CN205418106U - Duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle - Google Patents
Duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle Download PDFInfo
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- CN205418106U CN205418106U CN201521049781.XU CN201521049781U CN205418106U CN 205418106 U CN205418106 U CN 205418106U CN 201521049781 U CN201521049781 U CN 201521049781U CN 205418106 U CN205418106 U CN 205418106U
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Abstract
The utility model provides a duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle belongs to aircraft technical field. Hybrid unmanned aerial vehicle includes the frame, with being provided with main duct in the frame, be provided with main paddle in the main duct, main duct both sides set up two stationary vanes. The utility model provides a hybrid unmanned aerial vehicle convenient operation, continuous line time is long. The wide application is in fields such as pipeline inspection, forest fire prevention, geology reconnaissance, aviation shootings.
Description
Technical field
This utility model relates to a kind of culvert type fixed-wing oil electric mixed dynamic unmanned plane, belongs to vehicle technology field.
Background technology
SUAV, due to low cost, the feature such as easy of use, obtains using the most widely in consumption and industrial circle.Unmanned plane mainly has three classes the most both at home and abroad, and the first kind is fixed-wing unmanned plane, and Equations of The Second Kind is the unmanned helicopter of traditional type, and the 3rd class is electronic multiaxis unmanned plane.The fixed-wing unmanned plane during flying efficiency of the first kind high but cannot VTOL, using area is limited；Traditional depopulated helicopter of Equations of The Second Kind can VTOL, but machinery and power transmission arrangment are complicated, and cost is high, safety is low and operation easier is big；3rd class electronic multiaxis unmanned plane is simple to operate, but owing to using driven by power to make the flight time limited, generally about half an hour.
Summary of the invention
Goal of the invention of the present utility model is to provide a kind of culvert type fixed-wing oil electric mixed dynamic unmanned plane, and it is easy to operate, and the time that continues is long.
For achieving the above object, this utility model provides a kind of culvert type fixed-wing oil electric mixed dynamic unmanned plane, and it includes frame 32, it is characterized in that, being 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, the fixed-wing of frame 32 both sides is respectively arranged with little duct, in little duct, is respectively arranged with little blade.
Preferably, the front and back of frame 32 is respectively arranged with little blade in being respectively provided with in leading edge and rear wing, leading edge and rear wing and being respectively arranged with the little duct of little duct, leading edge and trailing edge.
Preferably, rear wing is provided with vee tail.
Preferably, main blade is provided power by fuel engines.
Preferably, little blade is provided power, motor to be provided the energy by battery by motor.
Preferably, battery is rechargeable battery.
Preferably, culvert type fixed-wing oil electric mixed dynamic unmanned plane also includes electromotor and power splitting mechanism, and power produced by fuel engines is converted to drive the power of main blade and drive the power of electromotor by described motive distributor gear.
Preferably, can charge to rechargeable battery after electric rectified filtering produced by electromotor.
Compared with prior art, the advantage of culvert type fixed-wing oil electric mixed dynamic unmanned plane that this utility model provides is: when main body duct uses fuel engines to provide prevailing lift to be greatly prolonged the boat of unmanned plane for unmanned plane, arranges four little duct motors of employing at fixed-wing and fuselage forebody-afterbody outer end simultaneously and adjusts attitudes.This special oil is electrically coupled mode and improves the energy efficiency of culvert type unmanned plane and control motility, has helicopter, fixed-wing and the advantage of multiaxis rotor wing unmanned aerial vehicle concurrently.
Accompanying drawing explanation
Fig. 1 is the culvert type hybrid power unmanned plane contour structures schematic diagram that this utility model provides；
Fig. 2 is the schematic diagram of the culvert type hybrid power unmanned plane drive system that this utility model first embodiment provides；
Fig. 3 is the schematic diagram of the culvert type hybrid power unmanned plane drive system that this utility model the second embodiment provides；
Fig. 4 is the control system composition frame chart of the culvert type hybrid power unmanned plane that this utility model provides.
Detailed description of the invention
Below in conjunction with the accompanying drawings and embodiment describe in detail operation principle of the present utility model.Identical reference represents identical parts.
Fig. 1 is the culvert type hybrid power unmanned plane contour structures schematic diagram that this utility model provides.As it is shown in figure 1, the culvert type fixed-wing oil electric mixed dynamic unmanned plane that this utility model provides includes frame 32, frame 32 is provided with main duct 43, is provided with support 34 in described main duct 43, support 34 is provided with main blade 33.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, the oil consumption rate of the fuel engines in reduction main body duct.The fixed-wing of frame 32 both sides is respectively arranged with little duct 43 and little duct 42, in little duct, is respectively arranged with little blade (not shown).The front and back of frame is respectively arranged with little blade (not shown) in being provided with the little duct being respectively arranged with little duct 41 and little duct 44, leading edge and rear wing 37 in leading edge 38 and rear wing 37, leading edge 38 and rear wing 37.It is V-shaped that empennage 29 and empennage 40, empennage 29 and empennage 40 are set, in order to increase flight stability on rear wing.Main blade is provided power by fuel engines.Little blade is provided power, motor to be provided the energy by battery by motor.Battery is rechargeable 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 rotation.Thrust flow deflector is provided below at culvert channel blade or fan simultaneously, produces the thrust that moves ahead.
Frame, leading edge, rear wing and empennage use aluminum alloy framework, outer paving carbon fibre composite, alleviate 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 electromotor 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 plane drive system that this utility model that this utility model first embodiment provides provides.In Fig. 2, electromotor 1 is arranged in fuselage (not shown), and has output shaft (or crank axle) 2.Planetary gears 3 includes central gear 4, ring gear 5, planet pinion 6 and planet carrier 7.Crank axle 2 is connected with planet carrier 7.Electromotor 8 includes coil 9 and rotor 10.Rotor 10 is connected coil 9 simultaneously and is supported on fuselage with central gear 4.One end of power universal drive shaft 11 is connected with ring gear 5.In the drive system so constituted, planetary gears 3 is operable is used for distributing to the power received from electromotor electromotor 8 and the power universal drive shaft 11 as wheel drive shaft.Therefore, planetary gears 3 is used as power splitting mechanism.Power universal drive shaft 11 is directly connected to main screw.
Electromotor 8, produces 3 cross streams electricity (u phase, v phase, w phase).The outlet side of electromotor 8 connects changer 13, and changer 13 at least has rectifier filter, and AC energy is converted to direct current energy by it, and is charged in accumulator 14.Accumulator provides electric energy to dc motor 15, dc motor 17, dc motor 19 and dc motor 19, the output shaft of dc motor 15, dc motor 17, dc motor 19 and dc motor 19 connects four minor spiral oars 16 in four little ducts respectively, 18,20 and 22.Dc motor, is converted into the direct current energy of acquisition the rotation energy of rotor, and is supplied to motor output shaft.
The electric energy that battery 14 is exported also is converted to various unidirectional current 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 plane drive system that this utility model the second embodiment provides；In Fig. 3, electromotor 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 is directly connected to main screw.Being provided with gear 45 on universal drive shaft 11, gear 45 engages with the gear 46 rotated, and the output shaft of gear 46 is connected on the line shaft of electromotor 8, and electromotor 8 includes coil 9 and rotor 10.Rotor 10 is connected coil 9 simultaneously and is supported on fuselage with central gear 4.In the drive system so constituted, planetary gear 45 is used as power splitting mechanism.
Electromotor 8, produces 3 cross streams electricity (u phase, v phase, w phase).The outlet side of electromotor 8 connects changer 13, and changer 13 at least has rectifier filter, and AC energy is converted to direct current energy by it, and is charged in accumulator 14.Accumulator provides electric energy to dc motor 15, dc motor 17, dc motor 19 and dc motor 19, the output shaft of dc motor 15, dc motor 17, dc motor 19 and dc motor 19 connects four minor spiral oars 16 in four little ducts respectively, 18,20 and 22.Dc motor, is converted into the direct current energy of acquisition the rotation energy of rotor, and is supplied to motor output shaft.
The electric energy that battery 14 is exported also is converted to various unidirectional current 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 the culvert type hybrid power unmanned plane that this utility model provides.As shown in Figure 4, control system includes processor 29, also includes for detection as the generator rotation angular transducer 8b of the rotational angle of the rotor of power shaft and for detecting the alternator current sensor 8c of the amplitude (with the sizableness of electric current) of the alternating current of generation.The battery controller 14a of discharge and recharge that is that control system also includes the charge capacity of monitoring battery 14 and that control battery 14.When battery 14 charges, alternating current produced by electromotor 8 part or all be converted to the unidirectional current of assigned voltage by changer after import battery 14.When battery 14 discharges, unidirectional current supplies to four dc motors.Control system also includes for controlling supply to the drive motor torque controller 15a of the current value of dc motor 15, for detecting the drive motor rotation angle sensor 15b of the rotor rotational angle of drive motor 15.Control system also includes for controlling supply to the drive motor torque controller 17a of the current value of dc motor 17, for detecting the drive motor rotation angle sensor 17b of the rotor rotational angle of drive motor 15.Control system also includes for controlling supply to the drive motor torque controller 19a of the electric current of dc motor 19, for detecting the drive motor rotation angle sensor 19b of the rotor rotational angle of drive motor 19.Control system also includes for controlling supply to the drive motor torque controller 21a of the current value of dc motor 21, for detecting the drive motor rotation angle sensor 21b of the rotor rotational angle of drive motor 21.
Control system also includes 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 target carries out shooting the video camera of image, is also equipped with memorizer, communication system 27 and antenna 28.Processor is CPU, and memorizer includes ROM, RAM, and specifically, controller is also temporarily stored in RAM the flight then controlling unmanned plane according to the instruction of satellite receiver from communication system, the program being previously stored in ROM by CPU execution.
The above is only to describe embodiment of the present utility model in detail; should be understood that; for those skilled in the art; on the premise of without departing from this utility model know-why; can also make some improvement and modification, these improve and modification also should be regarded as protection domain of the present utility model.
Claims (9)
1. a culvert type fixed-wing oil electric mixed dynamic unmanned plane, it includes frame (32), it is characterized in that, frame (32) is provided with main duct (43), being provided with main blade (33) in described main duct (43), described frame (32) both sides are respectively arranged with a fixed-wing.
Culvert type fixed-wing oil electric mixed dynamic unmanned plane the most according to claim 1, it is characterised in that be respectively arranged with little duct in the fixed-wing of frame (32) both sides, be respectively arranged with little blade in little duct.
Culvert type fixed-wing oil electric mixed dynamic unmanned plane the most according to claim 2, it is characterized in that, the front and back of frame (32) is respectively provided with in leading edge and rear wing, leading edge and rear wing in being respectively arranged with the little duct of little duct, leading edge and rear wing and is respectively arranged with little blade.
Culvert type fixed-wing oil electric mixed dynamic unmanned plane the most according to claim 3, it is characterised in that be provided with vee tail on rear wing.
5. according to the arbitrary described culvert type fixed-wing oil electric mixed dynamic unmanned plane of claim 1-4, it is characterised in that main blade is provided power by fuel engines.
Culvert type fixed-wing oil electric mixed dynamic unmanned plane the most according to claim 5, it is characterised in that little blade is provided power, motor to be provided the energy by battery by motor.
Culvert type fixed-wing oil electric mixed dynamic unmanned plane the most according to claim 6, it is characterised in that battery is rechargeable battery.
Culvert type fixed-wing oil electric mixed dynamic unmanned plane the most according to claim 7, it is characterized in that, also including electromotor and power splitting mechanism, power produced by fuel engines is converted to drive the power of main blade and drive the power of electromotor by described power splitting mechanism.
Culvert type fixed-wing oil electric mixed dynamic unmanned plane the most according to claim 8, it is characterised in that can charge to rechargeable battery after the rectified filtering of alternating current produced by electromotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521049781.XU CN205418106U (en) | 2015-12-17 | 2015-12-17 | Duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521049781.XU CN205418106U (en) | 2015-12-17 | 2015-12-17 | Duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle |
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| CN205418106U true CN205418106U (en) | 2016-08-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201521049781.XU Expired - Fee Related CN205418106U (en) | 2015-12-17 | 2015-12-17 | Duct formula stationary vane oil -electricity hybrid vehicle unmanned aerial vehicle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105480418A (en) * | 2015-12-17 | 2016-04-13 | 北京猎鹰无人机科技有限公司 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
| 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 |
| CN110091997A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure of the reduction rotary wings vertical take-off and landing drone main screw lift flown based on oil electrification |
| CN111268117A (en) * | 2020-02-29 | 2020-06-12 | 南京航空航天大学 | A multi-ducted aircraft with constant lift and its working method |
-
2015
- 2015-12-17 CN CN201521049781.XU patent/CN205418106U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105480418A (en) * | 2015-12-17 | 2016-04-13 | 北京猎鹰无人机科技有限公司 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
| 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 |
| CN110091997A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure of the reduction rotary wings vertical take-off and landing drone main screw lift flown based on oil electrification |
| CN111268117A (en) * | 2020-02-29 | 2020-06-12 | 南京航空航天大学 | A multi-ducted aircraft with constant lift and its working method |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160803 |
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| CF01 | Termination of patent right due to non-payment of annual fee |