CN217425637U - Aircraft oil filling pipe with damage detection device - Google Patents

Abstract

An aircraft fuel filler tube with a damage detection device, comprising: an internal structure; an intermediate structure disposed about the inner structure, and an outer structure disposed about the intermediate structure such that the intermediate structure is positioned between the inner structure and the outer structure, the filler tube further including a sensing device disposed along the filler tube and embedded within the outer structure, the sensing device being made of an electrically conductive material.

Description

Aircraft oil filling pipe with damage detection device

Technical Field

The utility model relates to an aircraft filling device especially relates to an aircraft adds oil pipe with bad detection device of loss.

Background

The use of a filler tube to refuel an aircraft from a fuel depot or tanker is a common type of aircraft refuelling device and the depending portion of the filler tube and the connection may be damaged by the impact of the aircraft when attempting to contact the aircraft tank and the filler tube may also be damaged by wear of the structure adjacent to it when wound in a drum. Therefore, it is necessary to periodically check whether the filler pipe is damaged.

Existing periodic inspections are typically performed by visual inspection after the tube is stretched to determine if it has been damaged. Such a measurement method increases the detection cost, and also makes it difficult to detect breakage of the tube. Simultaneously, owing to need stretch the oil filling pipe to reduce the life who adds the oil pipe.

Disclosure of Invention

In order to solve at least one among the above-mentioned technical problem, the utility model provides an aircraft adds oil pipe, its detection device that has the pipe damage detects the geminate transistor under the condition that does not need tensile pipe.

In order to achieve the above purpose, the utility model adopts the following technical scheme: an aircraft fuel filler tube, comprising:

an internal structure;

an intermediate structure disposed around the inner structure, an

An outer structure disposed about the intermediate structure such that the intermediate structure is located between the inner structure and the outer structure,

the fuel filler tube further includes at least one detection device disposed axially along the fuel filler tube and embedded within the outer structure, wherein the detection device is made of an electrically conductive material.

Preferably, the inner, intermediate and outer structures are made of materials having different rigidities, the rigidity of the intermediate structure being greater than the rigidity of the inner and outer structures.

Preferably, said outer structure comprises an inner surface facing the intermediate structure and an outer surface opposite said inner surface, said detection means being arranged along said outer structure between said outer surface and said inner surface of said outer structure.

Preferably, an electric current can be transmitted along the detection means, the electric continuity of the electric current is detected by a detection system, and whether the filler pipe is damaged or not is judged by the detection system detecting the interruption or stop of the electric current.

Preferably, the detection device is two or more detection devices located at different tube depths of the outer structure, the two or more detection devices being electrically isolated from each other.

Preferably, the detection means comprise at least a first wire helically wound along the outer structure and embedded inside the outer structure, so that the inner structure of the tube is covered by the wire over the entire length of the tube.

Preferably, the two or more detection means are two or more first wires, which are arranged coaxially with each other within the outer structure.

Preferably, the filler tube comprises two ends and two electrical terminals provided at one end of the tube or at both ends of the tube respectively, each of the electrical terminals being connected to the detection means and arranged to measure electrical continuity along the detection means.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the principles of the invention.

FIG. 1 shows a schematic perspective view of a filler tube of the present novel embodiment;

FIG. 2 shows a schematic view of the filler tube of the present novel embodiment;

FIG. 3 shows a schematic cross-sectional view of a portion of the filler tube of the present novel embodiment.

FIG. 4 shows a schematic cross-sectional view of a portion of a filler tube of yet another embodiment of the present invention.

1. Internal structure

2. Intermediate structure

3. Exterior structure

4. Detection device

4.1 first detection device

4.2 second detection device

4.3 third detection device

4.4 fourth detection device

5. First electric terminal

6. Second electric terminal

7. Second end portion

8. External detection system

9. Oil filling port

10. First end part

11. Damaged opening of oil filling pipe

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the invention. It should be noted that, for the convenience of description, only the parts related to the present invention are shown in the drawings.

It should be noted that the embodiments and features of the embodiments of the present invention may be combined with each other without conflict. The present invention will be described in detail with reference to the accompanying drawings in conjunction with embodiments.

As shown in fig. 1 and 2, an aircraft fuel filler tube includes: an internal structure 1; an intermediate structure 2 arranged around an inner structure 1, and an outer structure 3 arranged around said intermediate structure 2, such that said intermediate structure 2 is located between said inner structure 1 and said outer structure 3,

the filler tube further comprises a detection device 4 disposed along the filler tube and embedded within the outer structure, wherein the detection device 4 is made of an electrically conductive material.

The inner structure 1, the intermediate structure 2 and the outer structure 3 are made of materials having different rigidities, the rigidity of the intermediate structure 2 being greater than the rigidity of the inner structure 1 and the rigidity of the outer structure 34.

With reference to fig. 3, the external structure 3 comprises an internal surface facing the intermediate structure 2 and an external surface opposite to the internal surface, the detection means 4 being arranged along the external structure between the external surface and the internal surface of the external structure 3.

In addition to the provision of the detection means 4, the three-layer structure of the filler tube can be a conventional filler tube structure, the specific structural composition of which is readily apparent to the skilled person, and a spring can also be provided intermediate the filler tube inner structure 1 and the intermediate structure 2, so that the inner structure can be extended and or retracted from the intermediate structure.

As shown in connection with fig. 2, the filler tube further comprises two first 10 and second 7 ends, at the second end 7 a trumpet-shaped filler opening is provided for refueling the aircraft, at the first end 10 two electrical connection terminals 5, 6 are provided, both the first 5 and the second 6 electrical connection terminals being connected to the detection device 4, and at the same time for connecting the detection device 4 to an external detection system 8.

It is understood that the first and second electric terminals 5 and 6 in the present embodiment are both provided at the first end 10 of the filler pipe, but of course, the first and second electric terminals 5 and 6 may be provided at the first and second ends 10 and 7, respectively.

Due to the detection device 4 made of the electric conductor material, when the external detection system 8 is connected to the detection device 4 through the first electric terminal 5 and the second electric terminal 6 and external current is applied to the detection device 4, the external current can be transmitted along the detection device and forms a loop, the electric continuity of the current is detected through the external detection system 8, and whether the oil filling pipe is damaged or not is judged through the detection system detecting the interruption or stopping of the current.

For example, when the filler tube is broken as shown in fig. 3 or 4, the conductive material of the detecting means 4 is interrupted, resulting in the current loop being terminated, and the external current is interrupted.

According to another embodiment of the present invention, the detection means may comprise more than two, for example four, which are located at different tube depths of the outer structure 3, of course electrically isolated from each other. It will be understood that four detection means are only given as an example, and that a person skilled in the art may set a specific number of detection means, for example 3, 5 or naturally several others, depending on the thickness of the outer structure 3 and the need to tolerate damage to the outer structure 3.

The detection means may be in the form of a wire spirally wound along the outer structure 3 and embedded inside the outer structure 3 so that the inner structure 1 of the filler tube is covered by the wire over the entire length of the filling.

When a plurality of detection devices are employed, a plurality of wires may be employed, the plurality of wires being disposed coaxially with one another within the outer structure.

One end of each of the plurality of wires can be electrically connected and fixed to the second end portion 7 of the filler tube by a connecting device. The other end of one of the wires is connected to a first electrical terminal 5 and the other end of the other of the plurality of wires is electrically connected to a second electrical terminal 6. When the external detection system 8 inputs current into the detection device 4 through the first electric terminal 5 and the second electric terminal 6, no multiple wires can input current at the same time, and damage to the external structure can be detected.

Through this neotype aircraft that has detection device adds oil pipe's structural design, the damaged degree that adds oil pipe can be effective convenient detection to ensure the safe handling of adding oil pipe, avoid the emergence of incident such as oil leakage.

In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

It should be understood by those skilled in the art that the above embodiments are only for clarity of explanation and are not intended to limit the scope of the present application. Other variations or modifications will occur to those skilled in the art based on the foregoing disclosure and are still within the scope of the present application.

Claims (7)

1. An aircraft fuel filler pipe with a damage detection device comprises,

an internal structure;

an intermediate structure disposed around the inner structure, an

An outer structure disposed about the intermediate structure such that the intermediate structure is located between the inner structure and the outer structure, characterized in that:

the fuel filler tube further comprising at least one detection device disposed axially along the fuel filler tube and embedded within the outer structure, wherein the detection device is made of an electrically conductive material;

the detection means includes at least one wire helically wound along the outer structure and embedded within the outer structure such that the inner structure of the filler tube is covered by the wire over the entire length of the tube.

2. An aircraft fuel filler tube as claimed in claim 1, wherein: the inner, intermediate and outer structures are made of materials having different rigidities, the rigidity of the intermediate structure being greater than the rigidity of the inner and outer structures.

3. An aircraft fuel filler tube as claimed in claim 1 or 2, wherein: the outer structure comprises an inner surface facing the intermediate structure and an outer surface opposite the inner surface, the detection device being arranged along the outer structure between the outer surface and the inner surface of the outer structure.

4. An aircraft fuel filler tube as claimed in claim 1 or 2, wherein: the detection device can transmit current along the interior of the detection device, the electrical continuity of the current is detected through the detection system, and whether the oil filling pipe is damaged or not is judged by detecting the interruption or stopping of the current through the detection system.

5. An aircraft fuel filler tube as claimed in claim 1 or 2, wherein: the detection device is more than two detection devices, the more than two detection devices are positioned at different pipe depths of the external structure, and the more than two detection devices are electrically isolated.

6. An aircraft fuel filler tube as claimed in claim 5, wherein: the two or more detection devices are two or more wires, and the two or more wires are coaxially arranged with each other in the outer structure.

7. An aircraft fuel filler tube as claimed in claim 1 or 2, wherein: the filler tube includes two ends and two electrical terminals disposed at one end of the filler tube or at both ends of the filler tube, respectively, each of the electrical terminals being connected to the detection device and configured to measure electrical continuity along the detection device.

Images