CN216834262U

CN216834262U - Big load foldable six-rotor unmanned aerial vehicle

Info

Publication number: CN216834262U
Application number: CN202220049235.XU
Authority: CN
Inventors: 张柏博; 刘聪聪; 罗勇冠
Original assignee: Yantai Yundu Hawk Uav Application Technology Co ltd
Current assignee: Yantai Yundu Hawk Uav Application Technology Co ltd
Priority date: 2022-01-10
Filing date: 2022-01-10
Publication date: 2022-06-28
Anticipated expiration: 2032-01-10

Abstract

The utility model provides a six collapsible rotor unmanned aerial vehicle of big load, including setting up fixed arm and the folding arm in unmanned aerial vehicle body four corners position, both sides portion respectively, the one end of folding arm is connected with the fixed arm through two locating pins that are parallel to each other, and the other end of folding arm is provided with the impeller frame, and the impeller frame is connected with the wing through the pivot. Two folding arms at one end of the unmanned aerial vehicle body can be arranged in a left-right rotating mode, and the wings are arranged above the folding arms; two folding arms at the other end of the wing can be arranged in a left-right rotating manner, and wings are arranged below the folding arms; the folding arms at the two sides can be arranged in a vertical rotating way, and the wings are arranged below the folding arms. The utility model provides a six collapsible rotor unmanned aerial vehicle of big load has made things convenient for the folding process of rotor among the six rotor unmanned aerial vehicle of big load, not only has higher joint strength, folding process also convenient and fast simultaneously, portable.

Description

Big load foldable six-rotor unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicle, it relates to a six collapsible rotor unmanned aerial vehicle of big load specifically to say so.

Background

The unmanned aerial vehicle is an unmanned aerial vehicle operated by a radio remote control device or a self program control device, and can be divided into military and civil aspects according to the application field, the unmanned aerial vehicle is divided into a reconnaissance plane and a target plane, and the unmanned aerial vehicle is applied in the civil aspect, the unmanned aerial vehicle and the industry and 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 the industrial application and develop the unmanned aerial vehicle technology.

Among the prior art, the unmanned aerial vehicle of some fixed arms may only have a slice rotor, and the unmanned aerial vehicle of some helicopter class may have two or more than two rotors, and every rotor makes the air current on every side change through rotating to form the lift, a plurality of rotors have taken the most sectional area of unmanned aerial vehicle, have brought the inconvenience for carrying of unmanned aerial vehicle.

Although foldable variant-wing drones now appear, but are generally used in situations with a small number of rotors (generally 1-4 rotors), and the mechanical connection strength is convenient and not as desirable, the folding arm of the six-rotor drone is optimized and modified in the scheme so as to solve the technical problems.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a six collapsible rotor unmanned aerial vehicle of big load has solved the inconvenient technical problem of the rotor folding difficulty among the six rotor unmanned aerial vehicle of big load, not only has higher joint strength, folding process convenient and fast also simultaneously, portable.

The utility model provides a six collapsible rotor unmanned aerial vehicle of big load, includes the unmanned aerial vehicle body, still including setting up fixed arm and the folding arm in unmanned aerial vehicle body four corners position, both sides portion respectively, the one end of folding arm through two locating pins that are parallel to each other with the fixed arm is connected, the other end of folding arm is provided with the impeller frame, the impeller frame is connected with the wing through the pivot.

The two front folding arms at the front end of the unmanned aerial vehicle body can be arranged in a left-right rotating mode, the two rear folding arms at the rear end of the unmanned aerial vehicle body can be arranged in a left-right rotating mode, and the side folding arms at the two side parts of the unmanned aerial vehicle body can be arranged in an up-down rotating mode;

the wings are arranged above the front folding arm, below the rear folding arm and below the side folding arms respectively.

The front folding arm and the rear folding arm are consistent in length, and the length of the side folding arm is smaller than that of the front folding arm and that of the rear folding arm;

the included angle of the two front folding arms is smaller than 60 degrees, and the included angle of the two rear folding arms is smaller than 60 degrees.

The below of unmanned aerial vehicle body is provided with the undercarriage, the undercarriage has two and sets up respectively the aircraft nose direction and the tail direction of unmanned aerial vehicle body, two the undercarriage sets up towards the outside slope respectively.

The impeller frame is provided with the motor, the motor pass through the pivot with the wing is connected, the pivot is 87 with the contained angle of folding arm.

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

(1) the fixed arm is connected with the folding arm through two positioning pins which are parallel to each other, so that on one hand, the connecting strength is high, on the other hand, when the unmanned aerial vehicle stops being used, one positioning pin can be pulled out, and under the action of the other positioning pin, the folding arm can rotate to form a folding effect, and the unmanned aerial vehicle is convenient and quick;

in addition, the folding arms at the two ends of the unmanned aerial vehicle rotate left and right, and the folding arms at the side parts rotate up and down, so that the interference of the folding arms in the rotating process can be avoided;

in addition, when the folding operation is carried out, only the positioning pin needs to be disassembled, the operation is simple, and the cost is low;

(2) this design is a six rotor unmanned aerial vehicle of big load, and its standard payload capacity is 100 kilograms, mainly is applied to fields such as unmanned aerial vehicle commodity circulation, emergency rescue, emergent fire control.

Drawings

Fig. 1 is the utility model provides an unmanned aerial vehicle's whole block diagram.

Fig. 2 is the utility model discloses in the embodiment of the wing structure chart of one of them tip of unmanned aerial vehicle.

Fig. 3 is the embodiment of the utility model provides an unmanned aerial vehicle wherein a folding organism structure chart of tip.

Fig. 4 is the utility model discloses wing structure chart of lateral part in the embodiment of the utility model.

Fig. 5 is the embodiment of the utility model provides an in unmanned aerial vehicle folding organism structure picture of lateral part.

Fig. 6 is the holistic fold condition picture of unmanned aerial vehicle in the embodiment of the utility model.

Wherein, in the figure: 1. an airfoil; 2. a front folding arm; 21. a side folding arm; 22. a rear folding arm; 3. a landing gear; 5. an unmanned aerial vehicle body; 5-1 and a first fixed arm; 5-2 and a second fixing arm; 6. a rotating shaft; 8. an impeller base; 9. a movable portion; 92. and a positioning pin.

Detailed Description

In order to clearly illustrate the technical features of the present solution, the present solution is described below by way of specific embodiments.

Referring to fig. 1, a six collapsible rotor unmanned aerial vehicle of heavy load, including unmanned aerial vehicle body 5, still including setting up fixed arm and the folding arm 2 in 5 four corners positions of unmanned aerial vehicle body, both sides portion respectively, the one end of folding arm 2 is connected with the fixed arm through two locating pins 92 that are parallel to each other, and the other end of folding arm 2 is provided with impeller frame 8, and impeller frame 8 is connected with wing 1 through pivot 6.

Further, the positioning pin 92 may be replaced with a bolt, a hinge shaft, or the like.

In this scheme, the bottom of unmanned aerial vehicle body 5 is provided with undercarriage 3, and when folding arm 2 can rotate, the fixed arm is connected for movable part 9 with folding between the arm 2.

For convenience in understanding, the fixed arm at the end part is a fixed arm I5-1, and the fixed arm at the side part is a fixed arm II 5-2.

Referring to fig. 2, 3, 4 and 5, the two front folding arms 2 at the front end of the unmanned aerial vehicle body 5 can be arranged in a left-right rotating manner, the two rear folding arms 22 at the rear end of the unmanned aerial vehicle body can be arranged in a left-right rotating manner, and the side folding arms 21 at the two side parts can be arranged in a vertical rotating manner;

the wing 1 is arranged above the front folding arm 2, below the rear folding arm 22 and below the side folding arm 21.

The length of the front folding arm 2 is consistent with that of the rear folding arm 22, and the length of the side folding arm 21 is smaller than that of the front folding arm 2 and that of the rear folding arm 22;

the angle between the two front folding arms 2 is less than 60 °.

The below of unmanned aerial vehicle body 5 is provided with undercarriage 3, undercarriage 3 has two and sets up respectively the aircraft nose direction and the tail direction of unmanned aerial vehicle body 5, two undercarriage 3 sets up towards the outside slope respectively.

The impeller frame 8 is provided with a motor, the motor passes through the rotating shaft 6 and the wing 1 is connected, and the included angle between the rotating shaft 6 and the folding arm is 87 degrees.

The utility model discloses a concrete working process:

referring to fig. 6, in use, according to the above description of the present solution, the fixed arm and six folding arms are installed and fastened by two positioning pins;

when the rotation of each folding arm of needs is folding, dismantle one of them locating pin, rotatory to adjacent lateral part direction with each folding arm of unmanned aerial vehicle tip, the folding arm of side is rotatory downwards, reaches the fold condition that can conveniently carry.

Note:

at present, the load capacity of most unmanned aerial vehicles is hundreds of grams to tens of kilograms, and the load capacity is small and is not suitable for application scenes with large loads. The structural design difficulty of the large-load unmanned aerial vehicle is that the large-load unmanned aerial vehicle is light in weight and small in transportation size under the condition that the strength of the unmanned aerial vehicle body is high, and the technical scheme mainly lies in the structural design of the large-load unmanned aerial vehicle;

the screw does not need to be dismantled in the folding in this scheme, and after folding arm rotation, the carbon plate on it can play the effect of supporting the impeller frame as relying on.

The technical features that the utility model has not been described can be realized through or adopt prior art, and no longer give unnecessary details here, and of course, the above-mentioned explanation is not right the utility model discloses a restriction, the utility model discloses also not only be limited to the above-mentioned example, ordinary skilled person in this technical field is in the utility model discloses a change, modification, interpolation or replacement made in the essential scope also should belong to the utility model discloses a protection scope.

Claims

1. The utility model provides a six collapsible rotor unmanned aerial vehicle of big load, includes unmanned aerial vehicle body (5), its characterized in that, still including setting up fixed arm and folding arm (2) in unmanned aerial vehicle body (5) four corners position, both sides portion respectively, the one end of folding arm (2) through two locating pin (92) that are parallel to each other with the fixed arm is connected, the other end of folding arm (2) is provided with impeller frame (8), impeller frame (8) are connected with wing (1) through pivot (6).

2. A heavy load foldable six-rotor unmanned aerial vehicle according to claim 1, wherein the two front folding arms (2) at the front end of the unmanned aerial vehicle body (5) can be arranged in a left-right rotating manner, the two rear folding arms (22) at the rear end can be arranged in a left-right rotating manner, and the side folding arms (21) at the two side parts can be arranged in a vertical rotating manner;

the wings (1) are arranged above the front folding arm (2), below the rear folding arm (22) and below the side folding arm (21) respectively.

3. A heavy load foldable hexa-rotor drone according to claim 2, characterised in that the front folding arm (2) is of the same length as the rear folding arm (22), the side folding arms (21) being of a smaller length than the front folding arm (2), the rear folding arm (22);

the included angle of the two front folding arms (2) is smaller than 60 degrees, and the included angle of the two rear folding arms (2) is smaller than 60 degrees.

4. A heavy load foldable hexa-rotor unmanned aerial vehicle according to claim 3, wherein the undercarriage (3) is arranged below the unmanned aerial vehicle body (5), the undercarriage (3) has two and is respectively arranged in the nose direction and the tail direction of the unmanned aerial vehicle body (5), and the two undercarriage (3) are respectively arranged obliquely towards the outer side.

5. A heavy load foldable hexa-rotor unmanned aerial vehicle according to claim 4, wherein the impeller base (8) is provided with a motor, the motor is connected with the wing (1) through the rotating shaft (6), and the included angle between the rotating shaft (6) and the folding arm is 87 °.