CN113460314A - Engine starting device for unmanned aerial vehicle and unmanned aerial vehicle power device - Google Patents
Engine starting device for unmanned aerial vehicle and unmanned aerial vehicle power device Download PDFInfo
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- CN113460314A CN113460314A CN202110718648.2A CN202110718648A CN113460314A CN 113460314 A CN113460314 A CN 113460314A CN 202110718648 A CN202110718648 A CN 202110718648A CN 113460314 A CN113460314 A CN 113460314A
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- engine
- unmanned aerial
- aerial vehicle
- starting device
- engine starting
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- 230000006698 induction Effects 0.000 claims description 13
- 230000035939 shock Effects 0.000 claims description 7
- 238000012544 monitoring process Methods 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 abstract description 16
- 230000007246 mechanism Effects 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
Images
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
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
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- 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
- F02N11/00—Starting of engines by means of electric motors
- F02N11/08—Circuits or control means specially adapted for starting of engines
- F02N11/0814—Circuits or control means specially adapted for starting of engines comprising means for controlling automatic idle-start-stop
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- 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
- F02N11/00—Starting of engines by means of electric motors
- F02N11/08—Circuits or control means specially adapted for starting of engines
- F02N11/0848—Circuits or control means specially adapted for starting of engines with means for detecting successful engine start, e.g. to stop starter actuation
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- 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
- F02N11/00—Starting of engines by means of electric motors
- F02N11/08—Circuits or control means specially adapted for starting of engines
- F02N11/087—Details of the switching means in starting circuits, e.g. relays or electronic switches
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
Compared with the prior art that the engine is indirectly driven by a mechanical mechanism to start, the engine starting device for the unmanned aerial vehicle provided by the embodiment of the invention can avoid an intermediate transmission device by adopting a direct driving mode, improves the transmission efficiency and simultaneously improves the reliability of the engine starting device.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to an engine starting device for an unmanned aerial vehicle and an unmanned aerial vehicle power device.
Background
The starting device of the existing piston engine for the unmanned aerial vehicle mostly adopts a starting motor to drive a mechanical mechanism to indirectly drive an engine to start, the mode has more connecting pieces, the transmission efficiency is lower, the transmission mechanism is mostly exposed, after long-time work, the starting device breaks down or even fails due to abrasion, foreign matters and the like, the reliability of the engine is seriously affected, the transmission mechanism is complex, the related part components are more, the maintainability is poor, and the reason for troubleshooting is difficult after the problem occurs.
Disclosure of Invention
The invention aims to provide an engine starting device for an unmanned aerial vehicle, which is used for solving the technical problems of poor reliability and low transmission efficiency of the engine starting device for the unmanned aerial vehicle in the prior art, which adopts a mechanical mechanism driven by a motor to indirectly drive an engine.
In order to achieve the purpose, the invention adopts the technical scheme that: provided is an engine starting device for an unmanned aerial vehicle, comprising:
the motor power output shaft of the motor is connected with the engine main shaft;
the connecting frame is fixed on the engine shell;
one end of the retainer integrated base plate is connected with the connecting frame, and the retainer integrated base plate is matched with the outside of the power output shaft of the motor through a bearing device;
the stator is arranged on the outer surface of the integrated bottom plate of the retainer in a surrounding manner;
the outer rotor shell assembly is arranged outside the stator in a surrounding mode, and one end of the outer rotor shell assembly is fixed on the retainer integrated base plate;
when the engine starting device works, the engine starting device directly drives the main shaft of the engine to rotate.
In one embodiment, the power output shaft of the motor and the main shaft of the engine are in an integrated structure.
In one embodiment, the engine starting device for the unmanned aerial vehicle further comprises a speed measuring part, the speed measuring part is used for measuring the rotation speed of the main shaft of the engine, the speed measuring part is electrically connected with the engine starting device, and the speed measuring part controls the engine starting device to work according to the measured value.
In one embodiment, the speed measuring part includes:
the infrared inductor is fixed on the outer rotor shell assembly;
the infrared reflection area is arranged on the main shaft of the engine, the infrared sensor is matched with the infrared reflection area for use, and when the main shaft of the engine rotates to a specific angle, the infrared sensor can just detect the infrared reflection area.
In one embodiment, the motor further comprises:
the connecting frame is fixed on the engine shell;
one end of the retainer integrated base plate is connected with the connecting frame, and the retainer integrated base plate is matched with the outside of the power output shaft of the motor through a bearing device;
the stator is arranged on the outer surface of the integrated bottom plate of the retainer in a surrounding manner;
and the outer rotor shell assembly is arranged outside the stator in a surrounding manner, and one end of the outer rotor shell assembly is fixed on the retainer integrated base plate.
In one embodiment, the retainer integrated base plate, the outer rotor housing assembly, and the connecting frame are all made of composite materials.
Another object of the present invention is to provide an unmanned aerial vehicle power device, including the engine starting device in any of the above embodiments, the unmanned aerial vehicle power device including:
an engine body;
the engine mounting seat is arranged at the bottom of the engine body and used for fixing the engine body to the unmanned aerial vehicle;
the air propeller is arranged at the end part of the main shaft of the engine body;
the engine starting device is arranged on the main shaft of the engine body.
In one embodiment, the unmanned aerial vehicle power device further comprises an engine shock pad, and the engine shock pad is arranged on the surface of the engine mounting seat matched with the unmanned aerial vehicle.
In one embodiment, the engine starting device further comprises an induction control part, the induction control part is arranged on the engine starting device and used for monitoring the rotating speed of the air propeller, and when the air propeller is greatly reduced under the condition of non-manual control, the induction control part controls the engine starting device to work.
One or more technical solutions described above in the embodiments of the present invention have at least the following technical effects or advantages:
compared with the prior art that the engine is indirectly driven to start by a mechanical mechanism, the engine starting device for the unmanned aerial vehicle provided by the embodiment of the invention can avoid an intermediate transmission device by adopting a direct driving mode, improves the transmission efficiency and simultaneously improves the reliability of the engine starting device.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic structural diagram of an engine starting device for an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a speed measuring unit according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an unmanned aerial vehicle power plant provided in an embodiment of the present invention.
Wherein the respective reference numerals are as follows:
1. an engine starting device for an unmanned aerial vehicle; 2. an engine body; 3. an engine mount; 4. an air propeller; 5. an engine cushion; 11. a motor power output shaft; 12. a connecting frame; 13. a holder integrated base plate; 14. a stator; 15. an outer rotor housing assembly; 16. a bearing; 17. a speed measuring section; 21. an engine main shaft; 171. an infrared sensor; 172. an infrared reflective region.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Referring to fig. 1, an engine starting device 1 for an unmanned aerial vehicle according to an embodiment of the present application includes a motor power output shaft 11, a connecting frame 12, a retainer integrated base plate 13, a stator 14, and an outer rotor housing assembly 15. The motor power output shaft 11 is connected with the engine main shaft 21, and the axes of the motor power output shaft and the engine main shaft are overlapped. The attachment bracket 12 is fixed to the engine housing and the attachment bracket 12 is used to secure the engine starting device to the engine. One end of the retainer integrated base plate 13 is connected with the connecting frame 12, and the retainer integrated base plate 13 is matched with the outside of the power output shaft 11 of the motor through a bearing 16 device. The stator 14 is disposed around the outer surface of the holder integrated base plate 13. The outer rotor housing assembly 15 is disposed around the outside of the stator 14, and one end of the outer rotor housing assembly 15 is fixed to the holder integrated base plate 13. When the engine starting device is operated, the engine starting device directly drives the main engine shaft 21 to rotate. When the engine starting device 1 for the unmanned aerial vehicle is electrified, the motor power output shaft 11 starts to rotate and drives the engine main shaft 21 connected with the motor power output shaft, so that the engine main shaft 21 rotates along with the motor power output shaft, and starting of the engine of the unmanned aerial vehicle is achieved.
Compared with the traditional mode of indirectly driving the engine spindle 21 by the motor to start, the engine starting device 1 for the unmanned aerial vehicle provided by the embodiment has no other redundant transmission mechanisms, so that the whole structure is more compact, and the weight is lighter. And because the power take-off shaft of the engine starting device is directly connected with the engine main shaft 21 to directly drive the engine main shaft 21, the power generated by the engine starting device can be transmitted to the engine main shaft 21 to the maximum extent, and no other transmission devices consume energy in the transmission process, so that the transmission efficiency is higher. In addition, since the power output shaft (the motor power output shaft 11) of the engine starting device 1 for the unmanned aerial vehicle provided by the embodiment is connected with the engine main shaft 21, the phenomenon that the transmission fails due to corrosion and rusting caused by exposure of the transmission in the traditional indirect driving mode does not exist, and the stability of the engine starting device 1 for the unmanned aerial vehicle is further higher.
In one embodiment, the motor power output shaft 11 and the engine main shaft 21 are of an integral structure, and the motor power output shaft 11 and the engine main shaft 21 can be regarded as the same shaft. By arranging the motor power output shaft 11 and the engine main shaft 21 into an integrated structure, the motor power output shaft 11 and the engine main shaft 21 are connected without other structures, so that the transmission efficiency is improved to the maximum extent, and the functional stability of the engine starting device 1 for the unmanned aerial vehicle is improved.
In one embodiment, the engine starting device 1 for the unmanned aerial vehicle further includes a speed measuring unit 17, the speed measuring unit 17 is configured to measure a rotation speed of the engine spindle 21, the speed measuring unit 17 is electrically connected to the engine starting device, and the speed measuring unit 17 controls the engine starting device to operate according to the measured value. By arranging the speed measuring part 17 on the engine starting device, when the engine starting device drives the engine spindle 21 to rotate, and the speed measuring part 17 detects that the rotating speed of the engine spindle 21 reaches a preset speed, the detection part controls the motor in the engine starting device to be powered off, so that the operation of the engine starting device is automatically stopped, and the motor in the engine starting device cannot block the high-speed rotation of the engine spindle 21.
Referring to fig. 2, in an embodiment, the speed measuring unit 17 includes an infrared sensor 171 and an infrared reflection area 172. The infrared inductor 171 is fixed to the outer rotor case assembly 15. The infrared reflection area 172 is arranged on the engine spindle 21, the infrared sensor 171 is used in cooperation with the infrared reflection area 172, when the engine spindle 21 rotates to a specific angle, the infrared sensor 171 can just detect the infrared reflection area 172, that is, every time the engine spindle 21 rotates for one circle, the infrared sensor 171 can receive a reflection signal, and the infrared sensor 171 calculates the number of revolutions of the engine spindle 21 in unit time by recording the number of times of the reflection signal received in unit time, so as to obtain the revolution speed of the engine spindle 21.
In one embodiment, cage integrated base plate 13, outer rotor housing assembly 15, and connecting frame 12 are all made of a composite material. Make holder integral type bottom plate 13, external rotor housing subassembly 15 and link 12 all through adopting combined material for engine starting drive reduces self weight when satisfying sufficient intensity requirement by a wide margin, and then lightens unmanned aerial vehicle's complete machine weight, improves unmanned aerial vehicle's flight load capacity.
Referring to fig. 3, another object of the present invention is to provide an unmanned aerial vehicle power device, which includes the engine starting device in any of the above embodiments, and the unmanned aerial vehicle power device includes an engine body 2, an engine mounting base 3, an air propeller 4, and an engine starting device. Engine mount pad 3 sets up in the bottom of engine body 2, and engine mount pad 3 is used for fixing engine body 2 to unmanned aerial vehicle on. The air screw 4 is provided at a main shaft end portion of the engine body 2. The engine starting device is provided on the main shaft of the engine body 2. Preferably, unmanned aerial vehicle power device still includes engine shock pad 5, and engine shock pad 5 sets up on engine mount pad 3 and unmanned aerial vehicle matched with face, and engine shock pad 5 can reduce the influence that engine vibration gave unmanned aerial vehicle flight by a wide margin.
In one embodiment, the system further comprises an induction control part, the induction control part is arranged on the engine starting device and used for monitoring the rotating speed of the air propeller 4, and when the air propeller 4 is greatly reduced under the condition of non-artificial control, the induction control part controls the engine starting device to work, wherein the induction control part can adopt a structure similar to the speed measuring part 17. When the engine of unmanned aerial vehicle breaks down and leads to the engine can't give 4 sufficient whirling powers of air screw and maintain unmanned aerial vehicle flight, the rotational speed of engine main shaft 21 descends this moment, and when the rotational speed of engine main shaft 21 dropped to the early warning value (specific size can be set for according to the in service behavior), the control of induction control portion was crossed the monitoring and is found engine main shaft 21 rotational speed and low excessively, judged that unmanned aerial vehicle's engine is in abnormal state. At this time, the induction control unit controls the engine starting device to start operation, and positions the rotation of the engine main shaft 21 and the air screw propeller 4 in a short time, thereby preventing the unmanned aerial vehicle from falling down due to engine failure. The engine starting device provided by the invention adopts a mode of directly connecting with the engine main shaft 21, so that the rotating power generated by the engine starting device can be almost completely transmitted to the engine main shaft 21 and the air propeller 4 (at the moment, the traditional engine starting device adopting indirect drive can not maintain the flight of the unmanned aerial vehicle due to low transmission efficiency), and further the unmanned aerial vehicle can land relatively stably under the maintenance of the engine starting device, and the flight safety of the unmanned aerial vehicle is improved.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. An engine starting device for an unmanned aerial vehicle, characterized by comprising:
the motor power output shaft of the motor is connected with the engine main shaft;
when the engine starting device works, the engine starting device directly drives the main shaft of the engine to rotate.
2. The engine starting device for the unmanned aerial vehicle according to claim 1, characterized in that:
the power output shaft of the motor and the main shaft of the engine adopt an integrated structure.
3. The engine starting device for the unmanned aerial vehicle according to claim 1, characterized in that:
the engine starting device for the unmanned aerial vehicle further comprises a speed measuring part, wherein the speed measuring part is used for measuring the rotating speed of the main shaft of the engine, the speed measuring part is electrically connected with the engine starting device, and the speed measuring part controls the engine starting device to work according to a measured value.
4. The engine starting device for the unmanned aerial vehicle as claimed in claim 3, wherein the speed measuring unit includes:
the infrared inductor is fixed on the outer rotor shell assembly;
the infrared reflection area is arranged on the main shaft of the engine, the infrared sensor is matched with the infrared reflection area for use, and when the main shaft of the engine rotates to a specific angle, the infrared sensor can just detect the infrared reflection area.
5. The engine starting device for the unmanned aerial vehicle as claimed in claim 1, wherein the motor further comprises:
the connecting frame is fixed on the engine shell;
one end of the retainer integrated base plate is connected with the connecting frame, and the retainer integrated base plate is matched with the outside of the power output shaft of the motor through a bearing device;
the stator is arranged on the outer surface of the integrated bottom plate of the retainer in a surrounding manner;
and the outer rotor shell assembly is arranged outside the stator in a surrounding manner, and one end of the outer rotor shell assembly is fixed on the retainer integrated base plate.
6. The engine starting device for the unmanned aerial vehicle according to claim 5, wherein:
the retainer integrated base plate, the outer rotor shell assembly and the connecting frame are all made of composite materials.
7. An unmanned aerial vehicle power plant comprising an engine starting apparatus as claimed in any one of claims 1 to 6, wherein the unmanned aerial vehicle power plant comprises:
an engine body;
the engine mounting seat is arranged at the bottom of the engine body and used for fixing the engine body to the unmanned aerial vehicle;
the air propeller is arranged at the end part of the main shaft of the engine body;
the engine starting device is arranged on the main shaft of the engine body.
8. An unmanned aerial vehicle power plant of claim 7, characterized in that:
unmanned aerial vehicle power device still includes the engine shock pad, the engine shock pad set up in on engine mount pad and unmanned aerial vehicle matched with face.
9. An unmanned aerial vehicle power plant of claim 7, characterized in that:
still include the induction control portion, the induction control portion set up in on the engine starting drive, the induction control portion is used for monitoring the slew velocity of air screw, when the air screw appears reducing by a wide margin under the condition of non-artificial control, the control of induction control portion makes engine starting drive work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110718648.2A CN113460314A (en) | 2021-06-28 | 2021-06-28 | Engine starting device for unmanned aerial vehicle and unmanned aerial vehicle power device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110718648.2A CN113460314A (en) | 2021-06-28 | 2021-06-28 | Engine starting device for unmanned aerial vehicle and unmanned aerial vehicle power device |
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| Publication Number | Publication Date |
|---|---|
| CN113460314A true CN113460314A (en) | 2021-10-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110718648.2A Pending CN113460314A (en) | 2021-06-28 | 2021-06-28 | Engine starting device for unmanned aerial vehicle and unmanned aerial vehicle power device |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2239895A1 (en) * | 1995-12-08 | 1997-06-19 | Magnet-Motor Gesellschaft Fur Magnetmotorische Technik Mbh | Motor vehicle with electrical generator |
| CN205190100U (en) * | 2015-12-07 | 2016-04-27 | 唐建军 | Motorcycle engine electricity starting drive |
| CN207384836U (en) * | 2017-07-25 | 2018-05-22 | 青岛欧森系统技术有限公司 | A kind of easy engine model electric starter |
| CN110562446A (en) * | 2019-09-16 | 2019-12-13 | 中国人民解放军总参谋部第六十研究所 | Engine auxiliary starting device for helicopter |
| CN110963051A (en) * | 2019-12-10 | 2020-04-07 | 中国空气动力研究与发展中心 | Starting integrated oil-electricity hybrid power system with speed reduction gear ring outer rotor |
| CN210971555U (en) * | 2019-09-30 | 2020-07-10 | 珠海天晴航空航天科技有限公司 | Starting and power generating device of unmanned aerial vehicle |
| US20200277072A1 (en) * | 2018-12-20 | 2020-09-03 | Airbus Helicopters | Method for assisting a single-engine rotorcraft during an engine failure |
| CN111746806A (en) * | 2020-06-15 | 2020-10-09 | 西安爱生技术集团公司 | Unmanned aerial vehicle inspiring system and integrated control method |
-
2021
- 2021-06-28 CN CN202110718648.2A patent/CN113460314A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2239895A1 (en) * | 1995-12-08 | 1997-06-19 | Magnet-Motor Gesellschaft Fur Magnetmotorische Technik Mbh | Motor vehicle with electrical generator |
| CN205190100U (en) * | 2015-12-07 | 2016-04-27 | 唐建军 | Motorcycle engine electricity starting drive |
| CN207384836U (en) * | 2017-07-25 | 2018-05-22 | 青岛欧森系统技术有限公司 | A kind of easy engine model electric starter |
| US20200277072A1 (en) * | 2018-12-20 | 2020-09-03 | Airbus Helicopters | Method for assisting a single-engine rotorcraft during an engine failure |
| CN110562446A (en) * | 2019-09-16 | 2019-12-13 | 中国人民解放军总参谋部第六十研究所 | Engine auxiliary starting device for helicopter |
| CN210971555U (en) * | 2019-09-30 | 2020-07-10 | 珠海天晴航空航天科技有限公司 | Starting and power generating device of unmanned aerial vehicle |
| CN110963051A (en) * | 2019-12-10 | 2020-04-07 | 中国空气动力研究与发展中心 | Starting integrated oil-electricity hybrid power system with speed reduction gear ring outer rotor |
| CN111746806A (en) * | 2020-06-15 | 2020-10-09 | 西安爱生技术集团公司 | Unmanned aerial vehicle inspiring system and integrated control method |
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