CN111765028B - Engine starting/power generation integrated device for small unmanned aerial vehicle - Google Patents
Engine starting/power generation integrated device for small unmanned aerial vehicle Download PDFInfo
- Publication number
- CN111765028B CN111765028B CN202010628039.3A CN202010628039A CN111765028B CN 111765028 B CN111765028 B CN 111765028B CN 202010628039 A CN202010628039 A CN 202010628039A CN 111765028 B CN111765028 B CN 111765028B
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- Prior art keywords
- engine
- generator
- starting
- rotating shaft
- integrated
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- 238000010248 power generation Methods 0.000 title claims abstract description 14
- 230000008878 coupling Effects 0.000 claims abstract description 27
- 238000010168 coupling process Methods 0.000 claims abstract description 27
- 238000005859 coupling reaction Methods 0.000 claims abstract description 27
- 238000004804 winding Methods 0.000 claims abstract description 15
- 230000005540 biological transmission Effects 0.000 description 4
- 230000010354 integration Effects 0.000 description 4
- 239000007858 starting material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
- F02N3/00—Other muscle-operated starting apparatus
- F02N3/02—Other muscle-operated starting apparatus having pull-cords
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
- H02K7/1807—Rotary generators
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention provides an engine starting/power generation integrated device for a small unmanned aerial vehicle, which is used for realizing the starting of an engine and maintaining the stable work of a power generator on the premise of occupying very low weight and comprises the following components: an engine 1; a fixed plate 11 connected to the body of the engine 1; a generator 12 fixed to the fixing plate 11; and a starting/coupling integrated part 6 which is provided with a generator end connecting hole 19 and an engine end connecting hole 16 which are coaxial. Wherein: the rotating shaft 5 of the engine is connected with the generator end connecting hole 19, the connecting hole 16 is connected with the rotating shaft 5, the integrated part 6 is connected with the rotating shaft platform 14 of the generator, so that the integrated part 6 is connected with the rotating shaft 15 of the generator and power is transmitted to the generator 12, the integrated part 6 is provided with a winding groove 26, and the pull wire 21 is wound on the winding groove 26, so that the engine is started by pulling the pull wire 21.
Description
Technical Field
The invention relates to an engine starting/generating integrated device in an engine power system,
belongs to the field of aviation design.
Background
The battery is most unmanned aerial vehicle's main power supply unit, however to unmanned aerial vehicle when overlength is voyaged, the duration of the unmanned aerial vehicle that the weight that a large amount of batteries brought can significantly reduce.
Disclosure of Invention
The inventor has recognized that in order to overcome the above problems of the prior art, it is necessary to consider the use of a generator instead of a battery to reduce the overall weight, but this requires a robust connection between the generator and the engine's drive shaft. The inventor further realizes that in order to avoid using a ground-attached starter and simplify the starting process of the unmanned aerial vehicle, a light and simple structure is required; the invention provides a light and simple structure, and the dragging starting of the engine can be realized only by a long rope.
The integrated engine starting and power generating device combining the characteristics has the characteristics of lightness, simplicity, reliable performance and the like, meets the convenient starting requirement of the unmanned aerial vehicle during long-term flight, and ensures that the unmanned aerial vehicle performs a flight task during ultra-long-term flight by stably connecting the generator and the engine rotating shaft.
For the ultra-long time-of-flight unmanned aerial vehicle, the weight reduction and the improvement of the utilization rate of the internal space of the aircraft are one of the factors for improving the endurance time of the unmanned aerial vehicle. The generator is necessary to get rid of a large amount of weight brought by the battery, but the installation of the generator usually brings extra weight and occupies a certain space. In addition, the cumbersome ground starter can reduce the ease of use of the drone if a starting system is not installed in the aircraft.
According to the engine starting/power generation integrated device, the mounting connection of the generator and the hand-pulling starting function of the engine are realized simultaneously on the premise of not obviously increasing the volume and the weight.
According to one aspect of the present invention, there is provided an integrated engine start/power generation device for a small unmanned aerial vehicle, comprising:
an engine for a vehicle, the engine having a motor,
a stationary plate connected to a body of the engine,
a generator fixed to the fixing plate,
a starting/coupling integrated part having a generator end connection hole and an engine end connection hole which are coaxial
Wherein:
the engine rotating shaft is connected with the generator end connecting hole,
the engine end connecting hole of the starting/coupling integrated component is connected with the engine rotating shaft,
the starting/coupling integrated component is matched and connected with the generator rotating shaft platform, thereby realizing the connection of the starting/coupling integrated component and the generator rotating shaft and the transmission of power to the generator,
the starting/coupling integrated member has a winding groove for winding a traction wire, for winding the traction wire onto the winding groove in the middle of the starting/coupling integrated member, thereby starting the engine by pulling the traction wire.
Drawings
FIG. 1 is an exploded perspective view of an integrated engine start/power generation apparatus according to one embodiment of the present invention.
Fig. 2 is a front exploded view of the integrated engine start/power generation apparatus of fig. 1.
Fig. 3 is an overall view of the integrated engine starting/generating apparatus of fig. 1.
Fig. 4 is a front view of the start/coupling integration part of fig. 1.
Fig. 5 is a left side view of the engine start/coupling integrated part of fig. 1.
FIG. 6 is a top view of the engine start/coupling integration component of FIG. 1.
FIG. 7 is an isometric view of the engine start/coupling integration component of FIG. 1.
FIG. 8 is a cross-sectional isometric view of an engine start/coupling integration component according to an embodiment of the invention taken in cross-section along a plane perpendicular to and passing through the axis of the set screw hole.
FIG. 9 is a cross-sectional view of an engine start/coupling integrated component taken in a plane perpendicular to the generator shaft platform and passing through the generator shaft axis, according to one embodiment of the present invention.
Fig. 10 is a schematic view of a fixing plate employed in the present invention.
FIG. 11 is a schematic diagram of a start-up process for an integrated engine start/power generation apparatus according to an embodiment of the present invention.
Detailed Description
The invention is mainly applied to small-sized long-endurance unmanned aerial vehicles. In order to achieve an ultra-long endurance, it is essential to consider the small-sized long-endurance drone to reduce the overall weight of the aircraft as much as possible.
Integral structure
The overall structure of the integrated engine starting/generating device according to one embodiment of the present invention is shown in fig. 1, 2, 3 and 10, in which a generator (12) is fixed to a fixed plate (11) by four mounting points (23), and the fixed plate (11) is connected to the body of an engine (1) by support columns (8, 9, 10). The generator rotating shaft (15) is inserted into a generator end connecting hole (19) of the starting/coupling integrated component (6), and an engine end connecting hole (16) of the starting/coupling integrated component (6) is connected to the engine rotating shaft (5).
Engine starting device
As shown in fig. 1, 2, 4, 5, 6, 7, and 8, the starting device of the starting/power generation integrated power device starts the engine by the engagement of the starting/coupling integrated member (6) and the traction wire (21). And winding the traction wire (21) on a winding groove (26) in the middle of the starting/coupling integrated component (6). The friction between the traction wire (21) and the winding groove (26) is greatly increased by the winding groove knurling (18). The engine is started by pulling the traction wire (21) in the traction direction (24) (see fig. 11). The engine rotating shaft (5) is attached with right spiral threads, the engine end connecting hole (19) is in threaded connection with the engine rotating shaft (5), and the threads are connected and screwed when the traction wire (21) is pulled.
Power transmission path of generator
The generator power transmission path of the starting/generating integrated power device is shown in fig. 1, fig. 2, fig. 4, fig. 5, fig. 6, fig. 7, fig. 8 and fig. 9, namely, the power of the engine rotating shaft (5) is transmitted by means of the threaded connection between the engine end connecting hole (16) and the engine rotating shaft, the starting/coupling integrated component (6) is matched with a rotating shaft platform (14) of the generator through a fastening screw (7), the connection between the starting/coupling integrated component (6) and the rotating shaft (15) of the generator is realized, and the power is transmitted to the generator (12). The fastening screw (7) is screwed into the fastening screw thread (20), and the upper end of the fastening screw hole (17) can enable the cup head of the fastening screw to sink into the fastening screw.
As shown in fig. 8 and 11, after the traction rope is wound as shown in the figure, the traction rope is quickly pulled along the traction direction, the coupler drives the engine to rotate along the rotation direction marked in the figure, and the engine is started. Meanwhile, the generator is connected with the rotating shaft of the engine through the starting/coupling integrated component and is driven to rotate to start generating electricity.
The advantages of the invention include:
1) by using the starting/coupling integrated component, the engine can be started in a hand-pulling mode, and meanwhile, the integrated device also plays a role in power transmission of the generator, so that the functions of hand-pulling starting and generator connection are realized in a very compact space.
2) The generator and the starter are far away from the main rotating shaft end of the engine, so that the starting is safer, and the equipment runs more reliably.
3) When the engine is started by only the hand-pulling starting device, the rotating shaft of the engine is of a cantilever stress structure. After the generator, the fixed plate and the support column are added, when the engine is started by hand, the rotating shaft of the engine is of a two-fulcrum stress structure, so that the stress condition of the rotating shaft of the engine is better.
Claims (5)
1. An engine start/power generation integrated device for a small unmanned aerial vehicle, characterized by comprising:
an engine (1) is provided,
a fixed plate (11) connected to a body of the engine (1),
a generator (12) fixed to the fixed plate (11),
a start/coupling integrated part (6) having a generator end connection hole (19) and an engine end connection hole (16) which are coaxial,
wherein:
the engine rotating shaft (5) is connected with a generator end connecting hole (19),
the engine end connecting hole (16) is connected with the engine rotating shaft (5),
the starting/coupling integrated component (6) is matched and connected with a generator rotating shaft platform (14), so that the starting/coupling integrated component (6) is connected with a generator rotating shaft (15) and power is transmitted to the generator (12),
the integrated starting/coupling member (6) has a winding groove (26) for winding the traction wire (21) on the winding groove (26) in the middle of the integrated starting/coupling member (6) to start the engine (1) by pulling the traction wire (21),
the engine end connecting hole (19) is in threaded connection with the engine rotating shaft (5), and the threaded connection is screwed when the traction wire (21) is pulled.
2. The integrated engine start/power generation device of claim 1, wherein:
the winding groove (26) is provided with knurling (18) for improving the friction force between the traction wire (21) and the winding groove (26).
3. The integrated engine start/power generation device of claim 1, wherein:
the starting/coupling integrated component (6) is matched and connected with a generator rotating shaft platform (14) through a fastening screw (7).
4. The integrated engine start/power generation device of claim 1, wherein:
the fixed plate (11) is connected to the body of the engine (1) by a plurality of support columns (8, 9, 10).
5. The integrated engine start/power generation device of claim 1, wherein:
the generator (12) is fixed to the fixed plate (11) by four mounting points (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010628039.3A CN111765028B (en) | 2020-07-01 | 2020-07-01 | Engine starting/power generation integrated device for small unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010628039.3A CN111765028B (en) | 2020-07-01 | 2020-07-01 | Engine starting/power generation integrated device for small unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111765028A CN111765028A (en) | 2020-10-13 |
| CN111765028B true CN111765028B (en) | 2021-08-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010628039.3A Expired - Fee Related CN111765028B (en) | 2020-07-01 | 2020-07-01 | Engine starting/power generation integrated device for small unmanned aerial vehicle |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113030606B (en) * | 2021-02-22 | 2022-05-03 | 中国人民解放军国防科技大学 | Spherical power source running test device |
| CN114320696A (en) * | 2021-12-29 | 2022-04-12 | 北京航空航天大学 | Hand-pulling starter for engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4331110A (en) * | 1976-11-09 | 1982-05-25 | Robinet Norman A | Priming and starting apparatus for engines |
| JP2003129925A (en) * | 2001-10-25 | 2003-05-08 | Fuji Heavy Ind Ltd | Forced air-cooled engine with recoil startor |
| JP2004173343A (en) * | 2002-11-18 | 2004-06-17 | Fuji Heavy Ind Ltd | Engine generator |
| CN201202529Y (en) * | 2008-05-23 | 2009-03-04 | 隆鑫工业有限公司 | Engine electric generator |
| CN208036624U (en) * | 2018-03-23 | 2018-11-02 | 中科灵动航空科技成都有限公司 | Rotor wing unmanned aerial vehicle electricity generation system |
| CN110382850A (en) * | 2017-04-04 | 2019-10-25 | 本田技研工业株式会社 | Engine system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8421257B2 (en) * | 2009-03-11 | 2013-04-16 | Dimitri Chernyshov | Tethered glider system for power generation |
| CN109733621B (en) * | 2018-12-17 | 2022-01-18 | 南京航空航天大学 | Hybrid unmanned aerial vehicle of many propulsion modes |
-
2020
- 2020-07-01 CN CN202010628039.3A patent/CN111765028B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4331110A (en) * | 1976-11-09 | 1982-05-25 | Robinet Norman A | Priming and starting apparatus for engines |
| JP2003129925A (en) * | 2001-10-25 | 2003-05-08 | Fuji Heavy Ind Ltd | Forced air-cooled engine with recoil startor |
| JP2004173343A (en) * | 2002-11-18 | 2004-06-17 | Fuji Heavy Ind Ltd | Engine generator |
| CN201202529Y (en) * | 2008-05-23 | 2009-03-04 | 隆鑫工业有限公司 | Engine electric generator |
| CN110382850A (en) * | 2017-04-04 | 2019-10-25 | 本田技研工业株式会社 | Engine system |
| CN208036624U (en) * | 2018-03-23 | 2018-11-02 | 中科灵动航空科技成都有限公司 | Rotor wing unmanned aerial vehicle electricity generation system |
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| CN111765028A (en) | 2020-10-13 |
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