CN111661361A

CN111661361A - Fast assembly's unmanned aerial vehicle

Info

Publication number: CN111661361A
Application number: CN202010382283.6A
Authority: CN
Inventors: 贺军; 房佳琦; 曲长征; 杨鹏; 张秋豪; 熊灿松; 许兴
Original assignee: Zhuhai Tianqing Aerospace Technology Co ltd
Current assignee: Zhuhai Tianqing Aerospace Technology Co ltd
Priority date: 2020-05-08
Filing date: 2020-05-08
Publication date: 2020-09-15

Abstract

The invention discloses a rapidly assembled unmanned aerial vehicle, and relates to the technical field of aircrafts. The problem of wasting time and energy of unmanned aerial vehicle equipment and dismantlement can be solved. An unmanned aerial vehicle of fast assembly includes fuselage main part, central wing, rotor connecting rod, outer wing, fin, first landing gear, second undercarriage, rotary wing and rearmounted screw together. The center wing is detachably provided on the body. The outer wings are detachably disposed at both sides of the central wing. The rotor links are disposed on the central wing or the outer wing. The tail wing is detachably arranged at the tail end of the main body of the machine body. The first landing frame is arranged at the tail end of the machine body. The second landing gear is arranged at the front end of the fuselage main body. The rotor wing detachably sets up at rotor wing connecting rod both ends. The rear propeller is arranged at the tail end of the machine body main body. The rotor wing connecting rod and the rotary wing are fixed through a second locking device. Each part is connected by adopting a quick detachable mode, and the assembling and disassembling efficiency is obviously improved. In occasions such as search and rescue, topography reconnaissance, such efficiency promotion is vital.

Description

Fast assembly's unmanned aerial vehicle

Technical Field

The invention relates to the technical field of aircrafts, in particular to a rapidly-assembled unmanned aerial vehicle.

Background

Along with the development of science and technology, the unmanned aerial vehicle technology develops and popularizes rapidly, and whether military or civil unmanned aerial vehicle has great progress, is used widely in all trades, for example military investigation, agricultural pesticide sprays, takes photo by plane, remote control toy etc.. But in present civil unmanned aerial vehicle's the use, still have many inconveniences, unmanned aerial vehicle's the structure is most comparatively complicated, needs the longer time to assemble unmanned aerial vehicle before taking off, still needs the longer time to dismantle after the descending and accomodates unmanned aerial vehicle, has promoted unmanned aerial vehicle's the use degree of difficulty like this.

Disclosure of Invention

The invention aims to at least solve one of the technical problems in the prior art, and provides a rapid-assembly unmanned aerial vehicle which can rapidly complete assembly and disassembly.

According to a first aspect of the invention, there is provided a fast assembling drone comprising a fuselage body; a central wing detachably provided on the body; the outer wings are detachably arranged on two sides of the central wing; a rotor link disposed on the central wing or the outer wing; the tail wing is detachably arranged at the tail end of the machine body main body; the first landing frame is arranged at the tail end of the machine body main body; the second undercarriage is arranged at the front end of the fuselage main body; the rotary wings are detachably arranged at two ends of the rotor wing connecting rod; and the rear propeller is arranged at the tail end of the machine body main body.

The invention has the following beneficial effects: this fast assembly's unmanned aerial vehicle, including fuselage main part, central authorities' wing, outer wing, rotor connecting rod, fin, first landing gear, second undercarriage, rotary wing and rearmounted screw together. The fuselage main part all has adopted detachable the connection with central wing, rotor connecting rod, outer wing, fin and rotary wing, only needs to aim at the part to the relevant position after, can accomplish the equipment with the whole locks of first locking device and second locking device, promotes the packaging efficiency. Similarly, such efficiency improvements are of paramount importance in search and rescue, terrain exploration, and the like.

According to the fast-assembly unmanned aerial vehicle in the first aspect of the invention, the rotor wing connecting rod and the rotary wing are fixed through a second locking device, and the second locking device comprises a first connecting pipe connected to the rotor wing connecting rod; the second connecting pipe is hinged with the first connecting pipe and connected to the rotating wing; and one end of the clamping sleeve is movably sleeved on the second connecting pipe, and the other end of the clamping sleeve is screwed on the first connecting pipe. The hinge structure of the first connecting pipe and the second connecting pipe enables the rotary wing to be folded and stored. The removable and easy nature of the second locking mechanism enables the rotor wing and rotor wing link to be quickly assembled and disassembled without tools.

According to the fast-assembly unmanned aerial vehicle in the first aspect of the invention, a groove is formed in one end of the clamping sleeve, the groove is opposite to the first connecting pipe, and the groove is used for placing a check ring. The inner chamber of cutting ferrule is irritated to wind when retaining ring can prevent unmanned aerial vehicle flight, influences flight stability.

The fast-assembly unmanned aerial vehicle further comprises a load module, wherein the load module is fixed with the main body of the unmanned aerial vehicle body through the first locking device; the first locking device includes: a fixed hook; and the rotary buckle can be fixedly clamped with the fixed hook, one of the fixed hook and the rotary buckle is arranged on the machine body main body, and the other one is arranged on the load module. The removable and easy feature of the first locking means enables the load module and the body to be assembled and disassembled quickly without tools.

According to the fast-assembly unmanned aerial vehicle in the first aspect of the invention, the central wing and the main body of the vehicle body are fixed through a first locking device; the first locking device includes: a fixed hook; and the rotary buckle can be fixedly clamped with the fixed hook, one of the fixed hook and the rotary buckle is arranged on the machine body main body, and the other one is arranged on the central wing. The removable and easy nature of the first locking means enables the central wing and the fuselage body to be assembled and disassembled quickly without tools.

According to a fast assembling drone of the first aspect of the invention, the outer wing and the central wing are fixed by the first locking means; the first locking device includes: a fixed hook; and the rotary buckle can be fixedly clamped with the fixed hook, one of the fixed hook and the rotary buckle is arranged on the outer wing, and the other is arranged on the central wing. The removable and easy nature of the first locking means enables the outer and central wings to be quickly assembled and disassembled without tools.

According to the fast-assembly unmanned aerial vehicle in the first aspect of the invention, the tail wing and the main body of the main body are fixed through the first locking device; the first locking device includes: a fixed hook; and the rotary buckle can be fixedly clamped with the fixed hook, one of the fixed hook and the rotary buckle is arranged on the machine body, and the other one is arranged on the tail wing. The removable and easy feature of the first locking means enables the tail wing and the main body of the fuselage to be assembled and disassembled quickly without tools.

According to the fast-assembly unmanned aerial vehicle, one end of the first supporting pipe is fixed on the outer wing, the other end of the first supporting pipe penetrates through the central wing, the first supporting pipe serves as a framework to support the connection between the central wing and the outer wing, and the connection strength and the structural strength of the central wing and the outer wing are enhanced.

According to the fast-assembly unmanned aerial vehicle, one end of the second supporting pipe is fixed on the tail wing, the other end of the second supporting pipe penetrates through the main body of the main.

According to the fast-assembly unmanned aerial vehicle in the first aspect of the invention, the tail comprises a left tail and a right tail, and the left tail and the right tail are arranged in a V shape.

The invention has the beneficial effects that:

this unmanned aerial vehicle's of fast assembly fuselage main part and central wing, rotor connecting rod, outer wing, fin, rotary wing and load module have all adopted detachable connection, only need aim at the part to corresponding position after, can accomplish the equipment with the whole locks of first locking device and second locking device, promote packaging efficiency. Likewise, such efficiency improvements are of paramount importance in situations such as search and rescue.

Drawings

In order to more clearly illustrate the technical solution in the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly described below. Obviously, the described figures are only some embodiments of the invention, not all embodiments, and other designs and figures can be obtained by those skilled in the art without inventive effort, based on these figures:

FIG. 1 is a schematic structural diagram of a preferred embodiment of the present invention;

FIG. 2 is an exploded view of the preferred embodiment of the present invention;

FIG. 3 is a top view of the preferred embodiment of the present invention;

FIG. 4 is a schematic structural diagram of a first locking device according to a preferred embodiment of the present invention;

FIG. 5 is a cross-sectional view of a first locking device in accordance with a preferred embodiment of the present invention;

FIG. 6 is a schematic structural view of a second locking device according to a preferred embodiment of the present invention;

fig. 7 is a cross-sectional view of a second locking device in accordance with a preferred embodiment of the present invention.

Detailed Description

Reference will now be made in detail to the present preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to like elements throughout.

In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as the upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and larger, smaller, larger, etc. are understood as excluding the number, and larger, smaller, inner, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.

Referring to fig. 1 to 3, a fast-assembling drone according to an embodiment of the present invention includes a fuselage body 10, a central wing 20, a rotor link 30, an outer wing 40, a tail wing 50, a first landing gear 60, a second landing gear 70, a rotary wing 80, and a rear propeller 90. The center wing 20 is detachably provided on the body 10. The outer wings 40 are detachably provided at both sides of the central wing 20. Rotor links 30 are disposed on either center wing 20 or outer wing 40. The rear wing 50 is detachably provided at the end of the body 10. The first landing gear 60 is disposed at an end of the body 10. The second landing gear 70 is provided at the forward end of the fuselage body 10. Rotary wings 80 are detachably provided at both ends of rotor link 30. The rear propeller 90 is provided at the end of the body main body 10.

Referring to fig. 2 to 5, the unmanned aerial vehicle further includes a load module 100, and the load module 100 is fixed to the main body 10 by a first locking device 110. The first locking device includes a fixed hook 111 and a rotating buckle 112 that can be fastened to the fixed hook 110. The fixed hook 111 and the rotating buckle 112 are mounted on the main body 10, and the other is mounted on the load module 100. The detachable and easy nature of the first locking means 110 enables the load module 100 and the body 10 to be quickly assembled and disassembled without tools.

The center wing 20 is fixed to the body 10 by the first locking device 110. The first locking device includes a fixed hook 111 and a rotating buckle 112 that can be fastened to the fixed hook 110. The fixed hook 111 and the rotating buckle 112 are mounted on the main body 10 alternatively, and the other is mounted on the central wing 20. The removable and easy feature of the first locking means 110 enables the central wing 20 and the fuselage body 10 to be assembled and disassembled quickly without tools.

The outer wing 40 is fixed with the central wing 20 by the first locking means 110. The first locking device includes a fixed hook 111 and a rotating buckle 112 that can be fastened to the fixed hook 110. The fixed hook 111 and the rotating buckle 112 are mounted on the outer wing 40, and the other is mounted on the central wing 20. The removable and easy nature of the first locking means 110 allows the outer wing 40 and the central wing 20 to be quickly assembled and disassembled without tools.

The rear wing 50 is fixed to the body 10 by the first locking means 120. The first locking device includes a fixed hook 111 and a rotating buckle 112 that can be fastened to the fixed hook 110. The fixed hook 111 and the rotating buckle 112 are mounted on the main body 10, and the other is mounted on the tail wing 50. The detachable and easy nature of the first locking means 110 enables the rear wing 50 and the body 10 to be assembled and disassembled quickly without tools.

This unmanned aerial vehicle still includes first stay tube 41, and first stay tube 41 one end is fixed on outer wing 40, and the setting is worn in central wing 20 to the other end. The coupling strength and the structural strength of the outer wing 40 and the central wing 20 are reinforced.

This unmanned aerial vehicle still includes second stay tube 53, and second stay tube 53 one end is fixed on fin 50, and the other end wears to establish in fuselage main part 10. The coupling strength and the structural strength of the rear wing 50 to the body 10 are reinforced. The tail 50 includes a left tail 51 and a right tail 52. The left and

right tail wings

51 and 52 are arranged in a V-shape.

Referring to fig. 6 to 7, the rotor link 30 and the rotary wing 80 are fixed by the second locking device 120. The second locking device 120 includes a first connection tube 121, a second connection tube 122, and a ferrule 123. First connection tube 121 is connected to rotor link 30. The second connection pipe 122 is hinged to the first connection pipe 121 and connected to the rotary wing 80. One end of the cutting sleeve 123 is movably sleeved on the second connecting pipe 122, and the other end of the cutting sleeve 123 is screwed on the first connecting pipe 121. The hinge structure of the first connection pipe 121 and the second connection pipe 122 enables the rotary wing 80 to be folded and stored.

A groove 123a is formed in one end of the ferrule 123, the groove 123a is opposite to the first connecting pipe 121, and the groove 123a is used for placing the check ring 124. The retaining ring can prevent that the cavity of cutting ferrule is irritated to wind when unmanned aerial vehicle flies, influences flight stability. Of course, it should be noted that the retainer ring 124 may be an orifice ring, a felt ring, or the like.

The second locking device 120 is used by first inserting the ferrule 123 into the fastening element 121 and then connecting the fastening element 121 to the spinner assembly 122 using the first pin 125. Finally, the clamping element 121 is clamped and fixed with the spinner assembly 122 through the clamping sleeve 123. The removable, easy feature of second locking device 120 enables rotary wing 80 and rotor linkage 30 to be quickly assembled and disassembled without tools.

During the unmanned aerial vehicle equipment, place each subassembly of unmanned aerial vehicle in the relevant position of fuselage main part 10, can accomplish the installation with whole locks of first locking device 110 and second locking device 120. When the first locking device 110 and the second locking device 120 are completely unlocked, the respective components can be detached from the main body 10.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.

Claims

1. A fast assembly's unmanned aerial vehicle, its characterized in that includes:

a body main body (10);

a center wing (20) detachably provided on the body (10);

outer wings (40) detachably disposed at both sides of the central wing (20);

a rotor link (30) disposed on the central wing (20) or the outer wing (40);

a tail wing (50) detachably provided at a distal end of the body (10);

a first landing shelf (60) provided at an end of the body (10);

a second landing gear (70) provided at a forward end of the fuselage body (10);

the rotary wing (80) is detachably arranged at two ends of the rotor wing connecting rod (30); and

and the rear propeller (90) is arranged at the tail end of the machine body main body (10).

2. A fast-assembling drone according to claim 1, characterized in that: the rotor wing connecting rod (30) and the rotary wing (80) are fixed through a second locking device (120), and the second locking device (120) comprises

A first connection tube (121) connected to the rotor link (30);

a second connection pipe (122) hinged to the first connection pipe (121) and connected to the rotary wing (80); and

the clamping sleeve (123), the movable cover of clamping sleeve (123) one end is established on second connecting pipe (122), the spiral shell of clamping sleeve (123) other end is established on first connecting pipe (121).

3. A fast-assembling drone according to claim 2, characterized in that: a groove (123a) is formed in one end of the clamping sleeve (123), the groove (123a) is opposite to the first connecting pipe (121), and the groove (123a) is used for placing a check ring (124).

4. A fast-assembling drone according to claim 1, characterized in that: the loading device further comprises a loading module (100), wherein the loading module (100) is fixed with the fuselage main body (10) through the first locking device (110); the first locking device comprises a fixed hook (111) and a rotating buckle (112) which can be tightly fixed with the fixed hook (110), wherein the fixed hook (111) and the rotating buckle (112) are selected to be installed on the machine body main body (10), and the other is installed on the load module (100).

5. A fast-assembling drone according to claim 1, characterized in that: the central wing (20) is fixed with the fuselage body (10) by means of the first locking device (110); the first locking device comprises a fixed hook (111) and a rotary buckle (112) which can be tightly fixed with the fixed hook (110), wherein the fixed hook (111) and the rotary buckle (112) are selected to be installed on the machine body main body (10), and the other is installed on the central wing (20).

6. A fast-assembling drone according to claim 1, characterized in that: the outer wing (40) and the central wing (20) are fixed by the first locking device (110); the first locking device comprises a fixed hook (111) and a rotating buckle (112) which can be clamped and fixed with the fixed hook (110), wherein one of the fixed hook (111) and the rotating buckle (112) is arranged on the outer wing (40), and the other is arranged on the central wing (20).

7. A fast-assembling drone according to claim 1, characterized in that: the tail wing (50) and the fuselage body (10) are fixed by the first locking device (120); the first locking device (110) comprises: fixed pothook (111) and can with fixed pothook (110) chucking fixed rotatory knot (112), fixed pothook (111) with rotatory knot (112) one is installed on fuselage main part (10), and another is installed on fin (50).

8. A fast-assembling drone according to claim 1, characterized in that: the wing-shaped structure is characterized by further comprising a first supporting pipe (41), wherein one end of the first supporting pipe (41) is fixed on the outer wing (40), and the other end of the first supporting pipe (41) penetrates through the central wing (20).

9. A fast-assembling drone according to claim 1, characterized in that: the novel aircraft tail wing supporting structure further comprises a second supporting pipe (53), one end of the second supporting pipe (53) is fixed on the tail wing (50), and the other end of the second supporting pipe (53) penetrates through the aircraft body (10).

10. A fast-assembling drone according to claim 1, characterized in that: the tail wing (50) comprises a left tail wing (51) and a right tail wing (52), and the left tail wing (51) and the right tail wing (52) are arranged in a V shape.