CN205293074U - Unmanned aerial vehicle with multiple rotor wings - Google Patents
Unmanned aerial vehicle with multiple rotor wings Download PDFInfo
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- CN205293074U CN205293074U CN201521016965.6U CN201521016965U CN205293074U CN 205293074 U CN205293074 U CN 205293074U CN 201521016965 U CN201521016965 U CN 201521016965U CN 205293074 U CN205293074 U CN 205293074U
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- fuselage
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Abstract
The utility model provides an unmanned aerial vehicle with multiple rotor wings, its characterized in that: it includes fuselage (1), a set of horizontal direction distribution constant head tank (2) of following of equipartition on fuselage (1), set up a set of cantilever (3), one end at every cantilever (3) is equipped with mounting platform (3a), be equipped with motor (5) and blade (5a) at mounting platform (3a), it corresponds complex grafting platform (3b) with constant head tank (2) to be equipped with at the other end of cantilever (3), and two platforms are the level setting, it has a set of supporting leg (4) still to articulate in the lower part of fuselage (1), fuselage (1) still be connected with battery (6), control module (7), positioner (8) and camera (9). The utility model discloses simple structure, convenient to use after the cantilever installation targets in place, need not the debugging and makes level, has shortened the time of single item production, has improved production efficiency, the cost is reduced.
Description
Technical field:
This utility model relates to a kind of aircraft, is exactly a kind of many rotor wing unmanned aerial vehicles specifically.
Background technology:
Many rotor wing unmanned aerial vehicles, are start a kind of aircraft practical gradually at present, its have maneuverability, reaction quickly, unmanned flight, operation require the advantages such as low. Unmanned plane loads multiclass sensor, such as photographic head, image real-time Transmission, high-risk areas detecting function can be realized, be widely used in the fields such as fire-fighting, military affairs, traffic, police service, exploration and meteorology, to realize cruise shooting and the supervision of specifying region.
At present, typically no on the body of many rotor wing unmanned aerial vehicles shell be set or be provided only with simple shell, it is not provided with shell or only arranges that unmanned plane wind resistance in flight course of simple shell is poor, flight resistance big, adding the energy consumption of unmanned plane, shorten the cruise time of unmanned plane.
Additionally, due to many rotor wing unmanned aerial vehicles have multiple rotor, so the installation of rotor and debugging are also relatively complicated, which increases the cycle of production, virtually raise the price of many rotor wing unmanned aerial vehicles, reduced the market competitiveness of many rotor wing unmanned aerial vehicles, hinder the popular development of many rotor wing unmanned aerial vehicles.
Utility model content:
This utility model is exactly for overcoming deficiency of the prior art, it is provided that a kind of simple in construction, easy to use, many rotor wing unmanned aerial vehicles that time that single product produce is short.
This utility model provides techniques below scheme:
A kind of many rotor wing unmanned aerial vehicles, it is characterized in that: it includes fuselage, uniform one group of Distribution and localization groove in the horizontal direction on fuselage, one group of cantilever is set, it is provided with mounting platform in one end of each cantilever, motor and blade it is provided with at mounting platform, the other end at cantilever is provided with and the grafting platform of the locating slot corresponding matching on fuselage, and two platform be and be horizontally disposed with, one group of supporting fuselage lower limb also it is hinged with in the bottom of fuselage, described fuselage is also associated with power supply, controls module, positioner and video camera.
On the basis of technique scheme, it is also possible to have technical scheme further below:
Described fuselage is to be made up of upper body plate and lower body plate, two body plates are evenly equipped with the locating slot being distributed in the horizontal direction, and the notch of the upper and lower locating slot on body plate is mutually corresponding, the bottom land of the locating slot on upper and lower body plate is additionally provided with one group of installing hole, is provided with installation bolt in installing hole.
With grafting platform not in the same plane, described mounting platform is slightly above grafting platform for the described mounting platform on cantilever.
Described cantilever with supporting leg are respectively equipped with one group of air-permeating hole.
The utility model has the advantage of:
This utility model simple in construction, easy to use, particularly fuselage is provided with the locating slot of horizontal distribution and matches with the grafting platform that is horizontally disposed with on cantilever, it is possible to quickly finishes fuselage and is connected with cantilever, simultaneously because cantilever also ensures that on horizontally disposed mounting platform, motor mounting plane, cantilever connect plane, fuselage plane, the horizontal distribution of three so that cantilever is installed after putting in place, levelling without debugging, shorten the time that single product produce, improve production efficiency, reduce cost.
Accompanying drawing illustrates:
Fig. 1 is this utility model axonometric chart;
Fig. 2 is the top view of Fig. 1;
Fig. 3 is the A-A sectional view in Fig. 2;
Fig. 4 is the B item enlarged drawing in Fig. 3;
Fig. 5 is attitude schematic diagram during this utility model flight.
Detailed description of the invention:
As Figure 1-5, a kind of many rotor wing unmanned aerial vehicles, it includes a horizontally disposed fuselage 1, and described fuselage 1 is to be that foursquare upper body plate 1a and lower body plate 1b is constituted by profile. It is equipped with chamfering 1c at the corner place of two body plates, it is provided with the locating slot 2 being distributed in the horizontal direction to the center position of body plate at the chamfering 1c place of two body plates, and the notch of the upper and lower locating slot 2 on body plate is mutually corresponding, the bottom land of the locating slot 2 on upper and lower body plate is additionally provided with one group of installing hole 2a, is provided with installation bolt 2b in installing hole 2a. The bottom land of described locating slot 2 and upper body plate 1a and lower body plate 1b are parallel to each other, and are and are horizontally disposed with.
One group of cantilever 3 is set, being provided with the mounting platform 3a of a level in one end of each cantilever 3, be provided with motor 5 at mounting platform 3a, the output shaft 5b upper end above motor 5 is provided with blade 5a, and described output shaft 5b and mounting platform 3a is perpendicular, namely blade 5a and mounting platform 3a is parallel to each other.
The other end at cantilever 3 is provided with the grafting platform 3b with locating slot 2 corresponding matching, described grafting platform 3b also for being horizontally disposed with, and is additionally provided with the screw of a group and the installing hole 2a corresponding matching on described upper and lower body plate on grafting platform 3b.
Not in the same plane, and described mounting platform 3a is slightly above grafting platform 3b for the described mounting platform 3a on cantilever 3 and grafting platform 3b. It is being additionally provided with one group of air-permeating hole 10 with the arm of mounting platform 3a, grafting platform 3b and cantilever 3. The design of this air-permeating hole reduction air drag when reducing all right flight of the present invention while the deadweight of cantilever 3.
During installation, the upper surface of grafting platform 3b is inserted in the horizontal direction respectively with lower surface in the locating slot 2 on upper body plate 1a and lower body plate 1b, then pass through installation bolt 2b and grafting platform 3b and upper body plate 1a and lower body plate 1b is linked together.
Owing to fuselage 1, locating slot 2, grafting platform 3b and mounting platform 3a are and are horizontally disposed with, so after just grafting platform 3b is connected to fuselage 1, being the state of mutual horizontal parallel between mounting platform 3a and fuselage 1, therefore also just eliminate the operation that debugging is levelling.
It is provided with a pair hinged seat 4a in the bottom of lower body plate 1b, a connector 4b all it is hinged with in each hinged seat 4a, a longitudinal bracing post 4c it is respectively connected with in one end of each connector 4b, being provided with cross-brace frame 4d in the mounting groove of the bottom of longitudinal bracing post 4c, described longitudinal bracing post 4c and cross-brace frame 4d constitutes supporting fuselage lower limb 4.It is equipped with one group of air-permeating hole 10 at longitudinal bracing post 4c and cross-brace frame 4d.
Air-permeating hole 10 design reduce supporting fuselage lower limb deadweight at the same time it can also be play reduce flight time air drag effect. Additionally, the design of hinged seat and connector makes supporting fuselage lower limb 4 can pack up when leaving ground, effectively improve the skyborne anti-gas flow capability of fuselage, improve the stability of fuselage, reduce operation easier, also reduce the deadweight of supporting fuselage lower limb 4.
It is provided with power supply 6 at described upper body plate 1a, the upper body plate of power supply 6 side is additionally provided with positioner 8, lower body plate 1b is provided with control module 7, the height of described control module 7 is less than the spacing between upper body plate 1a and lower body plate 1b, so that air-flow passes through between upper and lower body plate, play the effect reducing windage. Signal receiving/transmission device 8a and video camera 9 it is also associated with bottom lower body plate 1b.
Claims (4)
1. rotor wing unmanned aerial vehicle more than a kind, it is characterized in that: it includes fuselage (1), in upper uniform one group of Distribution and localization groove (2) in the horizontal direction of fuselage (1), one group of cantilever (3) is set, it is provided with mounting platform (3a) in one end of each cantilever (3), motor (5) and blade (5a) it is provided with at mounting platform (3a), the other end at cantilever (3) is provided with the grafting platform (3b) with locating slot (2) corresponding matching, and two platform be and be horizontally disposed with, one group of supporting fuselage lower limb (4) also it is hinged with in the bottom of fuselage (1), described fuselage (1) is also associated with power supply (6), control module (7), positioner (8) and video camera (9).
2. the many rotor wing unmanned aerial vehicles of one according to claim 1, it is characterized in that: described fuselage (1) is to be made up of upper body plate (1a) and lower body plate (1b), two body plates are evenly equipped with the locating slot (2) being distributed in the horizontal direction, and the notch of the upper and lower locating slot (2) on body plate is mutually corresponding, the bottom land of the locating slot (2) on upper and lower body plate is additionally provided with one group of installing hole (2a), is provided with installation bolt (2b) in installing hole (2a).
3. the many rotor wing unmanned aerial vehicles of one according to claim 1, it is characterised in that: with grafting platform (3b) not in the same plane, described mounting platform (3a) is slightly above grafting platform (3b) for the described mounting platform (3a) on cantilever (3).
4. the many rotor wing unmanned aerial vehicles of one according to claim 1, it is characterised in that: on described cantilever (3) with supporting leg (4), it is respectively equipped with one group of air-permeating hole (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521016965.6U CN205293074U (en) | 2015-12-09 | 2015-12-09 | Unmanned aerial vehicle with multiple rotor wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521016965.6U CN205293074U (en) | 2015-12-09 | 2015-12-09 | Unmanned aerial vehicle with multiple rotor wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205293074U true CN205293074U (en) | 2016-06-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521016965.6U Active CN205293074U (en) | 2015-12-09 | 2015-12-09 | Unmanned aerial vehicle with multiple rotor wings |
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| Country | Link |
|---|---|
| CN (1) | CN205293074U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416577A (en) * | 2015-12-09 | 2016-03-23 | 施恒锦 | Multi-rotor unmanned aerial vehicle |
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2015
- 2015-12-09 CN CN201521016965.6U patent/CN205293074U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416577A (en) * | 2015-12-09 | 2016-03-23 | 施恒锦 | Multi-rotor unmanned aerial vehicle |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |