CN114110107A - Transmission system of unmanned helicopter with front engine - Google Patents
Transmission system of unmanned helicopter with front engine Download PDFInfo
- Publication number
- CN114110107A CN114110107A CN202111382051.1A CN202111382051A CN114110107A CN 114110107 A CN114110107 A CN 114110107A CN 202111382051 A CN202111382051 A CN 202111382051A CN 114110107 A CN114110107 A CN 114110107A
- Authority
- CN
- China
- Prior art keywords
- shaft
- input shaft
- main
- tail
- transmission
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000005540 biological transmission Effects 0.000 title claims abstract description 66
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 21
- 238000013461 design Methods 0.000 abstract description 4
- 230000005484 gravity Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- 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
-
- B64D27/40—
-
- 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
-
- 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
-
- 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
Abstract
The invention belongs to the field of transmission system structure design, and particularly relates to a transmission system of an unmanned helicopter with a front engine. The transmission system comprises a lower belt wheel (2), a belt tensioning mechanism (3), an upper belt wheel (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 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 transmission system structure design, and particularly relates to a transmission system of an unmanned helicopter with a front engine.
Background
In light helicopters, the general layout mode of rear engine is generally adopted, the configuration mode is convenient for the arrangement of a transmission system, the engine firstly transmits power to a belt transmission device, and the belt transmission device respectively transmits power to a main speed reducer and a tail transmission shaft. However, in the unmanned helicopter, because a driver is not arranged at the head part, the rear gravity center of the whole helicopter is usually brought by the rear engine, in order to meet the requirement of the weight gravity center of the whole helicopter, the gravity center and the flight quality requirement can be met only by adding a balance weight at the head part, the weight of the whole helicopter is increased due to the addition of the balance weight, and the effective load capacity of a task is reduced.
One of the prior engines is that a power transmission shaft is adopted to transmit the power of the engine to a large 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 the advantages of complex structure, large occupied space, high weight cost and reduced effective load capacity of tasks; and the other scheme is a scheme of adopting a tail transmission shaft to detour, 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 as follows: the transmission system of the unmanned helicopter with the front engine is simple in structure and light in weight, and solves the problem of power transmission of the transmission system with the front engine.
The technical scheme of the invention is as follows: the transmission system comprises a lower belt wheel 2, a belt tensioning mechanism 3, an upper belt wheel 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 reducer input shaft 5, and the belt tensioning mechanism 3 is used for tensioning and contracting to drive the engine 1 to move up and down;
the engine 1 is in transmission connection with the lower belt wheel 2 and drives 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 a main reducer input shaft 5;
the main reducer input shaft 5 is in splined connection with a connecting shaft 6, the connecting shaft 6 is in splined connection with a tail transmission shaft 7, the tail transmission shaft 7 is in splined connection with a tail reducer input shaft 9, and the tail reducer input shaft 9 and a tail propeller shaft 8 are engaged and reversed by bevel gears; the tail rotor shaft 8 drives the tail rotor.
Further, the engine 1 is disposed at the front end of the unmanned helicopter.
Further, a small bevel gear on the main reducing input shaft 5 is meshed with a large bevel gear of the main rotor shaft, the main reducing 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 and gear mechanism and a lead screw nut mechanism 31 which are in transmission connection in sequence; the motor 30 reverses the rotating speed through the worm gear mechanism, and converts the rotating motion into the linear motion of the screw nut mechanism 31; the upper end of the screw nut mechanism 31 is connected to the main input shaft 5, and the lower end is connected to the engine case.
Further, the worm gear mechanism and the lead 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 the meshing force of the gears are provided on the left side of the bevel pinion 51 on the main input shaft 5.
Further, an overrunning clutch 11 is arranged on the upper belt wheel 4; the overrunning clutch is used for automatically separating the main reducing input shaft 5 from the upper belt wheel 4 when the engine 1 fails, so that the helicopter can autorotate and slide down.
Further, a pair of second bearings 101 for supporting and transmitting the meshing force of the 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 connected with the transmission shaft of the main rotor shaft 10 by screws.
The invention has the technical effects that: the engine is arranged in front, so that the problem of distribution of the weight center of the whole engine can be effectively solved. After the engine is preposed, power is directly transmitted to the tail transmission shaft by adding the connecting shaft, and the problem of power transmission route interference caused by the preposed engine is solved.
The invention provides a transmission system configuration which is simple in structure, low in weight cost and suitable for the front-end of an engine, and is used for solving the problem of power transmission of a helicopter.
Description of the drawings:
FIG. 1 is a schematic illustration of a transmission configuration.
The specific implementation mode is as follows:
the present invention is described in further detail below with reference to the attached drawings.
Referring to fig. 1, the present embodiment provides a transmission system of an unmanned helicopter with a front engine, where the transmission system includes a lower belt pulley 2, a belt tensioning mechanism 3, an upper belt pulley 4, a main reducing 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.
Wherein, the both ends of belt straining device 3 are connected with the casing and the main input shaft 5 that subtracts of engine 1 respectively, and the shrink motion drives engine 1 up-and-down motion through belt straining device 3 tensioning.
The engine 1 is in transmission connection with the lower belt wheel 2 and drives 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 a main reducer input shaft 5.
The small bevel gear on the main reducing input shaft 5 is meshed with the large bevel gear of the main rotor shaft, the main reducing input shaft 5 drives the main rotor shaft 10 to rotate, and the main rotor shaft drives the main rotor.
The main reducer input shaft 5 is in splined connection with a connecting shaft 6, the connecting shaft 6 is in splined connection with a tail transmission shaft 7, the tail transmission shaft 7 is in splined connection with a tail reducer input shaft 9, and the tail reducer input shaft 9 and a tail propeller shaft 8 are engaged and reversed by 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 distribution of the weight center of the whole helicopter is effectively solved.
In this embodiment, the belt tensioning mechanism 3 includes an electric motor 30, a worm gear mechanism and a lead screw nut mechanism 31 which are sequentially connected in a transmission manner; the motor 30 reverses the rotating speed through the worm gear mechanism, and converts the rotating motion into the linear motion of the screw nut mechanism 31; the upper end of the screw nut mechanism 31 is connected to the main input shaft 5, and the lower end is connected to the engine case. The worm gear mechanism and the lead 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, thereby achieving the disengagement and engagement of the engine 1 from the transmission.
In the present 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 are arranged at the upper end of a large bevel gear 100 on the main rotor shaft 10 and are used for supporting and transmitting the meshing force of the gears; the large bevel gear 100 is connected with the transmission shaft of the main rotor shaft 10 by screws. In the embodiment, 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 use of a bevel gear output structure, the bevel gear output structure is simple, the performance is reliable, the occupied space is greatly reduced, and the weight of a transmission system is reduced.
The work transfer process of this embodiment is: the lower belt wheel 2 transmits power and rotation speed to the upper belt wheel 4 through a transmission belt, and the tension of the belt is controlled through a belt tensioning mechanism 3. The upper belt wheel is fixedly connected with a main reducing input shaft 5, and the input shaft of the main reducing input shaft and the pinion 51 adopt an integrated design.
The pinion shaft 51 is mounted in a cantilever manner, and a pair of tapered roller bearings are provided on the left side thereof 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 big gear is connected with the main rotor shaft through a group of connecting pieces.
The bevel pinion transmits power to the main reduction input shaft through belt transmission, and the belt tensioning mechanism 3 controls the tensioning and loosening of the belt, so that the engine 1 is separated from and combined with the transmission. The upper belt wheel 4 is provided with an overrunning clutch 11; the overrunning clutch 11 is used for automatically separating the main reducing input shaft 5 from the upper belt wheel 4 when the engine 1 fails, so that the helicopter can autorotate and slide down.
On one hand, the main reduction input shaft is reversed and reduced through a pair of bevel gears, and then power is transmitted to the main rotor; on the other hand, the main input shaft transmits power to the tail transmission shaft assembly and the tail speed reducer, the tail speed reducer is reversed and accelerated through the pair of bevel gears, the power is transmitted to the tail rotor, and the tail rotor 9 is driven to rotate.
The invention is suitable for a light and small helicopter system with a front-mounted engine. The transmission system has 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 engine is characterized by comprising a lower belt wheel (2), a belt tensioning mechanism (3), an upper belt wheel (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 reducing input shaft (5), and the belt tensioning mechanism (3) is used for tensioning and contracting to drive the engine (1) to move up and down;
the engine (1) is in transmission connection with the lower belt wheel (2) and drives the lower belt wheel (2) to rotate;
the lower belt wheel (2) and the upper belt wheel (4) are in transmission through a belt, and the upper belt wheel (4) is fixedly connected with a main reducing input shaft (5);
a small bevel gear on the main reducing input shaft (5) is meshed with a large bevel gear of the main rotor shaft, the main reducing input shaft (5) drives the main rotor shaft (10) to rotate, and the main rotor shaft drives the main rotor;
the main reducer input shaft (5) is in splined connection with the connecting shaft (6), the connecting shaft (6) is in splined connection with the tail transmission shaft (7), the tail transmission shaft (7) is in splined connection with the tail reducer input shaft (9), and the tail reducer input shaft (9) and the tail propeller shaft (8) are engaged and reversed by adopting bevel gears; the tail rotor shaft (8) drives the tail rotor.
2. The transmission system of an unmanned helicopter with front engine according to claim 1, characterized in that the engine (1) is placed at the front end of the unmanned helicopter.
3. The transmission system of the unmanned helicopter with front engine as claimed in claim 1, characterized in that the belt tensioning mechanism (3) comprises an electric motor (30), a worm gear mechanism and a lead screw nut mechanism (31) which are in transmission connection in sequence; the motor (30) reverses the rotating speed through the worm gear mechanism, and converts the rotating motion into the linear motion of the screw and nut mechanism (31); the upper end of the screw nut mechanism (31) is connected with the main input shaft (5) and the lower end is connected with the engine shell.
4. The transmission system of the unmanned helicopter with front engine as claimed in claim 3, characterized in that the worm gear mechanism and the lead screw-nut mechanism (31) have a self-locking function.
5. The transmission system of the unmanned helicopter with front engine according to claim 3, characterized in that the bevel pinion on the main reducing input shaft (5) is designed integrally with the input shaft of the main reducing input shaft (5).
6. The transmission system of the unmanned helicopter with front engine according to claim 5, characterized in that 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.
7. The transmission system of the unmanned helicopter with front engine according to claim 1, characterized in that an overrunning clutch (11) is mounted on the upper pulley (4); the overrunning clutch (11) is used for automatically separating the main reducing input shaft (5) from the upper belt wheel (4) when the engine (1) fails, so that the helicopter can autorotate and slide downwards.
8. The transmission system of the unmanned helicopter with front engine as claimed in claim 1, characterized in that the upper end of the large bevel gear (100) on the main rotor shaft (10) is provided with a pair of second bearings (101) for supporting and transmitting the meshing force of the gears; the large bevel gear (100) is connected with a transmission shaft of the main rotor wing shaft (10) by screws.
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 true CN114110107A (en) | 2022-03-01 |
| CN114110107B CN114110107B (en) | 2023-11-07 |
Family
ID=80396914
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111382051.1A Active CN114110107B (en) | 2021-11-19 | 2021-11-19 | Transmission system of unmanned helicopter with front-mounted engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114110107B (en) |
Cited By (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 |
| CN117803688A (en) * | 2024-02-29 | 2024-04-02 | 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 |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5645250A (en) * | 1993-08-26 | 1997-07-08 | Gevers; David E. | Multi-purpose aircraft |
| US20080141921A1 (en) * | 2006-10-06 | 2008-06-19 | Mitja Victor Hinderks | Reciprocating devices |
| CN206171803U (en) * | 2016-08-24 | 2017-05-17 | 北京航景创新科技有限公司 | Unmanned helicopter |
| CN106697292A (en) * | 2017-01-23 | 2017-05-24 | 北京通用航空江西直升机有限公司 | Agricultural and forestal plant protection unmanned helicopter with large load capacity |
| CN109353526A (en) * | 2018-11-29 | 2019-02-19 | 吉林大学 | A kind of extended-range energy transfer mechanism for light-weight electric aircraft |
| CN109911218A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of multiple-input and multiple-output dynamical system and control method for rotary-wing aircraft |
| 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 |
| CN209905062U (en) * | 2019-05-06 | 2020-01-07 | 杭州星际低空直升机开发有限公司 | Automatic control mechanism 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 |
| EP3757014A1 (en) * | 2019-06-26 | 2020-12-30 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A thrust producing unit with a fail-safe electrical drive unit |
| CN113389864A (en) * | 2021-05-12 | 2021-09-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Composite propulsion helicopter transmission system |
| 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 |
-
2021
- 2021-11-19 CN CN202111382051.1A patent/CN114110107B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5645250A (en) * | 1993-08-26 | 1997-07-08 | Gevers; David E. | Multi-purpose aircraft |
| US20080141921A1 (en) * | 2006-10-06 | 2008-06-19 | Mitja Victor Hinderks | Reciprocating devices |
| CN206171803U (en) * | 2016-08-24 | 2017-05-17 | 北京航景创新科技有限公司 | Unmanned helicopter |
| CN106697292A (en) * | 2017-01-23 | 2017-05-24 | 北京通用航空江西直升机有限公司 | Agricultural and forestal plant protection unmanned helicopter with large load capacity |
| CN109353526A (en) * | 2018-11-29 | 2019-02-19 | 吉林大学 | A kind of extended-range energy transfer mechanism for light-weight electric aircraft |
| CN109911218A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of multiple-input and multiple-output dynamical system and control method for rotary-wing aircraft |
| 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 |
| CN209905062U (en) * | 2019-05-06 | 2020-01-07 | 杭州星际低空直升机开发有限公司 | Automatic control mechanism of unmanned helicopter |
| EP3757014A1 (en) * | 2019-06-26 | 2020-12-30 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A thrust producing unit with a fail-safe electrical drive unit |
| 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 |
| 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 |
| CN113389864A (en) * | 2021-05-12 | 2021-09-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Composite propulsion helicopter transmission system |
Cited By (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 |
| CN117803688A (en) * | 2024-02-29 | 2024-04-02 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114110107B (en) | 2023-11-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2359875C1 (en) | Reduction gear with separation of torque for rotary-wing aircraft with system of forward traction | |
| CN114110107A (en) | Transmission system of unmanned helicopter with front engine | |
| US3782223A (en) | Power transmission systems | |
| CN113389864A (en) | Composite propulsion helicopter transmission system | |
| CN105346712B (en) | Speed changing system of small single-rotor unmanned helicopter | |
| EP3038906B1 (en) | Light weight propulsor gearbox | |
| CN115681435A (en) | Light helicopter transmission device driven by synchronous belt | |
| CN113374611B (en) | Accessory transmission structure | |
| CN210102007U (en) | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing | |
| CN101561030A (en) | Reaction moment balance transmission system for single rotating motor | |
| CN201472663U (en) | Power propulsion propeller axis turning gear | |
| CN102431646A (en) | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft | |
| WO2019154369A1 (en) | Power system and unmanned helicopter | |
| CN104787346B (en) | A kind of electric drive main reducing gear | |
| CA2416479C (en) | Counter-rotating transmission | |
| CN109606701B (en) | Oil-electricity hybrid power matching method and system for rotary wing aircraft | |
| CN214493316U (en) | Manual-automatic integrated steering device and ship | |
| CN214900524U (en) | Coaxial line type driving motor assembly | |
| EP0023393B1 (en) | Freewheel devices | |
| CN111232228A (en) | Transmission mechanism of tandem double-rotor helicopter | |
| CN210240458U (en) | Coaxial planetary gear reducer | |
| CN210882570U (en) | Marine gearbox with auxiliary transmission case meeting PTO/PTI function | |
| WO2004097254A1 (en) | Dual stage differential speed transmission | |
| CN208749936U (en) | A kind of epicyclic gearing applied to MPV sliding door | |
| KR20110029763A (en) | Reducer for electric vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |