CN116853507A - Oil-electricity hybrid direct-drive system and vertical take-off and landing fixed wing unmanned aerial vehicle - Google Patents
Oil-electricity hybrid direct-drive system and vertical take-off and landing fixed wing unmanned aerial vehicle Download PDFInfo
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- CN116853507A CN116853507A CN202311043193.4A CN202311043193A CN116853507A CN 116853507 A CN116853507 A CN 116853507A CN 202311043193 A CN202311043193 A CN 202311043193A CN 116853507 A CN116853507 A CN 116853507A
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- 239000000446 fuel Substances 0.000 claims abstract description 82
- 238000010248 power generation Methods 0.000 claims abstract description 44
- 241000272525 Anas platyrhynchos Species 0.000 claims abstract description 11
- 230000005611 electricity Effects 0.000 claims description 30
- 238000000034 method Methods 0.000 claims description 8
- 230000001360 synchronised effect Effects 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 241000272517 Anseriformes Species 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 229910052744 lithium Inorganic materials 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000005406 washing Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/20—Vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Hybrid Electric Vehicles (AREA)
Abstract
The application provides a vertical take-off and landing fixed wing unmanned aerial vehicle of a fuel-electric hybrid direct-drive system, which comprises a propeller, an electric/power generation integrated machine and a fuel engine, wherein the electric/power generation integrated machine and the fuel engine can be linked or independently realize the rotation driving of the propeller, the electric/power generation integrated machine can also start the fuel engine, and the fuel engine can also drive the electric/power generation integrated machine to generate power; the fixed wing unmanned aerial vehicle comprises two groups of the oil-electricity hybrid direct-drive systems and further comprises a storage battery, wherein the two groups of the oil-electricity hybrid direct-drive systems are symmetrically arranged on the front sides of the two main wings or the front sides of the two duck wings. The oil-electricity hybrid direct-drive system can realize that the fuel engine directly drives the propeller to rotate, so that the fuel energy utilization rate can be improved; the electric/power generation integrated machine and the fuel engine can be linked to provide maximum power for the unmanned aerial vehicle, so that the power requirement of the fuel engine can be optimized, and the weight and cost of the engine are greatly reduced.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicles, in particular to an oil-electricity hybrid direct-driven system and a vertical take-off and landing fixed wing unmanned aerial vehicle.
Background
The applicant applied for a hybrid unmanned aerial vehicle in 2017, 04 and 17 (application publication number: CN 106864757A), the power source of the hybrid unmanned aerial vehicle mainly comprises a group of high-power density power sources and another group of high-energy density power sources, wherein the high-power density power sources are high-power lithium batteries, the high-energy density power sources are one or more of batteries, an oil-electricity hybrid power source, a fuel cell and a solar cell, preferably, the oil-electricity hybrid power source consists of an electricity generation/starting integrated machine and an internal combustion engine, the internal combustion engine can provide power for the electricity generation/starting integrated machine under a set condition to enable the electricity generation/starting integrated machine to generate electricity, and the electricity generation/starting integrated machine stores electric quantity in the high-power lithium batteries in the electricity generation process. In the hybrid unmanned aerial vehicle, although energy through the internal combustion engine is converted into the unmanned aerial vehicle to provide long endurance mileage by utilizing the high-density characteristic of fuel oil, driving of the unmanned aerial vehicle propeller is still a motor, fuel is only used for generating electricity, and the fuel energy utilization mode is lower in fuel energy utilization rate compared with a mode of directly driving the propeller by utilizing the internal combustion engine.
A vertical take-off and landing fixed wing aircraft (grant bulletin number CN 205686609U) applied by applicant at 14 of 2016 and a novel unmanned aerial vehicle (grant bulletin CN 217170961U) applied at 20 of 2021 and 10 provides a hardware basis for realizing the unmanned aerial vehicle in the application.
Disclosure of Invention
The application aims to provide a fuel-electric hybrid direct-drive system and a vertical take-off and landing fixed wing unmanned aerial vehicle, wherein the fuel-electric hybrid direct-drive system can realize that a fuel engine directly drives a propeller to rotate, so that the fuel energy utilization rate can be improved, and the duration of the unmanned aerial vehicle can be further improved; meanwhile, in the vertical take-off and landing stage, the electric/power generation integrated machine and the fuel engine can be linked to provide maximum power for the unmanned aerial vehicle, so that the power requirement of the fuel engine can be optimized, and the weight and cost of the engine are greatly reduced.
The technical scheme adopted for solving the technical problems is as follows: the utility model provides a hybrid direct-drive system of oil electricity, includes screw, electric/electricity generation all-in-one, fuel engine, electric/electricity generation all-in-one and fuel engine can link or realize alone the rotation drive of screw, electric/electricity generation all-in-one can also start the fuel engine, the fuel engine can also drive electric/electricity generation all-in-one generates electricity, through electric/electricity generation all-in-one and fuel engine linkage do the rotation of screw provides maximum power electric/electricity generation all-in-one and fuel engine linkage or fuel engine drive alone the screw rotates the in-process, when the fuel engine breaks down, electric/electricity generation all-in-one can independently realize right the rotation drive of screw.
Preferably, the direct-drive system further comprises a first clutch and a second clutch, wherein the first clutch is used for connecting the driving shaft of the propeller with the driving shaft of the electric/power generation integrated machine, and the second clutch is used for connecting the driving shaft of the electric/power generation integrated machine with the driving shaft of the fuel engine.
Further, the propeller is a variable pitch propeller.
Further, the first clutch and the second clutch are electromagnetic clutches.
The utility model provides a fixed wing unmanned aerial vehicle that takes off and land perpendicularly, includes fuselage, main wing, duck wing fuselage rear portion symmetry is provided with two the main wing fuselage front portion symmetry is provided with two the duck wing, this fixed wing unmanned aerial vehicle include two sets of above-mentioned oily electricity hybrid direct drive system and battery, oily electricity hybrid direct drive system all with this fixed wing unmanned aerial vehicle's main control processor electric connection, two sets of oily electricity hybrid direct drive system symmetry sets up two main wing front side or two duck wing front side.
Preferably, a synchronizing shaft is provided between the drive shafts of the two propellers.
The beneficial effects of the application are as follows: the fuel-electric hybrid direct-drive system can realize that the fuel engine directly drives the propeller to rotate, so that the fuel energy conversion utilization rate is greatly improved, and in the plane flight stage of the unmanned aerial vehicle, the fuel engine is utilized to independently drive the propeller to rotate, so that the duration of the unmanned aerial vehicle can be greatly prolonged, and meanwhile, the fuel engine can synchronously drive the electric/power generation integrated machine to generate power, so that the flight power reliability of the unmanned aerial vehicle is improved; the power required by the vertical take-off and landing of the unmanned aerial vehicle is about three times that of a plane, and when the unmanned aerial vehicle takes off and lands vertically, the fuel engine and the electric/power generation integrated machine work simultaneously, but the power provided by the electric/power generation integrated machine is mainly provided (the electric/power generation integrated machine provides about 70% of power, and the fuel engine provides about 30% of power), so that the power requirement optimization of the fuel engine is realized, the weight and the cost of the engine are greatly reduced, and meanwhile, the fuel engine is linked with the electric/power generation integrated machine, so that the flight reliability of the unmanned aerial vehicle can be greatly improved; in the process of flat flight, if the fuel engine fails and extinguishes, the fuel engine can be separated from the propeller power through the clutch, and then the electric/power generation integrated machine provides power to implement emergency landing, so that the flight safety is ensured.
Drawings
In order to more clearly illustrate the embodiments of the application or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are some preferred embodiments of the application and that other drawings can be obtained from these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the overall structure of the hybrid direct drive system;
FIG. 2 is a schematic overall construction of a first embodiment of a civil or military vertical take-off and landing fixed wing aircraft;
FIG. 3 is a schematic overall construction of a second embodiment of a civil or military vertical take-off and landing fixed wing aircraft;
FIG. 4 is a schematic overall structure of a first embodiment of a vertical take-off and landing fixed wing unmanned aerial vehicle;
in the figure: 1 propeller, 2 electric/electric power generation integrated machine, 3 fuel engine, 4 first clutch, 5 second clutch, 6 first fuselage, 61 first canard, 611 first aileron, 62 first main wing, 621 second aileron, 63 first vertical tail, 7 second fuselage, 71 second canard, 72 second main wing, 721 third aileron, 73 second vertical tail, 8 third fuselage, 81 third canard, 82 third main wing, 83 third vertical tail.
Detailed Description
The technical solutions of the embodiments of the present application will be clearly and completely described below with reference to specific embodiments and fig. 1 to 4, and it is obvious that the described embodiments are only some of the preferred embodiments of the present application, but not all embodiments. Similar modifications can be made by those skilled in the art without departing from the spirit of the application, and therefore the application is not to be limited by the specific embodiments disclosed below.
The application provides a fuel-electric hybrid direct-drive system (shown in figure 1), which comprises a propeller 1, an electric/power generation integrated machine 2 and a fuel engine 3, wherein the electric/power generation integrated machine 2 is a product of the prior art, such as China patent of the application with the application publication number of CN108616204A, an electric power generation integrated machine is disclosed, so the detailed structure and the working principle of the electric/power generation integrated machine 2 are not described in detail, the fuel engine 3 is a product of the prior art, in practical application, the fuel engine 3 can select a gasoline engine with smaller weight as a preferred embodiment, the electric/power generation integrated machine 2 and the fuel engine 3 can be linked or independently driven by rotation of the propeller 1, namely, the electric/power generation integrated machine 2 and the fuel engine 3 can simultaneously realize the rotation driving of the propeller 1 in a serial linkage mode, the rotation driving of the electric/power generation integrated machine 2 and the fuel engine 3 can also respectively independently realize the rotation driving of the propeller 1, the utilization rate of the fuel engine 1 can be greatly improved when the electric/power generation integrated machine 2 can also be driven by the electric power generation integrated machine 2 and the fuel engine 3 can also realize the rotation driving of the propeller 1 by the fuel engine 3 when the electric power generation integrated machine 2 and the fuel engine 3 can be simultaneously turned off by the electric power generation integrated machine 2 and the fuel engine 3 in the process of the fuel engine 3 is the fuel engine 3 or the fuel engine 3 is the most likely to be connected with the engine 1 in a series or the power generation integrated machine 3, the electric/power generation integrated machine 2 can independently realize the rotation driving of the propeller 1, thereby improving the operation reliability of the propeller 1.
In order to facilitate the power combination control of the electric/electric integrated machine 2 and the fuel engine 3, a first clutch 4 and a second clutch 5 can be added in the direct-drive system, the first clutch 4 is used for connecting the driving shaft of the propeller 1 with the driving shaft of the electric/electric integrated machine 2, the second clutch 5 is used for connecting the driving shaft of the electric/electric integrated machine 2 with the driving shaft of the fuel engine 3, when the electric/electric integrated machine 2 and the fuel engine 3 are required to be used for realizing the driving of the propeller 1, the electric/electric integrated machine 2 is in an electric driving station, and meanwhile, the first clutch 4 and the second clutch 5 are simultaneously closed, so that the driving shaft of the propeller 1, the driving shaft of the electric/electric integrated machine 2 and the driving shaft of the fuel engine 3 are connected in series, and synchronous driving of the electric/electric integrated machine 2 and the fuel engine 3 to the propeller 1 is realized; when the fuel engine 3 fails and the propeller 1 needs to be driven by the electric/power generation integrated machine 2 alone, the electric/power generation integrated machine 2 is in an electric driving station, the first clutch 4 is in a closed state, the second clutch 5 is in an open state, and the second clutch 5 is in an open state, so that the power transmission paths of the electric/power generation integrated machine 2 and the fuel engine 3 are cut off; when only the fuel engine 3 is needed to drive the propeller 1, the electric/power generation integrated machine 2 is in power generation work, the first clutch 4 and the second clutch 5 are simultaneously closed, and the fuel engine 3 drives the propeller 1 to rotate and simultaneously drives the electric/power generation integrated machine 2 to generate power.
In practical application, when the electric/electric integrated machine 2 and the fuel engine 3 drive the propeller 1 to rotate, the propeller 1 can be selected as a variable pitch propeller in order to enable the electric/electric integrated machine 2 and the fuel engine 3 to be capable of keeping the maximum power for power output; further, in order to facilitate the control convenience of the first clutch 4 and the second clutch 5, electromagnetic clutches are used for both the first clutch 4 and the second clutch 5.
The system can be directly applied to civil or military unmanned aerial vehicle by utilizing the characteristic that the fuel engine 3 of the system can directly drive the propeller 1 to rotate, so that the remote operation capability of the unmanned aerial vehicle can be greatly improved; meanwhile, the system can be directly applied to civil or military manned vertical take-off and landing fixed-wing aircraft, the civil or military manned vertical take-off and landing fixed-wing aircraft can take off directly under complex ground without a runway, and the military force can be directly transported and thrown to the rear of the enemy by utilizing the capability of the constant endurance time. Because the civil or military manned vertical take-off and landing fixed-wing aircraft is heavy in weight and large in volume, in the vertical take-off process, in order to facilitate the aircraft to obtain reliable pitching and pointing control, the torque control principle of the propeller of the existing helicopter can be used for realizing the torque control of the propeller 1 in the oil-electricity hybrid direct-drive system. The existing helicopters generally realize the torque change control of the propeller through a tilting disk (automatic tilting device), namely, the torque change of the propeller is realized by changing the position, the tilting direction and the angle of the tilting disk. In practical application, the tilting disk for changing the moment of the controller can be installed at the rear side of the propeller 1, after the moment of the propeller 1 is constantly increased or decreased by utilizing the change of the position of the tilting disk, the aircraft is lifted or lowered, the periodicity of the moment of the propeller 1 is increased or decreased by utilizing the change of the tilting direction and the angle of the tilting disk, so that the asymmetry of the moment is realized, at the moment, the pitching and pointing control of the aircraft can be realized, and the reliable pitching and pointing control can be provided for the suspended aircraft by utilizing the moment change of the propeller 1 in the taking-off process of the aircraft because of the larger moment of the propeller 1. In this embodiment, two embodiments of a civil or military manned vertical take-off and landing fixed wing aircraft are given, and in particular, a first embodiment (as shown in fig. 2) of the civil or military manned vertical take-off and landing fixed wing aircraft is as follows: the aircraft comprises a first airframe 6, two first duckwings 61 are symmetrically arranged left and right at the front part of the first airframe 6, two first main wings 62 are symmetrically arranged left and right at the rear part of the first airframe 6, two first vertical tail wings 63 are symmetrically arranged up and down at the rear part of the first airframe 6, two groups of the oil-electricity hybrid direct drive systems are symmetrically arranged at the outer ends of the two first duckwings 61 left and right, a first aileron 611 is arranged at the rear side of the first duckwings 61, and a second aileron 621 is arranged at the rear side of the first main wings 62, in the embodiment, when the aircraft vertically takes off, the second aileron 621 does not participate in vertical flight control, the pitching and heading main control during vertical flight is realized by utilizing the torque conversion control of the propeller 1, and simultaneously, the first aileron 611 deflects the downward washing airflow generated by the propeller 1, so that the additional pitching and pointing control moment is assisted, and the vertical stability take-off of the aircraft is further improved; in the plane flying state, the first aileron 611 is used for mainly realizing the pitching control of the plane, and the second aileron 621 is used for mainly realizing the rolling control of the plane; a second embodiment (as shown in fig. 3) of a civil or military manned fixed-wing aircraft for vertical take-off and landing is as follows: the aircraft comprises a second airframe 7, wherein two second duck wings 71 are symmetrically arranged left and right at the front part of the second airframe 7, two second main wings 72 are symmetrically arranged left and right at the rear part of the second airframe 7, two second vertical tail wings 73 are symmetrically arranged up and down at the rear part of the second airframe 7, two groups of oil-electricity hybrid direct drive systems are symmetrically arranged left and right at the outer ends of the two second main wings 72, a third auxiliary wing 721 is arranged at the rear side of the second main wings 72, when the aircraft vertically takes off, the pitching and heading main control during vertical flight is realized by utilizing the torque control of a propeller 1, and meanwhile, the third auxiliary wing 721 deflects the downward washing airflow generated by the propeller 1, so that the generation of additional pitching and pointing control moment is assisted, and the vertical take-off stability of the aircraft is improved; when the aircraft is flying in a flat state, the pitching and rolling control of the aircraft is realized by utilizing the deflection of the third auxiliary wing 721.
The application also provides a vertical lifting fixed wing unmanned aerial vehicle, which comprises a machine body, a main wing and a duck wing, wherein two main wings are symmetrically arranged at the rear part of the machine body, two duck wings are symmetrically arranged at the front part of the machine body, the vertical lifting fixed wing unmanned aerial vehicle further comprises the oil-electricity hybrid direct-drive system and a storage battery, the storage battery and the oil-electricity hybrid direct-drive system are electrically connected with a main control processor of the fixed wing unmanned aerial vehicle, the main control processor can set a control program according to the inside of the main control processor, the main control processor can control the real-time working states of the electric/power generation integrated machine 2, the fuel engine 3, the first clutch 4 and the second clutch 5, the storage battery can provide a starting power supply for the electric/power generation integrated machine 2, meanwhile, the storage battery can provide an operating power supply for a column control processor of the unmanned aerial vehicle, and the two groups of oil-electricity hybrid direct-drive systems are symmetrically arranged at the front sides of the two main wings or the front sides of the two main wings. The specific implementation mode of a specific embodiment of the fixed wing unmanned aerial vehicle is as follows: the unmanned aerial vehicle comprises a third machine body 8, wherein two third duck wings 81 are symmetrically arranged on the left and right sides of the front part of the third machine body 8, two third main wings 82 are symmetrically arranged on the left and right sides of the rear part of the third machine body 8, two third vertical tail wings 83 are symmetrically arranged on the upper and lower sides of the rear part of the third machine body 8, two groups of oil-electricity hybrid direct-driven systems are symmetrically arranged in the middle of the two third main wings 82, and a storage battery is arranged inside the third machine body 8.
In practical application, flight power is provided for the unmanned aerial vehicle through high-speed rotation of the propeller 1, so that the unmanned aerial vehicle can fly; the fuel-electricity hybrid direct-drive system can realize that the fuel engine 3 directly drives the propeller 1 to rotate, so that the fuel energy conversion utilization rate is greatly improved, and in the plane flight stage of the unmanned aerial vehicle with the fixed wing, the fuel engine 3 is utilized to independently drive the propeller 1 to rotate, so that the duration of the unmanned aerial vehicle can be greatly prolonged, and meanwhile, the fuel engine 3 can synchronously drive the electric/power generation integrated machine 2 to generate power, so that the flight power reliability of the unmanned aerial vehicle is improved; the power required by the vertical take-off and landing of the unmanned aerial vehicle is about three times that of a plane, when the unmanned aerial vehicle takes off and lands vertically, the fuel engine 3 and the electric/power generation integrated machine 2 work simultaneously, but the power provided by the electric/power generation integrated machine 2 is mainly provided (about 70% of power is provided by the electric/power generation integrated machine 2, about 30% of power is provided by the fuel engine 3), so that the power requirement optimization of the fuel engine 3 is realized, the weight and cost of the engine are greatly reduced, and meanwhile, the fuel engine 3 and the electric/power generation integrated machine 2 are linked, so that the flight reliability of the unmanned aerial vehicle can be greatly improved; in the flat flight process, if the fuel engine 3 fails and extinguishes, the fuel engine can be separated from the propeller 1 by the clutch, then, the electric/power generation integrated machine 2 provides power to implement emergency landing, so that the flight safety is ensured, a synchronous shaft can be arranged between the driving shafts of the two propellers 1 to further improve the flight reliability of the unmanned aerial vehicle, the synchronous shaft is utilized to realize the synchronous rotation of the two propellers 1, and when one propeller 1 loses driving power, the transmission of the synchronous shaft is utilized to still ensure that the propeller is in a rotating state, so that the flight reliability of the unmanned aerial vehicle can be improved.
The vertical take-off and landing fixed wing unmanned aerial vehicle is free from the limitation of geographical environment, has long-term aviation capability, and can greatly improve the operation efficiency and capability in the fields after being applied to the fields of logistics delivery, rescue, fire extinguishment and the like.
Other than the technical features described in the specification, all are known to those skilled in the art.
While the preferred embodiments and examples of the present application have been described in detail with reference to the accompanying drawings, the present application is not limited to the embodiments and examples, and it will be apparent to those skilled in the art that various modifications and variations can be made without departing from the spirit of the present application, and the scope of the application is also defined by the appended claims.
Claims (6)
1. The utility model provides a fuel-electric hybrid direct-drive system, its characterized in that includes screw, electronic/electricity generation all-in-one, fuel engine, electronic/electricity generation all-in-one and fuel engine can link or realize alone the rotation drive of screw, electronic/electricity generation all-in-one can also start the fuel engine, fuel engine can also drive electronic/electricity generation all-in-one electricity generation, through electronic/electricity generation all-in-one and fuel engine linkage provide maximum power for the rotation of screw in motor/electricity generation all-in-one and fuel engine linkage or fuel engine drive alone the screw rotates the in-process, when the fuel engine breaks down, electronic/electricity generation all-in-one can independently realize to the rotation drive of screw.
2. The hybrid direct-drive system according to claim 1, further comprising a first clutch that connects a drive shaft of the propeller to a drive shaft of the electric/power generation unit, and a second clutch that connects a drive shaft of the electric/power generation unit to a drive shaft of the fuel engine.
3. The hybrid direct drive system of claim 2, wherein the propeller is a variable pitch propeller.
4. The hybrid electric direct drive system of claim 2, wherein the first clutch and the second clutch are both electromagnetic clutches.
5. The utility model provides a fixed wing unmanned aerial vehicle that takes off and land perpendicularly, includes fuselage, main wing, duck wing fuselage rear portion symmetry is provided with two the main wing fuselage front portion symmetry is provided with two the duck wing, its characterized in that, this fixed wing unmanned aerial vehicle includes two sets of according to the oil electricity of any one of claims 1-4 and mixes system of driving, battery, oil electricity mix and drive system all with this fixed wing unmanned aerial vehicle's main control processor electric connection, two sets of oil electricity mix and drive system symmetry set up two main wing front side or two the duck wing front side.
6. The fixed wing vertical take-off and landing unmanned aerial vehicle of claim 5, wherein a synchronizing shaft is disposed between the drive shafts of the two propellers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311043193.4A CN116853507A (en) | 2023-08-17 | 2023-08-17 | Oil-electricity hybrid direct-drive system and vertical take-off and landing fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311043193.4A CN116853507A (en) | 2023-08-17 | 2023-08-17 | Oil-electricity hybrid direct-drive system and vertical take-off and landing fixed wing unmanned aerial vehicle |
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| CN116853507A true CN116853507A (en) | 2023-10-10 |
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| CN202311043193.4A Pending CN116853507A (en) | 2023-08-17 | 2023-08-17 | Oil-electricity hybrid direct-drive system and vertical take-off and landing fixed wing unmanned aerial vehicle |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080184906A1 (en) * | 2007-02-07 | 2008-08-07 | Kejha Joseph B | Long range hybrid electric airplane |
| CN109733621A (en) * | 2018-12-17 | 2019-05-10 | 南京航空航天大学 | A kind of hybrid power unmanned plane promoting mode more |
| KR102004227B1 (en) * | 2018-11-07 | 2019-07-30 | 문창모 | VERTICAL TAKE OFF AND LANDING AIRCRAFT USING HYBRID-ELECTRIC PROPULSION SYSTEM and THE CONTROL METHOD |
| CN212501058U (en) * | 2020-07-10 | 2021-02-09 | 安徽鸠兹航空智能产业技术研究院有限公司 | High-speed hybrid unmanned aerial vehicle |
| CN112758335A (en) * | 2021-01-20 | 2021-05-07 | 南京航空航天大学 | Series-parallel hybrid power unmanned aerial vehicle power system and control method thereof |
-
2023
- 2023-08-17 CN CN202311043193.4A patent/CN116853507A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080184906A1 (en) * | 2007-02-07 | 2008-08-07 | Kejha Joseph B | Long range hybrid electric airplane |
| KR102004227B1 (en) * | 2018-11-07 | 2019-07-30 | 문창모 | VERTICAL TAKE OFF AND LANDING AIRCRAFT USING HYBRID-ELECTRIC PROPULSION SYSTEM and THE CONTROL METHOD |
| CN109733621A (en) * | 2018-12-17 | 2019-05-10 | 南京航空航天大学 | A kind of hybrid power unmanned plane promoting mode more |
| CN212501058U (en) * | 2020-07-10 | 2021-02-09 | 安徽鸠兹航空智能产业技术研究院有限公司 | High-speed hybrid unmanned aerial vehicle |
| CN112758335A (en) * | 2021-01-20 | 2021-05-07 | 南京航空航天大学 | Series-parallel hybrid power unmanned aerial vehicle power system and control method thereof |
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