CN205168923U - Many rotor unmanned aerial vehicle hybrid power system - Google Patents
Many rotor unmanned aerial vehicle hybrid power system Download PDFInfo
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- CN205168923U CN205168923U CN201520895185.7U CN201520895185U CN205168923U CN 205168923 U CN205168923 U CN 205168923U CN 201520895185 U CN201520895185 U CN 201520895185U CN 205168923 U CN205168923 U CN 205168923U
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- 239000000295 fuel oil Substances 0.000 claims description 12
- 239000002828 fuel tank Substances 0.000 claims description 12
- 239000003921 oil Substances 0.000 claims description 9
- 230000003584 silencer Effects 0.000 claims description 5
- 230000005611 electricity Effects 0.000 abstract description 5
- 239000000446 fuel Substances 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 3
- 238000010248 power generation Methods 0.000 abstract 2
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 230000007423 decrease Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 230000001141 propulsive effect Effects 0.000 description 3
- 230000000630 rising effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
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Abstract
The utility model discloses a many rotor unmanned aerial vehicle hybrid power system, including organism and horn, the horn is connected to the organism, is equipped with control system in the organism, and control system is connected with power generation system including electricity generation the control unit and drive the control unit, electricity generation the control unit, and drive the control unit is connected with the actuating system, and power generation system includes oil tank and oily electric generator, and the oil tank is connected with the engine, and oily electric generator is connected to the engine, and oily electric generator is connected with the rectifier, and the rectifier is connected with the battery, and the actuating system includes main drive system and secondary drive system. The all driving method who crosses oil -electricity hybrid vehicle of this department have greatly prolonged many rotor unmanned aerial vehicle's time of endurance. The hybrid power system who adopts has not only avoided many rotor unmanned aerial vehicle's of traditional fuel power the flame -out risk of bringing, moreover in the flame -out back of engine, and many rotor unmanned aerial vehicle of manipulation safe landing of the electric energy safety of still usable storage.
Description
Technical field
The utility model relates to many rotor wing unmanned aerial vehicles hybrid power system.
Background technology
The aircraft used in the world at present mainly contains autogyro, fixed wing aircraft, autogiro, propeller-parachuting, dynamic-delta-wing etc., but there is a kind of novel aircraft in recent years, be called multi-rotor aerocraft at home, the physical construction of this cyclogyro is simple, making is easy, handling is good, have extraordinary manoevreability and alerting ability, can easily realize taking off vertically, land, the action such as hovering.But, power resources for this cyclogyro are the problems of those skilled in the art institute in-depth study always, single employing battery power drives, although the alerting ability of many rotor wing unmanned aerial vehicles, handling good, but need to maintain a large amount of electric energy of lift consumption, cause the flight time too short, cannot run for a long time.Adopt engine petrol then just the opposite.Therefore, need research and development one can ensure aircraft alerting ability, its long playing cyclogyro can be ensured again.
Utility model content
The purpose of this utility model is to provide many rotor wing unmanned aerial vehicles hybrid power system, and this system architecture is simple, science is convenient, with strong points, degree of automation is high, solves the power driven problem of many rotor wing unmanned aerial vehicles well.This system, by the type of drive of oil electric mixed dynamic, greatly extends the cruise duration of many rotor wing unmanned aerial vehicles.The hybrid power system adopted, not only avoids the flame-out risk brought of many rotor wing unmanned aerial vehicles of conventional fuel oil power, and after engine off, still can utilize manipulation many rotor wing unmanned aerial vehicles safe landing of the electric energy safe of storage.
In order to solve the problems of the technologies described above, adopt following technical scheme:
Many rotor wing unmanned aerial vehicles hybrid power system, comprise body and horn, body connects horn, it is characterized in that: in body, be provided with control system, control system comprises generation control unit and driving control unit, generation control unit is connected with power generating system, driving control unit is connected with drive system, power generating system comprises fuel tank and oily electric generator, fuel tank is connected with driving engine, driving engine connects oily electric generator, oil electric generator is connected with rectifier, rectifier is connected with storage battery, drive system comprises main drive system and secondary drive system, main drive system is positioned at the top of body, secondary drive system is positioned at the side of body.The quantity of horn has four, is individually fixed on the four direction of body, each horn is provided with a secondary drive system, for many rotor wing unmanned aerial vehicles provide power.Control system, by generation control unit and driving control unit, controls the work of power generating system and drive system respectively, makes many rotor wing unmanned aerial vehicles be in best mode of operation.Power generating system is first stored in storage battery, for drive system work is used by fuel tank and oily electric generator produce power.When many rotor wing unmanned aerial vehicles are started working, power generating system does not work, by storage battery for drive system provides propulsive effort.When storage battery electricity lower than 50% time, power generating system is started working, for storage battery fill can, ensure effectively carrying out of many rotor wing unmanned aerial vehicles work.Main drive system is as the main lift system of many rotor wing unmanned aerial vehicles, for many rotor wing unmanned aerial vehicles provide lift, secondary drive system is as the main power system of many rotor wing unmanned aerial vehicles, be not only the major impetus that many rotor wing unmanned aerial vehicles provide advance, and for the balance that controls many rotor wing unmanned aerial vehicles and direction, and small part lift is provided, makes many rotor wing unmanned aerial vehicles not only have the alerting ability of pure Electric aircraft, and there is the hoverning stability of fuel oil aircraft.In addition, many rotor wing unmanned aerial vehicles also have the manoevreability of rapid flight and many flight advantages such as heavy load, length continuation of the journey of oily electric generator.
Further, main drive system comprises main drive motor and main driving rotor, and main drive motor is fixedly installed in body, and main drive motor is connected with main rotor shaft, and main rotor shaft is provided with main rotor head, and main rotor head connects main driving rotor.Main drive system is as the main lift system of many rotor wing unmanned aerial vehicles, for many rotor wing unmanned aerial vehicles provide lift, main rotor shaft is driven to make high speed rotary motion by main drive motor, thus drive main driving rotor also and then to make high speed rotary motion, for many rotor wing unmanned aerial vehicles provide lift, realize normal rising and the decline of many rotor wing unmanned aerial vehicles.
Further, secondary drive system comprises secondary drive motor and secondary driving shaft, and secondary drive motor and secondary driving shaft are installed in horn, secondary drive motor is connected with auxiliary-motor output shaft, auxiliary-motor output shaft is connected with coupler, and coupler auxiliary connection axle drive shaft, secondary driving shaft is provided with drive bevel gear.
Further, the inner of horn connects body, and the outer end of horn is connected with secondary rotor seat, is provided with and uploads moving axis and lower drive shaft in secondary rotor seat, and upload the top that moving axis is positioned at secondary rotor seat, lower drive shaft is positioned at the bottom of secondary rotor seat.
Further, the lower end of uploading moving axis is provided with driven wheel of differential, upper driven wheel of differential is meshed with drive bevel gear, the upper end of uploading moving axis is provided with rotor head, upper rotor head is connected with rotor, and the upper end of lower drive shaft is provided with lower driven wheel of differential, and lower driven wheel of differential is meshed with drive bevel gear, the lower end of lower drive shaft is provided with lower rotor head, and lower rotor head is connected with lower rotor.Secondary drive system, as the main power system of many rotor wing unmanned aerial vehicles, is not only the major impetus that many rotor wing unmanned aerial vehicles provide advance, and for the balance that controls many rotor wing unmanned aerial vehicles and direction, and small part lift is provided.Secondary drive system is provided with 4 secondary drive motor, control fourth officer pair respectively and drive rotor, and be installed on the four direction of body, the hand of rotation of adjacent two secondary driving rotors is contrary, prevent the secondary rotor that drives that the uneven many rotor wing unmanned aerial vehicles center of gravity deflection caused is set, add the flight stability of many rotor wing unmanned aerial vehicles.Secondary drive motor drives secondary drive motor to make high speed rotary motion, by the engagement of upper driven wheel of differential and drive bevel gear, in drive, rotor makes high speed rotary motion, by the engagement of lower driven wheel of differential and drive bevel gear, lower rotor is driven to make high speed rotary motion, the hand of rotation of upper rotor and lower rotor is just contrary, prevent consistent the caused moment unbalance of hand of rotation, while utilizing a driving arrangement, in drive, rotor and lower rotor move simultaneously, ensure that the stability of many rotor wing unmanned aerial vehicles while not increasing cost.
Further, be provided with oil pipeline between fuel tank and driving engine, oil pipeline is provided with fuel oil filter and airfilter.By fuel oil filter and airfilter, purifying treatment is carried out to fuel oil, not only make driving engine be in rational mode of operation, and make the fuel economy of overall many rotor wing unmanned aerial vehicles reach the highest, reduce the discharge of pollutants simultaneously, protect air environment.
Further, driving engine is connected with silencer.The huge noise produced when reducing engine operation by silencer.
Owing to adopting technique scheme, there is following beneficial effect:
The utility model is many rotor wing unmanned aerial vehicles hybrid power system, and this system architecture is simple, science is convenient, with strong points, degree of automation is high, solves the power driven problem of many rotor wing unmanned aerial vehicles well.This system, by the type of drive of oil electric mixed dynamic, greatly extends the cruise duration of many rotor wing unmanned aerial vehicles.The hybrid power system adopted, not only avoids the flame-out risk brought of many rotor wing unmanned aerial vehicles of conventional fuel oil power, and after engine off, still can utilize manipulation many rotor wing unmanned aerial vehicles safe landing of the electric energy safe of storage.The quantity of horn has four, is individually fixed on the four direction of body, each horn is provided with a secondary drive system, for many rotor wing unmanned aerial vehicles provide power.Control system, by generation control unit and driving control unit, controls the work of power generating system and drive system respectively, makes many rotor wing unmanned aerial vehicles be in best mode of operation.Power generating system is first stored in storage battery, for drive system work is used by fuel tank and oily electric generator produce power.When many rotor wing unmanned aerial vehicles are started working, power generating system does not work, by storage battery for drive system provides propulsive effort.When storage battery electricity lower than 50% time, power generating system is started working, for storage battery fill can, ensure effectively carrying out of many rotor wing unmanned aerial vehicles work.Main drive system is as the main lift system of many rotor wing unmanned aerial vehicles, for many rotor wing unmanned aerial vehicles provide lift, secondary drive system is as the main power system of many rotor wing unmanned aerial vehicles, be not only the major impetus that many rotor wing unmanned aerial vehicles provide advance, and for the balance that controls many rotor wing unmanned aerial vehicles and direction, and small part lift is provided, makes many rotor wing unmanned aerial vehicles not only have the alerting ability of pure Electric aircraft, and there is the hoverning stability of fuel oil aircraft.In addition, many rotor wing unmanned aerial vehicles also have the manoevreability of rapid flight and many flight advantages such as heavy load, length continuation of the journey of oily electric generator.
Main drive system is as the main lift system of many rotor wing unmanned aerial vehicles, for many rotor wing unmanned aerial vehicles provide lift, main rotor shaft is driven to make high speed rotary motion by main drive motor, thus drive main driving rotor also and then to make high speed rotary motion, for many rotor wing unmanned aerial vehicles provide lift, realize normal rising and the decline of many rotor wing unmanned aerial vehicles.Secondary drive system, as the main power system of many rotor wing unmanned aerial vehicles, is not only the major impetus that many rotor wing unmanned aerial vehicles provide advance, and for the balance that controls many rotor wing unmanned aerial vehicles and direction, and small part lift is provided.Secondary drive system is provided with 4 secondary drive motor, control fourth officer pair respectively and drive rotor, and be installed on the four direction of body, the hand of rotation of adjacent two secondary driving rotors is contrary, prevent the secondary rotor that drives that the uneven many rotor wing unmanned aerial vehicles center of gravity deflection caused is set, add the flight stability of many rotor wing unmanned aerial vehicles.Secondary drive motor drives secondary drive motor to make high speed rotary motion, by the engagement of upper driven wheel of differential and drive bevel gear, in drive, rotor makes high speed rotary motion, by the engagement of lower driven wheel of differential and drive bevel gear, lower rotor is driven to make high speed rotary motion, the hand of rotation of upper rotor and lower rotor is just contrary, prevent consistent the caused moment unbalance of hand of rotation, while utilizing a driving arrangement, in drive, rotor and lower rotor move simultaneously, ensure that the stability of many rotor wing unmanned aerial vehicles while not increasing cost.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, the utility model is described in further detail:
Fig. 1 is the structural representation of many rotor wing unmanned aerial vehicles hybrid power system in the utility model;
Fig. 2 is the structure for amplifying schematic diagram at I place in Fig. 1 in the utility model;
Fig. 3 is that in the utility model, drive system is installed on the structural representation on body and wing;
Fig. 4 is the structure for amplifying schematic diagram at II place in Fig. 3 in the utility model;
Fig. 5 is the inner structure schematic diagram of body in the utility model.
Detailed description of the invention
As shown in Figures 1 to 5, many rotor wing unmanned aerial vehicles hybrid power system, comprise body 1 and horn 2, body 1 connects horn 2.Be provided with control system 5 in body 1, control system 5 comprises generation control unit 51 and driving control unit 52, and generation control unit 51 is connected with power generating system 6, and driving control unit 52 is connected with drive system.Power generating system 6 comprises fuel tank 61 and oily electric generator 67, and fuel tank 61 is connected with driving engine 65, and driving engine 65 connects oily electric generator 67, and oily electric generator 67 is connected with rectifier 68, and rectifier 68 is connected with storage battery 69.Be provided with oil pipeline 62 between fuel tank 61 and driving engine 65, oil pipeline 62 is provided with fuel oil filter 63 and airfilter 64.By fuel oil filter 63 and airfilter 64; purifying treatment is carried out to fuel oil, not only makes driving engine 65 be in rational mode of operation, and make the fuel economy of overall many rotor wing unmanned aerial vehicles reach the highest; reduce the discharge of pollutants simultaneously, protect air environment.Driving engine 65 is connected with silencer 66.The huge noise produced when driving engine 65 works is reduced by silencer 66.The quantity of horn 2 has four, is individually fixed on the four direction of body 1, each horn 2 is provided with a secondary drive system, for many rotor wing unmanned aerial vehicles provide power.Control system 5, by generation control unit 51 and driving control unit 52, controls the work of power generating system 6 and drive system respectively, makes many rotor wing unmanned aerial vehicles be in best mode of operation.Power generating system 6 is first stored in storage battery 69, for drive system work is used by fuel tank 61 and oily electric generator 67 produce power.When many rotor wing unmanned aerial vehicles are started working, power generating system 6 does not work, by storage battery 69 for drive system provides propulsive effort.When storage battery 69 electricity lower than 50% time, power generating system 6 is started working, for storage battery 69 fill can, ensure effectively carrying out of many rotor wing unmanned aerial vehicles work.
Drive system comprises main drive system 3 and secondary drive system 4, and main drive system 3 is positioned at the top of body 1, and secondary drive system 4 is positioned at the side of body 1.Main drive system 3 is as the main lift system of many rotor wing unmanned aerial vehicles, for many rotor wing unmanned aerial vehicles provide lift, secondary drive system 4 is as the main power system of many rotor wing unmanned aerial vehicles, be not only the major impetus that many rotor wing unmanned aerial vehicles provide advance, and for the balance that controls many rotor wing unmanned aerial vehicles and direction, and small part lift is provided, makes many rotor wing unmanned aerial vehicles not only have the alerting ability of pure Electric aircraft, and there is the hoverning stability of fuel oil aircraft.In addition, many rotor wing unmanned aerial vehicles also have the manoevreability of rapid flight and many flight advantages such as heavy load, length continuation of the journey of oily electric generator 67.
Main drive system 3 comprises main drive motor 34 and main driving rotor 32, and main drive motor 34 is fixedly installed in body 1, and main drive motor 34 is connected with main rotor shaft 33, and main rotor shaft 33 is provided with main rotor head 31, and main rotor head 31 connects main driving rotor 32.Main drive system 3 is as the main lift system of many rotor wing unmanned aerial vehicles, for many rotor wing unmanned aerial vehicles provide lift, main rotor shaft 33 is driven to make high speed rotary motion by main drive motor 34, thus drive main driving rotor 32 also and then to make high speed rotary motion, for many rotor wing unmanned aerial vehicles provide lift, realize normal rising and the decline of many rotor wing unmanned aerial vehicles.
Secondary drive system 4 comprises secondary drive motor 35 and secondary driving shaft 38, secondary drive motor 35 and secondary driving shaft 38 are installed in horn 2, secondary drive motor 35 is connected with auxiliary-motor output shaft 36, auxiliary-motor output shaft 36 is connected with coupler 37, coupler 37 auxiliary connection axle drive shaft 38, secondary driving shaft 38 is provided with drive bevel gear 39.The inner of horn 2 connects body 1, and the outer end of horn 2 is connected with secondary rotor seat 41, is provided with and uploads moving axis 44 and lower drive shaft 48 in secondary rotor seat 41, and upload the top that moving axis 44 is positioned at secondary rotor seat 41, lower drive shaft 48 is positioned at the bottom of secondary rotor seat 41.The lower end of uploading moving axis 44 is provided with driven wheel of differential 45, upper driven wheel of differential 45 is meshed with drive bevel gear 39, the upper end of uploading moving axis 44 is provided with rotor head 42, upper rotor head 42 is connected with rotor 43, the upper end of lower drive shaft 48 is provided with lower driven wheel of differential 49, lower driven wheel of differential 49 is meshed with drive bevel gear 39, and the lower end of lower drive shaft 48 is provided with lower rotor head 46, and lower rotor head 46 is connected with lower rotor 47.Secondary drive system 4, as the main power system of many rotor wing unmanned aerial vehicles, is not only the major impetus that many rotor wing unmanned aerial vehicles provide advance, and for the balance that controls many rotor wing unmanned aerial vehicles and direction, and small part lift is provided.Secondary drive system 4 is provided with 4 secondary drive motor 35, control fourth officer pair respectively and drive rotor, and be installed on the four direction of body 1, the hand of rotation of adjacent two secondary driving rotors is contrary, prevent the secondary rotor that drives that the uneven many rotor wing unmanned aerial vehicles center of gravity deflection caused is set, add the flight stability of many rotor wing unmanned aerial vehicles.Secondary drive motor 35 drives secondary drive motor 35 to make high speed rotary motion, by the engagement of upper driven wheel of differential 45 with drive bevel gear 39, in drive, rotor 43 makes high speed rotary motion, by the engagement of lower driven wheel of differential 49 with drive bevel gear 39, lower rotor 47 is driven to make high speed rotary motion, the hand of rotation of upper rotor 43 and lower rotor 47 is just contrary, prevent consistent the caused moment unbalance of hand of rotation, while utilizing a driving arrangement, in drive, rotor 43 and lower rotor 47 move simultaneously, the stability of many rotor wing unmanned aerial vehicles is ensure that while not increasing cost.
These are only specific embodiment of the utility model, but technical characteristic of the present utility model is not limited thereto.Any based on the utility model, for solving substantially identical technical matters, realize substantially identical technique effect, done ground simple change, equivalent replacement or modification etc., be all covered by among protection domain of the present utility model.
Claims (7)
1. more than rotor wing unmanned aerial vehicle hybrid power system, comprise body and horn, described body connects described horn, it is characterized in that: in described body, be provided with control system, described control system comprises generation control unit and driving control unit, described generation control unit is connected with power generating system, described driving control unit is connected with drive system, described power generating system comprises fuel tank and oily electric generator, described fuel tank is connected with driving engine, described driving engine connects described oily electric generator, described oily electric generator is connected with rectifier, described rectifier is connected with storage battery, described drive system comprises main drive system and secondary drive system, described main drive system is positioned at the top of described body, described secondary drive system is positioned at the side of described body.
2. many rotor wing unmanned aerial vehicles hybrid power system according to claim 1, it is characterized in that: described main drive system comprises main drive motor and main driving rotor, described main drive motor is fixedly installed in described body, described main drive motor is connected with main rotor shaft, described main rotor shaft is provided with main rotor head, and described main rotor head connects described main driving rotor.
3. many rotor wing unmanned aerial vehicles hybrid power system according to claim 1, it is characterized in that: described secondary drive system comprises secondary drive motor and secondary driving shaft, described secondary drive motor and described secondary driving shaft are installed in described horn, described secondary drive motor is connected with auxiliary-motor output shaft, described auxiliary-motor output shaft is connected with coupler, described coupler connects described secondary driving shaft, and described secondary driving shaft is provided with drive bevel gear.
4. many rotor wing unmanned aerial vehicles hybrid power system according to claim 3, it is characterized in that: the inner of described horn connects described body, the outer end of described horn is connected with secondary rotor seat, be provided with in described secondary rotor seat and upload moving axis and lower drive shaft, describedly upload the top that moving axis is positioned at described secondary rotor seat, described lower drive shaft is positioned at the bottom of described secondary rotor seat.
5. many rotor wing unmanned aerial vehicles hybrid power system according to claim 4, it is characterized in that: described in upload moving axis lower end be provided with driven wheel of differential, described upper driven wheel of differential is meshed with described drive bevel gear, described upper end of uploading moving axis is provided with rotor head, described upper rotor head is connected with rotor, the upper end of described lower drive shaft is provided with lower driven wheel of differential, described lower driven wheel of differential is meshed with described drive bevel gear, the lower end of described lower drive shaft is provided with lower rotor head, and described lower rotor head is connected with lower rotor.
6. many rotor wing unmanned aerial vehicles hybrid power system according to claim 1, it is characterized in that: be provided with oil pipeline between described fuel tank and described driving engine, described oil pipeline is provided with fuel oil filter and airfilter.
7. many rotor wing unmanned aerial vehicles hybrid power system according to claim 1, is characterized in that: described driving engine is connected with silencer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520895185.7U CN205168923U (en) | 2015-11-11 | 2015-11-11 | Many rotor unmanned aerial vehicle hybrid power system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520895185.7U CN205168923U (en) | 2015-11-11 | 2015-11-11 | Many rotor unmanned aerial vehicle hybrid power system |
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| CN205168923U true CN205168923U (en) | 2016-04-20 |
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| CN201520895185.7U Expired - Fee Related CN205168923U (en) | 2015-11-11 | 2015-11-11 | Many rotor unmanned aerial vehicle hybrid power system |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882954A (en) * | 2016-05-25 | 2016-08-24 | 沈阳航空航天大学 | Hybrid-power unmanned aerial vehicle with four auxiliary wings and control method thereof |
| CN107054667A (en) * | 2017-05-26 | 2017-08-18 | 广东电网有限责任公司清远供电局 | A kind of multi-rotor unmanned aerial vehicle |
| WO2018006439A1 (en) * | 2016-07-04 | 2018-01-11 | 深圳市龙云创新航空科技有限公司 | Integrated power multi-axis unmanned aerial vehicle |
| CN107585297A (en) * | 2016-07-06 | 2018-01-16 | 襄阳联航动力技术有限公司 | A kind of more rotor parallel type hybrid dynamic unmanned planes |
| CN107933903A (en) * | 2017-12-03 | 2018-04-20 | 佛山市神风航空科技有限公司 | One kind stablizes more rotor hook goods aircraft |
| CN108128438A (en) * | 2018-01-16 | 2018-06-08 | 沈阳朗峰科技有限公司 | A kind of dynamic trapezoidal VTOL equipment of circle of oil |
| CN108674670A (en) * | 2018-05-25 | 2018-10-19 | 河南亿诺航空科技有限公司 | A kind of mixed dynamic formula unmanned plane of oil electricity |
| CN108945412A (en) * | 2018-06-21 | 2018-12-07 | 北京理工大学 | Dynamical system, starting control method and the system of heavy rotor craft |
| CN109987222A (en) * | 2018-01-02 | 2019-07-09 | 上海骄翔智能技术有限公司 | Unmanned aerial vehicle, power train and method of reducing air resistance in unmanned aerial vehicle |
| CN110155345A (en) * | 2019-06-05 | 2019-08-23 | 重庆隆鑫通航发动机制造有限公司 | Unmanned plane hybrid power system |
| CN113665824A (en) * | 2021-08-20 | 2021-11-19 | 浙江点辰航空科技有限公司 | Small-size aerocraft hybrid device |
-
2015
- 2015-11-11 CN CN201520895185.7U patent/CN205168923U/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882954A (en) * | 2016-05-25 | 2016-08-24 | 沈阳航空航天大学 | Hybrid-power unmanned aerial vehicle with four auxiliary wings and control method thereof |
| WO2018006439A1 (en) * | 2016-07-04 | 2018-01-11 | 深圳市龙云创新航空科技有限公司 | Integrated power multi-axis unmanned aerial vehicle |
| CN107585297A (en) * | 2016-07-06 | 2018-01-16 | 襄阳联航动力技术有限公司 | A kind of more rotor parallel type hybrid dynamic unmanned planes |
| CN107054667A (en) * | 2017-05-26 | 2017-08-18 | 广东电网有限责任公司清远供电局 | A kind of multi-rotor unmanned aerial vehicle |
| CN107933903A (en) * | 2017-12-03 | 2018-04-20 | 佛山市神风航空科技有限公司 | One kind stablizes more rotor hook goods aircraft |
| CN109987222A (en) * | 2018-01-02 | 2019-07-09 | 上海骄翔智能技术有限公司 | Unmanned aerial vehicle, power train and method of reducing air resistance in unmanned aerial vehicle |
| CN109987222B (en) * | 2018-01-02 | 2022-06-24 | 上海峰飞航空科技有限公司 | Unmanned aerial vehicle, power train and method of reducing air resistance in unmanned aerial vehicle |
| CN108128438A (en) * | 2018-01-16 | 2018-06-08 | 沈阳朗峰科技有限公司 | A kind of dynamic trapezoidal VTOL equipment of circle of oil |
| CN108674670A (en) * | 2018-05-25 | 2018-10-19 | 河南亿诺航空科技有限公司 | A kind of mixed dynamic formula unmanned plane of oil electricity |
| CN108945412A (en) * | 2018-06-21 | 2018-12-07 | 北京理工大学 | Dynamical system, starting control method and the system of heavy rotor craft |
| CN108945412B (en) * | 2018-06-21 | 2024-06-11 | 北京理工大学 | Power system, starting control method and system of heavy-duty rotor craft |
| CN110155345A (en) * | 2019-06-05 | 2019-08-23 | 重庆隆鑫通航发动机制造有限公司 | Unmanned plane hybrid power system |
| CN110155345B (en) * | 2019-06-05 | 2022-09-13 | 重庆隆鑫通航发动机制造有限公司 | Hybrid power system of unmanned aerial vehicle |
| CN113665824A (en) * | 2021-08-20 | 2021-11-19 | 浙江点辰航空科技有限公司 | Small-size aerocraft hybrid device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160420 Termination date: 20161111 |