CN210364408U - Unmanned helicopter driven by double motors - Google Patents
Unmanned helicopter driven by double motors Download PDFInfo
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- CN210364408U CN210364408U CN201920736200.1U CN201920736200U CN210364408U CN 210364408 U CN210364408 U CN 210364408U CN 201920736200 U CN201920736200 U CN 201920736200U CN 210364408 U CN210364408 U CN 210364408U
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- connecting rod
- unmanned helicopter
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Abstract
The utility model discloses a double-motor driven unmanned helicopter, which comprises a frame, a driving component and a main shaft which are arranged on the frame, a main rotor connected with the main shaft and a tail propeller; the driving assembly comprises a main power brushless motor and a tail brushless motor, a first synchronizing wheel is arranged on a motor shaft of the main power brushless motor, a second synchronizing wheel is arranged at the lower end of the main shaft, and the first synchronizing wheel and the second synchronizing wheel are transmitted through a synchronous belt to provide rotary power for the main rotor; the tail brushless motor directly drives a tail propeller arranged at the tail of the frame, and the tail propeller and the propeller of the main rotor wing are arranged at a 90-degree right angle, so that the tail propeller provides course control of the helicopter. The unmanned helicopter driven by the double motors is simple in structure and convenient to assemble, and saves the tail adjusting mechanism with variable pitch while reducing mechanical transmission loss.
Description
Technical Field
The utility model relates to an aeromodelling and unmanned aerial vehicle helicopter technical field specifically, relate to a two motor drive's unmanned helicopter.
Background
The unmanned helicopter is very popular among children and adults due to excellent interestingness and entertainment. The model airplane can fly stably at high altitude and flexibly change the direction, and the self gravity and wind resistance need to be overcome.
However, in the existing traditional helicopter, the rotary power of the main rotor is transmitted to the tail variable-pitch rotor through a gear or a synchronous belt, so that a mechanical transmission mechanism needs to be installed in a tail pipe of the helicopter, the overall weight of the remote control helicopter is increased invisibly, the electric energy consumption is too high, and the endurance mileage is shortened seriously. Meanwhile, the mechanical transmission mechanism is arranged in the tail pipe of the helicopter, so that the mounting and dismounting operations are complicated, and the tail pipe is easy to damage in the using process, thereby increasing the maintenance cost.
Therefore, it is highly desirable to provide a remote control helicopter with simple structure and dual drive to solve the above technical problems.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a two motor drive's unmanned helicopter, this two motor drive's unmanned helicopter simple structure, the equipment is convenient, has saved variable pitch's afterbody adjustment mechanism when reducing mechanical transmission loss.
In order to achieve the purpose, the utility model provides a double-motor driven unmanned helicopter, which comprises a frame, a driving assembly and a main shaft which are arranged on the frame, a main rotor connected with the main shaft and a tail propeller; wherein the content of the first and second substances,
the driving assembly comprises a main power brushless motor and a tail brushless motor, a first synchronizing wheel is arranged on a motor shaft of the main power brushless motor, a second synchronizing wheel is arranged at the lower end of the main shaft, and the first synchronizing wheel and the second synchronizing wheel are in transmission with a synchronous belt through a spring pinch roller to provide rotary power for the main rotor; the tail brushless motor directly drives a tail propeller arranged at the tail of the frame, and the tail propeller and the propeller of the main rotor wing are arranged at a 90-degree right angle, so that the tail propeller provides course control of the helicopter.
Preferably, the device also comprises a pull rod, a tilting disk, a main connecting rod and an auxiliary connecting rod; wherein the content of the first and second substances,
the tilting disk comprises a fixed tilting part and a rotary tilting part connected with the fixed tilting part, the fixed tilting part of the tilting disk is provided with a pull rod connecting part protruding towards the periphery of the tilting disk corresponding to the pull rod, and the pull rod is movably connected with the pull rod connecting part;
the rotary tilting part of the tilting disk is provided with a main connecting rod connecting part and an auxiliary connecting rod connecting part which are protruded towards the periphery of the tilting disk corresponding to the main connecting rod and the auxiliary connecting rod respectively, one end of the main connecting rod is movably connected to the main wing, the other end of the main connecting rod is movably connected to the main connecting rod connecting part of the rotary tilting part of the tilting disk, one end of the auxiliary connecting rod is movably connected to the auxiliary wing, and the other end of the auxiliary connecting rod is movably connected to the auxiliary connecting rod connecting.
Preferably, the tail rotor is a fixed pitch rotor.
Preferably, the tail rotor and/or the rotor of the main rotor are two-blade or multi-blade rotors.
Preferably, the tail propeller is arranged on one side surface of the tail part of the machine frame, and the rotating surface is parallel to the tail part of the machine frame.
Preferably, the other side surface of the tail part of the rack is provided with a tail wing.
Preferably, the tail fins extend upwardly and/or downwardly and form an angle of 45 ° to 60 ° with the horizontal plane.
Preferably, the diameter of the first synchronizing wheel is 1-2 cm.
Preferably, the diameter of the second synchronizing wheel is 5-10 cm.
According to the above technical scheme, the utility model discloses constitute main flight driving system by main power brushless motor and afterbody brushless motor, main motor shaft is equipped with first synchronizing wheel, the second synchronizing wheel is equipped with to helicopter main shaft lower extreme, main power motor provides main rotor rotary power through synchronous belt transmission, and be equipped with the spring pinch roller for the hold-in range, need not to adjust the distance clearance of first motor synchronizing wheel and main shaft second synchronizing wheel, the spring pinch roller plays the tensioning hold-in range effect, compare with gear drive, transmission noise is littleer with vibrations, and need not to adjust the transmission tooth interval, it is more convenient to maintain and install. The tail motor directly drives the fixed-pitch propeller, the tail propeller and the main rotor propeller are installed at 90 degrees, and the propeller driven by the tail motor provides course control of the helicopter. Like this, avoided traditional helicopter to pass through gear drive with main rotor rotary power, perhaps synchronous belt drive to afterbody variable pitch rotor. A mechanical transmission mechanism in a tail pipe of the helicopter is canceled, electric energy is transmitted to a tail electronic speed regulator through a lead, the rotating speed of an electric control motor is changed to directly drive a fixed-pitch rotor wing, and the course is controlled through the rotating speed change. Therefore, the mechanical transmission loss is reduced, the tail adjusting mechanism with variable screw pitch is reduced, and the effects of saving energy and cost and reducing the assembly complexity are achieved.
Other features and advantages of the present invention will be described in detail in the detailed description which follows.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic view of the overall structure of a dual-motor driven unmanned helicopter according to an embodiment of the present invention;
fig. 2 is a schematic view of an installation structure inside a frame of a dual-motor driven unmanned helicopter according to an embodiment of the present invention;
fig. 3 is an enlarged view of a tail structure of a dual motor driven unmanned helicopter according to an embodiment of the present invention.
Description of the reference numerals
1-frame 2-main rotor
3-tail propeller 4-main power brushless motor
5-Tail brushless motor 6-first synchronous wheel
7-second synchronizing wheel 8-synchronous belt
9-empennage 10-spring pinch roller
Detailed Description
The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings. It is to be understood that the description of the embodiments herein is for purposes of illustration and explanation only and is not intended to limit the invention.
In the present invention, unless otherwise specified, the terms of orientation such as "upper, lower, inner, outer" and the like included in the terms only represent the orientation of the terms in a conventional use state or are colloquially known by those skilled in the art, and should not be construed as limiting the terms.
Referring to fig. 1 to 3, the present invention provides a dual-motor driven unmanned helicopter, which includes a frame 1, a driving assembly and a main shaft mounted on the frame 1, a main rotor 2 connected to the main shaft, and a tail rotor 3; wherein the content of the first and second substances,
the driving assembly comprises a main power brushless motor 4 and a tail brushless motor 5, a first synchronizing wheel 6 is arranged on a motor shaft of the main power brushless motor 4, a second synchronizing wheel 7 is arranged at the lower end of a main shaft, and the first synchronizing wheel 6 and the second synchronizing wheel 7 are transmitted with a synchronizing belt 8 through a spring pinch roller 10 to provide rotating power for the main rotor 2; the tail brushless motor 5 directly drives the tail rotor 3 mounted at the tail of the frame 1, and the tail rotor 3 is mounted at a 90-degree right angle to the rotor of the main rotor 2 so that the tail rotor 3 provides directional control of the helicopter.
Through the technical scheme, the main flight power system is formed by the main power brushless motor 4 and the tail brushless motor 5, the main motor shaft is provided with the first synchronous wheel 6, the lower end of the main shaft of the helicopter is provided with the second synchronous wheel 7, the main power motor provides the rotary power of the main rotor 2 through the transmission of the synchronous belt 8, the synchronous belt transmission is quieter, and the vibration is small. The gear transmission noise is large, the vibration is large, the gear clearance is difficult to debug, and the synchronous wheel transmission has more advantages. The tail motor directly drives the fixed-pitch propeller, the tail propeller 3 and the main rotor 2 are installed at 90 degrees, and the propeller driven by the tail motor provides course control of the helicopter. Like this, avoided traditional helicopter to pass through gear drive with main rotor 2 rotary power, perhaps synchronous belt drive to afterbody variable pitch rotor. A mechanical transmission mechanism in a tail pipe of the helicopter is canceled, electric energy is transmitted to a tail electronic speed regulator through a lead, the rotating speed of an electric control motor is changed to directly drive a fixed-pitch rotor wing, and the course is controlled through the rotating speed change. Therefore, the mechanical transmission loss is reduced, the tail adjusting mechanism with variable screw pitch is reduced, and the effects of saving energy and cost and reducing the assembly complexity are achieved.
In this embodiment, in order to optimize the driving structure of the two-motor driven unmanned helicopter, it is preferable that the unmanned helicopter further includes a tie rod, a tilt disk, a main link, and an auxiliary link; wherein the content of the first and second substances,
the tilting disk comprises a fixed tilting part and a rotary tilting part connected with the fixed tilting part, the fixed tilting part of the tilting disk is provided with a pull rod connecting part protruding towards the periphery of the tilting disk corresponding to the pull rod, and the pull rod is movably connected with the pull rod connecting part;
the rotary tilting part of the tilting disk is provided with a main connecting rod connecting part and an auxiliary connecting rod connecting part which are protruded towards the periphery of the tilting disk corresponding to the main connecting rod and the auxiliary connecting rod respectively, one end of the main connecting rod is movably connected to the main wing, the other end of the main connecting rod is movably connected to the main connecting rod connecting part of the rotary tilting part of the tilting disk, one end of the auxiliary connecting rod is movably connected to the auxiliary wing, and the other end of the auxiliary connecting rod is movably connected to the auxiliary connecting rod connecting.
In one embodiment, the tail rotor 3 is preferably a fixed pitch rotor.
In order to achieve the technical effect of ensuring stability during flight while reducing the weight of the dual-motor driven unmanned helicopter, it is preferable that the tail rotor 3 and/or the rotor of the main rotor 2 be a two-blade or multi-blade rotor.
In addition, in order to facilitate the control of the flight heading by the tail rotor 3, it is preferable that the tail rotor 3 is installed at one side of the tail portion of the frame 1 and the rotation plane is parallel to the tail portion of the frame 1.
In order to further improve the flight stability of the dual-motor driven unmanned helicopter and ensure safe and reliable flight, the other side surface of the tail part of the frame 1 is preferably provided with a tail wing 9.
In order to generate lateral forces on the flight 9 to help the main rotor balance the reaction torque, the flight 9 preferably extends upwards and/or downwards and forms an angle of 45-60 degrees with the horizontal.
In addition, in order to assemble the synchronous belt 8 conveniently, the function transmission effect after the first synchronous wheel 6 and the second synchronous wheel 7 are matched is better, the synchronous performance of the first synchronous wheel and the second synchronous wheel is stronger, and preferably, the diameter of the first synchronous wheel 6 is 1-2 cm.
While the diameter of the second synchronizing wheel 7 is preferably 5-10 cm.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, however, the present invention is not limited to the details of the above embodiments, and the technical concept of the present invention can be within the scope of the present invention to perform various simple modifications to the technical solution of the present invention, and these simple modifications all belong to the protection scope of the present invention.
It should be noted that the various technical features described in the above embodiments can be combined in any suitable manner without contradiction, and in order to avoid unnecessary repetition, the present invention does not need to describe any combination of the features.
In addition, various embodiments of the present invention can be combined arbitrarily, and the disclosed content should be regarded as the present invention as long as it does not violate the idea of the present invention.
Claims (9)
1. The unmanned helicopter driven by the double motors is characterized by comprising a frame (1), a driving assembly and a main shaft which are arranged on the frame (1), a main rotor (2) connected to the main shaft and a tail propeller (3); wherein the content of the first and second substances,
the driving assembly comprises a main power brushless motor (4) and a tail brushless motor (5), a first synchronizing wheel (6) is installed on a motor shaft of the main power brushless motor (4), a second synchronizing wheel (7) is installed at the lower end of the main shaft, and the first synchronizing wheel (6) and the second synchronizing wheel (7) are in transmission with a synchronizing belt (8) through a spring pinch roller (10) to provide rotating power for the main rotor (2); the tail brushless motor (5) is directly driven and installed on the tail propeller (3) at the tail of the frame (1), and the tail propeller (3) and the propeller of the main rotor (2) are installed in a 90-degree right-angle mode, so that the tail propeller (3) provides course control of a helicopter.
2. The dual motor driven unmanned helicopter of claim 1 further comprising a tie rod, a swashplate, a primary link, and a secondary link; wherein the content of the first and second substances,
the tilting disk comprises a fixed tilting part and a rotary tilting part connected with the fixed tilting part, the fixed tilting part of the tilting disk is provided with a pull rod connecting part protruding towards the periphery of the tilting disk corresponding to the pull rod, and the pull rod is movably connected with the pull rod connecting part;
the rotary inclined part of the inclined disc corresponds to the main connecting rod and the auxiliary connecting rod which are respectively provided with a main connecting rod connecting part and an auxiliary connecting rod connecting part protruding towards the periphery of the inclined disc, one end of the main connecting rod is movably connected to the main wing, the other end of the main connecting rod is movably connected to the main connecting rod connecting part of the rotary inclined part of the inclined disc, one end of the auxiliary connecting rod is movably connected to the auxiliary wing, and the other end of the auxiliary connecting rod is movably connected to the auxiliary connecting rod connecting part of the rotary inclined.
3. The dual motor driven unmanned helicopter of claim 1, characterized in that the tail rotor (3) is a fixed pitch rotor.
4. The dual-motor unmanned helicopter of claim 1, characterized in that the propellers of the tail rotor (3) and/or the main rotor (2) are two-blade or multi-blade propellers.
5. The dual-motor unmanned helicopter of claim 4, characterized in that the tail propeller (3) is installed at one side of the tail of the frame (1) and the rotation plane is parallel to the tail of the frame (1).
6. The dual-motor unmanned helicopter of claim 5, characterized in that the other side of the tail of the frame (1) is mounted with a tail (9).
7. The dual-motor unmanned helicopter of claim 6, wherein the tail (9) extends upwardly and/or downwardly and forms an angle of 45 ° -60 ° with the horizontal.
8. The dual-motor driven unmanned helicopter of claim 1, characterized in that the diameter of the first synchronizing wheel (6) is 1-2 cm.
9. The dual-motor driven unmanned helicopter of claim 8, characterized in that the diameter of the second synchronizing wheel (7) is 5-10 cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920736200.1U CN210364408U (en) | 2019-05-21 | 2019-05-21 | Unmanned helicopter driven by double motors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920736200.1U CN210364408U (en) | 2019-05-21 | 2019-05-21 | Unmanned helicopter driven by double motors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210364408U true CN210364408U (en) | 2020-04-21 |
Family
ID=70261189
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920736200.1U Expired - Fee Related CN210364408U (en) | 2019-05-21 | 2019-05-21 | Unmanned helicopter driven by double motors |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210364408U (en) |
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2019
- 2019-05-21 CN CN201920736200.1U patent/CN210364408U/en not_active Expired - Fee Related
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200421 |
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| CF01 | Termination of patent right due to non-payment of annual fee |