Flight logging device

Abstract

The utility model discloses a flight logging device which comprises an aircraft, an upper detection portion and a lower detection portion, the upper detection portion is arranged at the upper end of the aircraft, the lower detection portion is arranged at the lower end of the aircraft, and the aircraft is a rotor type aircraft. In this way, the aircraft drives the upper detection part and the lower detection part to enter the vertical shaft so as to detect the shaft wall of the vertical shaft.

Description

Technical Field

[0001] The utility model belongs to the technical field of vertical well detection, in particular to a flying well logging device. Background Art

[0002] At present, the detection of pipeline wells is mostly carried out by lowering a sonar probe into the vertical shaft using a sling or a telescopic rod, and the sonar probe detects the well wall of the vertical shaft. However, such equipment is cumbersome to operate. CN217820859U "A sonar logging assembly" and document number CN217820858U "A motorized telescopic rod and sonar well detection equipment" both disclose devices for logging vertical wells, but both are based on lowering the sonar probe into the well by a rod, which is inconvenient to operate and has a limited operating depth. Utility Model Content

[0003] In order to solve the above technical problems, the purpose of the present utility model is to provide a flying logging device which has a simple structure and can conveniently detect vertical wells.

[0004] In order to achieve the above-mentioned purpose, the technical solution of the present invention is as follows: a flying logging device, comprising an aircraft, an upper detection part and a lower detection part, the upper detection part is arranged at the upper end of the aircraft, the lower detection part is arranged at the lower end of the aircraft, and the aircraft is a rotorcraft.

[0005] The beneficial effect of the above technical solution is that the aircraft can carry the upper detection part and the lower detection part into the vertical shaft to detect the shaft wall.

[0006] The aircraft in the above technical solution includes an aircraft body and a hollow protective shell cover, the aircraft body is arranged in the protective shell cover, the upper detection part is arranged at the upper end of the protective shell cover, and the lower detection part is arranged at the lower end of the protective shell cover.

[0007] The beneficial effect of the above technical solution is that the rotor of the aircraft body can be protected by providing a protective shell cover, thereby preventing the aircraft body from being damaged due to the rotor touching the well wall.

[0008] The protective shell cover in the above technical solution is a spherical cover.

[0009] The beneficial effects of the above technical solution are: its structure is simple and its appearance is beautiful, and it can better protect the aircraft body.

[0010] The protective shell cover in the above technical solution includes an upper cover body and a lower cover body, both of which are hollow parts, the aircraft body is arranged on the upper cover body or the lower cover body, and the open ends of the upper cover body and the lower cover body are detachably connected to enclose the aircraft body in the protective shell cover.

[0011] The beneficial effect of the above technical solution is that the upper cover and the lower cover can be disassembled to perform maintenance on the aircraft body.

[0012] The aircraft body described in the above technical solution is a four-rotor drone.

[0013] The beneficial effects of the above technical solution are: its structure is simple, and it has good stability during flight and strong controllability.

[0014] The upper detection part described in the above technical solution is a sonar probe.

[0015] The beneficial effect of the above technical solution is that the upper detection part can perform circumferential scanning detection on the shaft wall in the shaft.

[0016] The lower detection part in the above technical solution includes a ranging probe, the detection end of which faces downward, and is used to detect the distance between the aircraft and the obstacle below.

[0017] The beneficial effect of the above technical solution is that when such a suitable aircraft descends in a well, the ranging probe can detect the depth of the well bottom in real time, thereby preventing the aircraft from descending to the bottom.

[0018] The lower detection part in the above technical solution also includes a camera, and the camera lens faces sideways.

[0019] The beneficial effect of the above technical solution is that when the aircraft moves up and down in the shaft, the camera can be used to photograph the shaft wall to obtain image data of the shaft wall.

[0020] The camera described in the above technical solution is a Pisces camera.

[0021] The beneficial effects of the above technical solution are: it is compact and has high imaging accuracy.

[0022] The lower detection part in the above technical solution also includes a fill light, which is used to fill light for the shooting field of view of the camera.

[0023] The beneficial effect of the above technical solution is that it enables the camera to obtain better clarity when shooting. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic structural diagram of the flight logging device according to an embodiment of the present utility model;

[0025] Figure 2 This is an elevation view of the flying logging device according to an embodiment of the present invention from another perspective;

[0026] Figure 3This is a schematic diagram of electrical connections for the in-flight logging device according to an embodiment of the present utility model;

[0027] Figure 4 This is a schematic diagram of the upper cover and the lower cover in an embodiment of the present invention being connected via a buckle.

[0028] In the figure: 1. Aircraft; 11. Aircraft body; 12. Protective shell; 121. Upper cover; 122. Lower cover; 2. Upper detection unit; 3. Lower detection unit; 31. Distance measuring probe; 32. Camera; 33. Fill light; 4. Fastener; 41. Male fastener; 42. Female fastener. DETAILED DESCRIPTION

[0029] The principles and features of the present invention are described below with reference to the accompanying drawings. The examples provided are intended only to illustrate the present invention and are not intended to limit the scope of the present invention. The following paragraphs describe the present invention in more detail by way of example with reference to the accompanying drawings. The advantages and features of the present invention will become more apparent from the following description and claims. It should be noted that the drawings are in a very simplified form and are not in exact proportions, and are only used to facilitate and clearly illustrate the embodiments of the present invention.

[0030] like Figure 1 and Figure 2 As shown, this embodiment provides a flying well logging device, including an aircraft 1, an upper detection part 2 and a lower detection part 3. The upper detection part 2 is arranged at the upper end of the aircraft 1, and the lower detection part 3 is arranged at the lower end of the aircraft 1. The aircraft 1 is a rotorcraft, so that the aircraft carries the upper detection part and the lower detection part into the vertical shaft to detect the shaft wall. Specifically, the aircraft 1 includes an aircraft body 11 and a hollow protective shell 12. The aircraft body 11 is arranged in the protective shell 12, the upper detection part 2 is arranged at the upper end of the protective shell 12, and the lower detection part 3 is arranged at the lower end of the protective shell 12. By providing the protective shell, the rotor of the aircraft body can be protected to prevent the aircraft body from being damaged due to the rotor touching the well wall.

[0031] The protective shell cover 12 in the above technical solution is a spherical cover, which has a simple structure and beautiful appearance, and can also provide better protection for the aircraft body.

[0032] The aircraft body 11 described in the above technical solution is a four-rotor drone (which belongs to the existing technology and a mature four-rotor drone on the market can be used). It has a simple structure, good stability during flight, and strong maneuverability.

[0033] The upper detection part 2 in the above technical solution is a sonar probe, so that the upper detection part can perform circumferential scanning detection on the shaft wall in the shaft.

[0034] The lower detection part 3 in the above technical solution includes a ranging probe 31, the detection end of the ranging probe 31 is facing downward, and it is used to detect the distance between the aircraft 1 and the obstacle below. In this way, when the aircraft is descending in the well, the ranging probe can detect the depth of the bottom of the well in real time, thereby preventing the aircraft from descending to the bottom.

[0035] The lower detection part 3 in the above technical solution also includes a camera 32, and the lens of the camera 32 faces sideways, so that when the aircraft moves up and down in the shaft, the camera can photograph the shaft wall to obtain image data of the shaft wall.

[0036] The camera 32 described in the above technical solution is a double fish camera, which is compact and has high imaging accuracy.

[0037] The lower detection part 3 in the above technical solution further includes a fill light 33, and the fill light 33 is used to fill light for the shooting field of view of the camera 32, so that the camera can obtain better clarity when shooting.

[0038] like Figure 3 As shown, the aircraft body 11 described in this embodiment has its own battery, controller and communication module (communicating with an external remote control terminal). The upper detection part 2 and the lower detection part 3 described in this embodiment can be electrically connected to the controller of the aircraft body and powered by the battery of the aircraft body. It should be noted that the conductive wires inside and outside the protective cover need to avoid the rotor setting of the aircraft body to prevent the wires from affecting the rotor rotation of the aircraft body. The data detected by the upper detection part, camera and ranging probe described in this embodiment can be transmitted to the remote control terminal through the aircraft body in a timely manner.

[0039] In this embodiment, the fill light may be a light strip, which is horizontally arranged and circumferentially arranged around the periphery of the camera, so that it can provide fill light to the surrounding circumferential area.

[0040] like Figure 4As shown, the protective shell cover 12 in the above technical solution includes an upper cover body 121 and a lower cover body 122, and the upper cover body 121 and the lower cover body 122 are both hollow parts. The aircraft body 11 is arranged on the upper cover body 121 or the lower cover body 122, and the open ends of the upper cover body 121 and the lower cover body 122 are detachably connected to enclose the aircraft body 11 in the protective shell cover 12, so that the upper cover body and the lower cover body can be disassembled to maintain the aircraft body. Specifically, the upper cover 121 and the lower cover 122 described in this embodiment are both hemispherical hollow covers, and the notch ends of the two can be connected to each other. Specifically, the notch ends of the two can be fastened with multiple circumferentially spaced fasteners 4 (so that the upper and lower covers can be easily disassembled and assembled). Specifically, multiple fastener male parts 41 can be evenly spaced circumferentially on the outer wall of the notch end of the lower cover, and multiple fastener female parts 42 can be evenly spaced circumferentially on the outer wall of the notch end of the upper cover. The multiple fastener female parts and the multiple fastener male parts correspond to each other and can be overlapped with each other (the corresponding fastener male parts and the corresponding fastener female parts together constitute a fastener part). Taking the connection between the aircraft body and the lower cover as an example, the four rotor arms of the aircraft body can be extended to connect with the inner wall of the lower cover near the notch to achieve the connection between the aircraft body and the protective cover.

[0041] The above description is only a preferred embodiment of the present invention and does not constitute any form of limitation to the present invention. Any ordinary technician in this industry can smoothly implement the present invention as shown in the drawings and described above. However, any equivalent changes, modifications and evolutions made by technicians familiar with this profession without departing from the scope of the technical solution of the present invention using the technical content disclosed above are all equivalent embodiments of the present invention. At the same time, any equivalent changes, modifications and evolutions made to the above embodiments based on the essential technology of the present invention are still within the scope of protection of the technical solution of the present invention.

Claims

1. A flying logging device, characterized in that: The invention comprises an aircraft (1), an upper detection part (2) and a lower detection part (3), wherein the upper detection part (2) is arranged at the upper end of the aircraft (1), and the lower detection part (3) is arranged at the lower end of the aircraft (1); the aircraft (1) is a rotary-wing aircraft.

2. The in-flight logging device according to claim 1, characterized in that: The aircraft (1) comprises an aircraft body (11) and a hollow protective shell (12); the aircraft body (11) is arranged in the protective shell (12); the upper detection part (2) is arranged at the upper end of the protective shell (12); and the lower detection part (3) is arranged at the lower end of the protective shell (12).

3. The in-flight logging device according to claim 2, characterized in that: The protective shell cover (12) is a spherical cover.

4. The in-flight logging device according to claim 2 or 3, characterized in that: The protective shell cover (12) comprises an upper cover body (121) and a lower cover body (122), both of which are hollow parts. The aircraft body (11) is arranged on the upper cover body (121) or the lower cover body (122), and the open ends of the upper cover body (121) and the lower cover body (122) are detachably connected to enclose the aircraft body (11) in the protective shell cover (12).

5. The in-flight logging device according to claim 2, characterized in that: The aircraft body (11) is a four-rotor unmanned aerial vehicle.

6. The in-flight logging device according to claim 1, characterized in that: The upper detection part (2) is a sonar probe.

7. The in-flight logging device according to claim 1, characterized in that: The lower detection part (3) comprises a distance measuring probe (31), the detection end of which faces downwards, and is used to detect the distance between the aircraft (1) and obstacles below.

8. The in-flight logging device according to claim 7, characterized in that: The lower detection part (3) further comprises a camera (32), wherein the lens of the camera (32) faces sideways.

9. The in-flight logging device according to claim 8, characterized in that: The camera (32) is a Pisces camera.

10. The in-flight logging device according to claim 8, characterized in that: The lower detection part (3) further comprises a fill light (33), and the fill light (33) is used to fill light for the shooting field of view of the camera (32).

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