A helicopter-borne artificial power inspection auxiliary device

Abstract

The utility model relates to the technical field of helicopter power inspection, and specifically to a helicopter-borne artificial power inspection auxiliary device, comprising a base assembly and a two-axis rotating assembly; the base assembly comprises a shock absorbing assembly and a rotating assembly connecting plate, the bottom of the shock absorbing assembly is fixedly connected to the inside of the helicopter cabin and is located near a window, and the top of the shock absorbing assembly is fixedly connected to the rotating assembly connecting plate; the two-axis rotating assembly comprises an azimuth rotating assembly, a pitch rotating assembly and a photoelectric load, the azimuth rotating assembly is rotatably connected to the rotating assembly connecting plate, the pitch rotating assembly is rotatably connected to the azimuth rotating assembly, and the photoelectric load is fixedly connected to the pitch rotating assembly. The device can rotate in two directions of azimuth and pitch, the shock absorber can effectively isolate the high-frequency vibration brought by the helicopter, and ensure clear imaging, and at the same time, the azimuth and pitch directions of braking can be realized through an azimuth brake switch and a pitch brake switch, and the labor intensity of personnel is effectively reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of helicopter power inspection, in particular to a helicopter-borne artificial power inspection auxiliary device. Background Art

[0002] The distribution of power transmission lines in power grids is generally characterized by complex geographical environments and harsh natural conditions. Power lines and tower accessories are long-term affected by mechanical tension, electrical flashover, material aging, etc., which are prone to damage such as broken strands, wear, corrosion, etc., which can lead to serious accidents. Therefore, it is necessary to conduct regular inspections of transmission lines to promptly discover and eliminate hidden dangers, prevent accidents, and ensure power supply safety.

[0003] At present, in order to achieve reliable inspection operations in different geographical environments, helicopter manual inspection is mainly adopted, that is, the inspectors take a helicopter to use optoelectronic loads such as visible light cameras to clearly image the towers and cable targets, so as to clearly identify the defects of key target points. In the actual inspection process, due to the continuous vibration of the helicopter and the need to ensure the relative stillness of the optoelectronic load and the target, this places high demands on the inspectors and the labor intensity of the inspectors is extremely high. Utility Model Content

[0004] Therefore, the technical problem to be solved by the utility model is to overcome the defects in the prior art, thereby providing a helicopter-borne artificial power inspection auxiliary device.

[0005] A helicopter-borne manual power inspection auxiliary device comprises a base assembly and a two-axis rotating assembly;

[0006] The base assembly includes a shock absorbing assembly and a rotating assembly connecting plate, the bottom of the shock absorbing assembly is fixedly connected to the inside of the helicopter cabin and is located near the window, and the top of the shock absorbing assembly is fixedly connected to the rotating assembly connecting plate;

[0007] The two-axis rotation assembly includes an azimuth rotation assembly, a pitch rotation assembly and an optoelectronic load. The azimuth rotation assembly is rotationally connected to the rotation assembly connecting plate, the pitch rotation assembly is rotationally connected to the azimuth rotation assembly, and the optoelectronic load is fixedly connected to the pitch rotation assembly.

[0008] Further, the shock absorbing assembly includes a shock absorber bottom plate, a shock absorber, a shock absorber top plate, a shock absorber assembly fixing frame and a rotating assembly fixing frame;

[0009] The two ends of the shock absorber are respectively fixedly connected to the shock absorber bottom plate and the shock absorber top plate, the shock absorber top plate is connected to the shock absorber assembly fixing frame, the shock absorber assembly fixing frame is connected to the rotating assembly fixing frame, and the top of the rotating assembly fixing frame is connected to the rotating assembly connecting plate.

[0010] Further, the shock absorbing assembly also includes a height adjustment frame;

[0011] A plurality of height adjustment frames are evenly arranged between the rotating assembly fixing frame and the shock absorber assembly fixing frame.

[0012] Further, the azimuth rotation assembly includes an azimuth transfer shaft, an azimuth brake, an azimuth bearing and an azimuth base plate;

[0013] The first stator of the azimuth bearing is fixedly connected to the rotating component connecting plate, the first rotor of the azimuth bearing is fixedly connected to the azimuth substrate, the first brake plate of the azimuth brake is installed on the rotating component connecting plate, and the first wire seat of the azimuth brake is connected to the azimuth substrate through the azimuth adapter shaft.

[0014] Further, the pitch rotation assembly includes a pitch base plate, a pitch bearing, a pitch adapter shaft, a pitch brake and an azimuth pitch adapter;

[0015] The azimuth-pitch adapter is fixedly connected to the azimuth base plate, the second stator of the pitch bearing is fixedly connected to the azimuth-pitch adapter, the second rotor of the pitch bearing is fixedly connected to the pitch base plate, the second brake plate of the pitch brake is installed on the azimuth-pitch adapter, and the second wire seat of the pitch brake is connected to the pitch base plate through the pitch adapter shaft.

[0016] Furthermore, the azimuth rotation assembly also includes an azimuth rotation handle, and the azimuth rotation handle is fixedly connected to the azimuth base plate.

[0017] Furthermore, the pitch rotation assembly also includes a pitch rotation handle, and the pitch rotation handle is fixedly connected to the pitch base plate.

[0018] Furthermore, the device also includes a frame reinforcement rib, which is fixedly connected to the azimuth base plate and the azimuth-pitch adapter.

[0019] Furthermore, the device also includes an azimuth brake switch and a pitch brake switch, wherein the azimuth brake switch is connected to the azimuth brake, and the pitch brake switch is connected to the pitch brake.

[0020] Furthermore, the azimuth brake switch and the pitch brake switch are foot-operated brake switches or hand-held brake switches.

[0021] The technical solution of the utility model has the following advantages:

[0022] The utility model provides a helicopter-borne artificial power inspection auxiliary device which can realize rotation in two directions of azimuth and pitch. The shock absorber in the base assembly can effectively isolate the high-frequency vibration caused by the helicopter to ensure clear imaging. At the same time, the azimuth brake switch and the pitch brake switch can realize braking in the azimuth and pitch directions, so that the photoelectric load can stably aim at a specific target. There is no need for inspection personnel to hold the photoelectric load for a long time, which can effectively reduce the labor intensity of the personnel and provide the possibility for imaging of large weight loads or multiple loads at the same time. At the same time, the overall structure of the device is simple and easy to disassemble and assemble. It can be adjusted according to changes in the helicopter and the installation position, and is easy to implement. At the same time, its design has the characteristics of easy manufacturing and low cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the specific implementation methods of the utility model or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0024] Figure 1 This is a schematic diagram of the location of the helicopter-borne manual power inspection auxiliary device installed on the helicopter;

[0025] Figure 2 This is the axonometric diagram of the helicopter-borne manual power inspection auxiliary device;

[0026] Figure 3 This is an exploded view of the base assembly;

[0027] Figure 4 This is an exploded view of a two-axis rotating component.

[0028] Description of reference numerals:

[0029] 1. Base assembly; 101. Shock absorber bottom plate; 102. Shock absorber; 103. Shock absorber top plate;

[0030] 104. shock absorber assembly fixing frame; 105. rotating assembly connecting plate;

[0031] 106. Rotating assembly fixing frame; 107. Height adjustment frame;

[0032] 2. Two-axis rotating assembly; 201. Azimuth transfer shaft; 202. Azimuth brake;

[0033] 203. Azimuth bearing; 204. Azimuth substrate; 205. Photoelectric load;

[0034] 206. Pitch base plate; 207. Pitch rotation handle; 208. Pitch bearing;

[0035] 209. Pitch transfer axis; 2010. Pitch brake; 2011. Azimuth rotation handle;

[0036] 2012. Frame reinforcement; 2013. Azimuth and pitch adapter;

[0037] 3. Window. DETAILED DESCRIPTION

[0038] The technical solution of the utility model will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0039] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0040] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0041] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0042] See also Figures 1 to 4 , a helicopter-borne artificial power inspection auxiliary device, comprising a base assembly 1 and a two-axis rotating assembly 2;

[0043] The base assembly 1 includes a shock absorbing assembly and a rotating assembly connecting plate 105, the bottom of the shock absorbing assembly is fixedly connected to the inside of the helicopter cabin and is located near the window 3, and the top of the shock absorbing assembly is fixedly connected to the rotating assembly connecting plate 105;

[0044] The two-axis rotation assembly 2 includes an azimuth rotation assembly, a pitch rotation assembly and an optoelectronic load 205. The azimuth rotation assembly is rotationally connected to the rotation assembly connecting plate 105, the pitch rotation assembly is rotationally connected to the azimuth rotation assembly, and the optoelectronic load 205 is fixedly connected to the pitch rotation assembly.

[0045] Please continue reading Figure 2 and Figure 3 In this embodiment, the shock absorbing assembly includes a shock absorber bottom plate 101, a shock absorber 102, a shock absorber top plate 103, a shock absorber assembly fixing frame 104 and a rotating assembly fixing frame 106;

[0046] The two ends of the shock absorber 102 are respectively fixedly connected to the shock absorber bottom plate 101 and the shock absorber top plate 103, the shock absorber top plate 103 is connected to the shock absorber assembly fixing frame 104, the shock absorber assembly fixing frame 104 is connected to the rotating assembly fixing frame 106, and the top of the rotating assembly fixing frame 106 is connected to the rotating assembly connecting plate 105; in this embodiment, a pair of shock absorber top plates 103 are arranged at the bottom of the rotating assembly fixing frame 106, and a pair of shock absorbers 102 are fixedly connected below the shock absorber top plates 103. The symmetrical structural design can better isolate the high-frequency vibration of the helicopter, thereby ensuring clear imaging of the optoelectronic payload 205. The specific setting method and number can be adjusted according to the actual usage scenario and needs.

[0047] Please continue reading Figure 3 , in this embodiment, the shock absorbing assembly further includes a height adjustment frame 107;

[0048] Multiple height adjustment frames 107 are evenly arranged between the rotating assembly fixed frame 106 and the shock absorber assembly fixed frame 104. The specific number and method of setting the height adjustment frames 107 are adjusted according to the helicopter model or installation position, thereby ensuring that the field of view of the optoelectronic payload 205 installed on the two-axis rotating platform will not be blocked.

[0049] Please continue reading Figure 3 and Figure 4 In this embodiment, the azimuth rotation assembly includes an azimuth adapter shaft 201, an azimuth brake 202, an azimuth bearing 203 and an azimuth base plate 204;

[0050] The first stator of the azimuth bearing 203 is fixedly connected to the rotating component connecting plate 105, and the first rotor of the azimuth bearing 203 is fixedly connected to the azimuth substrate 204, thereby realizing the relative rotation of the rotating component connecting plate 105 and the azimuth substrate 204. The azimuth brake 202 includes a first brake plate and a first wire seat, and the first brake plate is installed on the rotating component connecting plate 105. The first wire seat is connected to the azimuth substrate 204 through the azimuth adapter shaft 201. In the natural state, the first brake plate and the first wire seat of the azimuth brake 202 rotate relative to each other, and the brake plate and the wire seat can be controlled by a switch to be in a locked state.

[0051] Please continue reading Figure 2 and Figure 4 In this embodiment, the pitch rotation assembly includes a pitch base plate 206, a pitch bearing 208, a pitch adapter shaft 209, a pitch brake 2010 and an azimuth pitch adapter 2013;

[0052] The azimuth pitch adapter 2013 is fixedly connected to the azimuth base plate 204, the second stator of the pitch bearing 208 is fixedly connected to the azimuth pitch adapter 2013, and the second rotor of the pitch bearing 208 is fixedly connected to the pitch base plate 206, so as to realize the relative rotation between the azimuth pitch adapter 2013 and the pitch base plate 206. The pitch brake 2010 includes a second brake plate and a second wire seat, the second brake plate is installed on the azimuth pitch adapter 2013, and the second wire seat of the pitch brake 2010 is connected to the pitch base plate 206 through the pitch adapter shaft 209. In the natural state, the second brake plate and the second wire seat of the pitch brake 2010 rotate relative to each other, and the brake plate and the wire seat can be placed in a locked state by switch control; the photoelectric load 205 is installed on the pitch substrate 206 through an L-shaped connecting plate, and the position of the photoelectric load 205 in both the pitch and horizontal directions can be adjusted through the two-axis rotation component 2, which is convenient for the inspection personnel to aim at the target point. During actual use, multiple large-mass photoelectric loads 205 can be installed on the pitch substrate 206 at the same time, thereby realizing multi-band shooting of target defects.

[0053] Please continue reading Figure 4 In this embodiment, the azimuth rotation component also includes an azimuth rotation handle 2011, and the azimuth rotation handle 2011 is fixedly connected to the azimuth substrate 204. By providing the azimuth rotation handle 2011, it is convenient for inspection personnel to adjust and control the azimuth position.

[0054] Please continue reading Figure 4 In this embodiment, the pitch rotation assembly further includes a pitch rotation handle 207, and the pitch rotation handle 207 is fixedly connected to the pitch base plate 206 to facilitate inspection personnel to adjust and control the pitch position.

[0055] Please continue reading Figure 4In this embodiment, the device also includes a frame reinforcement rib 2012, which is fixedly connected to the azimuth substrate 204 and the azimuth-pitch adapter 2013. The frame reinforcement rib 2012 can be a triangle or other shape, and is used to connect the azimuth substrate 204 and the azimuth-pitch adapter 2013, thereby ensuring the rigidity of the entire device.

[0056] Please continue reading Figure 4 In this embodiment, the device also includes an azimuth brake switch and a pitch brake switch. The azimuth brake switch is connected to the azimuth brake 202, and the pitch brake switch is connected to the pitch brake 2010. The azimuth brake 202 and the pitch brake 2010 can be controlled to be in a locked state according to actual conditions through the azimuth brake switch and the pitch brake switch.

[0057] In this embodiment, the azimuth brake switch and the pitch brake switch are foot-operated brake switches, hand-held brake switches or other forms of brake switches, and the specific installation positions need to be set according to actual conditions.

[0058] The steps for using the helicopter-borne manual power inspection auxiliary device are as follows:

[0059] S1: Select appropriate shock absorbers 102 according to the total weight of the optoelectronic load 205 carried by the inspection task, select appropriate sizes and numbers of height adjustment frames 107 according to the helicopter model and installation location used in the inspection task, install the selected optoelectronic load 205 on the pitch substrate 206, and prepare to start the inspection operation;

[0060] S2: After the helicopter reaches the target inspection point, it remains in a hovering state. The inspection personnel adjust the position of the photoelectric load 205 by rotating the azimuth handle 2011 and the pitch rotation handle 207 to ensure that the target inspection point is within the field of view of the photoelectric load 205;

[0061] S3: Control the azimuth brake 202 and the pitch brake 2010 through the azimuth brake switch and the pitch brake switch respectively to make them locked, and then release the azimuth rotation handle 2011 and the pitch rotation handle 207. At this time, the helicopter-borne artificial power inspection auxiliary device remains stationary as a whole, and the inspection personnel can adjust the target inspection point and take pictures, and so on, until the shooting task of all inspection target points is completed.

[0062] The helicopter-mounted artificial power inspection auxiliary device can realize rotation in both azimuth and pitch directions. The shock absorber 102 in the base assembly can effectively isolate the high-frequency vibration caused by the helicopter to ensure clear imaging. At the same time, the azimuth brake switch and the pitch brake switch can realize braking in the azimuth and pitch directions, so that the photoelectric payload 205 can stably aim at a specific target. There is no need for inspection personnel to hold the photoelectric payload 205 for a long time, which can effectively reduce the labor intensity of personnel and provide the possibility for simultaneous imaging of large weight loads or multiple loads. At the same time, the overall structure of the device is simple and easy to disassemble and assemble. It can be adjusted according to changes in the helicopter and the installation position, and is easy to implement. At the same time, its design has the characteristics of easy manufacturing and low cost.

[0063] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention of the utility model.

Claims

1. A helicopter-mounted manual power inspection auxiliary device, characterized in that: It comprises a base assembly (1) and a two-axis rotating assembly (2); The base assembly (1) comprises a shock absorbing assembly and a rotating assembly connecting plate (105), the bottom of the shock absorbing assembly is fixedly connected to the interior of the helicopter cabin and is located near the window (3), and the top of the shock absorbing assembly is fixedly connected to the rotating assembly connecting plate (105); The two-axis rotation assembly (2) comprises an azimuth rotation assembly, a pitch rotation assembly and a photoelectric load (205); the azimuth rotation assembly is rotationally connected to the rotation assembly connecting plate (105); the pitch rotation assembly is rotationally connected to the azimuth rotation assembly; and the photoelectric load (205) is fixedly connected to the pitch rotation assembly.

2. The helicopter-mounted manual power inspection auxiliary device according to claim 1 is characterized in that: The shock absorbing assembly comprises a shock absorber bottom plate (101), a shock absorber (102), a shock absorber top plate (103), a shock absorber assembly fixing frame (104) and a rotating assembly fixing frame (106); The two ends of the shock absorber (102) are respectively fixedly connected to the shock absorber bottom plate (101) and the shock absorber top plate (103); the shock absorber top plate (103) is connected to the shock absorber assembly fixing frame (104); the shock absorber assembly fixing frame (104) is connected to the rotating assembly fixing frame (106); and the top of the rotating assembly fixing frame (106) is connected to the rotating assembly connecting plate (105).

3. The helicopter-mounted manual power inspection auxiliary device according to claim 2 is characterized in that: The shock absorbing assembly further comprises a height adjustment frame (107); A plurality of height adjustment frames (107) are evenly arranged between the rotating assembly fixing frame (106) and the shock absorber assembly fixing frame (104).

4. The helicopter-mounted manual power inspection auxiliary device according to claim 1 is characterized in that: The azimuth rotation assembly comprises an azimuth transfer shaft (201), an azimuth brake (202), an azimuth bearing (203) and an azimuth base plate (204); The first stator of the azimuth bearing (203) is fixedly connected to the rotating component connecting plate (105), the first rotor of the azimuth bearing (203) is fixedly connected to the azimuth base plate (204), the first brake plate of the azimuth brake (202) is mounted on the rotating component connecting plate (105), and the first wire seat of the azimuth brake (202) is connected to the azimuth base plate (204) via an azimuth adapter shaft (201).

5. The helicopter-mounted manual power inspection auxiliary device according to claim 4 is characterized in that: The pitch rotation assembly comprises a pitch base plate (206), a pitch bearing (208), a pitch adapter shaft (209), a pitch brake (2010) and an azimuth pitch adapter (2013); The azimuth-pitch adapter (2013) is fixedly connected to the azimuth base plate (204), the second stator of the pitch bearing (208) is fixedly connected to the azimuth-pitch adapter (2013), the second rotor of the pitch bearing (208) is fixedly connected to the pitch base plate (206), the second brake plate of the pitch brake (2010) is installed on the azimuth-pitch adapter (2013), and the second wire seat of the pitch brake (2010) is connected to the pitch base plate (206) via a pitch adapter shaft (209).

6. The helicopter-mounted manual power inspection auxiliary device according to claim 4 is characterized in that: The azimuth rotation component further comprises an azimuth rotation handle (2011), wherein the azimuth rotation handle (2011) is fixedly connected to the azimuth base plate (204).

7. The helicopter-mounted manual power inspection auxiliary device according to claim 5 is characterized in that: The pitch rotation assembly further comprises a pitch rotation handle (207), wherein the pitch rotation handle (207) is fixedly connected to the pitch base plate (206).

8. The helicopter-mounted manual power inspection auxiliary device according to claim 5 is characterized in that: The device also comprises a frame reinforcement rib (2012), wherein the frame reinforcement rib (2012) is fixedly connected to the azimuth base plate (204) and the azimuth-pitch adapter (2013).

9. The helicopter-mounted manual power inspection auxiliary device according to claim 5 is characterized in that: The device also includes an azimuth brake switch and a pitch brake switch, wherein the azimuth brake switch is connected to the azimuth brake (202) and the pitch brake switch is connected to the pitch brake (2010).

10. The helicopter-mounted manual power inspection auxiliary device according to claim 9, characterized in that: The azimuth brake switch and the pitch brake switch are foot-operated brake switches or hand-held brake switches.

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