CN213832091U

CN213832091U - Portable individual combat unmanned aerial vehicle with foldable wings

Info

Publication number: CN213832091U
Application number: CN202023170328.8U
Authority: CN
Inventors: 赵昆
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-12-25
Filing date: 2020-12-25
Publication date: 2021-07-30
Anticipated expiration: 2030-12-25

Abstract

The utility model discloses a portable individual soldier unmanned aerial vehicle of fighting of wing folding, including fuselage, wing and front end fin, the screw is installed on the top of fuselage, and the end-to-end connection of fuselage has the fin fuselage to connect the carbon fiber pole, the top of fuselage is connected with the rotation axis, and the top of rotation axis is connected with the wing, the terminal inboard of wing is connected with the aileron, and wing top avris has seted up first lockhole, the below of first lockhole is provided with the kayser axle, and the top outside of kayser axle is connected with first spring, the end-to-end connection of carbon fiber pole has the front end fin for the fin fuselage, and the inboard of front end fin is provided with the elevator, the end-to-end connection of front end fin has terminal fin. This portable individual soldier unmanned aerial vehicle of fighting of wing folding is convenient for fold respectively wing and fin and is accomodate, and the use of carrying is convenient for, and it is spacing to guarantee stable block simultaneously, guarantees stable the use.

Description

Portable individual combat unmanned aerial vehicle with foldable wings

Technical Field

The utility model relates to an ultra miniature unmanned aerial vehicle technical field specifically is a portable individual soldier unmanned aerial vehicle of fighting of wing folding.

Background

The ultra-miniature unmanned aerial vehicle is a small aircraft, can be used as battlefield investigation equipment carried by soldiers in a battlefield, has multiple functions, and also has wide application space in different fields;

and the super small-size unmanned aerial vehicle under the prior art background, structural style is single, and rotor class aircraft is mostly, and it is when using, is not convenient for accomodate and carries, can not guarantee to adapt to complicated battlefield environment, is unfavorable for guaranteeing that the soldier uses, consequently, we provide a portable individual soldier unmanned aerial vehicle of fighting of wing folding to in solving the problem that proposes in the aforesaid.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a portable individual soldier unmanned aerial vehicle of fighting of wing folding to solve present super microminiature unmanned aerial vehicle that above-mentioned background art provided, structural style is single, and the majority is rotor class aircraft, and it is when using, is not convenient for accomodate and carries, can not guarantee to adapt to complicated battlefield environment, is unfavorable for guaranteeing the problem that the soldier used.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a portable individual soldier unmanned aerial vehicle of fighting of wing folding, includes fuselage, wing and front end fin, the screw is installed on the top of fuselage, and the end-to-end connection of fuselage has fin fuselage to connect the carbon fiber pole, the top of fuselage is connected with the rotation axis, and the top of rotation axis is connected with the wing, the terminal inboard of wing is connected with the aileron, and wing top avris has seted up first lockhole, the below of first lockhole is provided with the kayser axle, and the top outside of kayser axle is connected with first spring to the bottom outside of kayser axle is provided with the second spring, the end-to-end connection of carbon fiber pole has the front end fin is connected to the fin fuselage, and the inboard of front end fin is provided with the elevator, the end-to-end connection of front end fin has terminal fin.

Preferably, the wing forms a rotating structure at the top of the fuselage through a rotating shaft, the rotating angle range of the wing is 0-90 degrees, and the wing is correspondingly clamped with the locking shaft through the first locking hole.

Preferably, the locking shaft forms an elastic structure at the top of the fuselage through the first spring and the second spring, the locking shaft is clamped with the first locking hole and the second locking hole, the second locking hole is correspondingly arranged at the top of the wing, and the first locking hole and the second locking hole are vertically arranged relative to a central shaft of the rotating shaft.

Preferably, the front tail wing is rotatably connected with the tail wing body connecting carbon fiber rod through a shaft rod arranged transversely, and the rotating angle of the front tail wing on the outer side of the tail wing body connecting carbon fiber rod is 0-120 degrees.

Preferably, the front end tail fin, the elevator and the tail end tail fin are arranged in one-to-one correspondence, the tail end tail fin is of a rotating structure at the tail end of the front end tail fin, and the rotating angle range of the tail end tail fin is 0-180 degrees.

Compared with the prior art, the beneficial effects of the utility model are that: the portable individual combat unmanned aerial vehicle with the foldable wings is convenient for folding and containing the wings and the empennage respectively, is convenient for carrying and using, and can ensure stable clamping and limiting and stable use;

1. the wings can rotate through the rotating shaft, so that the wings can rotate by 90 degrees for storage, and meanwhile, the front-end empennage and the empennage body are connected through rotation between the carbon fiber rods and can be folded through rotation between the front-end empennage and the tail end empennage, so that the carrying and use are convenient;

2. through the elastic action of first spring and second spring, can make the kayser axle go up the bullet to make kayser axle and first lockhole carry out the block, can guarantee the stability of first lockhole, when accomodating at the wing simultaneously, make to carry out the block between kayser axle and the second lockhole, can guarantee the stability of accomodating, portable.

Drawings

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

FIG. 2 is a schematic front view of the present invention;

FIG. 3 is a schematic side view of the present invention;

fig. 4 is the structural schematic diagram of the cutting of the latch shaft of the present invention.

In the figure: 1. a body; 2. a propeller; 3. the empennage body is connected with a carbon fiber rod; 4. a rotating shaft; 5. an airfoil; 6. an aileron; 7. a first lock hole; 8. a second lock hole; 9. a latch shaft; 10. a first spring; 11. a second spring; 12. a front end tail; 13. an elevator; 14. a tail end tail fin.

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.

Referring to fig. 1-4, the present invention provides a technical solution: a portable individual combat unmanned aerial vehicle with foldable wings comprises a body 1, a propeller 2, an empennage body connecting carbon fiber rod 3, a rotating shaft 4, wings 5, ailerons 6, a first lock hole 7, a second lock hole 8, a lock shaft 9, a first spring 10, a second spring 11, a front end empennage 12, an elevator 13 and a tail end empennage 14, wherein the top end of the body 1 is provided with the propeller 2, the tail end of the body 1 is connected with the empennage body connecting carbon fiber rod 3, the top of the body 1 is connected with the rotating shaft 4, the top end of the rotating shaft 4 is connected with the wings 5, the inner side of the tail end of the wings 5 is connected with the ailerons 6, the side of the top end of the wings 5 is provided with the first lock hole 7, the lock shaft 9 is arranged below the first lock hole 7, the outer side of the top of the lock shaft 9 is connected with the first spring 10, the outer side of the bottom of the lock shaft 9 is provided with the second spring 11, the tail end of the empennage body connecting carbon fiber rod 3 is connected with the front end 12, and the inner side of the front end tail wing 12 is provided with an elevator 13, and the tail end of the front end tail wing 12 is connected with a tail end tail wing 14.

As shown in fig. 1 and 4, the wing 5 forms a rotating structure at the top of the fuselage 1 through the rotating shaft 4, the rotating angle range of the wing 5 is 0-90 °, and the wing 5 is correspondingly clamped with the locking shaft 9 through the first locking hole 7, so that the wing 5 is limited, and stability can be guaranteed, the locking shaft 9 forms an elastic structure at the top of the fuselage 1 through the first spring 10 and the second spring 11, the locking shaft 9 is clamped with the first locking hole 7 and the second locking hole 8, the second locking hole 8 is correspondingly arranged at the top of the wing 5, and the first locking hole 7 and the second locking hole 8 are vertically arranged relative to the central shaft of the rotating shaft 4, so that automatic alignment is facilitated, and stable limiting use can be guaranteed.

As shown in the figures 1 and 3, the front end tail wing 12 is rotatably connected with the tail wing body connecting carbon fiber rod 3 through a shaft rod which is transversely arranged, the rotating angle of the front end tail wing 12 at the outer side of the tail wing body connecting carbon fiber rod 3 is 0-120 degrees, the storage is convenient, the front end tail wing 12, the elevator 13 and the tail end tail wing 14 are arranged in a one-to-one correspondence mode, the tail end tail wing 14 is of a rotating structure at the tail end of the front end tail wing 12, the rotating angle range of the tail end tail wing 14 is 0-180 degrees, the folding type carbon fiber rod tail wing can be folded, the occupied space is reduced, and the carrying type carbon fiber rod tail wing is convenient.

The working principle is as follows: when the portable individual combat unmanned aerial vehicle with the foldable wings is used, when the portable individual combat unmanned aerial vehicle is carried, as shown in fig. 1 and 3, the front-end tail wing 12 is connected with the tail wing body through the rotating connection between the carbon fiber rods 3, wherein the front-end tail wing 12 is connected through a shaft rod similar to the rotating shaft 4, so that the front-end tail wing 12 rotates to be in a vertical state, then the tail-end tail wing 14 rotates 180 degrees through the rotation between the front-end tail wing 12 and the tail-end tail wing 14 to be folded, as shown in fig. 1 and 4, the locking shaft 9 is pressed downwards, the wing 5 is rotated through the rotating shaft 4, after the wing 5 rotates 90 degrees, the second locking hole 8 is aligned with the locking shaft 9, the pressing of the locking shaft 9 is released, the locking shaft 9 is sprung up through the elastic action of the first spring 10 and the second spring 11, so that the locking shaft 9 is clamped with the second locking hole 8 to limit the wing 5, and the first spring 10 and the second spring 11 are respectively installed at the outer side and the inner side of the fuselage 1, and can ensure stable reset use, so that the wings 5 correspondingly rotate to the outer side of the tail wing 12 at the front end for storage, carrying and use, which is the whole working process of the portable individual combat unmanned aerial vehicle with foldable wings, and the content which is not described in detail in the specification belongs to the prior art which is known by professionals in the field.

The utility model discloses the standard part that uses all can purchase from the market, and dysmorphism piece all can be customized according to the description with the record of drawing of description, and the concrete connection mode of each part all adopts conventional means such as ripe bolt, rivet, welding among the prior art, and machinery, part and equipment all adopt prior art, and conventional model, including circuit connection adopts conventional connection mode among the prior art, does not detailed here again.

Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.

Claims

1. The utility model provides a portable individual combat unmanned aerial vehicle of wing folding, includes fuselage (1), wing (5) and front end fin (12), its characterized in that: the top end of the machine body (1) is provided with a propeller (2), the tail end of the machine body (1) is connected with an empennage machine body connecting carbon fiber rod (3), the top of the machine body (1) is connected with a rotating shaft (4), the top end of the rotating shaft (4) is connected with a wing (5), the inner side of the tail end of the wing (5) is connected with an aileron (6), a first lock hole (7) is formed on the edge side of the top end of the wing (5), a locking shaft (9) is arranged below the first lock hole (7), a first spring (10) is connected to the outer side of the top of the locking shaft (9), and the outer side of the bottom of the locking shaft (9) is provided with a second spring (11), the tail end of the empennage body connected with the carbon fiber rod (3) is connected with a front end empennage (12), and the inner side of the front end tail wing (12) is provided with an elevator (13), and the tail end of the front end tail wing (12) is connected with a tail end tail wing (14).

2. The portable individual combat drone with foldable wings according to claim 1, characterized in that: the wing (5) forms a rotating structure at the top of the fuselage (1) through the rotating shaft (4), the rotating angle range of the wing (5) is 0-90 degrees, and the wing (5) is correspondingly clamped with the clamping shaft (9) through the first locking hole (7).

3. The portable individual combat drone with foldable wings according to claim 1, characterized in that: the top of kayser axle (9) through first spring (10) and second spring (11) at fuselage (1) constitutes elastic construction, and kayser axle (9) all is the block setting between first lockhole (7) and second lockhole (8), and second lockhole (8) correspond the top that sets up at wing (5), and first lockhole (7) and second lockhole (8) between set up perpendicularly about the center pin of rotation axis (4) in addition.

4. The portable individual combat drone with foldable wings according to claim 1, characterized in that: the front end empennage (12) is rotatably connected with the empennage body connecting carbon fiber rod (3) through a shaft rod which is transversely arranged, and the rotating angle of the front end empennage (12) at the outer side of the empennage body connecting carbon fiber rod (3) is 0-120 degrees.

5. The portable individual combat drone with foldable wings according to claim 1, characterized in that: the front end tail wing (12), the elevator (13) and the tail end tail wing (14) are arranged in one-to-one correspondence, the tail end tail wing (14) is of a rotating structure at the tail end of the front end tail wing (12), and the rotating angle range of the tail end tail wing (14) is 0-180 degrees.