CN114110107B - Transmission system of unmanned helicopter with front-mounted engine - Google Patents
Transmission system of unmanned helicopter with front-mounted engine Download PDFInfo
- Publication number
- CN114110107B CN114110107B CN202111382051.1A CN202111382051A CN114110107B CN 114110107 B CN114110107 B CN 114110107B CN 202111382051 A CN202111382051 A CN 202111382051A CN 114110107 B CN114110107 B CN 114110107B
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- shaft
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 64
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 15
- 230000033001 locomotion Effects 0.000 claims description 10
- 230000005484 gravity Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 2
- 244000309464 bull Species 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H7/00—Gearings for conveying rotary motion by endless flexible members
- F16H7/02—Gearings for conveying rotary motion by endless flexible members with belts; with V-belts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H7/00—Gearings for conveying rotary motion by endless flexible members
- F16H7/08—Means for varying tension of belts, ropes, or chains
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H7/00—Gearings for conveying rotary motion by endless flexible members
- F16H7/08—Means for varying tension of belts, ropes, or chains
- F16H2007/0802—Actuators for final output members
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H7/00—Gearings for conveying rotary motion by endless flexible members
- F16H7/08—Means for varying tension of belts, ropes, or chains
- F16H2007/0802—Actuators for final output members
- F16H2007/0823—Electric actuators
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Toys (AREA)
Abstract
The invention belongs to the field of structural design of transmission systems, and particularly relates to a transmission system of an unmanned helicopter with a front-mounted engine. The transmission system comprises a lower belt pulley (2), a belt tensioning mechanism (3), an upper belt pulley (4), a main reduction input shaft (5), a connecting shaft (6), a tail transmission shaft (7), a tail speed reducer input shaft (9), a tail rotor shaft (8) and a main rotor shaft (10). The structure is simple in structure and light in weight, and the problem of power transmission of the front-mounted transmission system of the engine is solved.
Description
Technical Field
The invention belongs to the field of structural design of transmission systems, and particularly relates to a transmission system of an unmanned helicopter with a front-mounted engine.
Background
In light helicopters, a general layout mode of the rear engine is generally adopted, the layout mode is convenient for the arrangement of a transmission system, the engine transmits power to a belt transmission device firstly, and then the belt transmission device transmits power to a main speed reducer and a tail transmission shaft respectively. However, in the unmanned helicopter, because the driver is not arranged at the nose part, the rear gravity center of the whole helicopter is usually brought by the rear engine, in order to meet the weight gravity center requirement of the whole helicopter, the gravity center and the flight quality requirement can be met only by adding a counterweight at the nose position, the weight of the whole helicopter is increased by adding the counterweight, and the effective load capacity of a task is reduced.
The existing engine is arranged in front, and one is that a power transmission shaft is adopted to transmit the power of the engine to a big bevel gear of a main speed reducer, and then an output bevel gear is connected to transmit the power to a tail transmission shaft; the mode has complex structure, large occupied space and large weight cost, and reduces the effective load capacity of the task; and the other is a scheme of adopting a tail transmission shaft to bypass, so that the complexity of the system is increased. It is therefore necessary to design a new transmission system.
Disclosure of Invention
The purpose of the invention is that: the engine front-mounted unmanned helicopter transmission system is simple in structure and light in weight, and the problem of power transmission of the engine front-mounted transmission system is solved.
The technical scheme of the invention is as follows: the transmission system of the unmanned helicopter with the front-mounted engine comprises a lower belt pulley 2, a belt tensioning mechanism 3, an upper belt pulley 4, a main reduction input shaft 5, a connecting shaft 6, a tail transmission shaft 7, a tail reducer input shaft 9 and a tail rotor shaft 8;
two ends of the belt tensioning mechanism 3 are respectively connected with a shell of the engine 1 and the main reduction input shaft 5, and the engine 1 is driven to move up and down by tensioning and shrinking movement of the belt tensioning mechanism 3;
the engine 1 is in transmission connection with the lower belt pulley 2 and drives the lower belt pulley 2 to rotate;
the lower belt pulley 2 and the upper belt pulley 4 are driven by a belt, and the upper belt pulley 4 is fixedly connected with the main reduction input shaft 5;
the main reduction input shaft 5 is in spline connection with the connecting shaft 6, the connecting shaft 6 is in spline connection with the tail transmission shaft 7, the tail transmission shaft 7 is in spline connection with the tail speed reducer input shaft 9, and the tail speed reducer input shaft 9 and the tail rotor shaft 8 are in meshing reversing through bevel gears; the tail rotor shaft 8 drives the tail rotor.
Further, the engine 1 is placed at the front end of the unmanned helicopter.
Further, the small bevel gear on the main reduction input shaft 5 is meshed with the large bevel gear of the main rotor shaft, the main reduction input shaft 5 drives the main rotor shaft 10 to rotate, and the main rotor shaft drives the main rotor.
Further, the belt tensioning mechanism 3 comprises a motor 30, a worm gear mechanism and a screw nut mechanism 31 which are sequentially connected in a transmission way; the motor 30 performs rotational speed commutation by a worm and gear mechanism, and converts the rotational motion into linear motion of the screw nut mechanism 31; the screw nut mechanism 31 has an upper end connected to the main input shaft 5 and a lower end connected to the engine case.
Further, the worm wheel and worm mechanism and the screw nut mechanism 31 have a self-locking function.
Further, the bevel pinion on the main reduction input shaft 5 is designed integrally with the input shaft of the main reduction input shaft 5.
Further, a pair of first bearings 50 for supporting and transmitting meshing force of gears are provided on the left side of the bevel pinion 51 on the main reduction input shaft 5.
Further, an overrunning clutch 11 is arranged on the upper belt pulley 4; the overrunning clutch is used for automatically disengaging the main reduction input shaft 5 and the upper belt pulley 4 when the engine 1 fails, so as to realize the autorotation and downslide of the helicopter.
Further, a pair of second bearings 101 for supporting and transmitting meshing force of gears are provided at the upper end of the large bevel gear 100 on the main rotor shaft 10; the large bevel gear 100 is screwed to the drive shaft of the main rotor shaft 10.
The invention has the technical effects that: the engine is arranged in front, so that the problem of distribution of the weight center of gravity of the whole engine can be effectively solved. After the engine is arranged in front, the power is directly transmitted to the tail transmission shaft through the connecting shaft, so that the problem of interference of a power transmission route caused by the arrangement of the engine in front is solved.
The invention provides a transmission system configuration which is simple in structure and low in weight cost and is suitable for the front engine, and the transmission system configuration is used for solving the problem of power transmission of a helicopter.
Description of the drawings:
FIG. 1 is a schematic diagram of a driveline configuration.
The specific embodiment is as follows:
the invention is described in further detail below with reference to the accompanying drawings.
In combination with the illustration of fig. 1, the present embodiment provides an engine front unmanned helicopter transmission system, which comprises a lower belt pulley 2, a belt tensioning mechanism 3, an upper belt pulley 4, a main reduction input shaft 5, a connecting shaft 6, a tail transmission shaft 7, a tail reducer input shaft 9, a tail rotor shaft 8 and a main rotor shaft 10.
The two ends of the belt tensioning mechanism 3 are respectively connected with a shell of the engine 1 and the main reduction input shaft 5, and the engine 1 is driven to move up and down by tensioning and shrinking movement of the belt tensioning mechanism 3.
The engine 1 is connected with the lower belt pulley 2 in a transmission way, and drives the lower belt pulley 2 to rotate.
The lower belt pulley 2 and the upper belt pulley 4 are driven by a belt, and the upper belt pulley 4 is fixedly connected with the main reduction input shaft 5.
The small bevel gear on the main reduction input shaft 5 is meshed with the large bevel gear of the main rotor shaft, the main reduction input shaft 5 drives the main rotor shaft 10 to rotate, and the main rotor shaft drives the main rotor.
The main reduction input shaft 5 is in spline connection with the connecting shaft 6, the connecting shaft 6 is in spline connection with the tail transmission shaft 7, the tail transmission shaft 7 is in spline connection with the tail speed reducer input shaft 9, and the tail speed reducer input shaft 9 and the tail rotor shaft 8 are in meshing reversing through bevel gears; the tail rotor shaft 8 drives the tail rotor.
In the embodiment, the engine 1 is arranged at the front end of the unmanned helicopter, so that the problem of the distribution of the weight center of gravity of the whole helicopter is effectively solved.
In the embodiment, the belt tensioning mechanism 3 comprises a motor 30, a worm gear mechanism and a screw nut mechanism 31 which are sequentially connected in a transmission way; the motor 30 performs rotational speed commutation by a worm and gear mechanism, and converts the rotational motion into linear motion of the screw nut mechanism 31; the screw nut mechanism 31 has an upper end connected to the main input shaft 5 and a lower end connected to the engine case. The worm wheel and worm mechanism and the screw nut mechanism 31 have a self-locking function. In the present embodiment, the belt tensioning mechanism 3 controls the tensioning and releasing of the belt, so that the engine 1 is disconnected and combined with the transmission.
In this embodiment, the bevel pinion on the main reduction input shaft 5 is designed integrally with the input shaft of the main reduction input shaft 5. A pair of first bearings 50 are provided on the left side of the bevel pinion 51 on the main reduction input shaft 5 for supporting and transmitting the meshing force of the gears. A pair of second bearings 101 for supporting and transmitting the meshing force of gears are provided at the upper end of the large bevel gear 100 on the main rotor shaft 10; the large bevel gear 100 is screwed to the drive shaft of the main rotor shaft 10. In the embodiment, the power is transmitted to the tail transmission shaft and the tail speed reducer through the transmission of the main reduction input shaft, and compared with the output structure using the bevel gear, the power transmission device has the advantages of simple structure and reliable performance, greatly reduces the space occupation and reduces the weight of a transmission system.
The power transmission process of this embodiment is: the lower belt pulley 2 transmits power and rotation speed to the upper belt pulley 4 through a transmission belt, and the tension of the belt is controlled through the belt tensioning mechanism 3. The upper belt wheel is fixedly connected with a main reduction input shaft 5, and the input shaft of the main reduction input shaft and a pinion 51 are integrally designed.
The pinion shaft 51 is cantilever-mounted, and is provided at its left side with a pair of tapered roller bearings for supporting and transmitting the meshing force of the gears. The power and the rotating speed are transmitted to the large bevel gear through the meshing motion of the small bevel gear and the large bevel gear, and the large bevel gear is also installed by adopting a cantilever. The bull gear is connected to the main rotor shaft by a set of connectors.
The bevel pinion transmits power to the main reduction input shaft through belt transmission, and the belt tensioning mechanism 3 controls tensioning and loosening of a belt, so that the engine 1 is disconnected and combined with the transmission. An overrunning clutch 11 is arranged on the upper belt pulley 4; the overrunning clutch 11 is used for automatically disengaging the main reduction input shaft 5 and the upper belt pulley 4 when the engine 1 fails, so as to realize the autorotation and downslide of the helicopter.
The main reduction input shaft is subjected to reversing and speed reduction through a pair of bevel gears, and then power is transmitted to the main rotor wing; on the other hand, the main input shaft transmits power to the tail transmission shaft assembly and the tail reducer, and the tail reducer increases speed through reversing of a pair of bevel gears, transmits power to the tail rotor, and drives the tail rotor 9 to rotate.
The invention is suitable for the light and small helicopter system with the front-mounted engine. The transmission system with the configuration has a safe and reliable clutch function; the connection and disconnection of the engine and the belt transmission can be realized through the belt tensioning mechanism; the main input shaft is used for transmitting power, so that the structural complexity and the system weight can be effectively reduced, the processing cost and the installation and adjustment requirements can be reduced, the operation is flexible, the man-machine effect is good, and the maintenance is convenient.
Claims (8)
1. The transmission system of the unmanned helicopter with the front-mounted engine is characterized by comprising a lower belt pulley (2), a belt tensioning mechanism (3), an upper belt pulley (4), a main reduction input shaft (5), a connecting shaft (6), a tail transmission shaft (7), a tail reducer input shaft (9), a tail rotor shaft (8) and a main rotor shaft (10);
two ends of the belt tensioning mechanism (3) are respectively connected with a shell of the engine (1) and the main reduction input shaft (5), and the engine (1) is driven to move up and down by tensioning and shrinking movement of the belt tensioning mechanism (3);
the engine (1) is in transmission connection with the lower belt wheel (2) to drive the lower belt wheel (2) to rotate;
the lower belt wheel (2) and the upper belt wheel (4) are driven by a belt, and the upper belt wheel (4) is fixedly connected with the main reduction input shaft (5);
a small bevel gear on the main reduction input shaft (5) is meshed with a large bevel gear of the main rotor shaft, the main reduction input shaft (5) drives the main rotor shaft (10) to rotate, and the main rotor shaft drives the main rotor;
the main reduction input shaft (5) is in spline connection with the connecting shaft (6), the connecting shaft (6) is in spline connection with the tail transmission shaft (7), the tail transmission shaft (7) is in spline connection with the tail speed reducer input shaft (9), and the tail speed reducer input shaft (9) and the tail rotor shaft (8) are in meshing reversing through bevel gears; the tail propeller shaft (8) drives the tail propeller.
2. The engine front unmanned helicopter transmission according to claim 1, wherein the engine (1) is placed at the front end of the unmanned helicopter.
3. The engine front unmanned helicopter transmission system according to claim 1, wherein the belt tensioning mechanism (3) comprises a motor (30), a worm gear mechanism and a screw nut mechanism (31) which are in transmission connection in sequence; the motor (30) carries out rotating speed reversing through a turbine worm mechanism and converts the rotating motion into linear motion of a screw nut mechanism (31); the upper end of the screw nut mechanism (31) is connected with the main reduction input shaft (5), and the lower end is connected with the engine shell.
4. An engine front unmanned helicopter transmission according to claim 3, wherein the worm gear mechanism, screw nut mechanism (31) have a self-locking function.
5. An engine front unmanned helicopter transmission according to claim 3, wherein the bevel pinion on the main subtraction input shaft (5) is of integral design with the input shaft of the main subtraction input shaft (5).
6. The engine front unmanned helicopter transmission according to claim 5, wherein a pair of first bearings (50) for supporting and transmitting the meshing force of the gears are provided on the left side of a bevel pinion (51) on the main reduction input shaft (5).
7. The engine front unmanned helicopter transmission system according to claim 1, wherein the upper pulley (4) is provided with an overrunning clutch (11); the overrunning clutch (11) is used for automatically disconnecting the main reduction input shaft (5) and the upper belt wheel (4) when the engine (1) fails, so as to realize the autorotation and downslide of the helicopter.
8. The engine front unmanned helicopter transmission system according to claim 1, wherein a pair of second bearings (101) for supporting and transmitting the meshing force of gears are provided at the upper end of a large bevel gear (100) on the main rotor shaft (10); the big bevel gear (100) is connected with a transmission shaft of the main rotor shaft (10) by adopting a screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382051.1A CN114110107B (en) | 2021-11-19 | 2021-11-19 | Transmission system of unmanned helicopter with front-mounted engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382051.1A CN114110107B (en) | 2021-11-19 | 2021-11-19 | Transmission system of unmanned helicopter with front-mounted engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114110107A CN114110107A (en) | 2022-03-01 |
| CN114110107B true CN114110107B (en) | 2023-11-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111382051.1A Active CN114110107B (en) | 2021-11-19 | 2021-11-19 | Transmission system of unmanned helicopter with front-mounted engine |
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| Country | Link |
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| CN (1) | CN114110107B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116923753A (en) * | 2023-09-13 | 2023-10-24 | 四川腾盾科技有限公司 | Unmanned helicopter transmission system and use method |
| CN117803688B (en) * | 2024-02-29 | 2024-05-28 | 中国空气动力研究与发展中心低速空气动力研究所 | Belt transmission system with active tension control function |
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| CN209905075U (en) * | 2019-05-06 | 2020-01-07 | 杭州星际低空直升机开发有限公司 | Vertical front-end mechanism of engine of unmanned helicopter |
| CN210822785U (en) * | 2019-10-09 | 2020-06-23 | 北京中航智科技有限公司 | Unmanned aerial vehicle's generator flexible shock attenuation installation device |
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| CN214267982U (en) * | 2021-01-22 | 2021-09-24 | 河南坤宇无人机科技有限公司 | Double-engine unmanned aerial vehicle |
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2021
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|---|---|
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