CN205150227U - Tour aircraft of high -voltage line - Google Patents
Tour aircraft of high -voltage line Download PDFInfo
- Publication number
- CN205150227U CN205150227U CN201520798250.4U CN201520798250U CN205150227U CN 205150227 U CN205150227 U CN 205150227U CN 201520798250 U CN201520798250 U CN 201520798250U CN 205150227 U CN205150227 U CN 205150227U
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- Prior art keywords
- bar
- aircraft
- tension bus
- described main
- control module
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Abstract
The utility model discloses a tour aircraft of high -voltage line, its include a fuselage, with a plurality of horns of fuselage fixed connection, set up power device, a host system, a wireless receiver and a camera carry cloud platform system on each horn, host system, wireless receiver and camera carry cloud platform system configuration in on the fuselage, tour aircraft of high -voltage line still includes a shielding part, the shielding part covers host system.
Description
Technical field
The utility model, about a kind of aircraft, particularly relates to a kind of aircraft making an inspection tour high-tension bus-bar.
Background technology
In recent years, unmanned vehicle has been widely used in various field, such as, and Aerial photography or monitoring, scientific research, geological exploration, remote sensing etc.But unmanned vehicle is easily subject to the interference of electromagnetism and electric field in flight course, affects circuit and the controlled in wireless of unmanned vehicle, thus affect the normal operation of unmanned vehicle.Such as, when unmanned vehicle is used in the tour of high-tension bus-bar defect and hidden danger by people, because high-tension bus-bar can produce stronger electric field, existing unmanned vehicle is often subject to the impact of this electric field, thus affects the tour of unmanned vehicle to high-tension bus-bar.
Utility model content
In view of the foregoing, be necessary to provide a kind of not easily by the aircraft of the tour high-tension bus-bar of electric field influence.
A kind of aircraft making an inspection tour high-tension bus-bar, it comprises a fuselage, the some horns be fixedly connected with described fuselage, the engine installation be arranged on each horn, a main control module, a wireless receiver and a camera carry clouds terrace system, described main control module, wireless receiver and camera carry clouds terrace system are arranged on described fuselage, the aircraft of described tour high-tension bus-bar also comprises a shielding part, and described shielding part covers described main control module.
The aircraft of tour high-tension bus-bar of the present utility model, described shielding part covers described main control module, make the aircraft of described tour high-tension bus-bar when making an inspection tour high-tension bus-bar, weaken the electric field of high-tension bus-bar generation to the harmful effect of described main control module, thus make the aircraft normal operation of described tour high-tension bus-bar.
Accompanying drawing explanation
Fig. 1 is the schematic perspective view of the aircraft of the tour high-tension bus-bar of the utility model embodiment.
Fig. 2 is the generalized section of the aircraft of the tour high-tension bus-bar shown in Fig. 1.
Fig. 3 is the generalized section of the aircraft of the tour high-tension bus-bar of another embodiment of the utility model.
main element nomenclature
Detailed description of the invention
Refer to Fig. 1 and Fig. 2, embodiment of the present utility model provides a kind of aircraft 100 making an inspection tour high-tension bus-bar, and it comprises fuselage 10, the some horns 20 be fixedly connected with described fuselage 10, is arranged on each horn 20 for the engine installation 30 driving the aircraft 100 of described tour high-tension bus-bar to fly, main control module 40, wireless receiver 50 and the shielding part 60 be arranged on described fuselage 10.Described shielding part 60 covers described main control module 40.
Described fuselage 10 comprises substrate 11 and is formed at the main part 13 on described substrate 11.Described main part 13, in hollow, can be used for holding the electronic components such as power supply (not shown).
Described horn 20 is fixedly connected on described main part 13.In present embodiment, the quantity of described horn 20 is four, and described four horns 20 are roughly connected to main part 13 in " ten " font.
Each engine installation 30 comprises rotor 31 and actuator 33.Described rotor 31 is fixedly connected on described actuator 33.In present embodiment, described rotor 31 is two oars.Be appreciated that described rotor can also be other forms such as three oars.Described actuator 33 is fixedly connected on corresponding horn 20, rotates thus drive the aircraft 100 of described tour high-tension bus-bar to fly for rotor described in actuator 31.
Described main control module 40 is arranged at the surface of described main part 13 away from described substrate 11.Described main control module 40 is connected with described power electric.Be appreciated that described main control module 40 can be formed at other positions of fuselage 11.
Described wireless receiver 50 is placed in the described main body 13 in hollow, and corresponding described main control module 40 is arranged.Described wireless receiver 50 is electrically connected with described power supply, described main control module 40.The wireless control signal that described wireless receiver 50 is launched for receiving remote control equipment (RCE) (not shown), and described wireless control signal is converted to electric signal.Described main control module 40 obtains described electric signal and carries out operation according to the aircraft 100 that described electric signal controls described tour high-tension bus-bar.In present embodiment, described wireless receiver 50 is provided with to code button (not shown) with to code indicator lamp (not shown), so that the aircraft 100 debugging described tour high-tension bus-bar is connected with remote control equipment (RCE).
Described shielding part 60 is formed at the surface of described main part 13 away from described substrate 11, and covers described main control module 40.Because described shielding part 60 covers described main control module 40, at the aircraft 100 of described tour high-tension bus-bar when making an inspection tour high-tension bus-bar, weaken the harmful effect that brings of the impact of electric field on described main control module 40 that high-tension bus-bar produces.In present embodiment, described shielding part 60 is a shielding box.
The aircraft 100 of described tour high-tension bus-bar also comprises one and is arranged at the camera carry clouds terrace system (not shown) of described substrate 11 away from the surface of described main part 13, and it comprises camera, damping module, increases steady module.The aircraft 100 of described tour high-tension bus-bar controls described camera by remote control equipment (RCE) and makes an inspection tour high-tension bus-bar circuit, thus searches defect and the hidden danger of circuit.
The aircraft 100 of described tour high-tension bus-bar also can comprise a foot rest (not shown), and it is arranged at the surface of described substrate 11 away from described main part 13.Described foot rest is fixedly connected on described substrate 11 by fastener (not shown).The aircraft 100 of described tour high-tension bus-bar is supported in ground by foot rest.
In another embodiment, refer to Fig. 3, the contiguous described main part 13 of described wireless receiver 50 is arranged on described substrate 11.
In the third embodiment, it is in hollow body portion 13 that described main control module 40 is placed in described, and the contiguous described main part 13 of described wireless receiver 50 is arranged on described substrate 11.Now, described shielding part 60 is a screened film, and it is covered in the inwall of described main part 13.
Be appreciated that described four horns 20 can be roughly that " X " font is connected to main part 13.
Being appreciated that the quantity of described horn 20 is not defined as four, can also be six, eight etc.Described horn 20 with the center shaft of described fuselage 10 for center of circle circumference is evenly connected to described fuselage 10.The quantity of described engine installation 30 is identical with the quantity of described horn 20.
Be appreciated that described fuselage 10 can be one-body molded with described horn 20.
In the aircraft 100 of the tour high-tension bus-bar of embodiment of the present utility model, described shielding part 60 covers described main control module 40, make the aircraft 100 of described tour high-tension bus-bar when making an inspection tour high-tension bus-bar, weaken the electric field of high-tension bus-bar generation to the harmful effect of described main control module 40, thus make aircraft 100 normal operation of described tour high-tension bus-bar.
Note, above are only preferred embodiment of the present utility model and institute's application technology principle.Skilled person in the art will appreciate that the utility model is not limited to specific embodiment described here, various obvious change can be carried out for a person skilled in the art, readjust and substitute and protection domain of the present utility model can not be departed from.Therefore, although be described in further detail the utility model by above embodiment, but the utility model is not limited only to above embodiment, when not departing from the utility model design, can also comprise other Equivalent embodiments more, and scope of the present utility model is determined by appended right.
Claims (8)
1. make an inspection tour the aircraft of high-tension bus-bar for one kind, it comprises a fuselage, the some horns be fixedly connected with described fuselage, the engine installation be arranged on each horn, a main control module, a wireless receiver and a camera carry clouds terrace system, described main control module, wireless receiver and camera carry clouds terrace system are arranged on described fuselage, it is characterized in that: the aircraft of described tour high-tension bus-bar also comprises a shielding part, and described shielding part covers described main control module.
2. the aircraft making an inspection tour high-tension bus-bar as claimed in claim 1, it is characterized in that: described fuselage comprises substrate and is formed at the main part on described substrate, described main control module is arranged at the surface of described main part away from described substrate, described shielding part covers described main control module, and described shielding part is a shielding box.
3. the aircraft making an inspection tour high-tension bus-bar as claimed in claim 2, it is characterized in that: described main part is hollow, described wireless receiver is placed in described main part.
4. the aircraft making an inspection tour high-tension bus-bar as claimed in claim 2, is characterized in that: the contiguous described main part of described wireless receiver is arranged on described substrate.
5. the aircraft making an inspection tour high-tension bus-bar as claimed in claim 4, it is characterized in that: described main part is hollow, described main control module is placed in described main part, described shielding part is a screened film, this screened film covers the inwall of described main part, and the contiguous described main part of described wireless receiver is arranged on described substrate.
6. the aircraft making an inspection tour high-tension bus-bar as claimed in claim 1, is characterized in that: described camera carry clouds terrace system comprises camera, damping module, increases steady module, and described main control module camera according to the signal control received is taken.
7. the aircraft making an inspection tour high-tension bus-bar as claimed in claim 1, it is characterized in that: each engine installation comprises rotor and actuator, described rotor is fixedly connected on described actuator, and described actuator is fixedly connected with a horn.
8. the aircraft making an inspection tour high-tension bus-bar as claimed in claim 2, it is characterized in that: the aircraft of described tour high-tension bus-bar also comprises a foot rest, described foot rest is arranged at the surface of described substrate away from described main part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520798250.4U CN205150227U (en) | 2015-10-15 | 2015-10-15 | Tour aircraft of high -voltage line |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520798250.4U CN205150227U (en) | 2015-10-15 | 2015-10-15 | Tour aircraft of high -voltage line |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205150227U true CN205150227U (en) | 2016-04-13 |
Family
ID=55685945
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520798250.4U Expired - Fee Related CN205150227U (en) | 2015-10-15 | 2015-10-15 | Tour aircraft of high -voltage line |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205150227U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173069A (en) * | 2015-10-15 | 2015-12-23 | 厦门理工学院 | Aircraft for inspecting high-voltage line |
| CN108227743A (en) * | 2018-01-12 | 2018-06-29 | 国网福建省电力有限公司 | Improve for pass through unwrapping wire unmanned plane performance method and pass through line-putting method |
-
2015
- 2015-10-15 CN CN201520798250.4U patent/CN205150227U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173069A (en) * | 2015-10-15 | 2015-12-23 | 厦门理工学院 | Aircraft for inspecting high-voltage line |
| CN108227743A (en) * | 2018-01-12 | 2018-06-29 | 国网福建省电力有限公司 | Improve for pass through unwrapping wire unmanned plane performance method and pass through line-putting method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160413 Termination date: 20181015 |