CN217736171U - High-performance transmission structure of unmanned helicopter speed reducer - Google Patents
High-performance transmission structure of unmanned helicopter speed reducer Download PDFInfo
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- CN217736171U CN217736171U CN202221706686.2U CN202221706686U CN217736171U CN 217736171 U CN217736171 U CN 217736171U CN 202221706686 U CN202221706686 U CN 202221706686U CN 217736171 U CN217736171 U CN 217736171U
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Abstract
The utility model relates to the technical field of helicopter parts, in particular to a high-performance unmanned helicopter speed reducer transmission structure, one side of a gear box is provided with a horizontal transmission shaft, the top of the gear box is provided with a vertical main rotor shaft, the other side of the gear box is provided with a horizontal tail rotor shaft, wherein one end of the transmission shaft extending out of the gear box is connected with a driving shaft through a composite coupler, and one end of the transmission shaft extending into the gear box is connected with a transmission gear; one end of the main rotor shaft extending into the gear box is connected with a main rotor gear and a reduction gear, and the reduction gear is meshed with the transmission gear; the one end that the tail rotor shaft stretched into in the gear box is connected with tail rotor gear, and tail rotor gear and main rotor gear meshing. The transmission structure only uses 4 groups of gears in the process of transmitting the engine torque from the driving shaft to the main rotor wing shaft and the tail rotor wing shaft, reduces the mechanical loss and the fault rate among the gears, improves the transmission efficiency of the engine torque and is convenient to use.
Description
Technical Field
The utility model relates to a helicopter spare part technical field specifically is a high performance unmanned helicopter reduction gear transmission structure.
Background
Along with the high-speed development of unmanned aerial vehicle technology, the application of unmanned helicopter is also more and more extensive. The unmanned helicopter has the advantages of vertical take-off and landing and hovering, is mainly used for executing tasks such as information monitoring and reconnaissance, communication relay, battlefield supply and the like, and can also be used for carrying advanced mine detection, submarine detection sensors and attack weapons to execute anti-submarine and mine sweeping tasks. The civil unmanned helicopter can perform tasks such as flight line inspection, air transportation and the like. With the function of the unmanned helicopter becoming more and more powerful, the design requirements for the unmanned helicopter become more strict.
At present, a speed reducer is a key transmission part of a helicopter, a dozen groups of gears are often adopted in an existing transmission structure of an unmanned helicopter for transmission, one group of gears breaks down to interrupt the whole transmission process, and the torque transmission efficiency of an engine is reduced due to the increase of the number of the gears. In view of this, we propose a high performance unmanned helicopter speed reducer transmission structure.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned helicopter reduction gear transmission structure of high performance to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
a high performance unmanned helicopter speed reducer transmission structure, comprising: the device comprises a driving shaft, a composite coupler, a gear box, a transmission shaft, a transmission gear, a main rotor shaft, a main rotor gear, a reduction gear, a tail rotor shaft and a tail rotor gear; the transmission shaft in the horizontal direction is arranged on one side of the gear box, the main rotor shaft in the vertical direction is arranged at the top of the gear box, and the tail rotor shaft in the horizontal direction is arranged on the other side of the gear box, wherein one end, extending out of the gear box, of the transmission shaft is connected with the driving shaft through the composite coupler, and one end, extending into the gear box, of the transmission shaft is connected with the transmission gear; one end of the main rotor shaft extending into the gear box is connected with a main rotor gear and a reduction gear, and the reduction gear is meshed with the transmission gear; the tail rotor shaft stretches into one end in the gear box is connected with a tail rotor gear, just the tail rotor gear with the meshing of main rotor gear.
Preferably, the composite coupler is sequentially provided with an elastic coupler, an overrunning clutch and a centrifugal clutch along the driving shaft to the transmission direction of the transmission shaft.
Preferably, one end of the main rotor shaft extending out of the gear box is connected with a main rotor hub.
Preferably, the tail rotor shaft extends out of one end of the gear box and is connected with a tail rotor hub.
Preferably, drive gear's diameter is 9mm, drive gear's diameter is 77mm, main rotor gear's diameter is 50mm, tail rotor gear's diameter is 10mm.
Preferably, a temperature sensor and a pressure sensor are further mounted on the gear box.
Preferably, the transmission gear, the main rotor gear, the reduction gear and the tail rotor gear are all made of 14CrMnSiNi2MoA alloy structural steel.
Compared with the prior art, the beneficial effects of the utility model are that: according to the high-performance transmission structure of the unmanned helicopter speed reducer, torque transmitted by a helicopter engine is transmitted to a transmission shaft through a driving shaft and a composite coupler, the transmission shaft drives a transmission gear to rotate, the transmission gear is meshed with a reduction gear, so that a main rotor shaft rotates around the axial direction under the traction of the reduction gear and pulls the main rotor gear to rotate together, and a tail rotor gear is meshed with the main rotor gear, so that the tail rotor shaft rotates around the axial direction under the traction of the main rotor gear, the process that the whole engine torque is transmitted to the main rotor shaft and the tail rotor shaft from the driving shaft is completed, only 4 groups of gears are used in the transmission process, the mechanical loss and the fault occurrence rate among the gears are reduced, the transmission efficiency of the engine torque is improved, and the use is convenient.
Drawings
Fig. 1 is a block diagram of the overall structure of the present invention.
In the figure: 1. a drive shaft; 2. a composite coupling; 21. an elastic coupling; 22. an overrunning clutch; 23. a centrifugal clutch; 3. a gear case; 31. a temperature sensor; 32. a pressure sensor; 4. a drive shaft; 5. a transmission gear; 6. a main rotor shaft; 61. a main rotor hub; 7. a main rotor gear; 8. a reduction gear; 9. a tail rotor shaft; 91. a tail rotor hub; 10. a tail rotor gear.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying 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 the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
In the description of this patent, it is noted that unless otherwise specifically stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can include, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed. The specific meaning of the above terms in this patent may be understood by one of ordinary skill in the art as appropriate.
A high performance unmanned helicopter retarder drive configuration, as shown in fig. 1, comprising: the device comprises a driving shaft 1, a composite coupler 2, a gear box 3, a transmission shaft 4, a transmission gear 5, a main rotor shaft 6, a main rotor gear 7, a reduction gear 8, a tail rotor shaft 9 and a tail rotor gear 10; a horizontal transmission shaft 4 is arranged on one side of the gear box 3, a vertical main rotor shaft 6 is arranged on the top of the gear box 3, and a horizontal tail rotor shaft 9 is arranged on the other side of the gear box 3, wherein one end of the transmission shaft 4 extending out of the gear box 3 is connected with the driving shaft 1 through a composite coupler 2, and one end of the transmission shaft 4 extending into the gear box 3 is connected with a transmission gear 5; one end of the main rotor shaft 6 extending into the gear box 3 is connected with a main rotor gear 7 and a reduction gear 8, and the reduction gear 8 is meshed with the transmission gear 5; one end of the tail rotor shaft 9 extending into the gear box 3 is connected with a tail rotor gear 10, and the tail rotor gear 10 is meshed with the main rotor gear 7. Therefore, the torque transmitted by the helicopter engine is transmitted to the transmission shaft 4 through the driving shaft 1 and the composite coupler 2, the transmission shaft 4 drives the transmission gear 5 to rotate, the transmission gear 5 is meshed with the reduction gear 8, the main rotor shaft 6 rotates around the shaft under the traction of the reduction gear 8, the main rotor gear 7 rotates together with the traction, and the tail rotor gear 10 is meshed with the main rotor gear 7, so that the tail rotor shaft 9 rotates around the shaft under the traction of the main rotor gear 7, the process of transmitting the whole engine torque from the driving shaft 1 to the main rotor shaft 6 and the tail rotor shaft 9 is completed, only 4 groups of gears are used in the transmission process, the mechanical loss and the fault rate among the gears are reduced, the transmission efficiency of the engine torque is improved, and the use is convenient.
Furthermore, the composite coupling 2 is sequentially provided with an elastic coupling 21, an overrunning clutch 22 and a centrifugal clutch 23 along the transmission direction from the driving shaft 1 to the transmission shaft 4. Through the multiple groups of couplings, the connection can be timely disconnected when mechanical failure or overload occurs between the driving shaft 1 and the transmission shaft 4, and the damage to an engine is avoided.
It should be noted that one end of the main rotor shaft 6 extending out of the gear box 3 is connected with a main rotor hub 61; the end of the tail rotor shaft 9 extending out of the gear box 3 is connected with a tail rotor hub 91. The main rotor and the tail rotor of the helicopter are conveniently mounted through the main rotor hub 61 and the tail rotor hub 91.
Further, the diameter of the transmission gear 5 is 9mm, the diameter of the transmission gear 5 is 77mm, the diameter of the main rotor gear 7 is 50mm, and the diameter of the tail rotor gear 10 is 10mm. The diameter of the transmission gear 5 is the minimum, so the rotation speed of the torque transmitted from the driving shaft 1 is the maximum, and the diameter of the transmission gear 5 is the maximum, so the rotation speed of the transmission gear 5 is the minimum, thereby achieving the effect of speed reduction, meanwhile, the main rotor gear 7 and the tail rotor gear 10 of the embodiment are arranged according to the rotation speed requirement of the tail rotor, so that the rotation speed requirement of the tail rotor during flying can be met, and the sizes of the transmission gear 5, the main rotor gear 7 and the tail rotor gear 10 of the embodiment are not limited to the sizes under the condition of meeting the flight requirement parameters of the helicopter.
Specifically, a temperature sensor 31 and a pressure sensor 32 are also mounted on the gear case 3. The temperature sensor 31 and the pressure sensor 32 can facilitate monitoring of temperature data and pressure data inside the gearbox 3, avoiding excessive temperatures or pressures inside the gearbox 3.
In this embodiment, the transmission gear 5, the main rotor gear 7, the reduction gear 8 and the tail rotor gear 10 are all made of 14CrMnSiNi2MoA alloy structural steel. The 14CrMnSiNi2MoA alloy structural steel has good rigidity and toughness, reduces mechanical wear among gears, and prolongs the service life of the gears.
When the transmission structure of the high-performance unmanned helicopter speed reducer is used, torque transmitted by a helicopter engine is transmitted to a transmission shaft 4 through a driving shaft 1 and a composite coupler 2, the transmission shaft 4 drives a transmission gear 5 to rotate, the transmission gear 5 is meshed with a reduction gear 8, so that a main rotor shaft 6 rotates around an axis under the traction of the reduction gear 8 and pulls the main rotor gear 7 to rotate together, and a tail rotor gear 10 is meshed with the main rotor gear 7, so that a tail rotor shaft 9 rotates around the axis under the traction of the main rotor gear 7, and the process that the whole engine torque is transmitted to the main rotor shaft 6 and the tail rotor shaft 9 from the driving shaft 1 is completed.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the description in the above embodiments and the description is only the preferred embodiments of the present invention, and is not intended to limit the present invention, and that there may be various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications all fall within the scope of the present invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The utility model provides an unmanned helicopter reduction gear transmission structure of high performance which characterized in that includes: the device comprises a driving shaft (1), a composite coupler (2), a gear box (3), a transmission shaft (4), a transmission gear (5), a main rotor wing shaft (6), a main rotor wing gear (7), a reduction gear (8), a tail rotor wing shaft (9) and a tail rotor wing gear (10);
one side of the gear box (3) is provided with the horizontal transmission shaft (4), the top of the gear box (3) is provided with the vertical main rotor wing shaft (6), the other side of the gear box (3) is provided with the horizontal tail rotor wing shaft (9),
one end of the transmission shaft (4) extending out of the gear box (3) is connected with the driving shaft (1) through the composite coupler (2), and one end of the transmission shaft (4) extending into the gear box (3) is connected with a transmission gear (5);
one end, extending into the gear box (3), of the main rotor shaft (6) is connected with a main rotor gear (7) and a reduction gear (8), and the reduction gear (8) is meshed with the transmission gear (5);
tail rotor shaft (9) stretch into one end in gear box (3) is connected with tail rotor gear (10), just tail rotor gear (10) with main rotor gear (7) meshing.
2. The transmission structure of the high-performance unmanned helicopter reducer according to claim 1, characterized in that the composite coupling (2) is provided with an elastic coupling (21), an overrunning clutch (22) and a centrifugal clutch (23) in sequence along the transmission direction from the driving shaft (1) to the transmission shaft (4).
3. A high performance unmanned helicopter decelerator transmission structure according to claim 1, characterized by a main rotor hub (61) connected to the end of the main rotor shaft (6) that extends out of the gear box (3).
4. A high performance unmanned helicopter reducer transmission according to claim 1 wherein the end of said tail rotor shaft (9) that extends outside of said gear box (3) is connected to a tail rotor hub (91).
5. A high performance unmanned helicopter reducer transmission according to claim 1, characterized by that said drive gear (5) has a diameter of 9mm, said drive gear (5) has a diameter of 77mm, said main rotor gear (7) has a diameter of 50mm, and said tail rotor gear (10) has a diameter of 10mm.
6. A high performance unmanned helicopter reducer transmission according to claim 1 characterized in that a temperature sensor (31) and a pressure sensor (32) are also mounted on said gearbox (3).
7. The transmission structure of the high-performance unmanned helicopter reducer according to any of claims 1-6, characterized in that the transmission gear (5), the main rotor gear (7), the reduction gear (8), and the tail rotor gear (10) are all made of 14CrMnSiNi2MoA alloy structural steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221706686.2U CN217736171U (en) | 2022-07-04 | 2022-07-04 | High-performance transmission structure of unmanned helicopter speed reducer |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202221706686.2U CN217736171U (en) | 2022-07-04 | 2022-07-04 | High-performance transmission structure of unmanned helicopter speed reducer |
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| CN217736171U true CN217736171U (en) | 2022-11-04 |
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| CN202221706686.2U Active CN217736171U (en) | 2022-07-04 | 2022-07-04 | High-performance transmission structure of unmanned helicopter speed reducer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117739088A (en) * | 2024-02-18 | 2024-03-22 | 四川腾盾科技有限公司 | Unmanned aerial vehicle tail cabin door transmission system and unmanned aerial vehicle tail cabin door structure |
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2022
- 2022-07-04 CN CN202221706686.2U patent/CN217736171U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117739088A (en) * | 2024-02-18 | 2024-03-22 | 四川腾盾科技有限公司 | Unmanned aerial vehicle tail cabin door transmission system and unmanned aerial vehicle tail cabin door structure |
| CN117739088B (en) * | 2024-02-18 | 2024-04-30 | 四川腾盾科技有限公司 | Unmanned aerial vehicle tail cabin door transmission system and unmanned aerial vehicle tail cabin door structure |
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