CN219154767U

CN219154767U - Direct-drive small coaxial reverse-propeller aircraft

Info

Publication number: CN219154767U
Application number: CN202222404084.8U
Authority: CN
Inventors: 迟海旭
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-09-09
Filing date: 2022-09-09
Publication date: 2023-06-09
Anticipated expiration: 2032-09-09

Abstract

The utility model discloses a direct-drive small coaxial anti-propeller aircraft, which comprises a steering engine, a gesture control mechanism, a power mechanism and a rotor mechanism, wherein the steering engine, the gesture control mechanism and the power mechanism are coaxially arranged through a hollow shaft; the rotor wing mechanism comprises a blade mounting bracket and a blade clamp which are arranged on the power mechanism, and the end part of the blade clamp is connected with the blade; the utility model simplifies the transmission structure, omits gear transmission and directly drives the paddle to rotate through the power motor; the inclined disc type universal adjusting structure simplifies the gesture control part, and the blade inclination angle is periodically controlled to generate gesture control moment, so that the inclined disc type universal adjusting structure is small and simple in size, reliable and stable; through arranging the completely penetrating hollow shaft, wiring in the shaft is adopted, so that the wiring installation difficulty is greatly reduced; the machine reduces dead weight of the machine body to the greatest extent, and parts such as equipment bins, shells and the like are easy to install.

Description

Direct-drive small coaxial reverse-propeller aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a direct-drive small coaxial reverse propeller aircraft.

Background

With the development of small multi-axis unmanned aerial vehicles and small coaxial unmanned aerial vehicles, some defects still exist for model plane lovers in practical application; for example: the endurance time is relatively short when the small multi-axis unmanned aerial vehicle mounts a load, and the long-time working requirement cannot be met; the folding structure of the folding portable multi-axis unmanned aerial vehicle is relatively complex, so that accidental faults and maintenance cost which possibly occur are increased; the vector coaxial unmanned aerial vehicle adopts a thrust vector to control the gravity center of the aircraft, has complex structure, large volume and sensitive gravity center position, has the risk of influencing normal flight when carrying load, has difficult wiring, is not suitable for folding of the blades, and can not meet the use requirement.

Disclosure of Invention

In order to solve the technical problems, the technical scheme provided by the utility model is as follows: the direct-drive small coaxial anti-pitch aircraft comprises a steering engine, a gesture control mechanism, a power mechanism and a rotor mechanism, wherein the steering engine, the gesture control mechanism and the power mechanism are coaxially arranged through a hollow shaft, the rotor mechanism is arranged on the gesture control mechanism and is in transmission connection with the power mechanism, and the gesture control mechanism is in transmission connection with the steering engine; the rotor wing mechanism comprises a blade mounting bracket and a blade clamp which are arranged on the power mechanism, and the end part of the blade clamp is connected with the blade; steering wheel, power unit, gesture control mechanism set up in the casing, rotor mechanism sets up outside the casing.

The number of the steering engines is two, the gesture control mechanism comprises swing arms which are respectively arranged on the steering engines in a transmission mode, one end, far away from the steering engines, of each swing arm is hinged to a first pull rod, the other end of each first pull rod is hinged to a swash plate type universal adjusting structure, the rotor wing mechanism is hinged to the swash plate type universal adjusting structure through a pull rod assembly, the swash plate type universal adjusting structure is enabled to incline through the first pull rods under the driving of the steering engines, and meanwhile the rotor wing mechanism changes the inclination angle through the pull rod assembly; the swash plate type universal adjusting structure comprises a ball bearing, the ball bearing is externally connected with the ball bearing in a rotating manner, a steering engine connecting rod is arranged at the bottom of the ball bearing, a fish eye bearing is movably arranged at the center of the top of the ball bearing, the steering engine connecting rod is hinged with one end of a pull rod, and the outer wall of the ball bearing is hinged with the pull rod assembly; the steering engine connecting rod is connected with the guide rod on one side far away from the first pull rod, a corresponding guide slideway is vertically arranged on the machine shell, and the end part of the guide rod is slidably arranged in the guide slideway.

Compared with the prior art, the utility model has the advantages that: the utility model has simple and practical structure and fewer fault points; the cost is low, and a large number of finished products are used; easy to disassemble, assemble and maintain; is foldable;

the utility model simplifies the transmission structure, omits gear transmission and directly drives the paddle to rotate through the power motor; the inclined disc type universal adjusting structure simplifies the gesture control part, and the blade inclination angle is periodically controlled to generate gesture control moment, so that the inclined disc type universal adjusting structure is small and simple in size, reliable and stable; through arranging the completely penetrating hollow shaft, wiring in the shaft is adopted, so that the wiring installation difficulty is greatly reduced; the machine reduces dead weight of the machine body to the greatest extent, and parts such as equipment bins, shells and the like are easy to install.

Drawings

Fig. 1 is a schematic structural view of a direct-drive small coaxial contra-propeller aircraft.

Fig. 2 is a schematic diagram of the internal structure of a direct-drive small coaxial contra-propeller aircraft according to the present utility model.

Fig. 3 is a schematic structural view of an attitude control mechanism in a direct-drive small coaxial contra-propeller aircraft of the present utility model.

Fig. 4 is a schematic structural view of a swash plate type universal adjusting structure in a direct-drive small coaxial reverse-propeller aircraft.

Fig. 5 is a schematic structural view of a guide chute in a direct-drive small coaxial contra-propeller aircraft of the present utility model.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

In the description of the embodiments of the present utility model, it should be noted that, if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate an azimuth or a positional relationship based on that shown in the drawings, or an azimuth or a positional relationship in which the product of the present utility model is conventionally put when used, it is merely for convenience of describing the present utility model and simplifying the description, and it does not indicate or imply that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present utility model. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal," "vertical," "overhang" and the like, if any, do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the embodiments of the present utility model, "plurality" means at least 2.

In the description of the embodiments of the present utility model, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.

Examples:

with reference to fig. 1-5, the embodiment discloses a direct-drive small coaxial anti-pitch aircraft, which comprises a steering engine 1, a gesture control mechanism 2, a power mechanism 3 and a rotor mechanism 4, wherein the steering engine 1, the gesture control mechanism 2 and the power mechanism 3 are coaxially arranged through a hollow shaft 10, the rotor mechanism 4 is arranged on the gesture control mechanism 2 and is in transmission connection with the power mechanism 3, and the gesture control mechanism 2 is in transmission connection with the steering engine 1; the rotor mechanism 4 comprises a blade mounting bracket 401 and a blade clamp 402 which are arranged on the power mechanism 3, and the end part of the blade clamp 402 is connected with a blade 403; steering wheel 1, power unit 3, gesture control mechanism 2 set up in casing 5, and rotor mechanism 4 sets up outside casing 5.

The number of the steering engines 1 is two, the gesture control mechanism 2 comprises swing arms 201 which are respectively arranged on the steering engines 1 in a transmission way, one ends of the swing arms 201, which are far away from the steering engines 1, are hinged with a first pull rod 202, the other ends of the first pull rod 202 are hinged with a sloping plate type universal adjusting structure 203, the rotor wing mechanism 4 is hinged with the sloping plate type universal adjusting structure 203 through a pull rod assembly 6, so that the sloping plate type universal adjusting structure 203 is driven by the steering engines 1 to incline through the first pull rod 202, and meanwhile, the rotor wing mechanism 4 changes the inclination angle through the pull rod assembly 6; the bottom of the swash plate type universal adjusting structure 203 is rotatably arranged on the hollow shaft 10, and the steering engine 1 is arranged in the steering engine fixing bracket 9; the swash plate type universal adjusting structure 203 comprises a ball bearing 203a, a steering engine connecting rod 203b is arranged at the bottom of the ball bearing 203a, a fisheye bearing 203c is movably arranged in the center of the top, the steering engine connecting rod 203b is hinged with the end part of a first pull rod 202, and the outer wall of the ball bearing 203b is hinged with a pull rod assembly 6; one side of the steering engine connecting rod 203b, which is far away from the first pull rod 202, is connected with a guide rod 7, a corresponding guide slideway 8 is vertically arranged on the machine shell 5, and the end part of the guide rod 7 is arranged in the guide slideway 8 in a sliding way; the pull rod assembly 6 comprises a second pull rod 601, the top of the second pull rod 601 is hinged with the blade mounting bracket 401 through a pull rod connecting piece 602, and the bottom ball bearing outer wall 203b is hinged.

The blade mounting bracket 401 is rotatably arranged on the upper part of the fisheye bearing 203c, the blade mounting bracket 401 is in transmission connection with the power mechanism 3 through the lower rotor fixing bracket 403, and the lower rotor fixing bracket 403 is coaxially arranged with the fisheye bearing 203 c; the blade clamp 402 is attached to the blade mounting bracket 401 by a 90 degree hinge fold.

In this embodiment, the number of the rotor mechanisms 4 is two, including lower rotor mechanisms, upper rotor mechanisms, lower rotor mechanisms are in transmission connection with gesture control mechanisms, the power mechanism 3 comprises a lower driving motor 301 in transmission connection with the lower rotor mechanisms and an upper driving motor 302 in transmission connection with the upper rotor mechanisms, and a motor fixing bracket 303 is arranged between the upper driving motor 302 and the lower driving motor 301.

When the steering engine is specifically implemented, the steering engine drives the swing arm to swing up and down, the swing arm passes through the universal regulation structure of sloping cam plate on pull upper portion, simultaneously, set up the interval between the action of two steering engines, when one of them swing arm upwards moves, another swing arm downwardly moving, and then make one of them pull rod upwards promote the universal regulation structure of sloping cam plate, another pull rod downwards pulls the universal regulation structure of sloping cam plate, make the universal regulation structure of sloping cam plate periodically change angle, rotor mechanism is connected with the universal regulation structure of sloping cam plate through the pull rod subassembly simultaneously under power unit drive, make rotor mechanism's paddle also periodically change angle, make its both sides lifting force change.

The utility model and its embodiments have been described above with no limitation, and the actual construction is not limited to the embodiments of the utility model as shown in the drawings. In summary, if one of ordinary skill in the art is informed by this disclosure, a structural manner and an embodiment similar to the technical solution should not be creatively devised without departing from the gist of the present utility model.

Claims

1. The direct-drive small coaxial anti-oar aircraft is characterized by comprising a steering engine, an attitude control mechanism, a power mechanism and a rotor mechanism, wherein the steering engine, the attitude control mechanism and the power mechanism are coaxially arranged through a hollow shaft, the rotor mechanism is arranged on the attitude control mechanism and is in transmission connection with the power mechanism, and the attitude control mechanism is in transmission connection with the steering engine; the rotor wing mechanism comprises a blade mounting bracket and a blade clamp which are arranged on the power mechanism, and the end part of the blade clamp is connected with the blade; steering wheel, power unit, gesture control mechanism set up in the casing, rotor mechanism sets up outside the casing.

2. The direct-drive small coaxial anti-oar aircraft according to claim 1, wherein the number of steering engines is two, the gesture control mechanism comprises swing arms which are respectively arranged on the steering engines in a transmission mode, one ends of the swing arms, which are far away from the steering engines, are hinged with a first pull rod, the other ends of the first pull rods are hinged with a swashplate type universal adjusting structure, the rotor mechanism is hinged with the swashplate type universal adjusting structure through a pull rod assembly, the swashplate type universal adjusting structure is enabled to incline through the first pull rod under the driving of the steering engines, and meanwhile, the rotor mechanism changes the inclination angle through the pull rod assembly.

3. The direct-drive small coaxial anti-pitch aircraft according to claim 2, wherein the swash plate type universal adjusting structure comprises a ball bearing, a steering engine connecting rod is arranged at the bottom of the ball bearing, a fish-eye bearing is movably arranged at the center of the top of the ball bearing, the steering engine connecting rod is hinged with one end of a pull rod, and the outer wall of the ball bearing is hinged with a pull rod assembly.

4. The direct-drive small coaxial anti-oar aircraft according to claim 3, wherein one side of the steering engine connecting rod far away from the first pull rod is connected with a guide rod, a corresponding guide slideway is vertically arranged on the shell, and the end part of the guide rod is slidably arranged in the guide slideway.

5. The direct-drive small coaxial contra-paddle aircraft according to claim 2, wherein the pull rod assembly comprises a second pull rod, the top of the second pull rod is hinged with the paddle mounting bracket through a pull rod connecting piece, and the outer wall of the bottom ball bearing is hinged.

6. The direct-drive small coaxial anti-oar aircraft according to claim 3, wherein the bottom of the swash plate type universal adjusting structure is rotatably arranged on the hollow shaft, and the steering engine is arranged in the steering engine fixing bracket.

7. The direct-drive small coaxial contra-propeller aircraft according to claim 5, wherein the blade mounting bracket is rotatably arranged on the upper part of the fish-eye bearing, the blade mounting bracket is in transmission connection with the power mechanism through a lower rotor fixing bracket, and the lower rotor fixing bracket is coaxially arranged with the fish-eye bearing.

8. The direct drive small coaxial contra-paddle aircraft of claim 1 wherein the paddle clip is attached to the paddle mounting bracket by a 90 hinge fold.

9. The direct-drive small coaxial contra-oar aircraft according to claim 1, wherein the number of the rotor mechanisms is two, the helicopter comprises a lower rotor mechanism and an upper rotor mechanism, the lower rotor mechanism is in transmission connection with the gesture control mechanism, the power mechanism comprises a lower driving motor in transmission connection with the lower rotor mechanism and an upper driving motor in transmission connection with the upper rotor mechanism, and a motor fixing bracket is arranged between the upper driving motor and the lower driving motor.