CN219821781U - Hybrid unmanned aerial vehicle power system based on brushless motor - Google Patents
Hybrid unmanned aerial vehicle power system based on brushless motor Download PDFInfo
- Publication number
- CN219821781U CN219821781U CN202321117990.8U CN202321117990U CN219821781U CN 219821781 U CN219821781 U CN 219821781U CN 202321117990 U CN202321117990 U CN 202321117990U CN 219821781 U CN219821781 U CN 219821781U
- Authority
- CN
- China
- Prior art keywords
- brushless motor
- engine
- sensorless
- motor
- electrically connected
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000001939 inductive effect Effects 0.000 claims abstract description 74
- 239000000446 fuel Substances 0.000 claims abstract description 56
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 8
- 230000001105 regulatory effect Effects 0.000 abstract description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 3
- 229910052744 lithium Inorganic materials 0.000 description 3
- 230000001360 synchronised effect Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 238000005070 sampling Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
Landscapes
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The utility model discloses a hybrid unmanned aerial vehicle power system based on a brushless motor. The utility model uses the coaxial direct-drive direct-connection matching design of the propeller, the engine and the inductive brushless motor, and has simple, reliable and durable structure and extremely high power ratio, wherein the fuel engine and the inductive brushless motor are matched to form the oil-electricity hybrid system, the inductive brushless motor can start the engine and convert redundant power into electric energy to charge the storage battery to charge the inductive brushless motor, the torque mixed into the engine can be changed through the matching regulation and control of direct-current harmonic rectification, so that the rotating speed of the propeller can be accurately regulated and controlled, a three-purpose engine is formed, the engines with different discharge capacities can be matched with the inductive brushless motor with corresponding power, the matching of different powers can be used for unmanned aerial vehicles with different models and multi-rotor aircraft, and the matching of the engines with different powers and the inductive brushless motor can be combined to different accurate control and speed regulation range.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicles and aircrafts, and particularly relates to a hybrid unmanned aerial vehicle power system based on a brushless motor.
Background
Unmanned aerial vehicles ("UAVs") are unmanned aerial vehicles that are operated by means of radio remote control devices and self-contained programmed control devices;
referring to an "unmanned aerial vehicle power system" with an authorized patent number of CN209080172U, the unmanned aerial vehicle power system in this patent includes at least one fuel supply unit, at least one fuel cell power supply module, at least one lithium cell power supply module, at least one system control module, at least one circuit adjusting unit and at least one unmanned aerial vehicle power source, wherein the output end of the fuel supply unit is connected with the fuel cell power supply module, the output end of the fuel cell power supply module is connected with the circuit adjusting unit, the output end of the circuit adjusting unit is respectively connected with the lithium cell power supply module and the unmanned aerial vehicle power source, and two ends of the system control module are respectively connected with a voltage and current sampling point of the fuel cell power supply module and a voltage and current sampling point of the lithium cell power supply module;
however, when the present inventors embodied this device, the following drawbacks were found to exist:
1. the unmanned aerial vehicle provided by the patent is too single in starting mode, cannot form a composite efficient starting application, and lacks a stable starting setting for corresponding mixing adjustment; the starter is in an idle state after the engine is started, so that the dead weight of the unmanned aerial vehicle is increased, and the multipurpose of the unmanned aerial vehicle cannot be achieved;
2. the lack of a loop charging circuit design cannot realize the recycling of redundant power in the starting process of the unmanned aerial vehicle, and the reverse storage battery is charged, so that the endurance application performance is reduced;
3. the combination of a plurality of engines cannot more accurately adjust the required accurate rotation speed among the propellers;
there is therefore a need to propose a new solution to the above problems.
Disclosure of Invention
Accordingly, it is necessary to provide a brushless motor-based hybrid unmanned aerial vehicle power system, which has the beneficial effects.
In order to solve the technical problems, the utility model is realized by the following technical scheme:
the utility model provides a hybrid unmanned aerial vehicle power system based on brushless motor, includes the flight control, still includes battery, current control module, rotational speed control module, first brushless motor hybrid starting module and second brushless motor hybrid starting module, battery and current control module electric connection, battery and rotational speed control module electric connection, the battery is through current control module and rotational speed control module respectively with first brushless motor hybrid starting module and second brushless motor hybrid starting module connection.
Further, the current control module comprises a boost module, a first direct current regulator, a first rectifying element, a second direct current regulator and a second rectifying element, the output end of the battery is electrically connected with the boost module, the output end of the boost module is respectively electrically connected with the second direct current regulator and the first direct current regulator, the second direct current regulator is electrically connected with the second rectifying element, and the first direct current regulator is electrically connected with the first rectifying element.
Further, the rotation speed control module comprises a second sensorless electric adjuster, a first Hall element, a first sensorless electric adjuster and a second Hall element, wherein the second sensorless electric adjuster is electrically connected with the battery and the first sensorless electric adjuster, the first Hall element is arranged on one side of the second sensorless electric adjuster, and the second Hall element is arranged on one side of the first sensorless electric adjuster.
Further, the first brushless motor mixed starting module comprises a second inductive brushless motor, a second fuel engine and a second propeller, the top end of the second inductive brushless motor is fixedly connected with the second fuel engine, the top end of the second fuel engine is fixedly connected with the second propeller, one side of the second fuel engine is fixedly connected with a second engine throttle, the second inductive brushless motor and the second rectifying element are electrically connected with the second inductive brushless motor, and the first Hall element is electrically connected with the second inductive brushless motor.
Further, the second brushless motor mixed starting module comprises a first inductive brushless motor, a first fuel engine and a first propeller, wherein the top end of the first inductive brushless motor is fixedly connected with the first fuel engine, the top end of the first fuel engine is fixedly connected with the first propeller, one side of the first fuel engine is fixedly connected with a first engine throttle, the first inductive brushless motor and the first inductive brushless motor are electrically connected with the second inductive brushless motor, and the second Hall element is electrically connected with the first inductive brushless motor.
Further, one end fixedly connected with of first inductive brushless motor adjusts the steering wheel, it is connected with first engine throttle to adjust the steering wheel, it is used for controlling the degree of opening of first engine throttle to adjust the steering wheel, be connected through the gangbar between first engine throttle and the second engine throttle, the gangbar is used for transmitting the degree of adjustment of first engine throttle to the second engine throttle.
Further, the second inductive brushless electric device and the second rectifying element are both electrically connected with the flight control device, and the first inductive brushless electric device and the first rectifying element are both electrically connected with the flight control device.
Further, a one-key starting switch is further connected between the battery and the first inductive brushless motor and between the battery and the second inductive brushless motor.
Compared with the prior art, the utility model has the beneficial effects that:
(1) The utility model uses the coaxial direct-drive direct-connection matching design of the propeller, the engine and the inductive brushless motor, and has simple, reliable and durable structure and extremely high power ratio, wherein the fuel engine and the inductive brushless motor are matched to form the oil-electricity hybrid system, the inductive brushless motor can start the engine and convert redundant power into electric energy to charge the storage battery to charge the inductive brushless motor, the torque mixed into the engine can be changed through the matching regulation and control of direct-current harmonic rectification, so that the rotating speed of the propeller can be accurately regulated and controlled, a three-purpose engine is formed, the engines with different discharge capacities can be matched with the inductive brushless motor with corresponding power, the matching of different powers can be used for unmanned aerial vehicles with different models and multi-rotor aircraft, and the matching of the engines with different powers and the inductive brushless motor can be combined to different accurate control and speed regulation range.
(2) The utility model further discloses a matching design of the inductive brushless electric motor, the Hall element and the inductive brushless motor, thereby achieving the better control requirement of the rotation speed ratio.
(3) The utility model provides two different starting modes, one of which is to directly guide a battery to a brush permanent magnet motor for starting and match with synchronous starting of an engine, namely a one-key starting mode, and the other is to send a control command by a remote controller for starting a direct current brush electric regulator, so that a better application effect and a stable remote control starting mode are formed.
(4) Through the design and application of the electronic module, the problems of mixed regulation, starting, charging and operation conflict during time can be effectively solved, some useful energy conversion is realized, different starting and charging synchronous applications can be integrally formed, and therefore the recovery and charging of redundant power are realized, the charging module can be utilized to carry out damping regulation and control on the propeller, and the power energy is further saved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed for the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the overall structure of the present utility model.
In the drawings, the list of components represented by the various numbers is as follows:
1. a battery; 2. a boost module; 3. a first sensorless brushless electric tuning; 4. a second sensorless brushless electric tuning; 5. a first hall element; 6. a second Hall element; 7. a first sensorless brushless motor; 8. a second sensorless brushless motor; 9. a first fuel engine; 10. a second fuel engine; 11. a first engine throttle; 12. a second engine throttle; 13. a linkage rod; 14. adjusting a steering engine; 15. a first propeller; 16. a second propeller; 17. a first direct current regulator; 18. a second direct current regulator; 19. a first rectifying element; 20. and a second rectifying element.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1, a hybrid unmanned aerial vehicle power system based on brushless motor, including flying the accuse, still include battery 1, current control module, rotational speed control module, first brushless motor hybrid starting module and second brushless motor hybrid starting module, battery 1 and current control module electric connection, battery 1 and rotational speed control module electric connection, battery 1 is through current control module and rotational speed control module with first brushless motor hybrid starting module and second brushless motor hybrid starting module connection respectively.
The current control module comprises a boost module 2, a first direct current regulator 17, a first rectifying element 19, a second direct current regulator 18 and a second rectifying element 20, wherein the output end of the battery 1 is electrically connected with the boost module 2, the output end of the boost module 2 is respectively electrically connected with the second direct current regulator 18 and the first direct current regulator 17, the second direct current regulator 18 is electrically connected with the second rectifying element 20, and the first direct current regulator 17 is electrically connected with the first rectifying element 19.
The rotating speed control module comprises a second sensorless electric adjuster 4, a first Hall element 5, a first sensorless electric adjuster 3 and a second Hall element 6, wherein the second sensorless electric adjuster 4 is electrically connected with the battery 1 and the first sensorless electric adjuster 3 is electrically connected with the battery 1, the first Hall element 5 is arranged on one side of the second sensorless electric adjuster 4, and the second Hall element 6 is arranged on one side of the first sensorless electric adjuster 3.
The first brushless motor hybrid starting module comprises a second inductive brushless motor 8, a second fuel engine 10 and a second propeller 16, wherein the top end of the second inductive brushless motor 8 is fixedly connected with the second fuel engine 10, the top end of the second fuel engine 10 is fixedly connected with the second propeller 16, one side of the second fuel engine 10 is fixedly connected with a second engine throttle 12, the second inductive brushless motor 4 and the second rectifying element 20 are electrically connected with the second inductive brushless motor 8, and the first Hall element 5 is electrically connected with the second inductive brushless motor 8.
The second brushless motor mixed starting module comprises a first inductive brushless motor 7, a first fuel motor 9 and a first propeller 15, wherein the top end of the first inductive brushless motor 7 is fixedly connected with the first fuel motor 9, the top end of the first fuel motor 9 is fixedly connected with the first propeller 15, one side of the first fuel motor 9 is fixedly connected with a first engine throttle 11, the first inductive brushless motor 3 and the first inductive brushless motor 7 are electrically connected with the second inductive brushless motor 8, and the second Hall element 6 and the first inductive brushless motor 7 are electrically connected.
One end fixedly connected with of first inductive brushless motor 7 adjusts steering wheel 14, adjusts steering wheel 14 and first engine throttle 11 and is connected, adjusts steering wheel 14 and is used for controlling the degree of opening of first engine throttle 11, is connected through gangbar 13 between first engine throttle 11 and the second engine throttle 12, and gangbar 13 is used for transmitting the degree of adjustment of first engine throttle 11 to second engine throttle 12.
The second inductive brushless electric regulator 4 and the second rectifying element 20 are electrically connected in a flight control manner, and the first inductive brushless electric regulator 3 and the first rectifying element 19 are electrically connected in a flight control manner.
A one-key start switch is also connected between the battery 1 and the first inductive brushless motor 7 and between the battery 1 and the second inductive brushless motor 8.
In different embodiments, it is necessary to provide a corresponding frame of the aircraft or the unmanned aerial vehicle, so as to facilitate the system to be carried, and provide a corresponding oil tank in the frame, and connect the oil tank with the second fuel engine 10 and the first fuel engine 11 through the oil guide pipe, so as to facilitate the oil supply to the first fuel engine 11 and the second fuel engine 10.
Because the second inductive brushless motor 8 is in coaxial direct-connection transmission connection with the second fuel engine 10, the second inductive brushless motor 8 is used for starting the second fuel engine 10 and generating electric energy and outputting the electric energy under the driving of the second fuel engine 10 when the second inductive brushless motor 8 works, and is in an electric state as a whole when the second fuel engine 10 is in insufficient power, the second inductive brushless motor 8 is used for outputting power and providing auxiliary power for the second fuel engine 10;
because the first inductive brushless motor 7 is in coaxial direct-connection transmission connection with the first fuel engine 9, the first inductive brushless motor 7 is used for starting the first fuel engine 9, generating electric energy under the drive of the first fuel engine 9 and outputting the electric energy when the first inductive brushless motor 7 works, and is in an electric state as a whole when the first fuel engine 9 is insufficient in power, the power output is carried out through the first inductive brushless motor 7, and auxiliary power is provided for the first fuel engine 9;
in the first electric state, when the second sensorless motor 8 is required to accelerate, the dc voltage regulator connected to the second sensorless motor 8 is operated, the second rectifying element 20 and the second dc voltage regulator 18 connected to the second sensorless motor 8 are turned off, the first rectifying element 19 and the first dc voltage regulator 17 connected to the first sensorless motor 7 are turned on, the quick charge mode is realized, and simultaneously, the first sensorless motor 7 generates a damping action on the first fuel engine 9 when the power generation output is performed, so that the rotation speed of the first fuel engine 9 is reduced, the reverse speed regulation is realized, and when the first sensorless motor 7 is required to start and accelerate, the first dc voltage regulator 17 is turned off, the second dc voltage regulator 18 is turned on, and the first rectifying element 19 is turned off, so that the second rectifying element 20 is turned on.
The second sensorless motor 8 generates power to reduce the rotation speed of the second fuel engine 10.
When neither the second and first brushless inductive motors 8, 7 accelerate the mixing, both the second and first rectifying elements 20, 19 are turned on in the slow charge mode, so that both the second and first brushless inductive motors 8, 7 are in the slow charge power generation mode.
When the second inductive brushless motor 8 and the first inductive brushless motor 7 need to accelerate mixing, the direct current is fully turned on, and the second rectifying element 20 and the first rectifying element 19 are turned off;
in a specific charging method, the second inductive brushless motor 8 and the first inductive brushless motor 7 are inductive brushless motors, and when the second inductive brushless motor 8 and the first inductive brushless motor 7 are driven to rotate by the second fuel engine 10 and the first fuel engine 9, a back electromotive force generated can generate a voltage which rises along with the rising of the rotating speed, and the battery 1 is charged through the cooperation of the second rectifying element 20 and the first rectifying element 19.
In an electric speed regulation state, when the rotation speed of the second propeller 16 is to be changed, the second inductive brushless motor 8 is started to provide auxiliary power for the second fuel engine 10;
through flight control, a remote controller can be adopted in different embodiments, the control and adjustment steering engine 14 drives the first engine throttle 11 to adjust, the first engine throttle 11 drives the first fuel engine 9 to start, the linkage rod 13 transfers the adjustment of the first engine throttle 11 to the second engine throttle 12, and the second engine throttle 12 is controlled to drive the first fuel engine 9 to start in cooperation with the first torque provided for the second propeller 16 and the first propeller 15, so that the synchronous output power is realized;
and the rotation speeds of the second inductive brushless motor 8 and the first inductive brushless motor 7 are controlled by matching the second inductive brushless motor 4 and the first inductive brushless motor 3, and the output power of the second inductive brushless motor 8 and the first inductive brushless motor 7 is inserted into the rotation speed of the second propeller 16 and the rotation speed of the first propeller 15, so that the fine adjustment of the rotation speeds of the two propellers is completed.
In the description of the present specification, the descriptions of the terms "one embodiment," "example," "specific example," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present utility model. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the utility model disclosed above are intended only to assist in the explanation of the utility model. The preferred embodiments are not exhaustive or to limit the utility model to the precise form disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the utility model and the practical application, to thereby enable others skilled in the art to best understand and utilize the utility model. The utility model is limited only by the claims and the full scope and equivalents thereof.
Claims (8)
1. The utility model provides a hybrid unmanned aerial vehicle power system based on brushless motor, includes the accuse, and its characterized in that still includes battery (1), current control module, rotational speed control module, first brushless motor hybrid starting module and second brushless motor hybrid starting module, battery (1) and current control module electric connection, battery (1) and rotational speed control module electric connection, battery (1) are through current control module and rotational speed control module and first brushless motor hybrid starting module and second brushless motor hybrid starting module connection respectively.
2. The brushless motor-based hybrid unmanned aerial vehicle power system according to claim 1, wherein the current control module comprises a boost module (2), a first direct current regulator (17), a first rectifying element (19), a second direct current regulator (18) and a second rectifying element (20), the output end of the battery (1) is electrically connected with the boost module (2), the output end of the boost module (2) is electrically connected with the second direct current regulator (18) and the first direct current regulator (17) respectively, the second direct current regulator (18) is electrically connected with the second rectifying element (20), and the first direct current regulator (17) is electrically connected with the first rectifying element (19).
3. The brushless motor-based hybrid unmanned aerial vehicle power system according to claim 2, wherein the rotation speed control module comprises a second sensorless electric regulator (4), a first hall element (5), a first sensorless electric regulator (3) and a second hall element (6), the second sensorless electric regulator (4) is electrically connected with the battery (1) and the first sensorless electric regulator (3) is electrically connected with the battery (1), the first hall element (5) is arranged on one side of the second sensorless electric regulator (4), and the second hall element (6) is arranged on one side of the first sensorless electric regulator (3).
4. A brushless motor-based hybrid unmanned aerial vehicle power system according to claim 3, wherein the first brushless motor hybrid starting module comprises a second sensorless motor (8), a second fuel engine (10) and a second propeller (16), the top end of the second sensorless motor (8) is fixedly connected with the second fuel engine (10), the top end of the second fuel engine (10) is fixedly connected with the second propeller (16), one side of the second fuel engine (10) is fixedly connected with a second engine throttle (12), the second sensorless motor (4) and the second rectifying element (20) are electrically connected with the second sensorless motor (8), and the first hall element (5) is electrically connected with the second sensorless motor (8).
5. The brushless motor-based hybrid unmanned aerial vehicle power system according to claim 4, wherein the second brushless motor hybrid starting module comprises a first sensorless motor (7), a first fuel engine (9) and a first propeller (15), the top end of the first sensorless motor (7) is fixedly connected with the first fuel engine (9), the top end of the first fuel engine (9) is fixedly connected with the first propeller (15), one side of the first fuel engine (9) is fixedly connected with a first engine throttle (11), the first sensorless electric regulator (3) and the first sensorless motor (7) are electrically connected with the second sensorless motor (8), and the second hall element (6) is electrically connected with the first sensorless motor (7).
6. The brushless motor-based hybrid unmanned aerial vehicle power system according to claim 5, wherein one end of the first sensorless motor (7) is fixedly connected with an adjusting steering engine (14), the adjusting steering engine (14) is connected with the first engine throttle (11), the adjusting steering engine (14) is used for controlling the opening degree of the first engine throttle (11), the first engine throttle (11) is connected with the second engine throttle (12) through a linkage rod (13), and the linkage rod (13) is used for transmitting the adjustment degree of the first engine throttle (11) to the second engine throttle (12).
7. The brushless motor-based hybrid unmanned aerial vehicle power system according to claim 6, wherein the second inductive brushless motor (4) and the second rectifying element (20) are electrically connected to the flight control, and the first inductive brushless motor (3) and the first rectifying element (19) are electrically connected to the flight control.
8. The brushless motor-based hybrid unmanned aerial vehicle power system according to claim 7, wherein a one-key start switch is further interposed between the battery (1) and the first inductive brushless motor (7) and between the battery (1) and the second inductive brushless motor (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321117990.8U CN219821781U (en) | 2023-05-11 | 2023-05-11 | Hybrid unmanned aerial vehicle power system based on brushless motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321117990.8U CN219821781U (en) | 2023-05-11 | 2023-05-11 | Hybrid unmanned aerial vehicle power system based on brushless motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219821781U true CN219821781U (en) | 2023-10-13 |
Family
ID=88248384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321117990.8U Active CN219821781U (en) | 2023-05-11 | 2023-05-11 | Hybrid unmanned aerial vehicle power system based on brushless motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219821781U (en) |
-
2023
- 2023-05-11 CN CN202321117990.8U patent/CN219821781U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP2019519414A (en) | Hybrid power source drone | |
| US8409052B2 (en) | Starting method for hybrid electric vehicle and system architecture of hybrid electric vehicle | |
| CN109733621B (en) | Hybrid unmanned aerial vehicle of many propulsion modes | |
| CN109094790A (en) | A kind of the power configuration scheme and control method of the hybrid power system for helicopter | |
| CN102490584A (en) | Series-parallel combined type hybrid power assembly | |
| CN212501058U (en) | High-speed hybrid unmanned aerial vehicle | |
| CN112810822A (en) | Aviation aircraft with initiation integration function and control method thereof | |
| JPH05176420A (en) | Electric drive unit for automobile and said unit-loaded automobile | |
| CN204316269U (en) | The integrated apparatus of starting on mixed electrical automobile, generating, power-assisted | |
| CN219821781U (en) | Hybrid unmanned aerial vehicle power system based on brushless motor | |
| CN117585170A (en) | Distributed multi-oar vertical take-off and landing aircraft hybrid power system and management method | |
| CN108412655A (en) | Rotary engine inspires integrated apparatus and its control method | |
| CN220114826U (en) | Hybrid unmanned aerial vehicle power system | |
| CN207141405U (en) | A kind of long continuation of the journey multi-rotor unmanned aerial vehicle dynamical system of oil electricity mixing | |
| KR101507863B1 (en) | Driving apparatus for electric vehicle | |
| CN214247559U (en) | Wireless remote control one-key starting device for gasoline engine | |
| CN110963050B (en) | Multi-energy hybrid propulsion power system for unmanned aerial vehicle | |
| CN102922983B (en) | A kind of motor vehicle driven by mixed power | |
| CN115924052A (en) | Drive mode switching control method of oil-electricity dual-drive ship | |
| CN117246544A (en) | Hybrid unmanned aerial vehicle power system | |
| CN212099365U (en) | Hybrid power driving device and unmanned aerial vehicle | |
| CN210310866U (en) | Take propeller type, folding, five rotor unmanned vehicles of oil-electricity hybrid | |
| CN209739364U (en) | Hybrid four-rotor helicopter system with multiple working modes | |
| CN202669525U (en) | Starting and power generation integrated machine for extended-range electric vehicle | |
| CN208073664U (en) | Rotary engine inspires integrated apparatus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |