CN215972105U

CN215972105U - Propeller structure of drooping fixed-wing unmanned aerial vehicle

Info

Publication number: CN215972105U
Application number: CN202122525348.0U
Authority: CN
Inventors: 李炎; 郏震玄
Original assignee: Wuxi Yuanchuan Rongchuang Technology Co ltd
Current assignee: Wuxi Yuanchuan Rongchuang Technology Co ltd
Priority date: 2021-10-20
Filing date: 2021-10-20
Publication date: 2022-03-08
Anticipated expiration: 2031-10-20

Abstract

The utility model discloses a propeller structure of a vertical fixed wing unmanned aerial vehicle, which comprises propellers, wherein the propellers comprise a forward vertical propeller and a reverse vertical propeller; the forward-rotation vertical-lift propeller comprises a supporting piece, a first machine arm and a second machine arm which are rotatably connected with the supporting piece, and further comprises a transmission piece and a bearing seat for supporting the transmission piece; the transmission part is rotated along with the linkage part, so that the first arm and the second arm rotate on the support part, and an included angle between a positive propeller arranged on the first arm and a negative propeller arranged on the second arm is adjusted, therefore, the device utilizes the driver to drive the transmission part to continue rotating when flying, the first arm and the second arm are parallel to the transmission part, the device is convenient to store in the aircraft, the pneumatic layout in the aircraft flight is changed, the speed of the aircraft during flying is improved, the stability of the aircraft during flying is improved, and the voyage of the aircraft is improved.

Description

Propeller structure of drooping fixed-wing unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a propeller structure for a fixed-wing unmanned aerial vehicle to hang up.

Background

The arm of the vertical propeller of the existing vertical fixed wing unmanned aerial vehicle is fixed, and after the aircraft rises and starts to move forward, the wind resistance of the aircraft is increased, the aerodynamic layout of the aircraft body is influenced, and the flying speed and the stability of the aircraft are seriously reduced.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a propeller structure of a vertical fixed wing unmanned aerial vehicle, which aims to solve the problems in the background technology.

In order to achieve the purpose, the utility model provides the following technical scheme: a propeller structure of a vertical fixed wing unmanned aerial vehicle comprises propellers, wherein the propellers comprise a forward-rotation vertical propeller and a reverse-rotation vertical propeller which are consistent in structure; the forward-rotation vertical-lift propeller comprises a supporting piece, a first machine arm and a second machine arm, wherein the first machine arm and the second machine arm are rotatably connected with the supporting piece; the forward-rotation vertical-lift propeller further comprises a transmission piece and a bearing seat for supporting the transmission piece; the first machine arm is provided with a positive paddle, and the second machine arm is provided with a negative paddle; through the interaction of the arranged linkage part and the transmission part, one end of the first machine arm and one end of the second machine arm rotate on the support part, and then the positive paddle and the negative paddle are driven to move in the opposite direction or move back to back.

As a preferred technical scheme of the utility model: and a driving part for driving the transmission part to rotate is also arranged between the forward-rotation vertical propeller and the reverse-rotation vertical propeller.

As a preferred technical scheme of the utility model: the driving part is meshed with a driven gear arranged on the transmission part through a driving gear, so that the power of the driving part is transmitted to the transmission part.

As a preferred technical scheme of the utility model: the transmission part is a screw rod and is in threaded fit with one end of the linkage part.

As a preferred technical scheme of the utility model: one end of the linkage piece is in adaptive connection with the transmission piece through an arranged shaft sleeve, and the other end of the linkage piece is in sliding fit with the first machine arm through an arranged sliding sleeve; the sliding sleeve is connected with the linkage piece through a shaft pin, and the shaft sleeve is connected with the linkage piece through a shaft pin.

By adopting the technical scheme, the utility model has the beneficial effects that: the arm of the vertical propeller of the vertical fixed-wing unmanned aerial vehicle is designed to be controllable and movable, after the aircraft is lifted off and starts to move forward, the included angle between the two arms is controlled to enable the propeller to be collected into the aircraft cabin so as to reduce the wind resistance of the aircraft during flying, the aerodynamic layout of the aircraft body is further improved, and the flying speed and the stability of the aircraft are improved.

Drawings

FIG. 1 is a schematic view of the present invention in its expanded configuration;

fig. 2 is a schematic view of the accommodated structure of the present invention.

In the figure: 1. straightening a propeller; 2. reverse paddle; 3. a first arm; 4. a second arm; 5. a shaft sleeve; 6. a linkage member; 7. a sliding sleeve; 8. a transmission member; 9. a bearing seat; 10. a driving gear; 11. A support member; 12. a drive section; 13. a forward-rotation vertical-lift propeller; 14. the propeller is hung up in a reverse rotation mode.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the utility model and are not to be construed as limiting the utility model. In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "upper surface", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically connected, electrically connected or can communicate with each other; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

Referring to fig. 1-2, an embodiment of the present invention is shown: a propeller structure of a vertical fixed wing unmanned aerial vehicle comprises propellers, wherein the propellers comprise a forward vertical propeller 13 and a reverse vertical propeller 14 which are consistent in structure; the forward-rotation vertical-lift propeller 13 comprises a support 11, a first machine arm 3 and a second machine arm 4 which are rotatably connected with the support 11; the forward-rotation vertical-lift propeller 13 further comprises a transmission piece 8 and a bearing seat 9 for supporting the transmission piece 8; the first machine arm 3 is provided with a positive paddle 1, and the second machine arm 4 is provided with a negative paddle 2; through the interaction between the arranged linkage piece 6 and the transmission piece 8, one end of the first machine arm 3 and one end of the second machine arm 4 rotate on the supporting piece 11, and then the positive paddle 1 and the negative paddle 2 are driven to move towards or away from each other.

In this way, two forward rotation that the structure is unanimous hangs down screw 13 and the contra-rotation hangs down screw 14 and sets up side by side, assemble link 6 on driving medium 8, the other end and two horn connections of link 6, then install the bearing frame 9 at the both ends of two driving mediums 8, therefore, can drive link 6 work when driving medium 8 during operation, and then promote or stimulate two horn or back of the body motion in opposite directions, can realize the contained angle between two horns and adjust this moment, and then make the device when flight, the contained angle between two horns is adjusted both can be realized to work through remote controller control driving medium 8, consequently, make the device flight state adjustable, and then change the air current overall arrangement and also can prolong the range of aircraft simultaneously with the speed of stability when improving the aircraft flight and flight.

Specifically, the propeller is arranged in the middle of the airplane through the bearing seat 9, and then the propeller can be stored and unfolded in the airplane body, so that the propeller is convenient to retract into the shell of the airplane and extend out of the shell of the airplane.

In order to further optimize the structure of the device, a driving part 12 for driving the transmission parts 8 to rotate is further arranged between the forward-rotation vertical propeller 13 and the reverse-rotation vertical propeller 14, the driving part 12 can be made of a servo motor, so that the work of the driving part 12 is conveniently controlled remotely, and meanwhile, the driving part 12 is arranged between the two transmission parts 8, so that the space of the device is fully utilized, the structure of the device is further conveniently optimized, particularly, the driving part 12 is arranged in the middle of the device, the gravity center of the device is more stable, and the stability of the device in flight is powerfully improved.

The driving part 12 is meshed with a driven gear arranged on the transmission part 8 through the driving gear 10, so that the power of the driving part 12 is transmitted to the transmission part 8, the transmission capacity of the device is stable and reliable, and the controllability of the device is improved.

Furthermore, the transmission part 8 is a screw rod and is in threaded fit with one end of the linkage part 6, so that the transmission precision is further improved, and the processing technology of the transmission part 8 is simplified.

In order to further reduce the volume of the device after being stored, one end of the linkage piece 6 is in adaptive connection with the transmission piece 8 through a sliding sleeve 7, and the other end of the linkage piece 6 is in sliding fit with the first machine arm 3 through a shaft sleeve 5; the shaft sleeve 5 is connected with the linkage piece 6 through a shaft pin, and the sliding sleeve 7 is connected with the linkage piece 6 through a shaft pin. Through the mode, the transmission piece 8 and the two machine arms can be completely parallel after being stored, and the size of the device is further reduced. Wherein, the sliding sleeve 7 is a ball screw shaft sleeve.

Based on this, the operation through drive division 12 drives driving gear 10 and driven gear motion, and then drives transmission medium 8 and rotate two horn to the fixed wing unmanned aerial vehicle that hangs down and accomodate, simple structure not only, the fault rate is low, and entire system is not counted very high to the weight that the aircraft increased moreover, and the adjustable back of aerodynamic layout all has obvious promotion to the airspeed, stability and the flight stroke of aircraft simultaneously.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to 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 utility model, and the scope of protection is still within the scope of the utility model.

Claims

1. The utility model provides a hang down propeller structure of fixed wing unmanned aerial vehicle which characterized in that: comprises propellers, wherein the propellers comprise a forward-rotation vertical propeller (13) and a reverse-rotation vertical propeller (14) which are consistent in structure;

the forward-rotation vertical-lift propeller (13) comprises a support piece (11), and a first machine arm (3) and a second machine arm (4) which are rotatably connected with the support piece (11);

the forward-rotation vertical-lift propeller (13) further comprises a transmission piece (8) and a bearing seat (9) for supporting the transmission piece (8);

the first machine arm (3) is provided with a positive paddle (1), and the second machine arm (4) is provided with a negative paddle (2);

through the interaction of the arranged linkage piece (6) and the transmission piece (8), one end of the first machine arm (3) and one end of the second machine arm (4) rotate on the supporting piece (11), and then the positive paddle (1) and the negative paddle (2) are driven to move in opposite directions or move back to back.

2. A propeller structure for a vertical lift fixed wing drone according to claim 1, characterised in that: a driving part (12) used for driving the transmission part (8) to rotate is further arranged between the forward-rotation vertical propeller (13) and the reverse-rotation vertical propeller (14).

3. A propeller structure for a vertical lift fixed wing drone according to claim 2, characterised in that: the driving part (12) is meshed with a driven gear arranged on the transmission part (8) through a driving gear (10) so that the power of the driving part (12) is transmitted to the transmission part (8).

4. A propeller structure for a vertical lift fixed wing drone according to claim 1, 2 or 3, characterised in that: the transmission piece (8) is a screw rod and is in threaded fit with one end of the linkage piece (6).

5. A propeller structure of a vertical fixed wing drone according to claim 4, characterized in that: one end of the linkage piece (6) is in adaptive connection with the transmission piece (8) through a sliding sleeve (7) arranged on the linkage piece, and the other end of the linkage piece (6) is in sliding fit with the first machine arm (3) through a shaft sleeve (5) arranged on the linkage piece; the shaft sleeve (5) is connected with the linkage piece (6) through a shaft pin, and the sliding sleeve (7) is connected with the linkage piece (6) through a shaft pin.