CN218198794U

CN218198794U - Four rotor unmanned aerial vehicle wingspan beta structure

Info

Publication number: CN218198794U
Application number: CN202222610335.8U
Authority: CN
Inventors: 杨永琳; 刘青; 许敏
Original assignee: Chuzhou Vocational and Technical College
Current assignee: Chuzhou Vocational and Technical College
Priority date: 2022-09-30
Filing date: 2022-09-30
Publication date: 2023-01-03
Anticipated expiration: 2032-09-30

Abstract

The utility model discloses a four-rotor unmanned aerial vehicle wingspan folding structure, which comprises a body, wherein two rotor assemblies are respectively arranged on two sides of the body; the rotor subassembly includes branch, motor, change, first screw, rotating assembly and second screw, and branch one end sets up in the organism, and the motor is installed to branch other end below. The utility model provides a four rotor unmanned aerial vehicle span beta structure, will lock and connect the forward twisting of ring and move, with the outer crown plate lock joint of external looper and inscription looper, first screw and second screw after the folding are fixed, during the use, reverse operation carries out, fold the screw, the efficiency is accomodate in the improvement, drive the adjustment pinion anticlockwise rotation at two other diagonal angles through two linkage gears, make the rotor subassembly at two other diagonal angles rotatory accomodate in the folding groove, during the use, reverse operation can, fold unmanned aerial vehicle's wing, improve whole efficiency of accomodating.

Description

Four rotor unmanned aerial vehicle span beta structure

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is a four rotor unmanned aerial vehicle span beta structure.

Background

Four-rotor unmanned aerial vehicles are widely applied to the commercial field or the living field at present; to traditional four rotor unmanned aerial vehicle, its power unit's design and overall arrangement make four rotor unmanned aerial vehicle fuselage inner space, are unfavorable for loading and unloading bulky other equipment. Traditional four rotor unmanned aerial vehicle is under work flight state or idle unoperated state, and four rotor unmanned aerial vehicle is whole all to be in the extension state, and occupation space is bigger, the four rotor unmanned aerial vehicle's of not being convenient for accomodate and transport.

Publication No. CN109606661B discloses a foldable quad-rotor unmanned aerial vehicle, in which after the swing limit of a swing plate is released, the swing plate is folded in a swing manner; in order to make the balance plate rotate arbitrary angle, the swing of balance plate triangle end makes the sliding strip remove, the sliding strip removes after a series of transmissions, first rack drives first limiting plate rebound, the second rack drives the second limiting plate rebound, first limiting plate and second limiting plate relieve first sleeve like this, the telescopic spacing of second, the second sleeve can slide in first sleeve, the third sleeve can be rotatory in the second sleeve, indirectly reach balance plate can arbitrary direction pivoted purpose.

Although the above patent solves the problem of folding the swing plate, it has the following disadvantages:

1. firstly, the propeller cannot be folded, so that the propeller cannot be stored, and the propeller is easy to damage after being unfolded after the support is folded;

2. secondly, can't drive four supports simultaneously and accomodate simultaneously, lead to the adjustment process complicated.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a four rotor unmanned aerial vehicle span beta structure, will lock the ring forward and twist and move, with the outer crown plate lock joint of external looper and inscription looper, first screw and second screw after the folding are fixed, during the use, reverse operation carries out, fold the screw, improve and accomodate efficiency, drive the adjustment pinion anticlockwise rotation at two other diagonal angles through two linkage gears, make the rotor subassembly at two other diagonal angles rotate and accomodate in the folding groove, during the use, reverse operation can, fold the wing of unmanned aerial vehicle, improve whole efficiency of accomodating, the problem among the prior art has been solved.

In order to achieve the above object, the utility model provides a following technical scheme: a wingspan folding structure of a quad-rotor unmanned aerial vehicle comprises a body, wherein two rotor assemblies are respectively installed on two sides of the body;

the rotor wing assembly comprises a supporting rod, a motor, a rotating ring, a first propeller, a rotating assembly and a second propeller, wherein one end of the supporting rod is arranged in the machine body, the motor is arranged below the other end of the supporting rod, the rotating ring is sleeved on the output end of the motor, the first propeller and the second propeller are arranged on the outer side end of the rotating ring through the rotating assembly, and an adjusting structure for mounting the supporting rod is arranged at the inner end of the machine body;

the adjusting structure comprises an installation shaft, a driving main gear, an adjusting pinion and an adjusting cap, wherein the supporting rod is sleeved on the installation shaft, the adjusting pinion is installed above the installation shaft, the driving main gear is arranged in the middle of the adjusting pinion, and the driving main gear is sleeved on a linkage rod below the adjusting cap.

Preferably, the rotating assembly comprises a wrapping ring, an inner connecting bent ring, an outer connecting bent ring, a sliding groove and a locking ring, the outer end of the wrapping ring is provided with the outer connecting bent ring and the inner connecting bent ring, an outer ring plate of the outer connecting bent ring and the inner connecting bent ring is arranged on the outer side of the wrapping ring, the outer side of the outer connecting bent ring and the outer side of the outer ring plate of the inner connecting bent ring are wrapped with the locking ring, the outer connecting bent ring is connected with the second propeller through a rod body, the outer wall of the inner connecting bent ring is connected with the first propeller through the rod body, and the sliding groove used for sliding of the rod body is formed in the surface of the wrapping ring.

Preferably, the outer ring plates of the outer connecting curved ring and the inner connecting curved ring are provided with external threads, the inner wall of the locking ring is provided with internal threads, the locking ring is movably locked with the outer ring plates of the outer connecting curved ring and the inner connecting curved ring, and the middle of the locking ring is locked with the outer wall threads of the rotating ring.

Preferably, the adjusting cap is arranged at the upper end of the machine body, and the linkage rod below the adjusting cap is installed with the machine body through a bearing.

Preferably, a folding groove is formed in the machine body, and a driving groove is formed in the machine body in an extending mode above the folding groove.

Preferably, two diagonal adjustment pinions are meshed with the driving main gear, and the other two diagonal adjustment pinions are meshed with the driving main gear through linkage gears with the same size.

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

1. the utility model provides a four rotor unmanned aerial vehicle span beta structure, the lock joint ring is with the outer crown plate activity halving of external looper and inscription looper, lock joint ring centre and swivel outer wall screw thread halving, when folding, first screw and second screw on every group rotor subassembly rotate through rotating assembly and fold, first screw and the installation of staggering from top to bottom, when folding, reverse twist the lock joint ring, make the lock joint ring separate with the outer crown plate of external looper and inscription looper, it drives the body of rod and slides in the spout to rotate first screw, also drive the inscription looper and rotate, the second screw also drives external looper through the body of rod and rotates, thereby make first screw and second screw overlap the counterpoint, again with the lock joint ring forward twist, with the outer crown plate halving of external looper and inscription looper, fix first screw and second screw after the fifty percent discount, during the use, reverse operation carries out, fold the screw, improve efficiency of accomodating.

2. The utility model provides a four rotor unmanned aerial vehicle span beta structure, the drive groove has been seted up in the extension of folding groove top in the organism, the adjustment pinion and the meshing of drive master gear at two diagonal angles, in addition the adjustment pinion at two diagonal angles passes through the linkage gear and the meshing of drive master gear of the same size, during the shrink, it drives drive master gear anticlockwise rotation to rotate the adjustment pinion at two diagonal angles to rotate the adjustment master gear direct drive, thereby the rotor subassembly that drives two diagonal angles is rotatory to folding inslot, in drive master gear anticlockwise rotation, drive the adjustment pinion anticlockwise rotation at two other diagonal angles through two linkage gears, make the rotor subassembly at two other diagonal angles rotatory to folding inslot accomodate, in the use, reverse operation can, fold unmanned aerial vehicle's wing, improve whole efficiency of accomodating.

Drawings

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

fig. 2 is a cross-sectional view of the rotor assembly structure of the present invention;

FIG. 3 is an enlarged view of the point A of FIG. 2 according to the present invention;

FIG. 4 is a sectional view of the adjusting structure of the present invention;

fig. 5 is a schematic view of a folding structure of the rotor assembly of the present invention;

figure 6 is the utility model discloses a rotor subassembly beta structure section view.

In the figure: 1. a body; 11. a folding slot; 12. a drive slot; 2. a rotor assembly; 21. a strut; 22. a motor; 23. rotating the ring; 24. a first propeller; 25. a rotating assembly; 251. a cladding ring; 252. the curved ring is internally connected; 253. a curved ring is externally connected; 254. a chute; 255. a locking ring; 26. a second propeller; 3. adjusting the structure; 31. installing a shaft; 32. driving a main gear; 33. adjusting the pinion; 331. a linkage gear; 34. the cap is adjusted.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the 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 order to solve the problems that the existing propeller structure cannot be folded, so that the existing propeller structure cannot be stored, and the existing propeller structure is easy to be damaged when the bracket is folded, please refer to fig. 1 to 3, the embodiment provides the following technical solutions:

a wingspan folding structure of a four-rotor unmanned aerial vehicle comprises a body 1, two rotor assemblies 2 are respectively installed on two sides of the body 1, each rotor assembly 2 comprises a support rod 21, a motor 22, a rotating ring 23, a first propeller 24, a rotating assembly 25 and a second propeller 26, one end of each support rod 21 is arranged in the body 1, the motor 22 is installed below the other end of each support rod 21, the rotating ring 23 is sleeved on the output end of the motor 22, the first propeller 24 and the second propeller 26 are installed on the outer side end of each rotating ring 23 through the rotating assembly 25, each rotating assembly 25 comprises a wrapping ring 251, an inner bending ring 252, an outer bending ring 253, a sliding groove 254 and a locking ring 255, the inner end of each wrapping ring 251 is provided with the outer bending ring 253 and the inner bending ring 252, outer ring plates of the outer bending ring 253 and the inner bending ring 252 are arranged on the outer sides of the wrapping rings 251, the outer ring 253 and outer ring plates of the inner bending ring 252 are wrapped with the locking ring 255, the external curved ring 253 is connected with the second propeller 26 through a rod body, the outer wall of the internal curved ring 252 is connected with the first propeller 24 through the rod body, the surface of the wrapping ring 251 is provided with a sliding groove 254 used for sliding the rod body, the outer ring plates of the external curved ring 253 and the internal curved ring 252 are provided with external threads, the inner wall of the locking ring 255 is provided with internal threads, the locking ring 255 is movably locked with the outer ring plates of the external curved ring 253 and the internal curved ring 252, the middle of the locking ring 255 is locked with the outer wall of the rotating ring 23 through threads, when the rotor assembly 2 is folded, the first propeller 24 and the second propeller 26 on each group of rotor assemblies 2 are rotated and folded through the rotating assembly 25, the first propeller 24 and the second propeller 26 are arranged in a vertically staggered mode, when the rotor assembly is folded, the locking ring 255 is reversely screwed, the locking ring 255 is separated from the outer ring plates of the external curved ring 253 and the internal curved ring 252, the first propeller 24 is rotated to drive the rod body to slide in the sliding groove, also drive the rotation of inscribe looper 252, second screw 26 also drives external looper 253 through the body of rod and rotates to make first screw 24 and second screw 26 overlap the counterpoint, twist the forward of lock joint ring 255 again, with the outer annular plate lock joint of external looper 253 and inscribe looper 252, fix first screw 24 and second screw 26 after folding, during the use, carry out reverse operation, fold the screw, improve and accomodate efficiency.

In order to solve the problem that the prior structure cannot drive four brackets to be accommodated simultaneously, which results in a complicated adjustment process, please refer to fig. 1-3, the embodiment provides the following technical solutions:

the inner end of the machine body 1 is provided with an adjusting structure 3 for mounting a supporting rod 21, the adjusting structure 3 comprises a mounting shaft 31, a driving main gear 32, an adjusting pinion 33 and an adjusting cap 34, the supporting rod 21 is sleeved on the mounting shaft 31, the adjusting pinion 33 is mounted above the mounting shaft 31, the driving main gear 32 is arranged in the middle of the adjusting pinion 33, the driving main gear 32 is sleeved on a linkage rod below the adjusting cap 34, the adjusting cap 34 is arranged at the upper end of the machine body 1, the linkage rod below the adjusting cap 34 is mounted with the machine body 1 through a bearing, a folding groove 11 is formed in the machine body 1, a driving groove 12 is formed in the machine body 1 in an extending mode above the folding groove 11, the two diagonal adjusting pinions 33 are meshed with the driving main gear 32, the other two diagonal adjusting pinions 33 are meshed with the driving main gear 32 through a linkage gear 331 with the same size, when the machine body is retracted, the adjusting cap 34 is rotated to drive the driving main gear 32 to directly drive the two diagonal adjusting pinions 33 to rotate anticlockwise, and the two folding sub-gear 33 are used for carrying out integral folding operation of the folding unmanned aerial vehicle, and the unmanned aerial vehicle can be folded.

The working principle is as follows: when folded, the first propeller 24 and the second propeller 26 of each rotor assembly 2 are folded by the rotating assembly 25, the first propeller 24 and the second propeller 26 are arranged in a vertically staggered manner, when folded, the locking ring 255 is rotated in the reverse direction, so that the locking ring 255 is separated from the outer annular plates of the outer curved ring 253 and the inner curved ring 252, the rod body is rotated by the first propeller 24 to slide in the sliding groove 254, the inner curved ring 252 is also rotated, the second propeller 26 also drives the outer curved ring 253 to rotate through the rod body, so that the first propeller 24 and the second propeller 26 are aligned in an overlapping manner, the locking ring 255 is rotated in the forward direction, the locking ring is locked with the outer annular plates of the outer curved ring 253 and the inner curved ring 252, the first propeller 24 and the second propeller 26 after being folded are fixed, when used, the rotor assemblies 2 are operated in the reverse direction, when retracted, the driving main gear 32 is rotated counterclockwise, the driving two diagonal adjusting pinions 33 are directly driven to rotate counterclockwise, so that the two diagonal adjusting pinions 2 are folded into the grooves 11, and when the two diagonal adjusting caps 32 are retracted, the two rotors are rotated in the two diagonal adjusting pinions 33 are rotated counterclockwise, and the two rotors are used, and the two rotors are simultaneously, and the two rotors 11 are folded in the two rotors are rotated counterclockwise direction, and the two rotors are used.

It should be noted that, in this document, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various 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 a four rotor unmanned aerial vehicle span beta structure, includes organism (1), its characterized in that: two rotor assemblies (2) are respectively arranged on two sides of the machine body (1);

the rotor wing assembly (2) comprises a supporting rod (21), a motor (22), a rotating ring (23), a first propeller (24), a rotating assembly (25) and a second propeller (26), one end of the supporting rod (21) is arranged in the machine body (1), the motor (22) is arranged below the other end of the supporting rod (21), the rotating ring (23) is sleeved on the output end of the motor (22), the first propeller (24) and the second propeller (26) are arranged on the outer side end of the rotating ring (23) through the rotating assembly (25), and an adjusting structure (3) used for installing the supporting rod (21) is arranged at the inner end of the machine body (1);

the adjusting structure (3) comprises an installation shaft (31), a driving main gear (32), an adjusting pinion (33) and an adjusting cap (34), wherein the supporting rod (21) is sleeved on the installation shaft (31), the adjusting pinion (33) is installed above the installation shaft (31), the driving main gear (32) is arranged in the middle of the adjusting pinion (33), and the driving main gear (32) is sleeved on a linkage rod below the adjusting cap (34).

2. The wingspan folding structure of a quad-rotor unmanned aerial vehicle according to claim 1, wherein: the rotating assembly (25) comprises a wrapping ring (251), an inner-connecting curved ring (252), an outer-connecting curved ring (253), a sliding groove (254) and a locking ring (255), the inner end of the wrapping ring (251) is provided with the outer-connecting curved ring (253) and the inner-connecting curved ring (252), an outer ring plate of the outer-connecting curved ring (253) and an outer ring plate of the inner-connecting curved ring (252) are arranged on the outer side of the wrapping ring (251), the outer side of the outer ring plate of the outer-connecting curved ring (253) and the outer side of the outer ring plate of the inner-connecting curved ring (252) are wrapped with the locking ring (255), the outer-connecting curved ring (253) is connected with the second propeller (26) through a rod body, the outer wall of the inner-connecting curved ring (252) is connected with the first propeller (24) through a rod body, and the surface of the wrapping ring (251) is provided with the sliding groove (254) for the rod body to slide.

3. The wingspan folding structure of quadrotor unmanned aerial vehicle according to claim 2, wherein: the outer ring plates of the outer connecting curved ring (253) and the inner connecting curved ring (252) are provided with external threads, the inner wall of the locking ring (255) is provided with internal threads, the locking ring (255) is movably locked with the outer ring plates of the outer connecting curved ring (253) and the inner connecting curved ring (252), and the middle of the locking ring (255) is locked with the outer wall threads of the rotating ring (23).

4. The wingspan folding structure of a quad-rotor unmanned aerial vehicle according to claim 1, wherein: the adjusting cap (34) is arranged at the upper end of the machine body (1), and the linkage rod below the adjusting cap (34) is installed with the machine body (1) through a bearing.

5. The wingspan folding structure of quadrotor unmanned aerial vehicle according to claim 1, wherein: folding groove (11) are arranged in the machine body (1), and a driving groove (12) is arranged above the folding groove (11) in the machine body (1) in an extending mode.

6. The wingspan folding structure of a quad-rotor unmanned aerial vehicle according to claim 1, wherein: two diagonal adjustment pinions (33) are meshed with the drive main gear (32), and the other two diagonal adjustment pinions (33) are meshed with the drive main gear (32) through linkage gears (331) of the same size.