CN204606221U - A kind of many rotor fuel-electrics energy conversion aircraft - Google Patents
A kind of many rotor fuel-electrics energy conversion aircraft Download PDFInfo
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- CN204606221U CN204606221U CN201520284718.8U CN201520284718U CN204606221U CN 204606221 U CN204606221 U CN 204606221U CN 201520284718 U CN201520284718 U CN 201520284718U CN 204606221 U CN204606221 U CN 204606221U
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Abstract
The utility model discloses a kind of many rotor fuel-electrics energy conversion aircraft, belong to unmanned vehicle technical field.The utility model comprises aircraft body and the switching mechanism of oil electricity; Described aircraft body comprises battery, body, the horn stretched out along organism level direction and the support being arranged at organism bottom, and horn is provided with screw propeller away from one end of body, and the lower end of support is connected with base; Described oil electricity switching mechanism is positioned on base, this oily electric switching mechanism comprises fuel tank, driving engine, power wheel, driving band, electrical generator and power transmission line, the oil pipeline of fuel tank is connected with driving engine, driving engine and electrical generator are provided with power wheel, driving engine upper driving wheel is rotated by driving band drive electrical generators upper driving wheel, and electrical generator is electrically connected with battery by power transmission line.The utility model utilizes driving engine and electrical generator to coordinate the electric energy needed for aircraft by the chemical energy of oil, ensure that aircraft has effect of well continuing a journey.
Description
Technical field
The utility model relates to unmanned vehicle technical field, more particularly, relates to a kind of many rotor fuel-electrics energy conversion aircraft.
Background technology
The aircraft used in the world at present mainly contains autogyro, fixed wing aircraft, autogiro, propeller-parachuting, dynamic-delta-wing aircraft etc., in recent years because multi-rotor aerocraft has extraordinary manoevreability, alerting ability, easily can realize the advantage taking off vertically, land, hover, obtain at model airplane circle and apply more and more widely.
But existing multi-rotor aerocraft still also exists the defects such as such as cruise duration is short.This is mainly because multi-rotor aerocraft adopts powered battery, and aircraft performs the electric energy that airflight task needs consumption a large amount of, small-capacity cells cannot meet continuation of the journey requirement at all, use high potential, high-capacity battery again can be overweight because of battery, cause aircraft maneuverability poor, and the cruise duration of aircraft cannot be promoted equally.Therefore, the simple electric energy that uses more and more can not meet the continuation of the journey requirement of aircraft as the propulsion source of aircraft.
Through retrieval, Chinese Patent Application No. 201110411320.2, the applying date is on December 2nd, 2011, and invention and created name is: many rotor fuel-electric hybrid aircrafts; This application case comprises electronic governor, flight control system, fuel engines, electrical motor, battery pack, the fuselage of many arbors composition and multiple screw propeller, described screw propeller is divided into the first screw propeller adopting fuel engines to drive and the second screw propeller adopting direct motor drive, described multiple first screw propeller provides the prevailing lift of whole aircraft, and described multiple second screw propeller provides that whole aircraft balances, the fraction lift of direction and whole aircraft.This application case is provided by oil-burning machine by most lift, and fraction lift and balance control, direction controlling, height control to be provided by electrical motor.Realize the mixing of oil electricity, make aircraft have the heavy load ability of the manoevreability of pure Electric aircraft, alerting ability and oil-burning machine.But the structure of the whole aircraft of this application case is more complicated, and need design con-trol system to control respectively oil-burning machine, electrical motor, control difficulty and cost high.
Summary of the invention
1. the utility model technical matters that will solve
The deficiency that the cruise duration that the purpose of this utility model is to overcome existing multi-rotor aerocraft cannot meet the demands, provides a kind of many rotor fuel-electrics energy conversion aircraft; The utility model, by arranging oily electric switching mechanism, utilizes driving engine and electrical generator to coordinate the electric energy needed for aircraft by the chemical energy of oil, ensure that aircraft has effect of well continuing a journey.
2. technical scheme
For achieving the above object, the technical scheme that the utility model provides is:
One many rotor fuel-electrics energy conversion aircraft of the present utility model, comprises aircraft body and the switching mechanism of oil electricity; Described aircraft body comprises battery, body, the horn stretched out along organism level direction and the support being arranged at organism bottom, and horn is provided with screw propeller away from one end of body, and the lower end of support is connected with base; Described oil electricity switching mechanism is positioned on base, this oily electric switching mechanism comprises fuel tank, driving engine, power wheel, driving band, electrical generator and power transmission line, the oil pipeline of fuel tank is connected with driving engine, driving engine and electrical generator are provided with power wheel, driving engine upper driving wheel is rotated by driving band drive electrical generators upper driving wheel, and described electrical generator is electrically connected with battery by power transmission line.
Further improve as the utility model, described driving engine adopts 46 grades of S46A/A II two-cycle engines.
Further improve as the utility model, described fuel tank is provided with 2, and 2 fuel tanks are distributed in the both sides of driving engine.
Further improve as the utility model, described support is flexibly connected with base.
Further improve as the utility model, described organism bottom is serially connected with carry bar.
3. beneficial effect
The technical scheme adopting the utility model to provide, compared with existing known technology, has following beneficial effect:
(1) one many rotor fuel-electrics energy conversion aircraft of the present utility model, by arranging oily electric switching mechanism, driving engine and electrical generator is utilized to coordinate the electric energy needed for aircraft by the chemical energy of oil, when performing flight operation for aircraft, overcome the simple electric energy that uses as propulsion source, aircraft is short for cruise duration, and uses engine petrol for power, the alerting ability of aircraft and the manoevreability problem again not as taking electric energy as power;
(2) one many rotor fuel-electrics energy conversion aircraft of the present utility model, its driving engine adopts 46 grades of S46A/A II two-cycle engines, this model engine weight only has 450g, rotating speed can reach 2000 ~ 17500r/min, can meet completely and carry out the requirement of electric energy conversion for aircraft, and the load-carrying of unlikely too much increase aircraft, ensure that the manoevreability of aircraft flight.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of many rotor fuel-electrics energy conversion aircraft of the present utility model.
Label declaration in schematic diagram:
1, battery; 2, body; 21, horn; 22, carry bar; 23, support; 24, base; 31, motor cabinet; 32, motor; 33, screw propeller; 41, fuel tank; 42, driving engine; 431, power wheel; 432, driving band; 44, electrical generator; 45, power transmission line.
Detailed description of the invention
For understanding content of the present utility model further, in conjunction with the accompanying drawings and embodiments the utility model is described in detail.
Embodiment 1
Referring to Fig. 1, one many rotor fuel-electrics energy conversion aircraft of the present embodiment, comprises aircraft body and the switching mechanism of oil electricity.Wherein, described aircraft body comprises battery 1, body 2,4 horns 21 stretched out along body 2 horizontal direction, is serially connected with carry bar 22 bottom body 2, and is arranged at the support 23 bottom body 2.Flight-control component such as master controller, the IMU Attitude Calculation module etc. of aircraft are arranged on body 2, horn 21 adopts folding structure, this horn 21 is provided with motor cabinet 31 away from one end of body 2, motor cabinet 31 is connected with motor 32, the output shaft of this motor 32 connects screw propeller 33, motor 32 controls screw propeller 33 and rotates, for aircraft provides flight lift.Described carry bar 22 is for devices such as carry GPS navigator, camera, search lamps, actual when using, the function of extended flight device.The lower end of described support 23 is connected with base 24, and this base 24 is for carrying oily electric switching mechanism, and the present embodiment arranges support 23 and is flexibly connected with base 24, can be convenient to the assembling of oily electric switching mechanism and change.
Described oil electricity switching mechanism comprises fuel tank 41, driving engine 42, power wheel 431, driving band 432, electrical generator 44 and power transmission line 45.Described fuel tank 41 is provided with 2, and 2 fuel tanks 41 are distributed in the both sides of driving engine 42.The compound of splendid attire methyl alcohol and castor oil in fuel tank 41, the oil pipeline of this fuel tank 41 is connected with driving engine 42, driving engine 42 and electrical generator 44 are provided with power wheel 431, driving engine 42 upper driving wheel 431 is rotated by driving band 432 drive electrical generators 44 upper driving wheel 431, and then drives electrical generator 44 to produce electric energy.Described electrical generator 44 is electrically connected with battery 1 by power transmission line 45, is battery 1 transmission of electric energy.
The present embodiment is by arranging oily electric switching mechanism, driving engine 42 and electrical generator 44 is utilized to coordinate the electric energy of the chemical energy of oil for aircraft needs, when performing flight operation for aircraft, overcome the simple electric energy that uses as propulsion source, aircraft is short for cruise duration, and using engine petrol for power, the alerting ability of aircraft and the manoevreability problem again not as taking electric energy as power, aircraft is extended cruise duration greatly.As for the oily electric switching mechanism of increase, the problem that aircraft load-carrying increases, the driving engine 42 of the present embodiment adopts three leaf boards, 46 grades of S46A/A II two-cycle engines, this model engine weight only has 450g, rotating speed can reach 2000 ~ 17500r/min, can meet completely and carry out the requirement of electric energy conversion for aircraft, and the load-carrying of unlikely too much increase aircraft.Simultaneously, the body 2 of the present embodiment, horn 21, carry bar 22, support 23, base 24 all adopt carbon fibre material to prepare, carbon fibre material is a kind of high-temperature fibre with very high strength and modulus, the main body rack of unmanned plane adopts carbon fibre material, can ensure that unmanned plane frame strength is high and lightweight, ensure that aircraft has good alerting ability and manoevreability by above-mentioned design.
Schematically above be described the utility model and embodiment thereof, this description does not have restricted, and also just one of the embodiment of the present utility model shown in accompanying drawing, actual structure is not limited thereto.So, if those of ordinary skill in the art enlightens by it, when not departing from the utility model and creating aim, design the frame mode similar to this technical scheme and embodiment without creationary, protection domain of the present utility model all should be belonged to.
Claims (5)
1. the energy conversion of rotor fuel-electric a more than aircraft, comprises aircraft body, it is characterized in that: also comprise oily electric switching mechanism, described aircraft body comprises battery (1), body (2), the horn (21) stretched out along body (2) horizontal direction and is arranged at the support (23) of body (2) bottom, horn (21) is provided with screw propeller (33) away from one end of body (2), and the lower end of support (23) is connected with base (24), described oil electricity switching mechanism is positioned on base (24), this oily electric switching mechanism comprises fuel tank (41), driving engine (42), power wheel (431), driving band (432), electrical generator (44) and power transmission line (45), the oil pipeline of fuel tank (41) is connected with driving engine (42), driving engine (42) and electrical generator (44) are provided with power wheel (431), driving engine (42) upper driving wheel (431) is rotated by driving band (432) drive electrical generators (44) upper driving wheel (431), described electrical generator (44) is electrically connected with battery (1) by power transmission line (45).
2. one many rotor fuel-electrics energy conversion aircraft according to claim 1, is characterized in that: described driving engine (42) adopts 46 grades of S46A/A II two-cycle engines.
3. one many rotor fuel-electrics energy conversion aircraft according to claim 2, is characterized in that: described fuel tank (41) is provided with 2, and 2 fuel tanks (41) are distributed in the both sides of driving engine (42).
4. one many rotor fuel-electrics energy conversion aircraft according to claim 3, is characterized in that: described support (23) is flexibly connected with base (24).
5. one many rotor fuel-electrics energy conversion aircraft according to claim 4, is characterized in that: described body (2) bottom is serially connected with carry bar (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520284718.8U CN204606221U (en) | 2015-05-05 | 2015-05-05 | A kind of many rotor fuel-electrics energy conversion aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520284718.8U CN204606221U (en) | 2015-05-05 | 2015-05-05 | A kind of many rotor fuel-electrics energy conversion aircraft |
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| Publication Number | Publication Date |
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| CN204606221U true CN204606221U (en) | 2015-09-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520284718.8U Expired - Fee Related CN204606221U (en) | 2015-05-05 | 2015-05-05 | A kind of many rotor fuel-electrics energy conversion aircraft |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105129079A (en) * | 2015-09-29 | 2015-12-09 | 郝建新 | Hybrid power long-endurance multi-shaft air vehicle |
| CN105539828A (en) * | 2015-12-08 | 2016-05-04 | 陈蜀乔 | Petrol-electric hybrid multi-rotor aerial vehicle capable of self electricity generation |
| CN105711826A (en) * | 2016-03-31 | 2016-06-29 | 陈萌 | Tandem type oil-electric hybrid unmanned aerial vehicle |
| CN107176302A (en) * | 2016-03-10 | 2017-09-19 | 珠海市皓翔飞行器有限公司 | Unmanned plane |
| CN107284668A (en) * | 2017-07-20 | 2017-10-24 | 蜂巢航宇科技（北京）有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107914870A (en) * | 2017-11-22 | 2018-04-17 | 东北石油大学 | A kind of logistics distribution rotor robot |
| CN109319142A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Unmanned vehicle with closed type fuselage |
| CN109319145A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | The electric mixed unmanned plane of oil with closed type fuselage |
| CN109319143A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Unmanned plane with closed type fuselage |
| CN109319146A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Novel flight equipment |
| CN109319144A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Aircraft with closed type fuselage |
| CN109319141A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Oily cutting with closed type fuselage changes aircraft |
| CN110481767A (en) * | 2019-08-28 | 2019-11-22 | 三峡大学 | A kind of foldable varying pitch quadrotor and application method based on oil electric mixed dynamic |
| WO2019233060A1 (en) * | 2018-06-04 | 2019-12-12 | 广州市华科尔科技股份有限公司 | Control system and control method for oil-electric hybrid multi-rotor unmanned aerial vehicle |
| WO2021189164A1 (en) * | 2020-03-22 | 2021-09-30 | 南京唐壹信息科技有限公司 | Transportation unmanned aerial vehicle with buffering undercarriage |
-
2015
- 2015-05-05 CN CN201520284718.8U patent/CN204606221U/en not_active Expired - Fee Related
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105129079A (en) * | 2015-09-29 | 2015-12-09 | 郝建新 | Hybrid power long-endurance multi-shaft air vehicle |
| CN105539828A (en) * | 2015-12-08 | 2016-05-04 | 陈蜀乔 | Petrol-electric hybrid multi-rotor aerial vehicle capable of self electricity generation |
| CN107176302A (en) * | 2016-03-10 | 2017-09-19 | 珠海市皓翔飞行器有限公司 | Unmanned plane |
| CN105711826A (en) * | 2016-03-31 | 2016-06-29 | 陈萌 | Tandem type oil-electric hybrid unmanned aerial vehicle |
| CN107284668A (en) * | 2017-07-20 | 2017-10-24 | 蜂巢航宇科技（北京）有限公司 | Multi-rotor unmanned aerial vehicle |
| CN107914870A (en) * | 2017-11-22 | 2018-04-17 | 东北石油大学 | A kind of logistics distribution rotor robot |
| CN107914870B (en) * | 2017-11-22 | 2020-07-28 | 东北石油大学 | Rotor robot for logistics distribution |
| WO2019233060A1 (en) * | 2018-06-04 | 2019-12-12 | 广州市华科尔科技股份有限公司 | Control system and control method for oil-electric hybrid multi-rotor unmanned aerial vehicle |
| CN109319143A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Unmanned plane with closed type fuselage |
| CN109319146A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Novel flight equipment |
| CN109319144A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Aircraft with closed type fuselage |
| CN109319141A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Oily cutting with closed type fuselage changes aircraft |
| CN109319145A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | The electric mixed unmanned plane of oil with closed type fuselage |
| CN109319142A (en) * | 2018-08-29 | 2019-02-12 | 易瓦特科技股份公司 | Unmanned vehicle with closed type fuselage |
| CN110481767A (en) * | 2019-08-28 | 2019-11-22 | 三峡大学 | A kind of foldable varying pitch quadrotor and application method based on oil electric mixed dynamic |
| WO2021189164A1 (en) * | 2020-03-22 | 2021-09-30 | 南京唐壹信息科技有限公司 | Transportation unmanned aerial vehicle with buffering undercarriage |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20150902 Termination date: 20160505 |