CN214216137U

CN214216137U - Unmanned aerial vehicle with high-strength and difficult damage wings

Info

Publication number: CN214216137U
Application number: CN202022256601.2U
Authority: CN
Inventors: 李晴
Original assignee: Individual
Current assignee: Beijing Weilan Jizhi Technology Co ltd
Priority date: 2020-10-12
Filing date: 2020-10-12
Publication date: 2021-09-17
Anticipated expiration: 2030-10-12

Abstract

The utility model discloses an unmanned aerial vehicle that wing high strength is not fragile, the reciprocating impact tunnel drilling machine comprises a machine body, the fixed cover of the equal fixedly connected with in both sides of fuselage, the inner chamber fixedly connected with wing body of fixed cover, the one end fixedly connected with motor of fixed cover is kept away from to the wing body, the output of motor rotates and is connected with the screw, the equal fixedly connected with link in both sides of fuselage bottom, the bottom fixedly connected with bottom plate of link. The utility model discloses a set up fixed cover, can strengthen the fixed effect to the wing body, effectively promoted the stability of wing body, through setting up the enhancement layer, can increase the use intensity of wing body, effectively avoided the phenomenon that the atress was broken to appear in the wing body, through setting up the surface protection layer, can protect the surface of wing body, avoid receiving corruption and wearing and tearing and receive the damage, effectively promoted the life of wing body.

Description

Unmanned aerial vehicle with high-strength and difficult damage wings

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is a not fragile unmanned aerial vehicle of wing high strength.

Background

The low-altitude unmanned aerial vehicle is an aerial vehicle for executing a specific aviation task by utilizing wireless remote control or program control, and refers to a power aerial vehicle without carrying operators, adopts aerodynamic force to provide the aircraft with required lift force, and can automatically fly or remotely guide, the unmanned aerial vehicle has the characteristics of simple structure and low use cost, is suitable for tasks which are not suitable for being executed by a manned aircraft, such as reconnaissance of dangerous areas, air rescue command and remote sensing monitoring, along with the development of science and technology, the low-altitude unmanned aerial vehicle is widely applied to a plurality of fields in life, such as aerial photography, crop monitoring, pesticide spraying, herd monitoring and driving, wherein wings are used as important components of the unmanned aerial vehicle, mainly play a role in maintaining the balance of the unmanned aerial vehicle, ensure the stable running of the unmanned aerial vehicle, and are also a structure of main bearing capacity of the unmanned aerial vehicle, so that the unmanned aerial vehicle is required to have high strength, in addition, the panel is required to have the characteristics of high fatigue resistance and light weight, in the prior art, the main material of the panel for the wings of the unmanned aerial vehicle is an aluminum alloy wing, but the corrosion resistance effect of the aluminum alloy wing is poor, and the strength of the panel cannot meet the use requirement of the unmanned aerial vehicle under special conditions, such as use in severe weather.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a not fragile unmanned aerial vehicle of wing high strength possesses intensity height, and the weatherability is good, and long service life's advantage has solved that current aluminum alloy wing corrosion-resistant effect is poor, and its intensity can not satisfy the problem of unmanned aerial vehicle's use under the special conditions.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an unmanned aerial vehicle that wing high strength is not fragile, includes the fuselage, the fixed cover of the equal fixedly connected with in both sides of fuselage, the inner chamber fixedly connected with wing body of fixed cover, the one end fixedly connected with motor of fixed cover is kept away from to the wing body, the output of motor rotates and is connected with the screw, the equal fixedly connected with link in both sides of fuselage bottom, the bottom fixedly connected with bottom plate of link, the wing body includes surface protection layer, first substrate layer, enhancement layer and second substrate layer, the outside fixedly connected with enhancement layer of second substrate layer, the first substrate layer of outside fixedly connected with of enhancement layer, the outside fixedly connected with surface protection layer of first substrate layer, surface protection layer includes corrosion resistant layer and wearing layer.

Preferably, the outer side of the corrosion-resistant layer is fixedly connected with a wear-resistant layer, the thickness of the corrosion-resistant layer is 0.16mm, and the thickness of the wear-resistant layer is 0.24 mm.

Preferably, both sides of the bottom plate are fixedly connected with buffering supporting legs, and the bottoms of the buffering supporting legs are fixedly connected with buffering cushions.

Preferably, the first base material layer and the second base material layer are made of the same material, and the thicknesses of the first base material layer and the second base material layer are both larger than that of the reinforcing layer.

Preferably, the bottom of the machine body is fixedly connected with a camera shooting assembly, and the surface of the camera shooting assembly is fixedly connected with a waterproof film.

Compared with the prior art, the beneficial effects of the utility model are as follows:

1. the utility model discloses a set up fixed cover, can strengthen the fixed effect to the wing body, effectively promoted the stability of wing body, through setting up the enhancement layer, can increase the use intensity of wing body, effectively avoided the phenomenon that the atress was broken to appear in the wing body, through setting up the surface protection layer, can protect the surface of wing body, avoid receiving corruption and wearing and tearing and receive the damage, effectively promoted the life of wing body.

2. The utility model discloses an use of corrosion resistant layer, can avoid the wing body to receive the corruption of acid-base material and damage, the corrosion resisting property of wing body has effectively been promoted, use through the wearing layer, can avoid the wing body to receive abnormal wear and damage, the wear resistance of wing body has effectively been promoted, through setting up buffering supporting leg and buffer pad, can play the effect of buffering impact force in the twinkling of an eye when the device descends, the too big damage that causes the device of impact force when effectually having avoided descending, through the affirmation that uses the material, can optimize the production technology of wing body, the manufacturing cost of device has effectively been reduced, through setting up camera subassembly and water proof membrane, can carry out image acquisition in device flight process, the practicality of device has effectively been promoted.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a cross-sectional view of the wing body of the present invention;

fig. 3 is a cross-sectional view of the surface protection layer of the present invention.

In the figure: 1. a body; 2. a wing body; 3. a propeller; 4. buffering support legs; 5. a base plate; 6. a camera assembly; 7. a connecting frame; 8. a motor; 9. fixing a sleeve; 10. a surface protective layer; 11. a first base material layer; 12. a reinforcing layer; 13. a second substrate layer; 14. a corrosion-resistant layer; 15. and a wear-resistant layer.

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 "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end", 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 to be referred 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. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "provided", "connected", and the like are to be construed broadly, such as "connected", which may be fixedly connected, detachably connected, or integrally connected; 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 in specific cases to those skilled in the art.

The utility model discloses a fuselage 1, wing body 2, screw 3, buffering supporting leg 4, bottom plate 5, camera module 6, link 7, motor 8, fixed cover 9, surface protection layer 10, first substrate layer 11, enhancement layer 12, second substrate layer 13, corrosion resistant layer 14 and wearing layer 15 part are the parts that general standard spare or technical personnel in the field know, and its structure and principle all are that this technical personnel all can learn through the technical manual or learn through conventional experimental method.

Referring to fig. 1-3, an unmanned aerial vehicle with high-strength and uneasy damage wings comprises a body 1, fixed sleeves 9 fixedly connected to both sides of the body 1, a camera assembly 6 fixedly connected to the bottom of the body 1, a waterproof membrane fixedly connected to the surface of the camera assembly 6, and a propeller 3 rotatably connected to the output end of the motor 8, wherein the camera assembly 6 and the waterproof membrane are arranged to collect images during the flight of the device, thereby effectively improving the practicability of the device, a wing body 2 is fixedly connected to the inner cavity of the fixed sleeves 9, a motor 8 is fixedly connected to one end of the wing body 2 away from the fixed sleeves 9, a connecting frame 7 is fixedly connected to both sides of the bottom of the body 1, a bottom plate 5 is fixedly connected to the bottom of the connecting frame 7, buffer pads 4 are fixedly connected to both sides of the bottom plate 5, and buffer pads are fixedly connected to the bottoms of the buffer support legs 4, by arranging the buffering supporting legs 4 and the buffering pads, the device can play a role of buffering instant impact force when falling, the damage to the device caused by overlarge impact force when falling is effectively avoided, the wing body 2 comprises a surface protective layer 10, a first base material layer 11, a reinforcing layer 12 and a second base material layer 13, the reinforcing layer 12 is fixedly connected to the outer side of the second base material layer 13, the first base material layer 11 is fixedly connected to the outer side of the reinforcing layer 12, the surface protective layer 10 is fixedly connected to the outer side of the first base material layer 11, the first base material layer 11 and the second base material layer 13 are made of the same material, the thicknesses of the first base material layer 11 and the second base material layer 13 are both larger than that of the reinforcing layer 12, the production process of the wing body 2 can be optimized through the determination of the used material, the production cost of the device is effectively reduced, the surface protective layer 10 comprises a corrosion-resistant layer 14 and a wear-resistant layer 15, the outer side of the corrosion-resistant layer 14 is fixedly connected with a wear-resistant layer 15, the thickness of the corrosion-resistant layer 14 is 0.16mm, the thickness of the wear-resistant layer 15 is 0.24mm, the wing body 2 can be prevented from being damaged by corrosion of acid and alkali substances through the use of the corrosion-resistant layer 14, the corrosion resistance of the wing body 2 is effectively improved, the damage of the wing body 2 due to abnormal wear can be avoided through the use of the wear-resistant layer 15, the wear resistance of the wing body 2 is effectively improved, the fixing effect on the wing body 2 can be enhanced through the arrangement of the fixing sleeve 9, the stability of the wing body 2 is effectively improved, the use strength of the wing body 2 can be increased through the arrangement of the reinforcing layer 12, the phenomenon that the wing body 2 is broken due to stress is effectively avoided, the surface of the wing body 2 can be protected through the arrangement of the surface protective layer 10, and the damage caused by corrosion and wear is avoided, effectively prolonging the service life of the wing body 2.

When the aircraft wing is used, the first base material layer 11 and the second base material layer 13 are made of aluminum alloy, the flight effect can be improved and the production cost can be reduced by using the first base material layer 11 and the second base material layer 13, the use material of the reinforcing layer 12 is carbon fiber and epoxy resin composite material, the use strength of the wing body 2 can be increased by using the reinforcing layer 12, the phenomenon that the wing body 2 is stressed and broken is effectively avoided, the use material of the corrosion-resistant layer 14 is aluminum alloy baked fluorocarbon paint, the wing body 2 can be prevented from being corroded by acid and alkali substances and damaged by using the corrosion-resistant layer 14, the corrosion resistance of the wing body 2 is effectively improved, the use material of the wear-resistant layer 15 is polyurethane paint, the wing body 2 can be prevented from being damaged by abnormal wear and the wear resistance of the wing body 2 is effectively improved by using the wear-resistant layer 15, through the cooperation of above-mentioned structure, can make the device reach intensity height, the weatherability is good, long service life's advantage is fit for using widely.

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

1. The utility model provides an unmanned aerial vehicle that wing high strength is not fragile, includes fuselage (1), its characterized in that: the aircraft wing is characterized in that fixed sleeves (9) are fixedly connected to two sides of the fuselage (1), an inner cavity of each fixed sleeve (9) is fixedly connected with a wing body (2), one end of each wing body (2) far away from the corresponding fixed sleeve (9) is fixedly connected with a motor (8), an output end of each motor (8) is rotatably connected with a propeller (3), connecting frames (7) are fixedly connected to two sides of the bottom of the fuselage (1), a bottom fixedly connected with a bottom plate (5) of each connecting frame (7), each wing body (2) comprises a surface protective layer (10), a first base material layer (11), a reinforcing layer (12) and a second base material layer (13), a reinforcing layer (12) is fixedly connected to the outer side of the second base material layer (13), the first base material layer (11) is fixedly connected to the outer side of the reinforcing layer (12), and the surface protective layer (10) is fixedly connected to the outer side of the first base material layer (11), the surface protection layer (10) comprises a corrosion-resistant layer (14) and a wear-resistant layer (15).

2. The unmanned aerial vehicle of claim 1, wherein the unmanned aerial vehicle has high strength wings and is not easy to damage, and the unmanned aerial vehicle comprises: the outer side of the corrosion-resistant layer (14) is fixedly connected with a wear-resistant layer (15), the thickness of the corrosion-resistant layer (14) is 0.16mm, and the thickness of the wear-resistant layer (15) is 0.24 mm.

3. The unmanned aerial vehicle of claim 1, wherein the unmanned aerial vehicle has high strength wings and is not easy to damage, and the unmanned aerial vehicle comprises: the buffer support leg is characterized in that the buffer support legs (4) are fixedly connected to two sides of the bottom plate (5), and the buffer cushions are fixedly connected to the bottoms of the buffer support legs (4).

4. The unmanned aerial vehicle of claim 1, wherein the unmanned aerial vehicle has high strength wings and is not easy to damage, and the unmanned aerial vehicle comprises: the first base material layer (11) and the second base material layer (13) are made of the same material, and the thickness of the first base material layer (11) and the thickness of the second base material layer (13) are larger than that of the reinforcing layer (12).

5. The unmanned aerial vehicle of claim 1, wherein the unmanned aerial vehicle has high strength wings and is not easy to damage, and the unmanned aerial vehicle comprises: the camera shooting device is characterized in that a camera shooting assembly (6) is fixedly connected to the bottom of the machine body (1), and a waterproof film is fixedly connected to the surface of the camera shooting assembly (6).