CN212332951U - Quick-release wing of unmanned aerial vehicle - Google Patents
Quick-release wing of unmanned aerial vehicle Download PDFInfo
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- CN212332951U CN212332951U CN202020853550.9U CN202020853550U CN212332951U CN 212332951 U CN212332951 U CN 212332951U CN 202020853550 U CN202020853550 U CN 202020853550U CN 212332951 U CN212332951 U CN 212332951U
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Abstract
The utility model discloses an unmanned aerial vehicle quick detach wing belongs to the unmanned vehicles field, and it is complicated to have solved the dismouting, needs to be equipped with special instrument, the problem of the transport of not being convenient for, and its technical essential is: the wing technical indexes completely meet the design requirements, the dismounting mode is reverse operation of the mounting mode, the hasp is firstly unfastened, the left outer wing and the right outer wing are slowly drawn out, then the hasps among the left stay bar, the right stay bar and the central wing are unfastened, the left stay bar and the right stay bar are taken down, finally the central wing is dismounted from the body, and the wing dismounting is completed; the assembly and disassembly can be completed within 2 minutes without any special tool, and the size and the weight after being packed meet the requirements of users, so that the users can highly recognize the size and the weight.
Description
Technical Field
The utility model relates to an unmanned vehicles field specifically is to relate to an unmanned aerial vehicle quick detach wing.
Background
In recent years, with the high-speed development of unmanned aerial vehicles, the wide application of unmanned aerial vehicles in various industries is driven. Compared with a human machine, the unmanned aerial vehicle has the advantages of small target, strong penetration capability, no life cost and the like, not only becomes important force for acquiring battlefield information in the military field, but also plays a great role in civil fields such as forest protection, power line patrol, pipeline patrol, surveying and mapping, emergency and the like.
Wherein, small-size VTOL composite wing unmanned aerial vehicle receives user's favor more and more because of advantages such as convenient to use, with low costs, do not need special runway, however in the in-service use, has also exposed the dismouting complicated, need be equipped with special instrument, and the vanning size is too big, and vanning back weight is too heavy, a series of problems such as the transport of being not convenient for.
Therefore, in order to solve the problems brought by users, it is necessary to design a quick-release wing which can meet the requirements of flight performance, ground quick-release, and the like, and the size and weight of the wing after being packaged are as light as possible.
SUMMERY OF THE UTILITY MODEL
Not enough to prior art exists, the utility model provides an aim at provides an unmanned aerial vehicle quick detach wing to solve the problem in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
a quick-release wing of an unmanned aerial vehicle comprises a left outer wing, a central wing and a right outer wing, wherein the left outer wing, the central wing and the right outer wing are mounted on a fuselage and jointly form a vertical take-off and landing composite wing unmanned aerial vehicle together with a left stay bar, a right stay bar, a horizontal tail and an undercarriage;
the left outer wing, the central wing and the right outer wing are all composed of wing skins, wing ribs, a front wall, a rear wall, a central wing front beam and a central wing rear beam, and ailerons and backup ailerons are arranged on the left outer wing and the right outer wing;
all be equipped with outer wing front-axle and outer wing back-axle on left side outer wing and the right outer wing, still be equipped with the hasp mounting panel on left side outer wing and the right outer wing, install the hasp on the hasp mounting panel.
As a further scheme of the utility model, VTOL composite wing unmanned aerial vehicle's span length is 5m, VTOL composite wing unmanned aerial vehicle's quick dismantlement containing box, and the case size is not more than 2m 1m, and single weight is not more than 40kg behind the vanning.
As a further aspect of the present invention, the front wall and the rear wall are high-strength carbon plates, and a plurality of lightening holes are formed in the web of the front wall and the web of the rear wall and along the span direction.
As a further scheme of the utility model, central authorities 'wing front-axle beam and central authorities' wing back-axle beam are high strength carbon fiber pipe, and the wing covering is carbon fiber foam sandwich structure.
As a further proposal of the utility model, the wing profiles of the left outer wing, the central wing and the right outer wing select the NACA 1104 high-lift thin wing profile, and the lift-drag ratio is 12.23.
As a further proposal of the utility model, a groove is arranged on the wing at the installation position of the hasp.
As a further aspect of the present invention, the central wing and the fuselage are connected by 4 bolts with a diameter of 6mm, and the central wing is connected with the left outer wing and the right outer wing by adopting the form that the carbon tube is sleeved.
To sum up, compared with the prior art, the embodiment of the utility model has the following beneficial effects:
the technical indexes of the quick-release wing of the unmanned aerial vehicle completely meet the design requirements, the dismounting mode is the reverse operation of the mounting mode, the hasp is firstly unfastened, the left outer wing and the right outer wing are slowly drawn out, then the hasps among the left stay bar, the right stay bar and the central wing are unfastened, the left stay bar and the right stay bar are taken down, finally the central wing is dismounted from the body, and the wing dismounting is completed; the assembly and disassembly can be completed within 2 minutes without any special tool, and the size and the weight after being packed meet the requirements of users, so that the users can highly recognize the size and the weight.
To illustrate the structural features and functions of the present invention more clearly, the present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
Drawings
Fig. 1 is a schematic view of a certain type of vertical take-off and landing unmanned aerial vehicle according to the present invention;
fig. 2 is a schematic view of a wing structure of a certain type of vertical take-off and landing unmanned aerial vehicle according to the present invention;
FIG. 3 is a schematic view of the wing assembly and disassembly of the model VTOL UAV of the present invention;
reference numerals: 1-fuselage, 2-left outer wing, 3-center wing, 4-right outer wing, 5-left stay bar, 6-right stay bar, 7-horizontal tail, 8-landing gear, 9-wing skin, 10-wing rib, 11-front wall, 12-center wing front beam, 13-rear wall, 14-center wing rear beam, 15-backup aileron, 16-aileron, 17-outer wing front beam, 18-outer wing rear beam, 19-snap hook mounting plate, 20-snap hook and 21-snap hook.
Detailed Description
The technical solution of the present invention will be further explained with reference to the accompanying drawings and specific embodiments.
Example 1
Referring to fig. 1-3, a quick-release wing of an unmanned aerial vehicle, which belongs to an important part of a vertical take-off and landing composite wing unmanned aerial vehicle, mainly comprises a left outer wing 2, a central wing 3 and a right outer wing 4, wherein the left outer wing 2, the central wing 3 and the right outer wing 4 are arranged on a fuselage 1, and the vertical take-off and landing combined wing unmanned aerial vehicle is composed of a left support rod 5, a right support rod 6, a horizontal tail 7 and a landing gear 8, and is used as a multi-purpose unmanned aerial vehicle with long endurance and large load, wherein, the wing is a wing with a large aspect ratio, the span length is up to 5m, in order to meet the requirement of the long-endurance mission of the airplane, the lift-drag ratio of the unmanned aerial vehicle is required to reach more than 14, the unmanned aerial vehicle is as light as possible on the premise of meeting strength and rigidity indexes, the flight resistance is as small as possible, the unmanned aerial vehicle can rapidly disassemble the containing box, the size of the box is not more than 2m multiplied by 1m, and the single weight of the box after packing is not more than 40 kg.
In order to meet the above indexes, the fast-dismounting wing of the unmanned aerial vehicle of the embodiment of the present invention, the left outer wing 2, the central wing 3 and the right outer wing 4 are all composed of a wing skin 9, a wing rib 10, a front wall 11, a rear wall 13, a central wing front beam 12 and a central wing rear beam 14; the left outer wing 2 and the right outer wing 4 are provided with ailerons 16 and backup ailerons 15, in order to reduce the structural weight, each part is subjected to optimized weight reduction design, the front wall 11 and the rear wall 13 are high-strength carbon plates, a large number of lightening holes are formed in the web plates of the front wall 11 and the rear wall 13 along the wingspan direction, the central wing front beam 12 and the central wing rear beam 14 both adopt high-strength carbon fiber tubes and are main wing supporting force components, all parts of the wings are molded by a hot-pressing tank molding process, and the connection modes are all glue joint; the wing skin 9 adopts a carbon fiber foam sandwich structure, and has the lightest weight while ensuring strength and rigidity.
The airfoil profiles of the left outer wing 2, the central wing 3 and the right outer wing 4 adopt NACA 1104 high-lift thin airfoil profiles, and the lift-drag ratio reaches 12.23. In order to reduce flight resistance, the joints of the central wing 3 and the left support rod 5 and the right support rod 6, and the joints of the left outer wing 2 and the right outer wing 4 and the left support rod 5 and the right support rod 6 are subjected to pneumatic analysis and modification according to pneumatic analysis optimization, and the shape of the wing is modified, so that the wing is smooth and smooth, the resistance is minimum, and the resistance is reduced by 20% after modification.
The left outer wing 2 and the right outer wing 4 are both provided with an outer wing front beam 17 and an outer wing rear beam 18, the left outer wing 2 and the right outer wing 4 are also provided with snap hook mounting plates 19, the snap hooks mounting plates 19 are provided with snap hooks 21, and the wings at the mounting positions of the snap hooks 21 are provided with grooves.
Example 2
The quick release wing of the unmanned aerial vehicle in embodiment 1 mainly comprises three parts, namely a left outer wing 2, a central wing 3 and a right outer wing 4, wherein the left outer wing 2, the central wing 3 and the right outer wing 4 are installed on a fuselage 1 and form a vertical take-off and landing composite wing unmanned aerial vehicle together with a left stay bar 5, a right stay bar 6, a horizontal tail 7 and an undercarriage 8;
in order to meet the requirement of quick assembly and disassembly, the central wing 3 and the fuselage 1 are connected through 4 bolts with the diameter of 6mm, and are not generally disassembled in normal use, the central wing 3 is connected with the left outer wing 2 and the right outer wing 4 in a carbon tube sleeving mode, and after the sleeves are installed in place, the hasps 21 are buckled on the hasp hooks 20 and are pressed down for locking. The wing design groove at the installation position of the hasp 21 ensures that the hasp 21 does not protrude out of the wing surface and does not generate extra flight resistance.
The utility model discloses an unmanned aerial vehicle quick detach wing, wing technical index satisfy the designing requirement completely to can accomplish the dismouting in 2 minutes, need not any specialized tool, size, weight after the vanning all satisfy user's requirement, obtain user's high recognition.
The embodiment of the utility model provides an in, the mounting means of unmanned aerial vehicle quick detach wing does:
firstly, a central wing 3 is installed on a machine body 1 through 4 phi 6mm screws, then a left stay bar 5 and a right stay bar 6 are installed on a front central wing front beam 12 and a central wing rear beam 14 of the central wing 3, holes in the left stay bar 5 and the right stay bar 6 are aligned with beams of the central wing 3 during installation, and after the left stay bar 5 and the right stay bar are installed in place, a hasp 21 is used for buckling a hasp hook 20; and finally, connecting the left outer wing 2 and the right outer wing 4 with the central wing 3, aligning a front beam 17 and a rear beam 18 of the outer wings with a front beam 12 and a rear beam 14 of the central wing respectively during installation, slightly pushing the two outer wings towards the direction of the airplane body to enable the front beams 17 and the rear beams 18 of the outer wings to be sleeved into the front beam 12 and the rear beam 14 of the central wing 3 respectively, continuously pushing the two outer wings to enable the sleeved parts of the two outer wings to be sleeved completely, enabling the end surfaces of the left outer wing 2 and the right outer wing 4 to be completely attached to the outer side surfaces of the left support rod 5 and the right support rod 6, fastening and locking a buckle 21 with a buckle 20 on the support rod, and finishing wing installation.
The utility model discloses a wing is torn open to unmanned aerial vehicle piece, its dismantlement mode is the reverse operation of mounting means, unties hasp 21 earlier, takes left outer wing 2 and right outer wing 4 slowly out, unties hasp 21 between left vaulting pole 5, right vaulting pole 6 and the central authorities 'wing 3 again, takes off left vaulting pole 5 and right vaulting pole 6, pulls down central authorities' wing 3 from the body at last, and the wing is dismantled and is accomplished.
The technical principle of the present invention has been described above with reference to specific embodiments, which are merely preferred embodiments of the present invention. The utility model discloses a scope of protection not only limits in above-mentioned embodiment, and the all belongings the utility model discloses a technical scheme under the thinking all belongs to the utility model discloses a scope of protection. Those skilled in the art will appreciate that other embodiments of the invention can be devised which do not require inventive effort and which fall within the scope of the present invention.
Claims (7)
1. A quick-release wing of an unmanned aerial vehicle consists of a left outer wing (2), a central wing (3) and a right outer wing (4), and is characterized in that the left outer wing (2), the central wing (3) and the right outer wing (4) are mounted on a fuselage (1) and jointly form a vertical take-off and landing composite wing unmanned aerial vehicle with a left stay bar (5), a right stay bar (6), a horizontal tail (7) and an undercarriage (8);
the left outer wing (2), the central wing (3) and the right outer wing (4) are all composed of wing skins (9), wing ribs (10), a front wall (11), a rear wall (13), a central wing front beam (12) and a central wing rear beam (14), and ailerons (16) and backup ailerons (15) are installed on the left outer wing (2) and the right outer wing (4);
the left outer wing (2) and the right outer wing (4) are provided with an outer wing front beam (17) and an outer wing rear beam (18), the left outer wing (2) and the right outer wing (4) are further provided with snap hook mounting plates (19), and the snap hooks (21) are mounted on the snap hook mounting plates (19).
2. The fast-release wing of unmanned aerial vehicle of claim 1, wherein the span length of the VTOL composite wing UAV is 5m, the fast-release container of the VTOL composite wing UAV has a size of no more than 2m x 1m, and the individual weight of the container is no more than 40 kg.
3. The quick release wing of unmanned aerial vehicle of claim 1 or 2, characterized in that the front wall (11) and the rear wall (13) are high-strength carbon plates, and the web of the front wall (11) and the web of the rear wall (13) are respectively provided with a plurality of lightening holes along the wingspan direction.
4. The quick release wing of unmanned aerial vehicle of claim 3, characterized in that the center wing front spar (12) and the center wing back spar (14) are both high strength carbon fiber tubes, and the wing skin (9) is a carbon fiber foam sandwich structure.
5. The quick release wing of unmanned aerial vehicle according to claim 4, characterized in that the wing profiles of the left outer wing (2), the center wing (3) and the right outer wing (4) are NACA 1104 high lift thin wing profiles, and the lift-drag ratio is 12.23.
6. The quick release wing of unmanned aerial vehicle of claim 5, characterized in that the wing where the hasp (21) is installed is provided with a groove.
7. The quick release wing of unmanned aerial vehicle according to claim 6, characterized in that central wing (3) and fuselage (1) are connected through 4 bolts with diameter of 6mm, and central wing (3) adopts the form of carbon tube socket joint to be connected with left outer wing (2) and right outer wing (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020853550.9U CN212332951U (en) | 2020-05-20 | 2020-05-20 | Quick-release wing of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020853550.9U CN212332951U (en) | 2020-05-20 | 2020-05-20 | Quick-release wing of unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212332951U true CN212332951U (en) | 2021-01-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020853550.9U Active CN212332951U (en) | 2020-05-20 | 2020-05-20 | Quick-release wing of unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN212332951U (en) |
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- 2020-05-20 CN CN202020853550.9U patent/CN212332951U/en active Active
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