CN210083531U - Unmanned aerial vehicle aerial adjustment stabilizes fin - Google Patents
Unmanned aerial vehicle aerial adjustment stabilizes fin Download PDFInfo
- Publication number
- CN210083531U CN210083531U CN201920779903.2U CN201920779903U CN210083531U CN 210083531 U CN210083531 U CN 210083531U CN 201920779903 U CN201920779903 U CN 201920779903U CN 210083531 U CN210083531 U CN 210083531U
- Authority
- CN
- China
- Prior art keywords
- tail wing
- tail
- balance
- unmanned aerial
- aerial vehicle
- 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
Links
- 238000009434 installation Methods 0.000 claims abstract description 21
- 230000000087 stabilizing effect Effects 0.000 claims description 7
- 238000005265 energy consumption Methods 0.000 abstract description 4
- 239000002699 waste material Substances 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
Images
Abstract
The utility model discloses an aerial adjusting stable tail wing of an unmanned aerial vehicle, which comprises an installation main board and a balance tail wing; the inner wall of the balance tail wing is respectively provided with a limiting block inserted into the corresponding guide groove; the output end of the first electric telescopic rod is connected with the telescopic tail wing; the two balancing tail wings are respectively connected with an inclined push rod, and the upper ends of the two push rods are connected with the side surfaces of the adjacent connecting seats; the output end of the second electric telescopic rod vertically penetrates out of the mounting main board upwards and is welded and fixed with the connecting seat; the utility model is convenient for the unmanned plane to adjust the extension area of the telescopic tail wing in the driving process by embedding the telescopic tail wing in the balance tail wing, thereby adapting to the flight under different air resistance; through carrying out angle modulation to two balanced fin to adjust the flight resistance of fin, assist the lift of taking off simultaneously, greatly increased unmanned aerial vehicle flight's controllability, the power waste is little, the energy consumption is low, flight efficiency is high.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle field specifically is an unmanned aerial vehicle is aerial adjusts and stabilizes fin.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Compared with a piloted airplane, the piloted airplane has the advantages of small volume, low manufacturing cost, convenience in use, low requirement on the battle environment, strong battlefield viability and the like, and is more suitable for tasks which are too dull, dirty or dangerous. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles are divided into reconnaissance aircraft and target drone; in the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.
At present, unmanned aerial vehicle's fin comprises left and right sides two parts, and the afterbody at unmanned aerial vehicle is installed after two parts use the connecting piece to couple together, and this fin is mostly fixed mounting, and it extends area and angle and can not adjust, under the condition that different speeds of traveling and air flow, can not adjust as required, and it is big to lead to unmanned aerial vehicle to advance the resistance, and the power waste is big, the energy consumption is high, flight inefficiency etc. weak point.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned aerial vehicle is aerial to be adjusted and is stabilized fin to solve the problem that proposes in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: an unmanned aerial vehicle aerial adjustment stabilizing tail wing comprises a mounting main board, wherein balancing tail wings are symmetrically arranged on two sides of the mounting main board respectively; a telescopic tail wing is embedded in the balance tail wing and penetrates out of the balance tail wing, a plurality of guide grooves with outward openings are symmetrically formed in two sides of one end of the telescopic tail wing facing the balance tail wing, and limiting blocks inserted into the corresponding guide grooves are respectively arranged on the inner wall of the balance tail wing; one end of each of the two balancing tail wings close to the inside of the balancing tail wing is provided with a first electric telescopic rod, and the output end of each first electric telescopic rod is connected with the telescopic tail wing; the upward opposite surfaces of the two balancing tail wings are respectively connected with an inclined push rod, a connecting seat is arranged right above the middle part of the installation main board, and the upper ends of the two push rods are connected with the side surfaces of the adjacent connecting seats; and a second electric telescopic rod is installed in the installation mainboard, and the output end of the second electric telescopic rod vertically penetrates out of the installation mainboard and is welded and fixed with the connecting seat.
Preferably, the balance tail wing is rotatably hinged with the installation main board through a spherical connecting part; two ends of the push rod are respectively rotatably hinged with the balance tail wing and the connecting seat through spherical connecting parts.
Preferably, the limiting block and the balance tail wing are of an integral connecting structure, and the limiting block is arranged at one end, far away from the installation main board, of the balance tail wing.
Preferably, the first electric telescopic rod is fixed in the balance tail wing through a connecting flange and a fixing bolt.
Preferably, the four corners of the second electric telescopic rod are fixed on the inner wall of the installation main board through fixing bolts.
Preferably, the angle between said two balancing fins is in the range 60 ° to 180 °.
Compared with the prior art, the beneficial effects of the utility model are that: the utility model has the advantages that the telescopic tail fin is embedded in the balance tail fin and is driven to stretch through the first electric telescopic rod, so that the extension area of the telescopic tail fin can be conveniently adjusted by the stretching of the first electric telescopic rod in the driving process of the unmanned aerial vehicle, and the unmanned aerial vehicle can adapt to the flight under different air resistances; carry out angle modulation to two balanced fin through second electric telescopic handle cooperation push rod to adjust the flight resistance of fin, assist the lift of taking off simultaneously, greatly increased the controllability that unmanned aerial vehicle flies, the power waste is little, the energy consumption is low, flight efficiency is high.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
fig. 2 is a schematic view of the telescopic tail wing of the present invention.
In the figure: 1. installing a main board; 2. balancing the tail wing; 3. a spherical connecting portion; 4. a retractable tail wing; 5. a guide groove; 6. a limiting block; 7. a first electric telescopic rod; 8. a push rod; 9. a connecting seat; 10. and the second electric telescopic rod.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "vertical", "upper", "lower", "horizontal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
Referring to fig. 1-2, the present invention provides a technical solution: an unmanned aerial vehicle aerial adjustment stable tail wing comprises a mounting main board 1, wherein balance tail wings 2 are symmetrically arranged on two sides of the mounting main board 1 respectively; a telescopic tail wing 4 is embedded into the balance tail wing 2, the telescopic tail wing 4 penetrates out of the balance tail wing 2, a plurality of guide grooves 5 with outward openings are symmetrically formed in two sides of one end, facing the balance tail wing 2, of the telescopic tail wing 4, and limiting blocks 6 inserted into the corresponding guide grooves 5 are arranged on the inner wall of the balance tail wing 2; one end of each of the two balancing tail wings 2 close to the inside of the balancing tail wing 2 is provided with a first electric telescopic rod 7, and the output end of each first electric telescopic rod 7 is connected with the telescopic tail wing 4; the upward opposite surfaces of the two balancing tail wings 2 are respectively connected with an inclined push rod 8, a connecting seat 9 is arranged right above the middle part of the installation main board 1, and the upper ends of the two push rods 8 are connected with the side surfaces of the adjacent connecting seats 9; install second electric telescopic handle 10 in the installation mainboard 1, the output of second electric telescopic handle 10 upwards wears out installation mainboard 1 perpendicularly and connecting seat 9 welded fastening.
Further, the balance tail wing 2 is rotatably hinged with the installation main board 1 through a spherical connecting part 3; two ends of the push rod 8 are respectively hinged with the balance tail wing 2 and the connecting seat 9 through the spherical connecting part 3.
Furthermore, stopper 6 and balanced fin 2 connection structure as an organic whole, stopper 6 sets up in balanced fin 2 and keeps away from the one end of installing mainboard 1.
Further, the first electric telescopic rod 7 is fixed in the balance tail wing 2 through a connecting flange and a fixing bolt.
Furthermore, four corners of the second electric telescopic rod 10 are fixed on the inner wall of the installation main board 1 through fixing bolts.
Furthermore, the included angle between the two balancing tail wings 2 ranges from 60 degrees to 180 degrees.
The working principle is as follows: will install mainboard 1 through tail boom fixed mounting at the fuselage afterbody, the control end of first electric telescopic handle 7 and second electric telescopic handle 10 is connected with unmanned aerial vehicle's program control device respectively for carry out the program setting to balanced fin 2 and adjust. The extension area of the telescopic tail wing 4 is adjusted by controlling the extension and retraction of the first electric telescopic rod 7, so that the telescopic tail wing can adapt to flight under different air resistance; in the process of stretching the telescopic tail fin 4, the limiting block 6 inside the balance tail fin 2 is inserted into the guide groove 5 of the telescopic tail fin 4 to slide, so that the telescopic tail fin 4 can stably extend. Through the flexible of control second electric telescopic handle 10 to adjust the distance between connecting seat 9 and the installation mainboard 1, change the contained angle between two push rods 8, thereby adjust the contained angle between two balanced fin 2, make two balanced fin 2 can be the "V" type structure of different angles, reduce air resistance, also can be dull and stereotyped structure, increase the stationarity of flight, the controllability is strong, the power waste is little, the energy consumption is low, flight efficiency is high
It is worth noting that: the whole device is controlled by the master control button, and the equipment matched with the control button is common equipment, so that the device belongs to the existing well-known technology, and the electrical connection relation and the specific circuit structure of the device are not repeated.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. An unmanned aerial vehicle aerial adjustment stabilizing tail wing is characterized by comprising an installation main board (1), wherein balancing tail wings (2) are symmetrically arranged on two sides of the installation main board (1) respectively; a telescopic tail wing (4) is embedded into the balance tail wing (2), the telescopic tail wing (4) penetrates out of the balance tail wing (2), a plurality of guide grooves (5) with outward openings are symmetrically formed in two sides of one end of the telescopic tail wing facing the balance tail wing (2), and limiting blocks (6) inserted into the corresponding guide grooves (5) are respectively arranged on the inner wall of the balance tail wing (2); one end of each of the two balancing tail wings (2) close to the inside of the balancing tail wing (2) is provided with a first electric telescopic rod (7), and the output end of each first electric telescopic rod (7) is connected with the telescopic tail wing (4); the upward opposite surfaces of the two balance tail wings (2) are respectively connected with an inclined push rod (8), a connecting seat (9) is arranged right above the middle part of the installation main board (1), and the upper ends of the two push rods (8) are connected with the side surfaces of the adjacent connecting seats (9); install second electric telescopic handle (10) in installation mainboard (1), the output of second electric telescopic handle (10) upwards wears out installation mainboard (1) and connecting seat (9) welded fastening perpendicularly.
2. The unmanned aerial vehicle aerial adjustment stabilizing tail of claim 1, wherein: the balance tail wing (2) is rotatably hinged with the installation main board (1) through a spherical connecting part (3); two ends of the push rod (8) are respectively and rotatably hinged with the balance tail wing (2) and the connecting seat (9) through the spherical connecting part (3).
3. The unmanned aerial vehicle aerial adjustment stabilizing tail of claim 1, wherein: the limiting block (6) and the balance tail wing (2) are of an integral connecting structure, and the limiting block (6) is arranged at one end, far away from the installation main board (1), of the balance tail wing (2).
4. The unmanned aerial vehicle aerial adjustment stabilizing tail of claim 1, wherein: the first electric telescopic rod (7) is fixed in the balance tail wing (2) through a connecting flange and a fixing bolt.
5. The unmanned aerial vehicle aerial adjustment stabilizing tail of claim 1, wherein: and four corners of the second electric telescopic rod (10) are fixed on the inner wall of the installation main board (1) through fixing bolts.
6. The unmanned aerial vehicle aerial adjustment stabilizing tail of claim 1, wherein: the included angle between the two balancing tail wings (2) ranges from 60 degrees to 180 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920779903.2U CN210083531U (en) | 2019-05-28 | 2019-05-28 | Unmanned aerial vehicle aerial adjustment stabilizes fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920779903.2U CN210083531U (en) | 2019-05-28 | 2019-05-28 | Unmanned aerial vehicle aerial adjustment stabilizes fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210083531U true CN210083531U (en) | 2020-02-18 |
Family
ID=69480365
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920779903.2U Expired - Fee Related CN210083531U (en) | 2019-05-28 | 2019-05-28 | Unmanned aerial vehicle aerial adjustment stabilizes fin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210083531U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112429200A (en) * | 2020-10-14 | 2021-03-02 | 陈东旭 | Aviation aircraft device capable of assisting steering |
-
2019
- 2019-05-28 CN CN201920779903.2U patent/CN210083531U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112429200A (en) * | 2020-10-14 | 2021-03-02 | 陈东旭 | Aviation aircraft device capable of assisting steering |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20160244160A1 (en) | Convertible unmanned aerial vehicle | |
| CN105398561A (en) | Solar aircraft | |
| CN210083531U (en) | Unmanned aerial vehicle aerial adjustment stabilizes fin | |
| CN103803057B (en) | Row's wing sun power UAV aerodynamic layout structure | |
| CN205418094U (en) | Push -button aircraft | |
| CN207106845U (en) | A kind of stealthy unmanned plane for extending cruising time | |
| CN211252994U (en) | Perpendicular fin mounting structure of cartridge formula unmanned aerial vehicle | |
| CN105366044A (en) | Fog dispersal type unmanned aerial vehicle | |
| CN211468760U (en) | A undercarriage for unmanned aerial vehicle | |
| CN212980542U (en) | Unmanned aerial vehicle jettison device | |
| CN211996183U (en) | Unmanned vehicles ventral structure | |
| CN111431591A (en) | All-weather intelligent flight system of unmanned aerial vehicle | |
| CN113148188A (en) | Dual-power vertical take-off and landing fixed-wing unmanned aerial vehicle | |
| CN211064040U (en) | High-efficient heat radiation structure of unmanned aerial vehicle electron speed regulator | |
| CN216546668U (en) | Wing structure of light unmanned aerial vehicle | |
| CN110871891A (en) | Rotor VTOL fixed wing unmanned aerial vehicle verts to conventional overall arrangement | |
| CN213083480U (en) | Wing structure of composite material unmanned aerial vehicle | |
| CN213620292U (en) | Unmanned aerial vehicle's helping to fly slide rail frame | |
| CN215155601U (en) | Undercarriage device for vertical take-off and landing unmanned aerial vehicle | |
| CN205906229U (en) | Unmanned aerial vehicle with multiple rotor wings | |
| CN219406902U (en) | Engine structure for unmanned aerial vehicle | |
| CN215205366U (en) | General unmanned aerial vehicle that carries on | |
| CN217074782U (en) | Four-axis multi-rotor unmanned aerial vehicle casing | |
| CN209834024U (en) | Generator fixing part universal for engine | |
| CN209795817U (en) | Unmanned aerial vehicle undercarriage with stabilizer blade structure |
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: 20200218 Termination date: 20210528 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |