CN105480418A - Ducted fixed-wing oil-electric hybrid unmanned aircraft - Google Patents
Ducted fixed-wing oil-electric hybrid unmanned aircraft Download PDFInfo
- Publication number
- CN105480418A CN105480418A CN201510940762.4A CN201510940762A CN105480418A CN 105480418 A CN105480418 A CN 105480418A CN 201510940762 A CN201510940762 A CN 201510940762A CN 105480418 A CN105480418 A CN 105480418A
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- wing
- aerial vehicle
- unmanned aerial
- fixed
- culvert type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- 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
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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
- B64U50/11—Propulsion using internal combustion piston engines
-
- 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)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention provides a ducted fixed-wing oil-electric hybrid unmanned aircraft, which belongs to the technical field of aircraft. The ducted fixed-wing oil-electric hybrid unmanned aircraft comprises a frame in which a main duct is arranged, wherein a main blade is arranged in the main duct; and two fixed wings are arranged on the two sides of the main duct. The ducted fixed-wing oil-electric hybrid unmanned aircraft provided by the invention has the advantages of convenient operation and long endurance and is widely applied to the field of pipeline inspection, forest fire prevention, geological survey, aerial photography and the like.
Description
Technical field
The present invention relates to a kind of culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle, belong to vehicle technology field.
Background technology
SUAV (small unmanned aerial vehicle), because cost is low, be easy to the features such as use, obtains using more and more widely in consumption and industrial circle.Unmanned aerial vehicle mainly contains three classes both at home and abroad at present, and the first kind is fixed-wing unmanned aerial vehicle, and Equations of The Second Kind is the unmanned autogyro of traditional type, and the 3rd class is electronic multiaxis unmanned aerial vehicle.The fixed-wing unmanned plane during flying efficiency of the first kind is high but cannot vertical takeoff and landing, and using area is limited; Traditional depopulated helicopter of Equations of The Second Kind can vertical takeoff and landing, but machinery and power transmission arrangment complicated, cost is high, safety is low and operation easier is large; 3rd class electronic multiaxis unmanned plane is simple to operate, but owing to adopting driven by power to make the flight time limited, about being generally half an hour.
Summary of the invention
Goal of the invention of the present invention is to provide a kind of culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle, and it is easy to operate, and the time that continues is long.
For achieving the above object, the invention provides a kind of culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle, it comprises frame 32, it is characterized in that, be provided with main duct 43 in frame 32, be provided with main blade 33 in described main duct 43, described frame 32 both sides are respectively arranged with a fixed-wing.
Preferably, be respectively arranged with little duct in the fixed-wing of frame 32 both sides, in little duct, be respectively arranged with little blade.
Preferably, the front of frame 32 and rear arrange leading edge and rear wing respectively, are respectively arranged with little duct in leading edge and rear wing, are respectively arranged with little blade in the little duct of leading edge and trailing edge.
Preferably, rear wing is provided with vee tail.
Preferably, main blade provides power by fuel engines.
Preferably, little blade motor provides power, and electrical motor provides the energy by battery.
Preferably, battery is chargeable battery.
Preferably, culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle also comprises electrical generator and power splitting mechanism, and the described power conversion sent out power splitting mechanism described and produced by fuel engines is drive the power of main blade and drive the power of electrical generator.
Preferably, the electricity that electrical generator produces can charge to chargeable battery after rectifying and wave-filtering.
Compared with prior art, the advantage of culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle provided by the invention is: main body duct adopt fuel engines for unmanned plane provide prevailing lift greatly to extend the boat of unmanned plane time, employing four little duct motor adjustment attitude is set at fixed-wing and fuselage forebody-afterbody outer end simultaneously.This special oil is electrically coupled mode and improves the energy efficiency of culvert type unmanned plane and control alerting ability, has the advantage of helicopter, fixed-wing and multiaxis rotor wing unmanned aerial vehicle concurrently.
Accompanying drawing explanation
Fig. 1 is culvert type hybrid power unmanned aerial vehicle contour structures schematic diagram provided by the invention;
Fig. 2 is the schematic diagram of the culvert type hybrid power unmanned aerial vehicle drive system that first embodiment of the invention provides;
Fig. 3 is the schematic diagram of the culvert type hybrid power unmanned aerial vehicle drive system that second embodiment of the invention provides;
Fig. 4 is the control system composition frame chart of culvert type hybrid power unmanned aerial vehicle provided by the invention.
Detailed description of the invention
Principle of work of the present invention is described in detail below in conjunction with drawings and Examples.Identical Reference numeral represents identical parts.
Fig. 1 is culvert type hybrid power unmanned aerial vehicle contour structures schematic diagram provided by the invention.As shown in Figure 1, culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle provided by the invention comprises frame 32, is provided with main duct 43 in frame 32, is provided with support 34, support 34 is provided with main blade 33 in described main duct 43.Described frame 32 both sides are respectively arranged with fixed-wing 35 and fixed-wing 36, and during flight, the fixed-wing of both sides produces aerodynamic lift, reduces the gas consumption rate of the fuel engines in main body duct.Be respectively arranged with little duct 43 and little duct 42 in the fixed-wing of frame 32 both sides, in little duct, be respectively arranged with little blade (not shown).The front and back of frame is provided with leading edge 38 and rear wing 37, is respectively arranged with little duct 41 and little duct 44, is respectively arranged with little blade (not shown) in the little duct of leading edge and rear wing 37 in leading edge 38 and rear wing 37.Rear wing is arranged empennage 29 and empennage 40, empennage 29 and empennage 40 V-shaped, in order to increase flight stability.Main blade provides power by fuel engines.Little blade motor provides power, and electrical motor provides the energy by battery.Battery is chargeable battery.Anti-twisted power flow deflector is set in culvert channel blade face, the rotating torque produced during in order to balance culvert channel blade or fan turns.Thrust flow deflector is set below culvert channel blade or fan simultaneously, produces the thrust that moves ahead.
Frame, leading edge, rear wing and empennage adopt aluminum alloy framework, and outer paving carbon fiber composite material, alleviates fuselage weight while proof strength.Support be carbon fiber bar for supporting fuel engines, as the active force of duct unmanned aerial vehicle, the fuel tank of driving engine is placed in the circumferential perimeter of main body duct.Composite propeller adopted by motor in four little ducts.
Fig. 2 is the schematic diagram of the culvert type hybrid power unmanned aerial vehicle drive system provided by the invention that first embodiment of the invention provides.In Fig. 2, driving engine 1 is arranged in fuselage (not shown), and has output shaft (or crank shaft) 2.Sun and planet gear 3 comprises sun gear 4, Ring gear 5, planet pinion gear 6 and pinion carrier 7.Crank shaft 2 is connected with pinion carrier 7.Electrical generator 8 comprises coil 9 and rotor 10.Rotor 10 is connected coil 9 simultaneously and is supported on fuselage with sun gear 4.An end of power universal drive shaft 11 is connected with Ring gear 5.In the drive system formed like this, sun and planet gear 3 can operate power distribution for receiving from driving engine to electrical generator 8 and the power universal drive shaft 11 as wheel axle drive shaft.Therefore, sun and planet gear 3 is used as power splitting mechanism.Power universal drive shaft 11 directly connects main screw.
Electrical generator 8, produces 3 cross streams electricity (u phase, v phase, w phase).The outgoing side of electrical generator 8 connects changer 13, and changer 13 at least has rectifier filer, and AC energy is converted to direct current energy by it, and is charged in storage battery 14.Storage battery provides electric energy to DC motor 15, DC motor 17, DC motor 19 and DC motor 19, DC motor 15, DC motor 17, DC motor 19 and the output shaft of DC motor 19 are connected four minor spiral oars 16 in four little ducts respectively, 18,20 and 22.DC motor, is converted into the rotation energy of rotor, and is supplied to motor output shaft by the direct current energy of acquisition.
The electric energy that battery 14 exports also is converted to various direct current (DC) through DC/DC changer 30, to be supplied to the control system 31 of unmanned plane.
Fig. 3 is the schematic diagram of the culvert type hybrid power unmanned aerial vehicle drive system that second embodiment of the invention provides; In Fig. 3, driving engine 1 is arranged in fuselage (not shown), and has output shaft 2.Output shaft 2 is connected with power universal drive shaft 11, and power universal drive shaft 11 directly connects main screw.Universal drive shaft 11 is provided with gear 45, gear 45 engages with the gear 46 rotated, and the output shaft of gear 46 is connected on the dynamical axis of electrical generator 8, and electrical generator 8 comprises coil 9 and rotor 10.Rotor 10 is connected coil 9 simultaneously and is supported on fuselage with sun gear 4.In the drive system formed like this, planetary wheel 45 is used as power splitting mechanism.
Electrical generator 8, produces 3 cross streams electricity (u phase, v phase, w phase).The outgoing side of electrical generator 8 connects changer 13, and changer 13 at least has rectifier filer, and AC energy is converted to direct current energy by it, and is charged in storage battery 14.Storage battery provides electric energy to DC motor 15, DC motor 17, DC motor 19 and DC motor 19, DC motor 15, DC motor 17, DC motor 19 and the output shaft of DC motor 19 are connected four minor spiral oars 16 in four little ducts respectively, 18,20 and 22.DC motor, is converted into the rotation energy of rotor, and is supplied to motor output shaft by the direct current energy of acquisition.
The electric energy that battery 14 exports also is converted to various direct current (DC) through DC/DC changer 30, to be supplied to the control system 31 of unmanned plane.
Fig. 4 is the control system composition frame chart of culvert type hybrid power unmanned aerial vehicle provided by the invention.As shown in Figure 4, control system comprises treater 29, also comprises the alternator current sensor 8c of the generator rotation angular transducer 8b of the rotational angle for detecting the rotor as input shaft and the amplitude (with the sizableness of electric current) for the alternating current that detects generation.That control system also includes the charge capacity of monitoring battery 14 and control the battery controller 14a of the discharge and recharge of battery 14.When charging to battery 14, the alternating current that electrical generator 8 produces part or all be converted to the direct current (DC) of assigned voltage by changer after import battery 14.When discharging from battery 14, direct current (DC) is supplied to four DC motor.Control system also comprises drive motor torque controller 15a for controlling the current value being supplied to DC motor 15, for detecting the drive motor rotation angle sensor 15b of the rotor turns angle of drive motor 15.Control system also comprises drive motor torque controller 17a for controlling the current value being supplied to DC motor 17, for detecting the drive motor rotation angle sensor 17b of the rotor turns angle of drive motor 15.Control system also comprises drive motor torque controller 19a for controlling the electric current being supplied to DC motor 19, for detecting the drive motor rotation angle sensor 19b of the rotor turns angle of drive motor 19.Control system also comprises drive motor torque controller 21a for controlling the current value being supplied to DC motor 21, for detecting the drive motor rotation angle sensor 21b of the rotor turns angle of drive motor 21.
Control system also comprises the navigation positioning system 23 for determining unmanned plane position, for determining the MEMS module of the course of unmanned plane, speed, attitude, and for carrying out the pick up camera of photographic images to target, also possess memory device, communication system 27 and antenna 28.Treater is CPU, and memory device comprises ROM, RAM, and specifically, controller, according to the instruction of satellite receiver from communication system, performs by CPU the program that is stored in advance in ROM and is temporarily stored in the flight then controlling unmanned plane in RAM.
The above is only done detailed description to embodiments of the present invention; should be understood that; for those skilled in the art; under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and modification, these improve and modification also should be considered as protection scope of the present invention.
Claims (9)
1. a culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle, it comprises frame (32), it is characterized in that, main duct (43) is provided with in frame (32), be provided with main blade (33) in described main duct (43), described frame (32) both sides are respectively arranged with a fixed-wing.
2. culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle according to claim 1, is characterized in that, be respectively arranged with little duct, be respectively arranged with little blade in little duct in the fixed-wing of frame (32) both sides.
3. culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle according to claim 2, it is characterized in that, front and the rear of frame (32) arrange leading edge and rear wing respectively, be respectively arranged with little duct in leading edge and rear wing, in the little duct of leading edge and rear wing, be respectively arranged with little blade.
4. culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle according to claim 3, is characterized in that, rear wing is provided with vee tail.
5., according to the arbitrary described culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle of claim 1-4, it is characterized in that, main blade provides power by fuel engines.
6. culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle according to claim 5, it is characterized in that, little blade motor provides power, and electrical motor provides the energy by battery.
7. culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle according to claim 6, it is characterized in that, battery is chargeable battery.
8. culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle according to claim 7, it is characterized in that, also comprise electrical generator and power splitting mechanism, the described power conversion sent out power splitting mechanism described and produced by fuel engines is drive the power of main blade and drive the power of electrical generator.
9. culvert type fixed-wing oil electric mixed dynamic unmanned aerial vehicle according to claim 8, it is characterized in that, the alternating current that electrical generator produces can charge to chargeable battery after rectifying and wave-filtering.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510940762.4A CN105480418A (en) | 2015-12-17 | 2015-12-17 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510940762.4A CN105480418A (en) | 2015-12-17 | 2015-12-17 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
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| CN105480418A true CN105480418A (en) | 2016-04-13 |
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| CN201510940762.4A Pending CN105480418A (en) | 2015-12-17 | 2015-12-17 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923153A (en) * | 2016-05-21 | 2016-09-07 | 辽宁辽飞航空科技有限公司 | Fixed-wing aircraft capable of vertically taking off and landing |
| CN106603979A (en) * | 2016-12-14 | 2017-04-26 | 天津昕黎科技有限公司 | Unmanned aerial vehicle image data real-time processing system and processing method based on electromechanics |
| CN107640324A (en) * | 2017-10-15 | 2018-01-30 | 天津飞眼无人机科技有限公司 | Oil electric mixed dynamic rotor wing unmanned aerial vehicle |
| CN107640318A (en) * | 2017-10-15 | 2018-01-30 | 天津飞眼无人机科技有限公司 | Oil electric mixed dynamic fixed-wing unmanned plane |
| CN109421924A (en) * | 2017-08-28 | 2019-03-05 | 本田技研工业株式会社 | Multirotor helicopter |
| WO2020098170A1 (en) * | 2019-02-23 | 2020-05-22 | 伍景 | Aerial inspection vehicle |
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| US1662406A (en) * | 1928-01-10 | 1928-03-13 | Elmer H Thompson | Airplane |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
| CN104163241A (en) * | 2014-08-12 | 2014-11-26 | 中国航空工业经济技术研究院 | Unmanned logistics helicopter |
| CN104260875A (en) * | 2014-09-19 | 2015-01-07 | 苏州天益航空科技有限公司 | Collision-resistant structure of agricultural plant protection unmanned aerial vehicle |
| CN104843181A (en) * | 2015-04-10 | 2015-08-19 | 桂林航龙科讯电子技术有限公司 | Petrol-electric hybrid power fixed wing vertical take-off and landing unmanned plane system |
| CN205418106U (en) * | 2015-12-17 | 2016-08-03 | 北京猎鹰无人机科技有限公司 | Duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle |
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Patent Citations (6)
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| US1662406A (en) * | 1928-01-10 | 1928-03-13 | Elmer H Thompson | Airplane |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
| CN104163241A (en) * | 2014-08-12 | 2014-11-26 | 中国航空工业经济技术研究院 | Unmanned logistics helicopter |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923153A (en) * | 2016-05-21 | 2016-09-07 | 辽宁辽飞航空科技有限公司 | Fixed-wing aircraft capable of vertically taking off and landing |
| CN106603979A (en) * | 2016-12-14 | 2017-04-26 | 天津昕黎科技有限公司 | Unmanned aerial vehicle image data real-time processing system and processing method based on electromechanics |
| CN109421924A (en) * | 2017-08-28 | 2019-03-05 | 本田技研工业株式会社 | Multirotor helicopter |
| CN107640324A (en) * | 2017-10-15 | 2018-01-30 | 天津飞眼无人机科技有限公司 | Oil electric mixed dynamic rotor wing unmanned aerial vehicle |
| CN107640318A (en) * | 2017-10-15 | 2018-01-30 | 天津飞眼无人机科技有限公司 | Oil electric mixed dynamic fixed-wing unmanned plane |
| WO2020098170A1 (en) * | 2019-02-23 | 2020-05-22 | 伍景 | Aerial inspection vehicle |
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Application publication date: 20160413 |