CN110562446A - Engine auxiliary starting device for helicopter - Google Patents
Engine auxiliary starting device for helicopter Download PDFInfo
- Publication number
- CN110562446A CN110562446A CN201910872183.9A CN201910872183A CN110562446A CN 110562446 A CN110562446 A CN 110562446A CN 201910872183 A CN201910872183 A CN 201910872183A CN 110562446 A CN110562446 A CN 110562446A
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- engine
- belt wheel
- motor
- starting
- starting device
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- 230000001360 synchronised effect Effects 0.000 claims abstract description 25
- 239000002131 composite material Substances 0.000 claims abstract description 18
- 239000003638 chemical reducing agent Substances 0.000 claims description 11
- 239000003999 initiator Substances 0.000 claims description 4
- 238000009434 installation Methods 0.000 abstract description 6
- 238000012423 maintenance Methods 0.000 abstract description 3
- 239000007858 starting material Substances 0.000 description 5
- 230000000977 initiatory effect Effects 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention relates to an auxiliary starting device of an engine, which is used for assisting the starting of the engine which is difficult to start with load, the auxiliary starting device is connected with a rotor main shaft through a synchronous belt, the auxiliary starting device comprises a starting integrated motor, a motor belt pulley and a composite belt pulley, the motor belt pulley is arranged on an output shaft of the starting integrated motor, and the motor belt pulley is connected with the composite belt pulley through a wedge-shaped belt; the composite belt wheel is arranged on an output shaft of the engine, and an overrunning clutch is arranged between the output shaft of the engine and the composite belt wheel. Compared with the prior art, the starting device firstly utilizes the starting integrated motor to start the rotor main shaft in advance, then the engine is driven, and for the engine, the step of starting the rotor main shaft by utilizing the engine is omitted, so that a clutch device is not required to be additionally arranged, the overall maintenance quality of the airplane is firstly lightened, and the device has low requirement on installation space and strong adaptability.
Description
Technical Field
The invention relates to a mode for starting an engine in an auxiliary mode, which is used for starting the engine which cannot be started with a load in the auxiliary mode, in particular to a piston type or rotor type engine which is loaded on a helicopter in the auxiliary mode.
Background
Due to the advantage of fuel economy, piston or rotor engines are widely applied in the field of small and light helicopters. Because the engine is difficult to start and directly drive the helicopter rotor to rotate at the same time, a set of clutch device is designed between the engine and the rotor, and the clutch device can be a mature clutch (such as a centrifugal clutch, an electromagnetic clutch, a hydraulic clutch and the like), or a belt tightness driving device, such as a device for driving a tensioning steering wheel to change the position to realize the tightness of a driving belt, or a device for directly changing the axle distance between an output pulley of the engine and a driven pulley.
It is believed that piston or rotor engines will be widely used in small and light helicopters for a relatively long time in the future, and the need to achieve clutching between the engine and the load will exist for a relatively long time. There are some drawbacks to the various current clutching schemes.
The mode that directly changes the wheel base between engine output belt pulley and the driven pulley can reduce clutch's structural weight, but has the hoist and mount of engine complicated, the drive steering wheel has the defect such as reliability hidden danger, and what be worse is that this kind of scheme makes to have longer time relative slip between belt and the belt pulley, makes belt or belt pulley wearing and tearing serious, very big increase the use risk and inspect and maintain the burden. The device for driving the tensioning steering wheel to change the position to achieve tightness of the driving belt can effectively simplify installation of the engine, but reliability hidden danger of the tensioning driving motor is not reduced at all, use risk and inspection and maintenance burden are not improved due to relative sliding for a long time, and even worse, the device can also increase structural weight and has higher requirements on installation space.
the problem of belt and pulley wear is fundamentally solved by the clutch effecting engine to load clutching, but it appears to be more problematic than it is. Centrifugal clutches are the most attractive option in such a scheme, but the centrifugal clutches are heavy due to the low rotation speed of the helicopter rotor, so that the overall flight efficiency of the helicopter is affected by the unreasonable weight increase of the helicopter.
Disclosure of Invention
The invention aims to integrate the requirements from the overall consideration of the helicopter, assisting the engine start in a light, simple, reliable and safe way.
The invention is realized by the following technical means: an engine auxiliary starting device for a helicopter is connected with a rotor main shaft through a synchronous belt and comprises an initiation integrated motor, a motor belt wheel and a composite belt wheel, wherein the motor belt wheel is arranged on an output shaft of the initiation integrated motor, and the motor belt wheel is connected with the composite belt wheel through a wedge-shaped belt;
The composite belt wheel is arranged on an output shaft of the engine, and an overrunning clutch is arranged between the output shaft of the engine and the composite belt wheel.
The auxiliary starting device is arranged on the support, the support comprises a support frame and an initiator motor mounting frame, the support frame and the initiator motor mounting frame are arranged perpendicular to each other, a synchronous belt wheel is arranged at the top of the support frame, the synchronous belt wheel is connected with a rotor main shaft, and synchronous belts are arranged on the synchronous belt wheel and the motor belt wheel for connection and driving;
The mounting frame of the starting motor is provided with a mounting groove for mounting the starting integrated motor and the composite belt wheel.
Still include main reducer, synchronous pulley sets up on main reducer's input shaft, and main reducer's output connects the rotor main shaft.
compared with the prior art, the starting device firstly utilizes the starting integrated motor to start the rotor main shaft in advance, then the engine is driven, and for the engine, the step of starting the rotor main shaft by utilizing the engine is omitted, so that a clutch device is not required to be additionally arranged, the overall maintenance quality of the airplane is firstly lightened, and the device has low requirement on installation space and strong adaptability.
Drawings
FIG. 1 is a schematic representation of the invention in a helicopter application;
FIG. 2 is a detailed schematic diagram of an engine assisted starting apparatus;
Fig. 3 is a partial sectional view of the engine auxiliary starting apparatus.
Reference numbers in the figures: 1. auxiliary starting device, 2, hold-in range, 3, driven synchronous pulley, 4, support frame, 5, main reducer, 6, rotor main shaft, 7, engine output shaft interface, 8, the motor mounting bracket of initiating, 9, the integrative motor of initiating, 10, motor band pulley, 11, wedge area, 12, compound band pulley, 13, freewheel clutch.
Detailed Description
The invention and its application to helicopters are explained in further detail below:
the invention relates to an auxiliary starting device of an engine, in particular to a device for auxiliary starting of a piston type or rotor type engine used on a light and small helicopter. The helicopter rotor main shaft driving device is arranged on a set of conventional driving device, namely a support is arranged, a belt wheel and a driven synchronous belt wheel 3 are arranged on the support, the driven synchronous belt wheel 3 directly drives a rotor main shaft 6 of a helicopter, an engine output shaft interface 7 is arranged on the belt wheel, the belt wheel and the driven synchronous belt wheel 3 are connected through a synchronous belt 2, the engine directly drives the belt wheel to rotate, then the driven synchronous belt wheel 3 is driven to operate, the operation of the synchronous belt wheel drives the rotor main shaft 6 to operate, and therefore the operation of the helicopter is achieved.
The invention is provided with a set of auxiliary starting device on the basis of the original driving device, and meanwhile, the invention carries out some improvements on the original conventional driving device. The auxiliary starting device and the belt wheel are arranged at the same height, specifically, the auxiliary starting device comprises a starting integrated motor 9, a motor belt wheel 10 is arranged on an output shaft of the starting integrated motor 9, and the motor belt wheel and the belt wheel are connected through a wedge-shaped belt 11;
In the invention, the belt wheel is a composite belt wheel 12, the composite belt wheel is arranged on an output shaft of an engine, and an overrunning clutch is arranged between the output shaft of the engine and the composite belt wheel.
Further, the support includes support frame 4 and starter motor mounting bracket, support frame 4 sets up with starter motor mounting bracket mutually perpendicular, at the top of support frame 4, sets up synchronous pulley 3 be provided with the mounting groove of installing starter motor 9 and the compound band pulley 12 of installation on the starter motor mounting bracket.
the wind power generator further comprises a main speed reducer 5, the synchronous belt wheel 3 is arranged on an input shaft of the main speed reducer 5, and an output part of the main speed reducer 5 is connected with a rotor spindle 6.
The invention is described in detail below by means of specific examples:
The piston type or rotor type engine is usually difficult to drive the helicopter rotor to start, the invention adopts the starting integral motor 9 to drive the composite belt wheel 12 through the wedge-shaped belt 11, and then drives the driven synchronous belt wheel 3 to rotate through the synchronous belt 2, thereby realizing the purpose of driving the rotor to rotate in advance, and keeping the rotating speed of the rotor at the rotating speed of the rotor slightly higher than the idling rotating speed of the engine, thereby realizing the purpose of no-load starting of the engine under the driving of the starting motor of the engine. After the engine is kept at the idling speed for several seconds, the engine can enter the working speed according to a set program, and the starting and starting integrated motor 9 is driven to be switched to a generator mode at proper time. When the starter motor 9 drives the compound pulley 12, the engine is not driven to rotate due to the action of the overrunning clutch 13.
The auxiliary starting device of the engine has high reliability. Firstly, the starting integrated motor 9 is adopted to slowly start the rotor to a preset rotating speed, and then the engine is gradually used for driving the rotor, so that the impact on the blades and the main speed reducer is very small in the whole process; secondly, no relative friction mode is adopted in the whole transmission path to transmit load, so that the wear is smaller; thirdly, the tension of the synchronous belt 2 is offset by the support frame 4, so that no additional load is generated on the machine body by the tension of the synchronous belt 2; in addition, the installation mode of the engine is simpler after the auxiliary starting device is applied, and the reliability of the system is further improved to a certain extent; finally, because the engine still keeps the original starting motor, the starting load is small, and the starting motor can be completely changed into another starting integrated motor to be used as a backup of the starting integrated motor 9, so that the power supply of the whole engine is effectively ensured to be more reliable.
The auxiliary starting device of the engine has high safety. Firstly, the system has high reliability, and secondly, if the engine stops due to a fault at high altitude, the system can continuously generate electricity by utilizing self-sliding, ensure the necessary onboard system to work normally, and even allow a plurality of attempts to start the engine.
The auxiliary starting device of the engine has lighter structural weight, and a part of weight is saved due to the fact that a clutch or a steering wheel and a driving mechanism thereof are eliminated; secondly, after primary speed increasing, the rotating speed of the integral motor 9 is greatly improved, and the weight of the integral motor is greatly reduced; thirdly, the scheme reduces the load of part of the machine body structure, thereby being beneficial to reducing the structural weight of the machine body; finally, the two respectively independent starting integrated motors ensure the power utilization safety of the whole helicopter, and even if the engine stops, the starting integrated motor 9 still has certain power generation capacity, so that the capacity of a standby battery of the helicopter can be properly reduced, and the weight of the standby battery is effectively reduced.
Claims (3)
1. the utility model provides an engine auxiliary starting device for helicopter, auxiliary starting device passes through the hold-in range with the rotor main shaft and is connected its characterized in that: the auxiliary starting device comprises a starting integrated motor, a motor belt wheel and a composite belt wheel, wherein the motor belt wheel is arranged on an output shaft of the starting integrated motor, and the motor belt wheel is connected with the composite belt wheel through a wedge-shaped belt;
the composite belt wheel is arranged on an output shaft of the engine, and an overrunning clutch is arranged between the output shaft of the engine and the composite belt wheel.
2. the engine starting aid device according to claim 1, characterized in that: the auxiliary starting device is arranged on the support, the support comprises a support frame and an initiator motor mounting frame, the support frame and the initiator motor mounting frame are arranged perpendicular to each other, a synchronous belt wheel is arranged at the top of the support frame, the synchronous belt wheel is connected with a rotor main shaft, and synchronous belts are arranged on the synchronous belt wheel and the motor belt wheel for connection and driving;
The mounting frame of the starting motor is provided with a mounting groove for mounting the starting integrated motor and the composite belt wheel.
3. the engine starting aid device according to claim 1, characterized in that: still include main reducer, synchronous pulley sets up on main reducer's input shaft, and main reducer's output connects the rotor main shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910872183.9A CN110562446A (en) | 2019-09-16 | 2019-09-16 | Engine auxiliary starting device for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910872183.9A CN110562446A (en) | 2019-09-16 | 2019-09-16 | Engine auxiliary starting device for helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110562446A true CN110562446A (en) | 2019-12-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910872183.9A Pending CN110562446A (en) | 2019-09-16 | 2019-09-16 | Engine auxiliary starting device for helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110562446A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113460314A (en) * | 2021-06-28 | 2021-10-01 | 江西壮龙无人机科技有限公司 | Engine starting device for unmanned aerial vehicle and unmanned aerial vehicle power device |
| CN113942655A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Light-duty helicopter piston sender transmission system |
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105492276A (en) * | 2013-09-13 | 2016-04-13 | 加特可株式会社 | Controller for hybrid vehicle |
| CN106927037A (en) * | 2017-03-27 | 2017-07-07 | 必扬星环（北京）航空科技有限公司 | A kind of export structure using the depopulated helicopter engine for surmounting one-way clutch |
| 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 |
| CN209324573U (en) * | 2018-12-22 | 2019-08-30 | 辽宁壮龙无人机科技有限公司 | A kind of preposition electric starter of novel unmanned vehicle engine |
| CN210942242U (en) * | 2019-09-16 | 2020-07-07 | 中国人民解放军总参谋部第六十研究所 | Engine auxiliary starting device for helicopter |
-
2019
- 2019-09-16 CN CN201910872183.9A patent/CN110562446A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105492276A (en) * | 2013-09-13 | 2016-04-13 | 加特可株式会社 | Controller for hybrid vehicle |
| CN106927037A (en) * | 2017-03-27 | 2017-07-07 | 必扬星环（北京）航空科技有限公司 | A kind of export structure using the depopulated helicopter engine for surmounting one-way clutch |
| CN209324573U (en) * | 2018-12-22 | 2019-08-30 | 辽宁壮龙无人机科技有限公司 | A kind of preposition electric starter of novel unmanned vehicle engine |
| 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 |
| CN210942242U (en) * | 2019-09-16 | 2020-07-07 | 中国人民解放军总参谋部第六十研究所 | Engine auxiliary starting device for helicopter |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113460314A (en) * | 2021-06-28 | 2021-10-01 | 江西壮龙无人机科技有限公司 | Engine starting device for unmanned aerial vehicle and unmanned aerial vehicle power device |
| CN113942655A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Light-duty helicopter piston sender transmission system |
| CN113942655B (en) * | 2021-10-09 | 2023-09-19 | 中国直升机设计研究所 | Light helicopter piston engine transmission system |
| 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 |
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