CN113942655B - Light helicopter piston engine transmission system - Google Patents
Light helicopter piston engine transmission system Download PDFInfo
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- CN113942655B CN113942655B CN202111176172.0A CN202111176172A CN113942655B CN 113942655 B CN113942655 B CN 113942655B CN 202111176172 A CN202111176172 A CN 202111176172A CN 113942655 B CN113942655 B CN 113942655B
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 43
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 30
- 230000008878 coupling Effects 0.000 claims description 10
- 238000010168 coupling process Methods 0.000 claims description 10
- 238000005859 coupling reaction Methods 0.000 claims description 10
- 230000007246 mechanism Effects 0.000 description 10
- 238000009434 installation Methods 0.000 description 8
- 238000009423 ventilation Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 230000009467 reduction Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 3
- 238000002955 isolation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000012827 research and development Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000002572 peristaltic effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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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
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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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Devices For Conveying Motion By Means Of Endless Flexible Members (AREA)
Abstract
The application belongs to the technical field of helicopter transmission systems, and discloses a light helicopter piston engine transmission system. The piston engine is fixed on the machine body structure; an output shaft of the piston engine sequentially passes through the lower belt pulley and the lower bearing seat; the output flange of the piston engine, the lower belt pulley and the lower bearing seat flange are fixed through bolts; the lower belt pulley drives the upper belt pulley to rotate through the V-shaped belt; the upper belt pulley is fixed with the clutch shaft and drives the clutch shaft to rotate; one end of the clutch shaft is connected with the main speed reducer, and the main rotor wing is driven to rotate through the main speed reducer; the other end of the clutch shaft is connected with a tail speed reducer through a tail transmission shaft, and the tail rotor wing is driven to rotate through the tail speed reducer; the upper bearing seat is fixed on the clutch shaft and is positioned on the same side as the lower bearing seat; the upper bearing seat is connected with the lower bearing seat through the electric actuator, and the distance between the upper bearing seat and the lower bearing seat is adjusted by adjusting the length between the upper end and the lower end of the electric actuator, so that the distance between the upper belt wheel and the lower belt wheel is adjusted, and the tensioning degree of the V-shaped belt is controlled.
Description
Technical Field
The application belongs to the technical field of helicopter transmission systems, and particularly relates to a light helicopter piston engine transmission system.
Background
Because the market requires the unmanned helicopter to have low price, the unmanned helicopter generally adopts a piston engine, and the piston engine has the advantages of low price, low fuel consumption rate and the like, but has the defects of large volume, heavy weight, low power-weight ratio and the like, so the piston engine on the unmanned helicopter is generally arranged below a main speed reducer platform and needs to transmit power by adopting a parallel transmission belt assembly.
The helicopter generally adopts a high-speed piston engine, the output rotating speed is about 6000rpm, and a centrifugal clutch is adopted to realize the clutch function; but aviation high-speed piston engines in the general aviation market have few types and small power coverage range, and are difficult to meet the requirements of helicopter research and development.
The general aviation fixed-wing propeller aircraft has the advantages of low price, mature development, high reliability, multiple models and large power coverage range of the aviation low-speed piston engine, and can better meet the research and development power requirements of the unmanned aerial vehicle; however, the output speed of the aviation low-speed piston engine is low, generally about 2000rpm, if the mature low-speed piston engine adopts a centrifugal clutch technical route of the high-speed piston engine, the matched clutch weight is too large (for example, the ROTAX914 with the output speed of 2420 of 100 horsepower needs to be matched with the centrifugal clutch to be about 20 kg), the aviation low-speed piston engine is unacceptable for the whole engine, and the low-speed piston engine needs to adopt a new technical route to realize the clutch function.
A belt-driven transmission system typically matching a fixedly mounted low speed piston engine (about 2000 rpm) is shown in fig. 1 and 2; the belt mechanism includes a toothed spline engine shaft 1015, a pulley support and tensioner support 1009, an electric actuator and load limiting mechanism and line system 1013, an upper pulley 1011 and overrun clutch assembly 1007, a lower pulley 1014, a tensioner 1012, and a V-belt 1010.
The front end of the engine shaft 1015 is connected with the engine through a gear-sleeved spline, and the rear end is connected with the lower belt wheel shaft 1016; the lower pulley 1014 is sleeved on the lower pulley shaft 1016, and the lower pulley shaft 1016 is mounted on the pulley bracket and the tensioning pulley bracket 1009 through 2 bearings; the tensioner and its mounting shaft 1012 are also mounted on the pulley bracket and tensioner bracket 1009 by 2 bearings; an upper pulley 1011 and an overrunning clutch assembly 1007 are sleeved on an upper pulley shaft 1008, the upper pulley shaft 1008 being mounted on a pulley bracket and a tensioner bracket 1009 by 2 bearings; the upper belt wheel shaft 1008 is sleeved on the main speed reducer input gear shaft, namely, the whole belt transmission assembly 1003 is hung on the main speed reducer input shaft;
the V-belt 1010 is installed in V-grooves of the upper pulley 1011, the lower pulley 1014, and the tension pulley 1012; the length of the electric actuator is changed by stretching, the tension wheel 1012 is pulled by the load limiting mechanism and the wire system 1013 to rotate around a connecting shaft between the tension wheel bracket and the belt pulley bracket, the V-shaped belt 1010 is tensioned or loosened, the clutch function is realized, and the power transmission and separation are achieved; the starting clutch of the low-speed piston engine is ensured.
With the development of helicopter technology, the requirements on belt transmission components are higher and higher, so that the requirements on vibration isolation, vibration reduction, ventilation and heat dissipation of a piston engine are met, and the belt transmission system structure with the belt mechanism is also required to have high reliability, simple structure, flexible operation, light weight, easy processing, convenient installation and adjustment and good man-machine effect, and the requirements must be met, so that the belt transmission system structure with the belt mechanism is provided.
Disclosure of Invention
The purpose of the application is that: according to the application, through further research on the overall layout of the unmanned aerial vehicle and the vibration isolation and damping installation and adjustment modes of the engine, a new configuration scheme of a belt mechanism-containing transmission system which is matched with the fixed installation of a piston engine is provided for the first time in China, a lower belt wheel and a lower bearing support are installed on an output flange plate of the engine, and the lower end of an electric tensioning actuating device is connected with the lower bearing support; the upper belt wheel and the upper bearing support are assembled into a whole through an overrunning clutch shaft assembly, and are connected with the main speed reducer and the tail transmission shaft assembly through a laminated coupling; the electric tension actuating device stretches to change the length, so that the distance between the two belt wheels is adjusted; the purpose of realizing the aviation low-speed piston engine starting clutch function through belt tensioning and loosening is achieved, engine load starting is avoided, constant and accurate control of belt tension is realized through digital circuit technologies such as pressure sensors, feedback control and the like, meanwhile, the belt can be ensured to work in an optimal state, the service life of the belt is prolonged, the processing and installation adjustment requirements are reduced, the operation is flexible, the man-machine effect is good, and the maintenance is convenient.
The technical scheme of the application is as follows: a lightweight helicopter piston engine transmission system, said system comprising: the device comprises a piston engine, a lower belt pulley, an upper belt pulley, a V-shaped belt, a lower bearing seat, an electric actuator, an upper bearing seat, a clutch shaft, a main speed reducer, a tail transmission shaft and a tail speed reducer;
the piston engine is fixed on the machine body structure; an output shaft of the piston engine sequentially passes through the lower belt pulley and the lower bearing seat; the output flange of the piston engine, the lower belt pulley and the lower bearing seat flange are fixed through bolts;
the lower belt pulley drives the upper belt pulley to rotate through the V-shaped belt; the upper belt pulley is fixed with the clutch shaft and drives the clutch shaft to rotate; one end of the clutch shaft is connected with the main speed reducer, and the main rotor wing is driven to rotate through the main speed reducer; the other end of the clutch shaft is connected with a tail speed reducer through a tail transmission shaft, and the tail rotor wing is driven to rotate through the tail speed reducer;
the upper bearing seat is fixed on the clutch shaft and is positioned on the same side as the lower bearing seat; the upper bearing seat is connected with the lower bearing seat through the electric actuator, and the distance between the upper bearing seat and the lower bearing seat is adjusted by adjusting the length between the upper end and the lower end of the electric actuator, so that the distance between the upper belt wheel and the lower belt wheel is adjusted, and the tensioning degree of the V-shaped belt is controlled.
Further, the lower end of the electric actuator is connected with the upper end face of the lower bearing seat through a first bolt; the upper end of the electric actuator is connected with the lower end face of the upper bearing seat through a second bolt; the first bolt is perpendicular to the setting direction of the second bolt.
Further, the arrangement direction of the first bolt is parallel to the output shaft of the piston engine; the setting direction of the second bolt is perpendicular to the output shaft of the piston engine and perpendicular to the connecting line of the axes of the upper belt wheel and the lower belt wheel.
Further, a pressure sensor is arranged in the electric actuator, the pressure value between the upper end and the lower end of the electric actuator is fed back through the pressure sensor, and the friction force between the V-shaped belt and the upper belt wheel and the friction force between the V-shaped belt and the lower belt wheel are accurately controlled according to the pressure value, so that the output power is controlled.
Further, the upper belt pulley is connected with a clutch shaft through an overrunning clutch.
Further, the upper pulley is located at a clutch shaft midpoint.
Further, the two ends of the clutch shaft are connected with the main speed reducer and the tail transmission shaft through laminated couplings.
Further, a fan is further arranged on the lower bearing seat, and is driven to rotate by the output shaft of the piston engine to radiate heat for the transmission system.
Furthermore, the electric actuator is matched with the tensioning control box, adopts a digital circuit technology, has strong anti-interference capability and is suitable for the strong vibration severe environment of the helicopter; the voltage value of the pressure sensor is detected, the V-shaped belt is slightly worn away from the upper belt pulley and the lower belt pulley, when the actual tension of the belt is reduced due to slight peristaltic motion of a mechanical rotating structure of the electric actuator caused by strong vibration of the helicopter, the control box can give out a signal according to the calibrated pressure value, so that the electric actuator can elongate slightly in real time, the friction force between the V-shaped belt and the upper belt pulley and the friction force between the electric actuator and the lower belt pulley are accurately controlled, and the output power is controlled.
Further, when the electric actuator performs V-shaped belt tensioning adjustment calibration in helicopter assembly and belt disassembly and assembly, a belt tension frequency detector is matched, the actual tensioning degree of the V-shaped belt is directly measured, the error influence of the measuring and controlling process, the environment temperature and the like on the actual tensioning force of the belt is eliminated, and the pressure sensor and the tensioning control box are calibrated and checked regularly, so that the tensioning force of the V-shaped belt is accurately controlled, and the output power is controlled.
Advantageous effects
The application is suitable for the layout of a fixed low-speed piston engine, can dispense with a belt pulley bracket, a tensioning wheel, a bracket and a tensioning line system, reliably realizes the starting clutch function of the aviation low-speed piston engine, can realize ventilation and heat dissipation of the engine and a main speed reducer by additionally installing a ventilation fan, has proper load transmission and vibration reduction design, effectively isolates and reduces the vibration of the engine, and is matched with the vibration reduction design of the main speed reducer, so that the vibration level of the whole engine is lower, and the vibration of the whole engine is smaller than 0.1g through the actual measurement of the test flight test.
The transmission system with the belt mechanism of the new configuration has the advantages of simple structure, light weight, high reliability of clutch function and accurate control of belt tension load, can ensure the layout, ventilation, heat dissipation and vibration isolation and reduction of the whole machine, ensures that the belt works in an optimal state, prolongs the service life of the belt, reduces the requirements of processing, installation and adjustment, and has flexible operation, good man-machine effect and convenient maintenance.
Drawings
FIG. 1 is a front view of a conventional engine rear self-damped belt drive;
FIG. 2 is a side view of a conventional engine rear self-damped belt drive;
FIG. 3 is a front view of a light helicopter piston engine drive system of the present application;
FIG. 4 is a schematic diagram of the components of the transmission system of the light helicopter piston engine of the present application;
in the figure, the transmission comprises a 1-main speed reducer, a 2-main speed reducer input flange, a 3-laminated coupling, a 4-clutch shaft front flange, a 5-clutch shaft, a 6-upper belt wheel and overrun clutch assembly, a 7-clutch shaft rear flange, an 8-tail transmission shaft, a 9-laminated coupling, a 10-electric actuator, an 11-combined V-shaped belt, a 12-lower belt wheel, a 13-piston engine, a 14-upper bearing seat, a 15-upper bearing seat side pull rod, a 16-upper bearing seat and electric actuator connecting bolt, a 17-lower bearing seat and electric actuator connecting bolt, a 18-lower bearing seat, a 19-connecting bolt, a 20-lower bearing seat flange shaft and a 21-engine output flange.
Detailed Description
The application is further illustrated by the following embodiments:
the construction and installation of the transmission system is illustrated by taking the transmission system configuration scheme with a belt mechanism matched with the fixed installation of a piston engine in the engine as an example, compared with the traditional configuration transmission system, the transmission system of the light helicopter piston engine omits a belt pulley bracket, a tensioning pulley bracket, a tensioning steel rope, a pulley, a spring load limiting mechanism, installation connecting pieces of the pulley and spring load limiting mechanism and the like, and the transmission system comprises a 1-main speed reducer, a 2-main speed reducer input flange, a 3-laminated shaft coupling, a 4-clutch shaft front flange, a 5-clutch shaft, a 6-upper belt pulley and overrunning clutch assembly, a 7-clutch shaft rear flange, an 8-tail transmission shaft, a 9-laminated shaft coupling, a 10-electric actuator, a 11-combined V-shaped belt, a 12-lower belt pulley, a 13-piston engine, a 14-upper bearing seat, a 15-upper bearing seat side pull rod, a 16-upper bearing seat and electric actuator connecting bolt, a 17-lower bearing seat and electric actuator connecting bolt, a 18-lower bearing seat, a 19-connecting bolt, a 20-lower bearing seat flange shaft and a 21-engine output flange.
Fixedly mounted engine output flange 21 with lower pulley 12 and lower bearing blockFlangeThe shaft 20 is directly connected through the connecting bolt 19; lower bearing pedestalFlangeThe shaft 20 may be connected to a cooling fan to create a forward-to-aft ventilation cooling air flow to ensure ventilation cooling of the final drive and piston engine. Lower shaftThe bearing 18 is connected with the lower end of the electric actuator 10 through a bolt 17, and the bolt 17 is parallel to the output axis of the engine; the electric actuator 10 comprises a high-precision pressure sensor, a direct current motor, a planetary gear, a worm and gear assembly, a screw nut assembly, a limit position switch, a sleeve shell, an anti-torsion sheet and the like; the upper end of the electric actuator 10 is connected with the upper bearing seat 14 through a bolt 16, and the bolt 16 is perpendicular to the output axis of the engine and perpendicular to the connecting line of the axes of the upper belt wheel and the lower belt wheel; the lower bearing seat 18 and the upper bearing seat 14 are arranged at the rear sides of the lower belt pulley 12 and the upper belt pulley 6 and the 11-combined V-shaped belt; the upper bearing seat 14 is connected with the machine body structure through an upper bearing seat side pull rod 15, and two ends of the upper bearing seat side pull rod 15 are respectively provided with a joint bearing; the upper bearing seat 14 is connected with the clutch shaft 5 through a rolling bearing; the clutch shaft 5 is sleeved with an overrunning clutch, the clutch shaft 5 is connected with an upper belt pulley 6 through the overrunning clutch, the upper belt pulley 6 is positioned at the middle point of the clutch shaft, the clutch shaft 5 is connected with an input flange 2 of the main speed reducer 1 through a laminated coupling 3, and the clutch shaft 5 is connected with an input flange 7 of a tail transmission shaft 8 through a laminated coupling 9; the upper pulley and the overrunning clutch 6 are connected with the lower pulley 12 through a V-shaped band 11, and the V-shaped band 11 is matched with the V-shaped grooves of the upper pulley and the overrunning clutch 6 as well as the lower pulley 12.
The length is changed through the telescopic travel of the electric actuator 10, the upper bearing seat 14 and the upper belt pulley 6 are pulled to move up and down relative to the fixedly installed engine 13 and the lower belt pulley 12, the distance between the upper belt pulley 6 and the lower belt pulley 12 is changed, the tensioning and the releasing of the combined V-shaped belt 11 are realized, the power transmission and the separation are realized, and the clutch function of the engine is realized; the starting clutch of the low-speed piston engine is ensured. The upper belt pulley 6 and the overrunning clutch are sleeved on the clutch shaft 5, the small distance change between the upper belt pulley 6 and the working rotation axis of the upper belt pulley is realized by utilizing the length of the clutch shaft 5 and the angle compensation capability of the laminated shaft joints 3 and 9 on the two sides, the distance change between the upper belt pulley and the lower belt pulley is realized by the length change operation of the electric tensioning actuating device, the tensioning and loosening functions of a belt are realized, and the effect of power transmission clutch is realized. The upper end bearing rubber ring and the upper end rubber vibration reduction pad of the electric clutch device are designed to isolate and reduce the influence of engine vibration on the engine body and the main speed reducer; meanwhile, the laminated shaft coupling skillfully eliminates the influence of belt tension on the input shaft of the main speed reducer. The method realizes the goal of using the aviation low-output-speed high-torque piston engine on the helicopter in a simple, efficient and high-reliability manner through the combination of the measures.
When the engine is started, the electric tensioning actuating device is in a contracted state, the distance between the two belt wheels is short, and the belt is in a loose state and cannot transmit power. When the engine works normally, the electric tensioning actuating device is in a tensioning state, the distance between the two belt pulleys is long, the belt is in the tensioning state to realize a power transmission function, and the electric tensioning actuating device realizes constant and accurate control of the belt tension through a tensioning control box of digital circuit technologies such as a pressure sensor, feedback control and the like; when the helicopter assembly and the belt disassembly and assembly are used for carrying out V-shaped belt tensioning adjustment calibration, the pressure sensor and the tensioning control box are calibrated and checked regularly through the belt tension frequency detector, so that the error influence on the actual tensioning force of the belt in the measuring and controlling process, the ambient temperature and the like is eliminated; the side surface of the upper bearing seat is connected with the machine body structure through a knuckle bearing side pull rod, and the lower end of the electric actuator is connected with the upper end surface of the lower bearing seat through a first bolt; the upper end of the electric actuator is connected with the lower end face of the upper bearing seat through a second bolt; the first bolt is perpendicular to the setting direction of the second bolt. The arrangement direction of the first bolt is parallel to the output shaft of the piston engine; the setting direction of the second bolt is perpendicular to the output shaft of the piston engine and acts together with the axis connecting line of the upper belt pulley and the lower belt pulley, so that the upper belt pulley can realize the target of the movement track according to the expected design
See fig. 3 and 4.
The foregoing is merely a detailed description of the application, which is not a matter of routine skill in the art. However, the scope of the present application is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present application should be included in the scope of the present application. The protection scope of the present application shall be subject to the protection scope of the claims.
Claims (4)
1. A lightweight helicopter piston engine transmission system, said system comprising: the device comprises a piston engine, a lower belt pulley, an upper belt pulley, a V-shaped belt, a lower bearing seat, an electric actuator, an upper bearing seat, a clutch shaft, a main speed reducer, a tail transmission shaft and a tail speed reducer;
the piston engine is fixed on the machine body structure; an output shaft of the piston engine sequentially passes through the lower belt pulley and the lower bearing seat; the output flange of the piston engine, the lower belt pulley and the lower bearing seat flange are fixed through bolts;
the lower belt pulley drives the upper belt pulley to rotate through the V-shaped belt; the upper belt pulley is fixed with the clutch shaft and drives the clutch shaft to rotate; one end of the clutch shaft is connected with the main speed reducer, and the main rotor wing is driven to rotate through the main speed reducer; the other end of the clutch shaft is connected with a tail speed reducer through a tail transmission shaft, and the tail rotor wing is driven to rotate through the tail speed reducer;
the upper bearing seat is fixed on the clutch shaft and is positioned on the same side as the lower bearing seat; the upper bearing seat is connected with the lower bearing seat through an electric actuator, and the distance between the upper bearing seat and the lower bearing seat is adjusted by adjusting the length between the upper end and the lower end of the electric actuator, so that the distance between the upper belt wheel and the lower belt wheel is adjusted to control the tensioning degree of the V-shaped belt;
the lower end of the electric actuator is connected with the upper end face of the lower bearing seat through a first bolt; the upper end of the electric actuator is connected with the lower end face of the upper bearing seat through a second bolt; the arrangement direction of the first bolt is perpendicular to the arrangement direction of the second bolt, and the arrangement direction of the first bolt is parallel to the output shaft of the piston engine; the setting direction of the second bolt is vertical to the output shaft of the piston engine and vertical to the connecting line of the axes of the upper belt wheel and the lower belt wheel;
the pressure sensor is arranged in the electric actuator, the pressure value between the upper end and the lower end of the electric actuator is fed back through the pressure sensor, and the friction force between the V-shaped belt and the upper belt pulley and the lower belt pulley is accurately controlled according to the pressure value, so that the output power is controlled;
and a fan is further arranged on the lower bearing seat, and is driven to rotate by the output shaft of the piston engine to radiate heat for the transmission system.
2. The light helicopter piston engine transmission system of claim 1 wherein said upper pulley is connected to a clutch shaft by an overrunning clutch.
3. The light helicopter piston engine transmission system of claim 1 wherein said upper pulley is located at a clutch shaft midpoint.
4. A light helicopter piston engine transmission system according to claim 1 wherein said clutch shaft is connected at both ends to a final drive and a final drive shaft by means of a laminated coupling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111176172.0A CN113942655B (en) | 2021-10-09 | 2021-10-09 | Light helicopter piston engine transmission system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111176172.0A CN113942655B (en) | 2021-10-09 | 2021-10-09 | Light helicopter piston engine transmission system |
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| CN113942655A CN113942655A (en) | 2022-01-18 |
| CN113942655B true CN113942655B (en) | 2023-09-19 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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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| CN113942655A (en) | 2022-01-18 |
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