CN221024221U

CN221024221U - Split type unmanned aerial vehicle rotor that can replace partially

Info

Publication number: CN221024221U
Application number: CN202322654991.2U
Authority: CN
Inventors: 刘波; 李明
Original assignee: Shenzhen Kaidafeng Precision Metal Products Co ltd
Current assignee: Shenzhen Kaidafeng Precision Metal Products Co ltd
Priority date: 2023-09-28
Filing date: 2023-09-28
Publication date: 2024-05-28
Anticipated expiration: 2033-09-28

Abstract

The utility model discloses a split type unmanned aerial vehicle rotor wing capable of being replaced partially, which relates to the technical field of unmanned aerial vehicles and comprises a servo motor and a connecting structure, wherein a buffer air column is vertically arranged at the bottom of the servo motor, a protective structure group is arranged at the left side and the right side of the servo motor, a connecting shaft bracket is arranged at the top power output end of the servo motor through a coupler, and the connecting structure is horizontally connected with the left end and the right end of the connecting shaft bracket. This split type unmanned aerial vehicle rotor that can replace partially uses through the structure that the coupling pedestal cooperation links up the structure, can carry out split dismouting to the screw flabellum, even if with structural maintenance, be convenient for again to the structure split accomodate, reduce the damage of screw flabellum, and through the buffer gas column that sets up in servo motor's bottom, the protection architecture group that sets up in its left and right sides of cooperation, the damage that can furthest's protection servo motor caused when unexpected falling to improve the structural protection nature.

Description

Split type unmanned aerial vehicle rotor that can replace partially

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a split type partially replaceable unmanned aerial vehicle rotor wing.

Background

Unmanned plane is called unmanned aerial vehicle for short, is unmanned aerial vehicle that utilizes radio remote control equipment and self-contained program control device to operate, wherein the most common is small-size rotor unmanned aerial vehicle, miniature rotor unmanned aerial vehicle is the product that micro-electromechanical system is integrated, unmanned aerial vehicle can divide into kind such as fixed wing formula, rotor formula and flapping wing formula unmanned aerial vehicle according to flight characteristics, wherein miniature rotor unmanned aerial vehicle has characteristics such as small, simple structure, control are more nimble, can take off and land perpendicularly, freely hover, can also adapt to various natural environment, possess advantages such as autonomous flight and landing ability, can carry out the operation in some complex and dangerous environment that are unsuitable for human entering, in recent years have more and more important application in scientific research institutions, government institutions, broadcast media, personal application and military field.

The rotor part of the conventional unmanned aerial vehicle is generally fixedly connected with the motor, and meanwhile, the rotor part of the conventional unmanned aerial vehicle does not have the split property of a part of the structure, so that the rotor and the motor are damaged simultaneously once the unmanned aerial vehicle falls in the operation process, and the cost of structural maintenance of the unmanned aerial vehicle is increased.

Accordingly, in view of the above, research and improvement are made on the existing structure and the existing defects, and a split type partially replaceable unmanned aerial vehicle rotor wing is proposed.

Disclosure of utility model

The utility model aims to provide a split type unmanned aerial vehicle rotor wing capable of being replaced partially so as to solve the problems in the background art.

In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a split type unmanned aerial vehicle rotor that can replace partially, includes servo motor and linking structure, the buffer gas post is installed perpendicularly to servo motor's bottom, and servo motor's left and right sides is provided with the protective structure group, and servo motor's top power take off installs the connection pedestal through the shaft coupling moreover, linking structure horizontal connection is in the both ends about the connection pedestal, and linking structure keeps away from the one end of connection pedestal and be connected with the screw flabellum, and connects vertical threaded connection has fastening bolt between pedestal and the linking structure moreover, linking structure includes linking piece, linking screw thread and linking spout, linking piece is close to the one end surface of connection pedestal and is provided with the linking screw thread, and linking piece is kept away from the inside linking spout of having seted up of one end of linking screw thread.

Further, the buffer air column is fixedly connected to the bottom center of the servo motor, and the protective structure group is installed in a bilateral symmetry mode by taking the vertical central axis of the servo motor as a symmetry axis.

Further, the protection structure group comprises a protection frame, a baffle, a movable shaft and a buffer spring, wherein one side, far away from the servo motor, of the protection frame is vertically connected with the baffle, the movable shaft is arranged between the baffle and the protection frame, and the buffer spring is horizontally arranged at one end, far away from the protection frame, of the baffle.

Further, the protective structure group is integrally arranged in a 匚 -shaped structure, and one side, away from the baffle, of the buffer spring is connected to the lower end of the side edge of the servo motor.

Further, the connecting shaft bracket comprises a central shaft, connecting rods and threaded pipes, wherein the connecting rods are arranged on the left side and the right side of the central shaft, and the threaded pipes are arranged in the connecting rods.

Furthermore, the connecting rod and the threaded pipe are symmetrically arranged left and right by taking the vertical central axis of the central shaft as a symmetrical axis, and the connecting rod and the central shaft are of an integrated structure.

Further, the inner surface structure of the threaded pipe is matched with the outer surface structure of the connecting thread, and the inner surface structure of the connecting chute and the outer surface structure of a section of the propeller blade, which is close to the connecting chute, are matched with each other.

Further, the fastening bolt is arranged in a bilateral symmetry mode by taking the vertical central axis of the connecting piece as a symmetry axis, and the fastening bolt penetrates through the connecting position of the connecting sliding groove and the propeller blade at the same time in a threaded mode.

The utility model provides a split type partially replaceable unmanned aerial vehicle rotor wing, which has the following beneficial effects:

1. According to the utility model, the unmanned aerial vehicle can accidentally fall due to various factors in the operation and control process, so that the whole rotor wing structure is damaged, therefore, the buffer air column arranged at the bottom of the servo motor is utilized, the relative impact received by the servo motor after the bottom is grounded is relieved to the greatest extent by utilizing the structural buffering property of the buffer air column, the protective structure groups arranged at the left side and the right side of the servo motor are made of composite materials, the structural weight can be reduced as much as possible, the reinforced buffering structure of the side edge of the servo motor can be added to reduce the shock impact received by the side edge of the servo motor after falling, and the buffer spring further assists the protective frame and the baffle to absorb and buffer the shock impact so as to protect the servo motor as much as possible.

2. According to the utility model, the whole connection structure can be in butt joint installation by utilizing the connection threads at one end of the connecting rods at the left and right sides of the center shaft, the screw blades are inserted into the connection sliding grooves at the other end of the connection piece in a sliding way along the horizontal direction in an aligned way, and the fastening bolts are screwed in from top to bottom in the vertical direction, so that the screw blades are fixed in the connection sliding grooves at one end of the connection piece.

Drawings

Fig. 1 is a schematic side view of a body of a split partially replaceable unmanned rotor according to the present utility model;

fig. 2 is a schematic top view of the body part structure of a split partially replaceable rotor wing of an unmanned aerial vehicle according to the present utility model;

Fig. 3 is a schematic diagram of a split type connection shaft bracket, a connection structure, a propeller blade and a fastening bolt of a split type partially replaceable unmanned aerial vehicle rotor wing;

Fig. 4 is an enlarged schematic view of the structure of fig. 1 of a split partially replaceable unmanned rotor according to the present utility model;

Fig. 5 is a schematic view of a connection structure of a split type partially replaceable unmanned aerial vehicle rotor wing and a partially connected three-dimensional structure of a propeller blade.

In the figure: 1. a servo motor; 2. a buffer gas column; 3. a protective structure group; 301. a protective frame; 302. a baffle; 303. a movable shaft; 304. a buffer spring; 4. a connecting shaft bracket; 401. a center shaft; 402. a connecting rod; 403. a threaded tube; 5. a connection structure; 501. a linking member; 502. connecting threads; 503. a connecting chute; 6. propeller blades; 7. and (5) fastening a bolt.

Detailed Description

Embodiments of the present utility model are described in further detail below with reference to the accompanying drawings and examples. The following examples are illustrative of the utility model but are not intended to limit the scope of the utility model.

As shown in fig. 1 to 4, a split type unmanned aerial vehicle rotor capable of being replaced partially comprises a servo motor 1 and a connection structure 5, wherein a buffer air column 2 is vertically arranged at the bottom of the servo motor 1, a protection structure group 3 is arranged at the left side and the right side of the servo motor 1, a connecting shaft bracket 4 is arranged at the top power output end of the servo motor 1 through a coupler, the connection structure 5 is horizontally connected at the left end and the right end of the connecting shaft bracket 4, one end of the connection structure 5 far away from the connecting shaft bracket 4 is connected with a propeller blade 6, a fastening bolt 7 is vertically connected between the connecting shaft bracket 4 and the connection structure 5 in a threaded manner, the buffer air column 2 is fixedly connected at the bottom center of the servo motor 1, the protection structure group 3 is symmetrically arranged and installed by taking the vertical central axis of the servo motor 1 as a symmetrical axis, the protection structure group 3 comprises a protection bracket 301, a baffle 302, a movable shaft 303 and a buffer spring 304, the baffle plate 302 is vertically connected to one side of the protective frame 301 far away from the servo motor 1, a movable shaft 303 is arranged between the baffle plate 302 and the protective frame 301, a buffer spring 304 is horizontally arranged at one end of the baffle plate 302 far away from the protective frame 301, the protective structure group 3 is integrally arranged in a 匚 -shaped structure, one side of the buffer spring 304 far away from the baffle plate 302 is connected to the lower end of the side edge of the servo motor 1, the buffer air column 2 arranged at the bottom of the servo motor 1 is utilized to furthest relieve the relative impact received by the servo motor 1 after the bottom is grounded by utilizing the structural buffering property of the buffer air column 2, the protective structure group 3 arranged at the left side and the right side of the servo motor 1 and the protective frame 301 and the baffle plate 302 which are made of composite materials can reduce the structural weight as far as possible and increase the reinforced buffer structure of the side edge of the servo motor 1, to reduce the shock impact on the falling rear side, and the buffer spring 304 further assists the protection frame 301 and the baffle 302 to absorb and buffer the shock impact so as to protect the servo motor 1 as much as possible.

The connecting shaft bracket 4 comprises a middle shaft 401, a connecting rod 402 and a threaded pipe 403, wherein the connecting rod 402 is arranged on the left side and the right side of the middle shaft 401, the threaded pipe 403 is arranged in the connecting rod 402, the connecting rod 402 and the threaded pipe 403 are symmetrically arranged on the left side and the right side of the vertical central axis of the middle shaft 401 as a symmetrical axis, the connecting rod 402 and the middle shaft 401 are of an integral structure, the connecting structure 5 comprises a connecting piece 501, connecting threads 502 and connecting sliding grooves 503, connecting threads 502 are arranged on one end surfaces of the connecting piece 501 close to the connecting shaft bracket 4, connecting sliding grooves 503 are formed in the inner parts of one ends of the connecting piece 501 far away from the connecting threads 502, connecting bolts 7 are symmetrically arranged on the left side and the right side of the vertical central axis of the connecting piece 501 as a symmetrical axis, the connecting bolts 7 penetrate through the connecting parts of the connecting sliding grooves 503 and the propeller blades 6 at the same time, the inner surface structures of the threaded pipe 403 are matched with the outer surface structures of the connecting threads 502, the inner surface structures of the connecting sliding grooves 503 are matched with the outer surface structures of the propeller blades 6 close to the connecting grooves 503, the inner structures of the connecting grooves 402 are arranged on the inner side of the connecting grooves 403, the connecting pieces of the connecting pieces 5 can be arranged by utilizing the butt joint threads 502 at one ends of the connecting pieces, the connecting pieces 502 and the inner screw grooves 403, the connecting pieces 5 can be arranged at the inner sides of the connecting pieces, the connecting pieces and the connecting pieces 6 are arranged at the right sides of the connecting pieces, the connecting pieces and the connecting pieces are arranged at the right sides of the connecting pieces and the connecting pieces, and the connecting pieces 6, and the connecting pieces are arranged at the connecting pieces 6, and the connecting pieces 6 are screwed up in the right sides and connected to the inner sides.

In summary, as shown in fig. 1 to fig. 4, when the split type partially replaceable unmanned aerial vehicle rotor wing is used, firstly, when the unmanned aerial vehicle rotor wing is required to be used, the connection structure 5 can be connected with the connection shaft frame 4 of the power output end at the top of the servo motor 1, the connection thread 502 arranged on one end surface of the connection piece 501 is axially screwed into the connecting rod 402 horizontally arranged at one end of the center shaft 401 in the horizontal direction, and the connection structure 5 is screwed into the connection shaft frame 4 through the threaded connection with the threaded pipe 403, and the connection part is screwed;

Then, one end of the connection part of the propeller blade 6 and the connection structure 5 is inserted into the connection sliding groove 503 formed at the other end of the connection piece 501 in a sliding way along the horizontal direction, the structures are aligned with each other, then, the screw is screwed in from top to bottom on the top surface of the connection piece 501 by using the fastening bolt 7, the screw penetrates through the connection structure 5 and the propeller blade 6 by using the pre-formed holes and threads at the same time, and the fastening bolt 7 is screwed, so that the connection structure 5 and the propeller blade 6 are fastened in a butt joint way;

When unmanned aerial vehicle is in the in-process of using the operation, when the accident falls, utilize the buffer gas post 2 of servo motor 1 bottom installation at this moment, can alleviate the relative impact that servo motor 1 received after the bottom lands to a certain extent, and the protective structure group 3 that sets up in servo motor 1 left and right sides, protective frame 301 and baffle 302 through combined material preparation can increase the reinforcement buffer structure of side for servo motor 1, in order to reduce the shock impact that receives at the back side that falls, and buffer spring 304 is the absorption buffering of further assistance protective frame 301, baffle 302 to shock impact in order to protect servo motor 1 as far as possible.

The embodiments of the utility model have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the utility model in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments were chosen and described in order to best explain the principles of the utility model and the practical application, and to enable others of ordinary skill in the art to understand the utility model for various embodiments with various modifications as are suited to the particular use contemplated.

Claims

1. The utility model provides a split type unmanned aerial vehicle rotor that can replace partially, includes servo motor (1) and links up structure (5), its characterized in that: buffer gas post (2) are installed perpendicularly to the bottom of servo motor (1), and the left and right sides of servo motor (1) is provided with protective structure group (3), and the top power take off end of servo motor (1) installs through the shaft coupling in addition and connects pedestal (4), link up structure (5) horizontal connection in the left and right sides both ends of connecting pedestal (4), and link up structure (5) and keep away from the one end of connecting pedestal (4) and be connected with screw flabellum (6), and connect vertical threaded connection between pedestal (4) and link up structure (5) have fastening bolt (7), link up structure (5) including link up piece (501), link up screw thread (502) and link up spout (503), link up piece (501) and be close to the one end surface of connecting pedestal (4) and link up screw thread (502) one end inside of having seted up link up.

2. The split partially replaceable unmanned aerial vehicle rotor according to claim 1, wherein the buffer air column (2) is fixedly connected to the bottom center of the servo motor (1), and the protective structure group (3) is installed in a bilateral symmetry mode with the vertical central axis of the servo motor (1) as a symmetry axis.

3. The split partially replaceable unmanned aerial vehicle rotor according to claim 1, wherein the protective structure group (3) comprises a protective frame (301), a baffle plate (302), a movable shaft (303) and a buffer spring (304), wherein the baffle plate (302) is vertically connected to one side of the protective frame (301) far away from the servo motor (1), the movable shaft (303) is arranged between the baffle plate (302) and the protective frame (301), and the buffer spring (304) is horizontally arranged at one end of the baffle plate (302) far away from the protective frame (301).

4. A split partially replaceable unmanned aerial vehicle rotor according to claim 3, wherein the protective structure group (3) is integrally arranged in a 匚' shape, and one side of the buffer spring (304) away from the baffle (302) is connected to the lower end of the side edge of the servo motor (1).

5. The split partially replaceable unmanned aerial vehicle rotor according to claim 1, wherein the connecting shaft bracket (4) comprises a central shaft (401), connecting rods (402) and threaded pipes (403), the connecting rods (402) are arranged on the left side and the right side of the central shaft (401), and the threaded pipes (403) are arranged inside the connecting rods (402).

6. The split partially replaceable unmanned aerial vehicle rotor according to claim 5, wherein the connecting rod (402) and the threaded pipe (403) are symmetrically arranged on the left and right sides by taking the vertical central axis of the central shaft (401) as a symmetry axis, and the connecting rod (402) and the central shaft (401) are of an integrated structure.

7. The split, partially replaceable unmanned aerial vehicle rotor of claim 5, wherein the inner surface structure of the threaded tube (403) and the outer surface structure of the engagement thread (502) are matched, and the inner surface structure of the engagement runner (503) and the outer surface structure of a section of the propeller blade (6) adjacent to the engagement runner (503) are matched.

8. The unmanned aerial vehicle rotor of claim 1, wherein the fastening bolt (7) is symmetrically arranged with the vertical central axis of the connecting piece (501) as a symmetry axis, and the fastening bolt (7) is simultaneously threaded at the connecting position of the connecting chute (503) and the propeller blade (6).