CN206437196U - A kind of vee tail unmanned plane of the foldable rotor arm of band - Google Patents
A kind of vee tail unmanned plane of the foldable rotor arm of band Download PDFInfo
- Publication number
- CN206437196U CN206437196U CN201720128998.2U CN201720128998U CN206437196U CN 206437196 U CN206437196 U CN 206437196U CN 201720128998 U CN201720128998 U CN 201720128998U CN 206437196 U CN206437196 U CN 206437196U
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- CN
- China
- Prior art keywords
- rotor arm
- unmanned plane
- vee tail
- folding
- folding rotor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a kind of vee tail unmanned plane of the foldable rotor arm of band, belongs to unmanned plane field to solve existing unmanned plane and generally carries out course changing control and using fixed rotor arm by the speed difference of coaxial propellers, there is the inflexible problem of steering.The utility model is provided with foldable rotor arm, is directly realized by the portable easily contained demand of aircraft；The utility model is due to being provided with V-type tail, and two propellers after two on foldable rotor arm are in that angle is identical with horizontal plane, directly provide the power of left rotation and right rotation, realize fast steering, the demand of stability contorting.
Description
Technical field
The utility model is related to a kind of unmanned plane, more particularly, to a kind of vee tail unmanned plane of the foldable rotor arm of band.
Background technology
Unmanned plane is the abbreviation of UAV, is to utilize radio robot and the presetting apparatus provided for oneself behaviour
Vertical not manned aircraft.Without driving cabin on machine, but the equipment such as automatic pilot, presetting apparatus are installed.On ground, naval vessels
Or machine tool remote control station personnel are by equipment such as radars, it is tracked, positioned, remote control, remote measurement and Digital Transmission.Can be wireless
Take off or launched with booster rocket as conventional airplane under electrical remote control, can also take aerial deliver to by machine tool and fly.Return
In the time receiving, the mode automatic Landing as conventional airplane landing mission can be used, can also be reclaimed by remote control parachute or block.
It can be reused several times.It is widely used in aerial reconnaissance, monitoring, communication, antisubmarine, electronic interferences etc..With compared with manned aircraft, it
With small volume, low cost and it is easy to use the features such as, therefore enjoy military, scientific research and the favor of Air Fan.
Existing unmanned plane generally carries out course changing control and using fixed rotor arm by the speed difference of coaxial propellers, has and turns
To dumb, lock tail and forbidden, the problems such as being spinned in flight course, and it is especially not readily portable.
Utility model content
The purpose of this utility model is：The problem of in order to solve above-mentioned fixed rotor arm aircraft, now providing a kind of band can
The vee tail unmanned plane of folding rotor arm, the unmanned plane realizes that body stores portable mesh by installing foldable rotor arm
's；In addition, two angles being located between tail undercarriage and horizontal plane of unmanned plane provided herein are equal, so as to provide
The power of left rotation and right rotation, rotary speed is fast and controls accurate.
The purpose of this utility model is to be achieved through the following technical solutions：
A kind of vee tail unmanned plane for the foldable rotor arm of band that the utility model is provided, including frame and it is installed on institute
The vee tail of frame aft is stated, is folded before being separately installed with first in the frame front end both sides relative with the vee tail
Folding rotor arm before rotor arm and second；It is provided with before described first on folding rotor arm before the first front propeller, described second
Second front propeller is installed on folding rotor arm；After being separately installed with first on the vee tail both sides folding rotor arm and
Folding rotor arm after second, is provided with folding rotor after the first rear screw shaft, described second after described first on folding rotor arm
Second rear screw shaft is installed on arm；Rolled over before described first before folding rotor arm, described second after folding rotor arm, described first
Folding rotor arm can be folded after folded rotor arm and described second.
Specifically, installation notch, second before being respectively arranged with first on the frame front left and right sides and/or vee tail
Installation notch after installation notch and second after preceding installation notch, first；One end of folding rotor arm and described before described first
Installed before one end of folding rotor arm is installed on described first by installed part respectively before second before installation notch and described second
In notch；One end of folding rotor arm is pacified by installed part respectively behind one end of folding rotor arm and described second after described first
Loaded in installation notch after installation notch and described second after described first.
In order to make whole unmanned plane be in fashion during keep balance and it is controllable, said first rear screw shaft with
The angle between angle and the second rear screw shaft and horizontal plane between horizontal plane is equal.
Specifically, between angle and the second rear screw shaft and horizontal plane between first rear screw shaft and horizontal plane
Angle is 45 °.
In order that unmanned plane provided by the utility model can be more firm, whole fuselage (frame and tail) is not easy to break
It is disconnected, here, herein described frame and the vee tail are integrally formed.
The utility model is as a result of above-mentioned technology, and the good effect for being allowed to have compared with prior art is：
The utility model is directly realized by the portable easily contained demand of aircraft due to being provided with foldable rotor arm；This reality
With new due to being provided with V-type tail, and two propellers after two on foldable rotor arm are in that angle is identical with horizontal plane, directly
The power there is provided left rotation and right rotation is connect, fast steering, the demand of stability contorting is realized.
Brief description of the drawings
Fig. 1 is the expansion effect stereogram of the utility model V tail aircraft；
Fig. 2 is the folding effect top view of the utility model V tail aircraft.
Embodiment
The accompanying drawing of the application combination herein is described in further detail to technical scheme provided by the utility model.
As illustrated in fig. 1 and 2, the vee tail unmanned plane of the foldable rotor arm of a kind of band provided by the utility model, including
To carry the frame 1 for flying control plate and power supply and the vee tail 2 for being installed on frame 1 afterbody, and in frame 1 and vee tail 2
Folding rotor arm 4 before folding rotor arm 3 and second before relative front end both sides are separately installed with first；In addition, being folded before first
It is provided with rotor arm 3 before first front propeller 5, second and second front propeller 6 is installed on folding rotor arm 4；Meanwhile, V-type
Folding rotor arm 8 after folding rotor arm 7 and second after being separately installed with first on the both sides of empennage 2, after first on folding rotor arm 7
It is provided with after the first rear screw shaft 9, second and second rear screw shaft 10 is installed on folding rotor arm 8；Wherein, rotation is folded before first
Folding rotor arm 8 is to fold after folding rotor arm 7 and second after folding rotor arm 4, first before wing arm 3, second, in discomfort
With or need to carry, then can be folded, as shown in Fig. 2 being convenient for carrying and placing.
And folded before folding rotor arm 3, second before first after folding rotor arm 4, first after folding rotor arm 7 and second
Motor, propeller are then installed on rotor arm 8 to adjust with electricity, folding rotor arm 4 before folding rotor arm 3 and second before being installed on first
On motor straight up, and the motor being installed on after first after folding rotor arm 7 and second on folding rotor arm 8 passes through electricity
Machine support base is fixed, and kinetic energy of the unmanned plane required for flight course is total is provided by motor.
Specifically, in the above-mentioned technical solutions, the is respectively arranged with the anterior left and right sides of frame 1 and/or vee tail 2
Installation notch (are not marked in figure after installation notch 21 and second after installation notch 12, first before installation notch 11, second before one
Note, while one end of folding rotor arm 4 before one end and second of folding rotor arm 3 before first is installed on by installed part respectively
Before first before installation notch 11 and second in installation notch 12, then its other end installs spiral before the first front propeller 5 and second
Oar 6；And one end of folding rotor arm 8 is installed by installed part respectively behind one end of folding rotor arm 7 and described second after first
In in installation notch, the other end is then provided with the first rear screw shaft 9 and after installation notch 21 and described second after described first
Two rear screw shafts 10；Wherein, described installed part can be any installed part, such as rivet, screw arbor assembly, only need to protect
Demonstrate,proving the first front propeller 5, the second front propeller 6, the first rear screw shaft 9 and the second rear screw shaft 10 can live in installation notch
It is dynamic to fold.
Here, in order to ensure that unmanned plane provided herein can keep balance during horizontal flight, this
The used technology of application is by between the angle between the first rear screw shaft and horizontal plane and the second rear screw shaft and horizontal plane
Angle be set to it is equal.The angle can keep any one angle of unmanned plane balance flight, such as 45 °, 30 °,
Or 60 °, when the angle number of degrees between the angle between the first rear screw shaft and horizontal plane and the second rear screw shaft and horizontal plane
When determining, the angle number of degrees between the first rear screw shaft and the second rear screw shaft are also just determined therewith, such as when between horizontal plane
Angle when being 45 °, the angle between the first rear screw shaft and the second rear screw shaft is 90 ° so that the propeller installed thereon
The power of left rotation and right rotation can be directly provided, fast steering, the demand of stability contorting is realized.
Here, described frame 1 and vee tail 2 can be by being welded as a whole, it is preferred that passing through mould one
Shaping, so as to strengthen the intensity of whole unmanned plane, is not easily broken it.
In addition, being additionally provided with the foot stool that rises and falls on the lower surface of frame 2, conveniently rise and fall, this stops in flight course
Shrink, stretched out in descent there is provided cushion effect, be easy to unmanned plane to rise and fall.
When needing to fold the utility model, as shown in Fig. 2 inwardly tightening up front and rear four foldable rotor arms, Zhi Daowu
Untill method is rotated further.When needing to use the utility model, as shown in figure 1, (outside) pushes foldable rotor open in reverse direction
Arm.
As can be seen here, unmanned plane provided by the utility model can directly provide the power positioned at left rotation and right rotation, and can
The characteristics of realizing the folding storage of body, thus, control stabilization quick with rotation, flight is accurate, and be easy to store.
General principle of the present utility model and principal character and advantage of the present utility model has been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Simply illustrate principle of the present utility model, on the premise of the utility model spirit and scope are not departed from, the utility model is also
Various changes and modifications are had, these changes and improvements are both fallen within the range of claimed the utility model.The utility model
Claimed scope is by appended claims and its equivalent thereof.
Claims (9)
1. a kind of vee tail unmanned plane of the foldable rotor arm of band, it is characterised in that：Including frame (1) and it is installed on the machine
The vee tail (2) of frame (1) afterbody, is separately installed with the frame (1) the front end both sides relative with the vee tail (2)
Folding rotor arm (4) before folding rotor arm (3) and second before one；Before first being provided with before described first on folding rotor arm (3)
Propeller (5), is provided with the second front propeller (6) before described second on folding rotor arm (4)；On vee tail (2) both sides
Folding rotor arm (8) after folding rotor arm (7) and second after being separately installed with first, after described first on folding rotor arm (7)
It is provided with after the first rear screw shaft (9), described second and second rear screw shaft (10) is installed on folding rotor arm (8)；Described
Before one before folding rotor arm (3), described second after folding rotor arm (4), described first after folding rotor arm (7) and described second
Folding rotor arm (8) can be folded.
2. a kind of vee tail unmanned plane of the foldable rotor arm of band according to claim 1, it is characterised in that：Described
Pacify before being respectively arranged with first on frame (1) the front portion left and right sides and/or the vee tail (2) before installation notch (11), second
Installation notch after installation notch (21) and second after tankage mouthful (12), first；One end of folding rotor arm (3) before described first
With described second before folding rotor arm (4) one end be installed on described first by installed part respectively before installation notch (11) and institute
Before stating second in installation notch (12)；Folding rotor arm (8) behind one end of folding rotor arm (7) and described second after described first
One end be installed on described first by installed part respectively after after installation notch (21) and described second in installation notch.
3. a kind of vee tail unmanned plane of the foldable rotor arm of band according to claim 1 or 2, it is characterised in that：It is described
Angle and second rear screw shaft (10) angle horizontal plane between of first rear screw shaft (9) between horizontal plane is equal.
4. a kind of vee tail unmanned plane of the foldable rotor arm of band according to claim 1 or 2, it is characterised in that：It is described
Angle and second rear screw shaft (10) angle horizontal plane between of first rear screw shaft (9) between horizontal plane is 45 °.
5. a kind of vee tail unmanned plane of the foldable rotor arm of band according to claim 3, it is characterised in that：Described
Angle and second rear screw shaft (10) angle horizontal plane between of one rear screw shaft (9) between horizontal plane is 45 °.
6. a kind of vee tail unmanned plane of the foldable rotor arm of band according to claim 1 or 2, it is characterised in that：It is described
Frame (1) and the vee tail (2) are integrally formed.
7. a kind of vee tail unmanned plane of the foldable rotor arm of band according to claim 3, it is characterised in that：The machine
Frame (1) and the vee tail (2) are integrally formed.
8. a kind of vee tail unmanned plane of the foldable rotor arm of band according to claim 4, it is characterised in that：The machine
Frame (1) and the vee tail (2) are integrally formed.
9. a kind of vee tail unmanned plane of the foldable rotor arm of band according to claim 5, it is characterised in that：The machine
Frame (1) and the vee tail (2) are integrally formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720128998.2U CN206437196U (en) | 2017-02-14 | 2017-02-14 | A kind of vee tail unmanned plane of the foldable rotor arm of band |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720128998.2U CN206437196U (en) | 2017-02-14 | 2017-02-14 | A kind of vee tail unmanned plane of the foldable rotor arm of band |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206437196U true CN206437196U (en) | 2017-08-25 |
Family
ID=59634091
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720128998.2U Expired - Fee Related CN206437196U (en) | 2017-02-14 | 2017-02-14 | A kind of vee tail unmanned plane of the foldable rotor arm of band |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206437196U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3678935A4 (en) * | 2018-11-30 | 2020-10-14 | SZ DJI Technology Co., Ltd. | Foldable unmanned aerial vehicle |
| CN116812184A (en) * | 2023-07-04 | 2023-09-29 | 深圳技术大学 | Six-axis unmanned aerial vehicle for radar mapping |
-
2017
- 2017-02-14 CN CN201720128998.2U patent/CN206437196U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3678935A4 (en) * | 2018-11-30 | 2020-10-14 | SZ DJI Technology Co., Ltd. | Foldable unmanned aerial vehicle |
| CN116812184A (en) * | 2023-07-04 | 2023-09-29 | 深圳技术大学 | Six-axis unmanned aerial vehicle for radar mapping |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170825 Termination date: 20180214 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |