CN213008728U - Diaxon vertical row formula fan wing unmanned aerial vehicle - Google Patents
Diaxon vertical row formula fan wing unmanned aerial vehicle Download PDFInfo
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- CN213008728U CN213008728U CN202021185079.7U CN202021185079U CN213008728U CN 213008728 U CN213008728 U CN 213008728U CN 202021185079 U CN202021185079 U CN 202021185079U CN 213008728 U CN213008728 U CN 213008728U
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Abstract
The utility model discloses a two-axis longitudinal type wing unmanned aerial vehicle, which comprises a first transverse flow wing and a second transverse flow wing which are arranged at intervals, fixed wings which are respectively connected with the first transverse flow wing and the second transverse flow wing, and side wings which are connected with the end part of the first transverse flow wing and the end part of the second transverse flow wing, wherein power cabins are arranged on the first transverse flow wing and the second transverse flow wing; the unmanned aerial vehicle has a reliable structure and good running performance, and the first cross flow wings and the second cross flow wings which are longitudinally arranged in front and back provide reliable upward lift force and forward thrust force for the unmanned aerial vehicle, so that the load capacity and the short-distance take-off and landing capacity are improved; thereby the thrust that rises that the crossflow blade produced around thereby changing through the rotational speed of the interior crossflow blade of drive piece control crossflow wing in the piggyback pod, and then carries out pitch control to unmanned aerial vehicle, and through diaxon vertical column structure, improves unmanned aerial vehicle and bears the reaction force at flight in-process air.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to diaxon vertical row formula fan wing unmanned aerial vehicle.
Background
The fan-wing aircraft is a new concept aircraft, and has the advantages of high flying efficiency, large load, simple structure and short take-off and landing, so that the fan-wing aircraft obtains great development advantages in the military and civil fields and gradually becomes a new research hotspot in the aircraft field. The novel layout form with larger load, higher control efficiency and stronger short-distance take-off and landing capacity is particularly important for popularization and application of the wing-mounted aircraft.
In order to reduce the dependence on the take-off and landing site, reduce the use cost and execute diversified flight tasks, the aircraft capable of taking off and landing at short distance is always the research focus in the field of aviation. The two cross flow fans are additionally arranged on the two wings of the traditional aircraft with the two fan wings, and the rotation of the fans provides necessary lift force and thrust for the aircraft, so that the fan wing aircraft has higher flight efficiency, better low-speed performance and larger load compared with a common fixed wing aircraft due to the unique principle and configuration. However, the wing fan of this configuration has a limited load because it has only two cross-flow fans. In addition, in order to reduce the interference to the airflow at the tail of the fan wing, the fuselage is generally short, so that the load-carrying capacity of the fuselage is further limited; in addition, in order to control the attitude of the aircraft, it is necessary to add components such as a horizontal outer wing and a tail wing, thereby increasing the aerodynamic and structural burdens of the aircraft. In addition, the efficiency and the accuracy of the posture control mode are low.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a diaxon vertical row formula fan wing unmanned aerial vehicle to solve the problem that current fan wing unmanned aerial vehicle flight performance is low.
The utility model provides an above-mentioned technical problem's technical scheme as follows: the utility model provides a diaxon vertical arrangement formula fan wing unmanned aerial vehicle, is the first crossflow wing and the second crossflow wing that set up at interval, connects fixed wing on first crossflow wing and second crossflow wing respectively and connect first crossflow wing tip with the wing of second crossflow wing tip, be provided with the piggyback pod on first crossflow wing and the second crossflow wing.
The first cross flow wing and the second cross flow wing respectively comprise a plurality of cross flow wing rings arranged at intervals and a plurality of cross flow blades arranged between the adjacent cross flow wing rings, gaps are reserved between the adjacent cross flow blades, the fixed wing is connected to the cross flow wing rings, and a driving piece used for driving the cross flow blades to work is arranged in the power cabin.
Further, the fixed wing comprises a connecting part which is connected on the cross flow wing ring in a matching mode and a side wing which is connected with the connecting part and forms an integrated structure, the connecting part is of a groove structure, and the groove structure surrounds the outer circumference of the cross flow wing ring.
Further, the edge wing comprises edge wing rings arranged at the end parts of the first cross flow wing and the second cross flow wing respectively and a wing plate connected between the two edge wing rings.
Furthermore, the upper end of the side wing of the fixed wing is of a downwardly extending arc-shaped structure, and the lower end of the side wing of the fixed wing is of an upwardly inclined arc-shaped structure.
Further, the area of the groove structure of the connection part wrapping the outer circumference of the crossflow wing ring is 1/2-2/3 of the outer circumference of the crossflow wing ring.
The utility model discloses following beneficial effect has: the utility model provides a diaxon vertical arrangement formula fan wing unmanned aerial vehicle, its structure is reliable, and the runnability is good, provides reliable lift and forward thrust for unmanned aerial vehicle through the first crossflow wing and the second crossflow wing of longitudinal arrangement around, promotes load and short-distance take-off and landing ability; thereby the thrust that rises that the crossflow blade produced around thereby changing through the rotational speed of the interior crossflow blade of drive piece control crossflow wing in the piggyback pod, and then carries out pitch control to unmanned aerial vehicle, and through diaxon vertical column structure, improves unmanned aerial vehicle and bears the reaction force at flight in-process air.
Drawings
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is a top view of the present invention;
FIG. 3 is a side view of the middle fixed wing of the present invention;
the reference numerals shown in fig. 1 to 3 are respectively expressed as: 1-first cross flow wing, 2-second cross flow wing, 3-fixed wing, 4-side wing, 5-power cabin, 10-cross flow wing ring, 11-cross flow blade, 30-connecting part, 31-side wing, 40-side wing ring and 41-wing plate.
Detailed Description
The principles and features of the present invention are described below in conjunction with the following drawings, the examples given are only intended to illustrate the present invention and are not intended to limit the scope of the present invention.
As shown in fig. 1 to 3, a two-axis tandem type wing-wing drone includes two rows of first cross flow wings 1 and second cross flow wings 2 arranged at intervals, fixed wings 3 respectively connected to the first cross flow wings 1 and the second cross flow wings 2, and wings 4 connected to the ends of the first cross flow wings 1 and the second cross flow wings 2, where the first cross flow wings 1 and the second cross flow wings 2 are provided with power compartments 5.
The first cross flow wing 1 and the second cross flow wing 2 both comprise a plurality of cross flow wing rings 10 arranged at intervals and a plurality of cross flow blades 11 arranged between the adjacent cross flow wing rings 10, gaps are formed between the adjacent cross flow blades 11, the fixed wing 3 is connected to the cross flow wing rings 10, and a driving piece for driving the cross flow blades 11 to work is arranged in the power cabin 5.
The unmanned aerial vehicle is reliable in structure and good in running performance, and reliable upward lift force and forward thrust force are provided for the unmanned aerial vehicle through the first cross flow wings 1 and the second cross flow wings 2 which are longitudinally arranged in front and back, so that the load capacity and the short-distance take-off and landing capacity are improved; thereby the rotational speed of crossing current blade 11 in the drive compartment 5 control crossing current wing changes the lift thrust that crossing current blade 11 produced around, and then carries out pitch control to unmanned aerial vehicle, and through the diaxon vertical structure, improves unmanned aerial vehicle and bears the reaction force at flight in-process air.
The fixed wing 3 includes a connection portion 30 that is fittingly connected to the cross flow wing ring 10, and a wing 31 that is connected to the connection portion 30 and forms an integrated structure, and the connection portion 30 is a groove structure that is surrounded on the outer circumference of the cross flow wing ring 10. The fixed wing and the cross-flow wing ring 10 are stably and reliably connected through the connecting part 30, the connection is reliable and stable, the cross-sectional area of the groove structure is larger than that of the rear edge of the fixed wing, and therefore the integral arc-shaped structure of the fixed wing is formed, the structural performance of the fixed wing is improved, the lift-drag ratio of the integral fan wing is increased, and the flight performance is improved.
The edge wing 4 comprises edge wing rings 40 respectively arranged at the ends of the first cross flow wing 1 and the second cross flow wing 2 and a wing plate 41 connected between the two edge wing rings 40. The wing plates 41 are of arc structures, so that airflow dispersion in the flying process is improved, and flying resistance is reduced. The size of the edge wing ring 40 is adapted to the end of the cross flow wing, improving the reliability of the bonding.
The upper end of the side wing 31 of the fixed wing 3 is an arc structure extending downwards, and the lower end of the side wing 31 of the fixed wing 3 is an arc structure inclining upwards. The integral structural performance of the fixed wing is improved by limiting the arc-shaped structures of the upper flange and the lower flange of the fixed wing.
The area of the groove structure of the connection portion 30 surrounding the outer circumference of the crossflow wing ring 10 is 1/2-2/3 of the outer circumference of the crossflow wing ring 10. Through the limited to groove structure and crossing the position area of being connected of flow wing ring 10, improve connection reliability between them, and avoid the weight increase that the full parcel is connected and is brought and influence unmanned aerial vehicle's flight performance.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.
Claims (5)
1. A two-axis tandem type wing unmanned aerial vehicle is characterized by comprising two rows of first cross flow wings (1) and second cross flow wings (2) which are arranged at intervals, fixed wings (3) which are respectively connected to the first cross flow wings (1) and the second cross flow wings (2), and side wings (4) which are connected to the end parts of the first cross flow wings (1) and the second cross flow wings (2), wherein power cabins (5) are arranged on the first cross flow wings (1) and the second cross flow wings (2);
the first cross flow wing (1) and the second cross flow wing (2) comprise a plurality of cross flow wing rings (10) arranged at intervals and a plurality of cross flow blades (11) arranged between the adjacent cross flow wing rings (10), a gap is reserved between the adjacent cross flow blades (11), the fixed wing (3) is connected to the cross flow wing rings (10), and a driving piece used for driving the cross flow blades (11) to work is arranged in the power cabin (5).
2. A two-axis tandem type wing drone according to claim 1, characterized in that the fixed wing (3) includes a connection portion (30) connected to the cross-flow wing ring (10) in a fitting manner and a side wing (31) connected to the connection portion (30) and forming an integral structure, the connection portion (30) is a groove structure, and the groove structure surrounds the outer circumference of the cross-flow wing ring (10).
3. A two-axis tandem wing drone according to claim 1, characterised in that the said wing (4) comprises wing rings (40) respectively arranged at the ends of the first and second cross flow wings (1, 2) and a wing (41) connected between the two wing rings (40).
4. A two-axis tandem type wing-type drone according to any one of claims 1 to 3, wherein the upper end of the side wing (31) of the fixed wing (3) is of a downwardly extending arc-shaped structure, and the lower end of the side wing (31) of the fixed wing (3) is of an upwardly inclined arc-shaped structure.
5. A two-axis tandem wing drone according to claim 2, wherein the groove structure of the connection part (30) wraps the outer circumference of the crossflow wing ring (10) in an area 1/2-2/3 of the outer circumference of the crossflow wing ring (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021185079.7U CN213008728U (en) | 2020-06-23 | 2020-06-23 | Diaxon vertical row formula fan wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021185079.7U CN213008728U (en) | 2020-06-23 | 2020-06-23 | Diaxon vertical row formula fan wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213008728U true CN213008728U (en) | 2021-04-20 |
Family
ID=75496929
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021185079.7U Expired - Fee Related CN213008728U (en) | 2020-06-23 | 2020-06-23 | Diaxon vertical row formula fan wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213008728U (en) |
-
2020
- 2020-06-23 CN CN202021185079.7U patent/CN213008728U/en not_active Expired - Fee Related
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| 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: 20210420 |
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| CF01 | Termination of patent right due to non-payment of annual fee |