CN209351594U - A kind of rotor wing unmanned aerial vehicle - Google Patents
A kind of rotor wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN209351594U CN209351594U CN201822011901.7U CN201822011901U CN209351594U CN 209351594 U CN209351594 U CN 209351594U CN 201822011901 U CN201822011901 U CN 201822011901U CN 209351594 U CN209351594 U CN 209351594U
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- fuselage
- aerial vehicle
- unmanned aerial
- connecting pin
- rotor wing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model discloses a kind of rotor wing unmanned aerial vehicle, which includes fuselage, detachable horn and control unit, and described control unit is arranged in fuselage；The fuselage side, which extends outwardly, is provided with connecting pin, and the detachable horn is mounted on the connecting pin；The connecting pin be with the integrally formed hollow connecting pin of fuselage, be provided with support plate in the fuselage, one end of the support plate is protruded into connecting pin.Rotor wing unmanned aerial vehicle according to the present utility model, one end of the support plate protrude into in the integrally formed hollow connecting pin of fuselage；The intensity of connecting pin and fuselage can effectively be reinforced, structure is simple, and the rotor wing unmanned aerial vehicle of the utility model can also ensure that the intensity of fuselage while mitigating and being self-possessed and reinforce and continuing a journey.
Description
Technical field
The utility model relates to a kind of unmanned plane more particularly to a kind of rotor wing unmanned aerial vehicles.
Background technique
UAV abbreviation unmanned plane is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft, the continuation of the journey of unmanned plane are a design focal point of the unmanned plane in design production process.Unmanned plane at this stage
Continuation of the journey is maintained by installing solar charging electrical component additional on unmanned plane, and unmanned plane can be made by the way that solar charging electrical component is arranged
Volume increases, and structure becomes complicated；Or the fuselage material by changing unmanned plane is self-possessed to mitigate unmanned plane, but this meeting
Cause the intensity of unmanned plane inadequate, is easily damaged.
Utility model content
The rotor wing unmanned aerial vehicle that the purpose of the utility model is to provide a kind of structures is simple, intensity is high.
The utility model is achieved through the following technical solutions: providing a kind of rotor wing unmanned aerial vehicle, the rotor wing unmanned aerial vehicle includes
Fuselage, detachable horn and control unit, described control unit are arranged in fuselage；The fuselage side, which extends outwardly, to be provided with
Connecting pin, the detachable horn are mounted on the connecting pin；The connecting pin is and the integrally formed hollow company of fuselage
End is connect, support plate is provided in the fuselage, one end of the support plate is protruded into connecting pin.
As a further improvement of the above technical scheme, the support plate includes being used to support the support of described control unit
The reinforcement end in connecting pin is held and protrudes into, the support plate fits with fuselage inner wall.
As a further improvement of the above technical scheme, described control unit includes battery, control circuit board and is used for
The mounting plate of battery and control circuit board is installed, the battery is mounted on the upside of mounting plate, and the control circuit board is mounted on
The downside of mounting plate, the mounting plate are connected with the support end of the support plate.
As a further improvement of the above technical scheme, the detachable horn includes linking arm and installs on the connecting arm
Wing, the linking arm is connected with the mode that the connecting pin is connected through a screw thread.
As a further improvement of the above technical scheme, the linking arm is hollow linking arm.
As a further improvement of the above technical scheme, there are six the detachable horn and connecting pin are respectively provided with.
As an alternative to the above-described technical solution, there are four the detachable horn and connecting pin be respectively provided with.
As a further improvement of the above technical scheme, the rotor wing unmanned aerial vehicle further includes the top cover being mounted on the upside of fuselage
With the undercarriage being mounted on the downside of fuselage.
As a further improvement of the above technical scheme, the carbon fiber fuselage that the fuselage is integrally formed.
The beneficial effects of the utility model include at least: in the rotor wing unmanned aerial vehicle of the utility model, the rotor wing unmanned aerial vehicle
Including fuselage, detachable horn；The fuselage side extends outwardly the connecting pin for being provided with and connecting detachable horn；The connection
End for the integrally formed hollow connecting pin of fuselage, be provided with support plate in fuselage, connection is protruded into one end of the support plate
In end；Support plate one end is protruded into connecting pin, can effectively reinforce the intensity of connecting pin, structure is simple, the utility model
Rotor wing unmanned aerial vehicle can also ensure that the intensity of fuselage while mitigating and being self-possessed and reinforce and continuing a journey.
Detailed description of the invention
Fig. 1 is the stereoscopic schematic diagram of the rotor wing unmanned aerial vehicle of first embodiment according to the present utility model；
Fig. 2 is the fuselage of first embodiment according to the present utility model and the stereoscopic schematic diagram of support plate；
Fig. 3 is the stereoscopic schematic diagram of the fuselage of first embodiment according to the present utility model；
Fig. 4 is the schematic side view of the support plate of first embodiment according to the present utility model；
Fig. 5 is the fuselage of first embodiment according to the present utility model and the schematic cross-sectional view of support plate；
Fig. 6 is the fuselage of first embodiment according to the present utility model and the stereoscopic schematic diagram of control unit；
Fig. 7 is the schematic side view of the control unit of first embodiment according to the present utility model；
Fig. 8 is the stereoscopic schematic diagram of the detachable horn of first embodiment according to the present utility model；
Fig. 9 is the stereoscopic schematic diagram of the rotor wing unmanned aerial vehicle of second embodiment according to the present utility model.
List of reference numerals: 100- rotor wing unmanned aerial vehicle；1- fuselage；The detachable horn of 2-；3- control unit；The connecting pin 11-；12-
Support plate；121- support end；122- reinforces end；31- battery；32- control circuit board；33- mounting plate；21- linking arm；22- machine
The wing；4- top cover；5- undercarriage.
Specific embodiment
Below in conjunction with attached drawing in the embodiments of the present invention, the technical scheme in the embodiment of the utility model is carried out
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.The component of the utility model embodiment being usually described and illustrated herein in the accompanying drawings can be with a variety of different configurations
To arrange and design.Therefore, below the detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit
The range of claimed invention processed, but it is merely representative of the selected embodiment of the utility model.It is practical new based on this
The embodiment of type, those skilled in the art's every other embodiment obtained without making creative work,
It fall within the protection scope of the utility model.
First embodiment
Firstly, the rotor wing unmanned aerial vehicle 100 being related to referring to figs. 1 to first embodiment of the Fig. 8 to the utility model is illustrated
As shown in Figure 1 to Figure 3, a kind of rotor wing unmanned aerial vehicle 100, the rotor wing unmanned aerial vehicle 100 include fuselage 1, removable unload the goods from the airplane
Arm 2 and control unit 3, described control unit 3 are arranged in fuselage 1；1 side of fuselage, which extends outwardly, is provided with connecting pin
11, the detachable horn 2 is mounted on the connecting pin 11；The connecting pin 11 is integrally formed hollow with fuselage 1
Connecting pin 11 is provided with support plate 12 in the fuselage 1, and one end of the support plate 12 is protruded into connecting pin 11.The fuselage
The 1 carbon fiber fuselage being integrally formed, light weight and intensity are high.
The utility model using the detachable horn 2 that can be freely disassembled, install so that the installation of rotor wing unmanned aerial vehicle 100 with
And maintenance is simpler, the detachable horn 2 that such as damage of detachable horn 2 need to only remove damage is replaced.Detachable horn
2 driving device can be connected by hollow connecting pin 11 with control unit 3.Integrally formed hollow 11 energy of connecting pin
The enough weight for effectively mitigating unmanned plane itself, 12 one end of support plate being arranged in fuselage 1 are protruded into connecting pin 11, can be effective
Reinforcement connecting pin intensity so that the rotor wing unmanned aerial vehicle 100 of the utility model mitigate be self-possessed reinforce continuation of the journey while can also
Enough guarantee the intensity of fuselage.
Refering to Fig. 4 and Fig. 5, in the present embodiment, the support plate 12 includes being used to support the support of described control unit 3
It holds 121 and protrudes into the reinforcement end 122 in connecting pin 11, the support plate 12 fits with 1 inner wall of fuselage.Support plate 1 and machine
1 inner wall of body, which fits, can effectively reinforce the intensity of fuselage 1, and control unit 3 is mounted on support end 121, the support plate 12
The intensity for being used not only for reinforcing fuselage 1 can also provide installation and support for control unit 3, without by separately setting support
Or fixed device is supported and installs to control unit 3, so that the structure of rotor wing unmanned aerial vehicle 100 is simpler, and can subtract
It is aggravated less using other supports or fixed device bring quality, enhances cruising ability.
Refering to Fig. 6 and Fig. 7, in the present embodiment, described control unit 3 includes battery 31, control circuit board 32 and uses
In the mounting plate 33 of installation battery 31 and control circuit board 32, the battery 31 is mounted on the upside of mounting plate 33, the control
Circuit board 32 is mounted on the downside of mounting plate 33, and the mounting plate 33 is connected with the support end 121 of the support plate 12.
As shown in figure 8, in the present embodiment, the detachable horn 2 includes linking arm 21 and is mounted on linking arm 21
Wing 22, the linking arm 21 is connected with the mode that the connecting pin 11 is connected through a screw thread.It is set on the connecting pin 11
It is equipped with screw thread, the end of the linking arm 21 is provided with the thread bush to match with the screw thread on connecting pin 11, by rotating spiral shell
Line covers so that linking arm 21 is connected with connecting pin 11
In the present embodiment, the linking arm 21 is hollow linking arm 21.Use can be set in hollow linking arm 21
The route with control unit 3, and hollow 21 light weight of linking arm are driven in connection wing, can effectively enhance cruising ability.
Refering to fig. 1, in the present embodiment, there are six the detachable horn 2 and connecting pin 11 are respectively provided with.In the present embodiment
In, the global shape of the fuselage 1 is similar to circle, and the detachable horn 2 and connecting pin 11 are equidistantly set around the side of fuselage 1
It sets.
In the present embodiment, the rotor wing unmanned aerial vehicle 100 further includes being mounted on the top cover 4 of 1 upside of fuselage and being mounted on machine
The undercarriage 5 of 1 downside of body.The top cover 4 and undercarriage 5 can be mounted on machine by the various ways such as being clamped or be screwed
On body 1, since this is common knowledge well-known to those skilled in the art, details are not described herein.
Second embodiment
Then, referring to Fig. 9, the rotor wing unmanned aerial vehicle 100b that the second embodiment of the utility model is related to is illustrated.This
Outside, unless stated otherwise, the composition for the rotor wing unmanned aerial vehicle 100 that second embodiment is related to, in first embodiment referring to figs. 1 to figure
The composition of 8 explanations is identical.Hereinafter, in the composition for the rotor wing unmanned aerial vehicle 100b being mainly related to second embodiment with first embodiment
Different composition parts are illustrated, and are simply said to the identical structure of the rotor wing unmanned aerial vehicle 100 being related to first embodiment
It is bright.
In the present embodiment, there are four the detachable horn 2b and connecting pin 11b is respectively provided with.In the present embodiment, institute
The global shape for stating fuselage 1b is similar to rectangle, four in the side of fuselage 1b of the detachable horn 2b and connecting pin 11b
At angle.
While there has been shown and described that the embodiments of the present invention in the description of the present invention, this field
Those of ordinary skill be understood that in the case where not departing from the principles of the present invention and objective can to these embodiments into
The a variety of change, modification, replacement and modification of row, the scope of the utility model are defined by the claims and their equivalents.
Claims (9)
1. a kind of rotor wing unmanned aerial vehicle, which is characterized in that the rotor wing unmanned aerial vehicle includes fuselage (1), detachable horn (2) and control
Unit (3), described control unit (3) are arranged in fuselage (1)；Fuselage (1) side, which extends outwardly, is provided with connecting pin
(11), the detachable horn (2) is mounted on the connecting pin (11)；The connecting pin (11) be with fuselage (1) one at
The hollow connecting pin (11) of type is provided with support plate (12) in the fuselage (1), and company is protruded into one end of the support plate (12)
It connects in end (11).
2. rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the support plate (12) is described including being used to support
The support end (121) of control unit (3) and the reinforcement end (122) in connecting pin (11) is protruded into, the support plate (12) and machine
Body (1) inner wall fits.
3. rotor wing unmanned aerial vehicle according to claim 2, which is characterized in that described control unit (3) includes battery (31), control
Circuit board (32) processed and mounting plate (33) for installing battery (31) and control circuit board (32), battery (31) installation
In the upside of mounting plate (33), the control circuit board (32) is mounted on the downside of mounting plate (33), the mounting plate (33) with
The support end (121) of the support plate (12) is connected.
4. rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the detachable horn (2) includes linking arm
(21) it is connected through a screw thread with the wing (22) that is mounted on linking arm (21), the linking arm (21) with the connecting pin (11)
Mode be connected.
5. rotor wing unmanned aerial vehicle according to claim 4, which is characterized in that the linking arm (21) is hollow linking arm
(21)。
6. rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the detachable horn (2) and connecting pin (11)
There are six being respectively provided with.
7. rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the detachable horn (2) and connecting pin (11)
There are four being respectively provided with.
8. rotor wing unmanned aerial vehicle according to claim 1, which is characterized in that the rotor wing unmanned aerial vehicle further includes being mounted on fuselage
(1) top cover (4) on the upside of and the undercarriage (5) being mounted on the downside of fuselage (1).
9. rotor wing unmanned aerial vehicle according to any one of claims 1 to 8, which is characterized in that the fuselage (1) is integrally formed
Carbon fiber fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822011901.7U CN209351594U (en) | 2018-11-30 | 2018-11-30 | A kind of rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822011901.7U CN209351594U (en) | 2018-11-30 | 2018-11-30 | A kind of rotor wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209351594U true CN209351594U (en) | 2019-09-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822011901.7U Active CN209351594U (en) | 2018-11-30 | 2018-11-30 | A kind of rotor wing unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN209351594U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113525697A (en) * | 2021-07-20 | 2021-10-22 | 北京长征天民高科技有限公司 | Fuel cell unmanned aerial vehicle |
-
2018
- 2018-11-30 CN CN201822011901.7U patent/CN209351594U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113525697A (en) * | 2021-07-20 | 2021-10-22 | 北京长征天民高科技有限公司 | Fuel cell unmanned aerial vehicle |
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