CN215663984U

CN215663984U - Aircraft

Info

Publication number: CN215663984U
Application number: CN202122451417.8U
Authority: CN
Inventors: 谢恩利; 范兴国
Original assignee: Flying Space Huizhou Technology Co ltd
Current assignee: Flying Space Huizhou Technology Co ltd
Priority date: 2021-10-12
Filing date: 2021-10-12
Publication date: 2022-01-28
Anticipated expiration: 2031-10-12

Abstract

The utility model relates to the technical field of flight, in particular to an aircraft, which comprises an aircraft body and wings arranged on two sides of the aircraft body, wherein a lifting framework and a propeller arranged on the lifting framework are arranged on the aircraft body; the lifting framework comprises a connecting seat connected with the machine body, a plurality of main frameworks of which one ends are connected with the connecting seat, two supporting frameworks connected with the other ends of the main frameworks and a ring frame connected with the end parts of the supporting frameworks, and an included angle is formed between the two supporting frameworks connected with the same main framework; the screw propellers are arranged at the joint of the main framework and the supporting framework and the joint of the supporting framework and the annular frame. The aircraft can vertically take off and land, realizes transportation of large loads, and has the advantages of firm structure, good stability, strong load and stable flight.

Description

Aircraft

Technical Field

The utility model relates to the technical field of flight, in particular to an aircraft.

Background

With the development of science and technology, the flight technology is more mature. Common aircrafts are airplanes, quadcopters and the like. Unmanned four shaft air vehicle has gained popularity in life at present, and it is widely used in a plurality of fields such as photography, fire control, agricultural. The four-axis aircraft utilizes four rotors as flight engines to fly in the air, has small size and light weight, can carry certain task load like an unmanned aircraft which is suitable for carrying and using, and has autonomous navigation flight capability. And the specific flight task is completed under the complex and dangerous environment. However, due to the structural limitation, the existing four-axis aircraft has insufficient load, small carrying load-bearing capacity, is not beneficial to carrying people and heavy load, and has poor stability during carrying.

SUMMERY OF THE UTILITY MODEL

Aiming at the defects of the prior art, the utility model provides the aircraft which has large bearing capacity and good stability, can realize vertical landing and is convenient for people and goods carrying.

In order to solve the technical problems, the utility model adopts the following technical scheme:

the utility model provides an aircraft, which comprises a fuselage and wings arranged on two sides of the fuselage, wherein the fuselage is provided with a lifting framework and propellers arranged on the lifting framework;

the lifting framework comprises a connecting seat connected with the machine body, a plurality of main frameworks of which one ends are connected with the connecting seat, two supporting frameworks connected with the other ends of the main frameworks and a ring frame connected with the end parts of the supporting frameworks, and an included angle is formed between the two supporting frameworks connected with the same main framework;

the screw propellers are arranged at the joint of the main framework and the supporting framework and the joint of the supporting framework and the annular frame.

The four main frameworks are uniformly distributed and connected to the connecting seat in the circumference; the propellers at the joints of the plurality of supporting frames and the ring frame are uniformly distributed on the ring frame.

The wing is provided with a connecting block, one end of the connecting block is connected with the wing, and the other end of the connecting block is connected with the ring frame.

Wherein, the wing is connected with a tail frame extending to the tail of the fuselage, and the ring frame is connected with the tail frame.

The tail frame comprises horizontal rods connected with wings on two sides, horizontal tail plates connected with the horizontal rods on the two sides and vertical tail plates connected with the horizontal rods, and the ring frame is connected with the top ends of the vertical tail plates.

Wherein, the afterbody of fuselage is provided with the propulsion screw that is used for propelling aircraft forward.

The aircraft body is provided with a flight cabin, and a seat is arranged in the flight cabin.

Wherein, the bottom of fuselage sets up in the undercarriage.

The utility model has the beneficial effects that:

the utility model provides an aircraft, which adopts wings on two sides of a fuselage to combine with a plurality of propellers arranged on a lifting framework, can vertically rise and fall, and realizes the transportation of a large load; the lifting framework adopts a plurality of main frameworks, supporting frameworks and ring frame connecting structures, and has firm structure and good stability; the propellers are arranged at the connecting positions of the main framework and the branch frameworks, and the propellers at the connecting positions form inner-ring propellers; the propellers are arranged at the connecting positions of the supporting frames and the ring frames, and the propellers at the connecting positions form outer ring propellers, so that the lifting force is large, the load is strong, and the flying is stable.

Drawings

Fig. 1 is a schematic perspective view of the present invention.

Fig. 2 is a schematic perspective view of another stereoscopic view of the present invention.

Fig. 3 is a schematic perspective view of the utility model after hiding part of the flight deck housing.

Fig. 4 is a schematic perspective view of another stereoscopic view of the present invention.

Detailed Description

In order to facilitate understanding of those skilled in the art, the present invention will be further described with reference to the following examples and drawings, which are not intended to limit the present invention. The present invention is described in detail below with reference to the attached drawings.

Referring to fig. 1 to 4, an aircraft includes a fuselage 1 and wings 2 disposed on two sides of the fuselage 1, wherein the fuselage 1 is provided with a lifting framework and a propeller 4 disposed on the lifting framework; the lifting framework comprises a connecting seat 31 connected with the machine body 1, a plurality of main frameworks 32 of which one ends are connected with the connecting seat 31, two supporting frameworks 33 connected with the other ends of the main frameworks 32 and a ring frame 34 connected with the end parts of the supporting frameworks 33, and an included angle is formed between the two supporting frameworks 33 connected with the same main framework 32; the propeller 4 is arranged at the joint of the main framework 32 and the supporting framework 33 and the joint of the supporting framework 33 and the ring frame 34.

The aircraft adopts the wings 2 on both sides of the aircraft body 1 and a plurality of propellers 4 arranged on the lifting framework, which can vertically rise and fall to realize the transportation of large load; the lifting framework adopts a connecting structure of a plurality of main frameworks 32, supporting frameworks 33 and ring frames 34, and has firm structure and good stability; the propellers 4 are arranged at the connecting part of the main framework 32 and the supporting framework 33, and the propellers 4 at the connecting part form the inner-ring propellers 4; the propellers 4 are arranged at the joints of the supporting frames 33 and the ring frames 34, and the propellers 4 at the joints form the outer ring propellers 4, so that the lifting force is large, the load is strong, and the flight is stable.

Specifically, the ring frame 34 has a circular or elliptical structure. The main frame 32 may be provided in two or more. Preferably, four main frameworks 32 are arranged, and the four main frameworks 32 are uniformly distributed and connected to the connecting seat 31 in the circumference; the propellers 4 at the joints of the plurality of supporting frames 33 and the ring frame 34 are uniformly distributed on the ring frame 34.

In this embodiment, the wing 2 is provided with a connecting block 5, one end of the connecting block 5 is connected with the wing 2, and the other end of the connecting block 5 is connected with the ring frame 34. The wing 2 is connected with a tail frame extending to the tail of the fuselage 1, and the ring frame 34 is connected with the tail frame; the tail stock includes the horizontal pole 61 of being connected with both sides wing 2, the vertical tailboard 63 of being connected with horizontal tailboard 62 and the horizontal pole 61 that the horizontal pole 61 is connected with both sides horizontal pole, the ring frame 34 is connected with the top of vertical tailboard 63, is convenient for further fixed and installation to ring frame 34 for the aircraft structure is more firm, and the flight is more steady.

In this embodiment, the tail of the fuselage 1 is provided with a propulsion propeller 7 for propelling the aircraft to move forward, so as to provide forward power for the aircraft to fly, and when the aircraft flies to a certain height, the propulsion propeller 7 can be independently used to work in cooperation with the wings 2 on two sides, so as to realize flight.

In this embodiment, the fuselage 1 is provided with a flight deck 11, and a seat 12 is provided in the flight deck 11. The bottom of the fuselage 1 is provided with landing gear 13. Preferably, the diameter of the ring frame 34 is larger than the length of the aircraft body 1, and the ring frame 34 larger than the aircraft body 1 is adopted, so that the distribution of a plurality of propellers 4 is facilitated, and meanwhile, the large-load and stable flight is realized.

Although the present invention has been described with reference to the above preferred embodiments, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the utility model as defined by the appended claims.

Claims

1. The utility model provides an aircraft, includes fuselage (1) and sets up wing (2) in fuselage (1) both sides, its characterized in that: the machine body (1) is provided with a lifting framework and a propeller (4) arranged on the lifting framework;

the lifting framework comprises a connecting seat (31) connected with the machine body (1), a plurality of main frameworks (32) with one ends connected with the connecting seat (31), two supporting frameworks (33) connected with the other ends of the main frameworks (32) and a ring frame (34) connected with the end parts of the supporting frameworks (33), and an included angle is formed between the two supporting frameworks (33) connected with the same main framework (32);

the propeller (4) is arranged at the joint of the main framework (32) and the supporting framework (33) and the joint of the supporting framework (33) and the ring frame (34).

2. The aircraft of claim 1, wherein: four main frameworks (32) are arranged, and the four main frameworks (32) are uniformly distributed and connected to the connecting seat (31) in the circumference; the propellers (4) at the joints of the plurality of supporting frames (33) and the ring frame (34) are uniformly distributed on the ring frame (34).

3. The aircraft of claim 1, wherein: the wing (2) is provided with a connecting block (5), one end of the connecting block (5) is connected with the wing (2), and the other end of the connecting block (5) is connected with the ring frame (34).

4. The aircraft of claim 1, wherein: the wing (2) is connected with a tail frame extending to the tail of the fuselage (1), and the ring frame (34) is connected with the tail frame.

5. The aircraft according to claim 4, characterized in that: the tail frame comprises horizontal rods (61) connected with the wings (2) on the two sides, horizontal tail plates (62) connected with the horizontal rods (61) on the two sides and vertical tail plates (63) connected with the horizontal rods (61), and the ring frame (34) is connected with the top ends of the vertical tail plates (63).

6. The aircraft of claim 1, wherein: the tail part of the aircraft body (1) is provided with a propelling propeller (7) for propelling the aircraft to advance.

7. The aircraft of claim 1, wherein: the aircraft body (1) is provided with a flight cabin (11), and a seat (12) is arranged in the flight cabin (11).

8. The aircraft of claim 1, wherein: the bottom of the fuselage (1) is arranged on the undercarriage (13).

9. The aircraft of claim 1, wherein: the ring frame (34) is in a circular or oval structure.

10. The aircraft according to any one of claims 1 to 9, characterized in that: the diameter of the ring frame (34) is larger than the length of the machine body (1).