided with the insertion core, the insertion core is composed of two connected rod bodies, the front end rod body is connected to the rear end rod body, and the rear end rod body is arranged on the insertion core inner frame; at least one insertion core is provided with a heat conduction piece and a temperature sensor, and the temperature of the insertion core is transmitted to the temperature sensor through the heat conduction piece. According to the utility model, the front end rod body can be rapidly replaced so as to adjust the length of the insertion core or match with different charging bases, thereby satisfying different use requirements, reducing the use cost of the power supply connector, improving the compatibility of the power supply connector, and prolonging the service life of the power supply connector. The temperature of the insertion core can be better transmitted to the temperature sensor through the heat conduction piece, the sensing effect of the temperature sensor is improved, and the socket is safe, reliable and high in stability.

Description

Technical Field

[0001] This utility model relates to an aircraft power connector with a replaceable plug, specifically an aircraft power connector with temperature signal feedback. Background Technology

[0002] In today's rapidly developing aviation industry, the safety performance of power connectors has become a critical issue affecting flight safety. Modern passenger aircraft are equipped with numerous electronic devices, and in the confined environment of high altitudes, continuously operating power connectors are prone to abnormal heat buildup due to current load. Without an effective temperature monitoring mechanism, these heat points may accelerate the aging of insulation materials, leading to circuit performance degradation or even short circuit risks. More seriously, the unique environment at 10,000 meters altitude makes traditional firefighting methods difficult to respond quickly, and subtle temperature anomalies, if not warned in time, may escalate into uncontrollable fires. Utility Model Content

[0003] The purpose of this invention is to provide an aircraft power connector with a replaceable plug, which allows for plug length adjustment or compatibility with different charging bases, thus improving the connector's compatibility. Simultaneously, it allows for better detection of plug temperature, ensuring safety, reliability, and strong stability.

[0004] To achieve the above-mentioned technical objectives, the technical solution of this utility model is as follows:

[0005] A replaceable plug aircraft power connector includes a housing, an inner plug holder inside the housing, a plug holder on the inner plug holder, and a plug holder consisting of two connected rods, with a front rod connected to a rear rod and the rear rod mounted on the inner plug holder; at least one plug holder is provided with a heat-conducting element (ceramic material) and a temperature sensor, and the temperature of the plug holder is transferred to the temperature sensor through the heat-conducting element.

[0006] Furthermore, the heat-conducting element is arc-shaped, and the arc-shaped heat-conducting element surrounds or partially surrounds the insert.

[0007] To further improve the sensing effect of the temperature sensor, the heat-conducting component has a temperature sensor mounting hole, and the temperature sensor is installed in the temperature sensor mounting hole.

[0008] Furthermore, the inner frame of the insert is provided with a heat-conducting component mounting cavity, and the heat-conducting component is disposed in the heat-conducting component mounting cavity.

[0009] Furthermore, the head of the rear rod is a hollow tubular structure, and the front rod is inserted into the rear rod.

[0010] Furthermore, the head of the rear end rod is provided with multiple contraction joints, which are arranged axially along the rear end rod. These multiple axial contraction joints divide the head of the rear end rod into multiple tube-wall segments, which are arranged sequentially along the circumference of the rear end rod (similar to flower petals). The tube-wall segments can contract inward or expand outward, thereby changing the inner diameter of the rear end rod.

[0011] To radially limit the rear end of the rod, a sleeve is provided on the head of the rear end of the rod. The sleeve is fitted around the outer periphery of the rear end of the rod to prevent the tube wall from expanding outward; when the sleeve is squeezed, the deformed sleeve can squeeze the tube wall, causing the tube wall to contract inward, thereby clamping the front end of the rod.

[0012] Furthermore, the sleeve is a C-shaped sleeve. At the opening of the C-shaped sleeve, there are a left convex portion and a right convex portion. The left convex portion is located at one end of the C-shaped sleeve, and the right convex portion is located at the other end of the C-shaped sleeve. By using a tool (pliers) to clamp the left and right convex portions, the inner diameter of the sleeve can be reduced. When the sleeve is reduced, it will squeeze the tube wall plate, causing the tube wall plate to contract inward (similar to the closing of flower petals), thereby making the tube wall plate fit tightly against the front end rod, and thus clamping the front end rod.

[0013] To circumferentially limit the movement of the front rod and prevent it from rotating on the rear rod, an anti-rotation rib is provided on the outer wall of the front rod. The anti-rotation rib is located within the contraction joint (or the limiting groove on the inner wall of the rear rod), thereby preventing the front rod from rotating.

[0014] In order to axially limit the front rod and prevent it from detaching from the rear rod, the front rod and the rear rod are provided with a connected screw hole, and a screw is connected in the screw hole.

[0015] As another way to achieve the movable connection between the front end rod and the rear end rod, the front end rod is threadedly connected to the rear end rod.

[0016] The front end of this invention can be quickly replaced to adjust the length of the plug or match different charging bases, meeting various usage needs, reducing the cost of power connectors, and improving power connector compatibility and product lifespan. This invention, through a heat-conducting component, can better transfer the plug temperature to the temperature sensor, improving the temperature sensor's sensing effect, ensuring safety, reliability, and strong stability. Attached Figure Description

[0017] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0018] Figure 1 This is a schematic diagram of the internal components of an aircraft power plug.

[0019] Figure 2 This is a schematic diagram of the ferrule inner frame and ferrule structure.

[0020] Figure 3 This is a schematic diagram of the temperature sensor mounting structure.

[0021] Figure 4 This is a schematic diagram of the finished structure of an aircraft power plug.

[0022] Figure 5 This is a schematic diagram of the second rear end rod structure.

[0023] Figure 6 This is a schematic diagram of the sleeve structure. Detailed Implementation

[0024] like Figure 1-6 As shown, an aircraft power connector with replaceable plugs includes an integrated injection-molded housing 1. Inside the housing 1 is a plug holder 4, which houses five silver-plated plugs. One of the plugs has an arc-shaped ceramic heat-conducting element 3 and a temperature sensor 2. The plug holder 4 has a heat-conducting element mounting cavity, within which the arc-shaped ceramic heat-conducting element 3 is installed. The arc-shaped ceramic heat-conducting element 3 partially surrounds (or can fully surround, as shown in the illustration, not partially surrounding) the plug and is close to its surface. The arc-shaped ceramic heat-conducting element 3 has a temperature sensor mounting hole, within which the temperature sensor 2 is installed. The temperature sensor 2 has two outwardly extending signal lines. The temperature of the first plug is transmitted to the temperature sensor 2 through the heat-conducting element 3, and the temperature sensor 2 transmits the signal through the signal lines. Alternatively, one or more of the other four plugs can also be equipped with temperature sensors and arc-shaped ceramic heat-conducting elements to monitor the plug temperature. The plug holder 4 can also accommodate more than five plugs to provide aircraft power connectors with different numbers of plugs.

[0025] The insert consists of two connected first front rods 8 and first rear rods 6. The first front rods 8 are hollow tubular structures with threads on the inner wall of their tails. The head of the first rear rod 6 has a threaded portion 13, the outer diameter of which is smaller than that of the first rear rod 6. The threaded portion 13 engages with the threaded part, allowing the first front rods 8 to be threadedly connected to the first rear rods 6. The tail of the first rear rods 6 is connected to the insert's inner frame 4. A positioning ring 11 is fitted onto the threaded portion 13, and a micro switch 10 is installed inside the cavity of the first front rods 8.

[0026] As another implementation of the ferrule, the ferrule consists of two connected second front end rods 7 and second rear end rods 5. The second rear end rod 5 is a hollow tubular structure. The second front end rod 7 is inserted into the second rear end rod 5, and the tail of the second rear end rod 5 is connected to the inner frame 4 of the ferrule.

[0027] The head of the second rear end rod 5 is provided with two contraction joints 51, both of which are arranged along the axial direction of the second rear end rod 5. The two contraction joints 51 divide the head of the second rear end rod 5 into two tube wall segments 52. Of course, the head of the second rear end rod 5 can also be provided with three or more contraction joints, thereby dividing the head of the second rear end rod 5 into more tube wall segments.

[0028] A sleeve 9 is fitted onto the head of the second rear end rod 5. The sleeve 9 has a sleeve hole 14, and the head of the second rear end rod 5 is located inside the sleeve hole 14. The sleeve 9 is a C-shaped sleeve. At the opening of the C-shaped sleeve, the outer wall of the C-shaped sleeve has a left protrusion 91 and a right protrusion 92. The left protrusion 91 is located at one end of the C-shaped sleeve, and the right protrusion 92 is located at the other end of the C-shaped sleeve. By using pliers to clamp the left protrusion 91 and the right protrusion 92, the inner diameter of the sleeve 9 (i.e., the inner diameter of the sleeve hole 14) can be reduced. When the sleeve 9 is reduced, the sleeve 9 will squeeze the two tube wall pieces 52, and the two tube wall pieces 52 will deform and shrink inward (similar to the closing of flower petals), so that the tube wall pieces 52 are pressed against the second front end rod 7, thereby clamping the second front end rod 7.

[0029] To axially limit the second front end rod 7 and prevent it from detaching from the inner cavity of the second rear end rod 5, the second rear end rod 5 and the second front end rod 7 are provided with connected screw holes 15, and screws 12 are connected inside the screw holes 15. The screws 12 are sequentially connected to the screw holes of the second rear end rod 5 and the second front end rod 7 to achieve axial limiting of the second front end rod 7.

[0030] To circumferentially limit the second front rod 7 and prevent it from rotating on the second rear rod 5, an anti-rotation rib 16 is provided on the outer wall of the tail of the second front rod 7. The anti-rotation rib 16 is arranged axially along the second front rod 7. When the second front rod 7 is inserted into the second rear rod 5, the anti-rotation rib 16 is located within the contraction joint 51, thus achieving circumferential limitation of the second front rod 7. Of course, a limiting groove that cooperates with the anti-rotation rib 16 can be provided on the inner wall of the second rear rod 5. When the second front rod 7 is inserted into the second rear rod 5, the anti-rotation rib 16 is located within the limiting groove, thus achieving circumferential limitation of the second front rod 7.

[0031] The ferrule is injection molded onto the inner frame 4. The second front rod 7 is inserted into the inner cavity of the second rear rod 5. A sleeve 9 is clamped with pliers to secure it, and then a screw is connected to the screw hole 15 to tightly connect the second rear rod 5 and the second front rod 7. A micro switch 10 is placed inside the inner cavity of the first front rod 8, which is threaded to the first rear rod 6. The heat-conducting component 3 is first placed in the heat-conducting component mounting cavity of the inner frame 4, and the temperature sensor 2 is installed in the temperature sensor mounting hole of the heat-conducting component 3. The heat-conducting component effectively transfers the temperature of the ferrule to the temperature sensor 2. With the combined action of the temperature sensor and the micro switch, the connection can be promptly disconnected when the internal current of the power connector is abnormal, ensuring electrical safety.

[0032] The above embodiments do not limit the present invention in any way. All technical solutions obtained by equivalent substitution or equivalent transformation fall within the protection scope of the present invention.

Claims

1. An aircraft power connector with replaceable plug, comprising a housing, an inner plug holder disposed within the housing, and a plug holder disposed on the inner plug holder, characterized in that, The insert is composed of two connected rods, with the front rod connected to the rear rod and the rear rod mounted on the inner frame of the insert; at least one insert is equipped with a heat-conducting element and a temperature sensor, and the temperature of the insert is transferred to the temperature sensor through the heat-conducting element.

2. The aircraft power connector with replaceable ferrule according to claim 1, characterized in that: The heat-conducting component is arc-shaped, and the arc-shaped heat-conducting component surrounds or partially surrounds the insert.

3. The aircraft power connector with replaceable plug according to claim 1, characterized in that: The heat-conducting component has a temperature sensor mounting hole, and the temperature sensor is disposed in the temperature sensor mounting hole.

4. The aircraft power connector with replaceable ferrule according to claim 1, characterized in that: The insert inner frame has a heat-conducting component mounting cavity, and the heat-conducting component is disposed in the heat-conducting component mounting cavity.

5. The aircraft power connector with replaceable plug according to claim 1, characterized in that: The head of the rear rod is a hollow tubular structure, and the front rod is inserted into the rear rod.

6. The aircraft power connector with replaceable ferrule according to claim 5, characterized in that: The head of the rear end rod is provided with multiple contraction joints, which are arranged along the axial direction of the rear end rod. A sleeve is provided on the rear end rod.

7. The aircraft power connector with replaceable plug according to claim 6, characterized in that: The sleeve is a C-shaped sleeve. At the opening of the C-shaped sleeve, the C-shaped sleeve has a left convex part and a right convex part. The left convex part is located at one end of the C-shaped sleeve, and the right convex part is located at the other end of the C-shaped sleeve.

8. The aircraft power connector with replaceable ferrule according to claim 5, characterized in that: The outer wall of the front end rod is provided with anti-rotation ribs.

9. The aircraft power connector with replaceable ferrule according to claim 4, characterized in that: The front and rear rods are provided with connected screw holes, and screws are connected in the screw holes.

10. The aircraft power connector with replaceable ferrule according to claim 1, characterized in that: The front end rod is threadedly connected to the rear end rod.

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