CN105329448B - A kind of vertical take-off and landing drone oil electric mixed dynamic system - Google Patents
A kind of vertical take-off and landing drone oil electric mixed dynamic system Download PDFInfo
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- CN105329448B CN105329448B CN201510834126.3A CN201510834126A CN105329448B CN 105329448 B CN105329448 B CN 105329448B CN 201510834126 A CN201510834126 A CN 201510834126A CN 105329448 B CN105329448 B CN 105329448B
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- ducted fan
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Abstract
The invention discloses a kind of vertical take-off and landing drone oil electric mixed dynamic system.The vertical take-off and landing drone oil electric mixed dynamic system includes：Turboshaft engine (5), it is sequentially connected with the first lift ducted fan (1), the second lift ducted fan (2) and postposition thrust ducted fan (3) respectively；Genemotor (6), it is sequentially connected with the preposition trim ducted fan (4)；Wherein, the turboshaft engine (5) is used to drive the first lift ducted fan (1), the second lift ducted fan (2) and postposition thrust ducted fan (3) work；The genemotor (6) is used to drive preposition trim ducted fan (4) work.Using this structure, relative to powerful engine is used in the prior art, transmission mechanism of the invention is relatively fewer, relative to using pure electric vehicle engine mode in the prior art, using the teaching of the invention it is possible to provide the enough power of unmanned plane.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, and in particular to a kind of vertical take-off and landing drone oil electric mixed dynamic system.
Background technology
The driving of four ducted fans is configured to boat-carrying unmanned plane, it is necessary to be configured on unmanned plane corresponding in order to realize
Dynamical system；According to routine, dynamical system can use oil two class allocation plan of dynamic engine and genemotor；Such as use pure oil
Dynamic engine options, since the inner space of unmanned plane is limited, most real scheme is：Using a powerful engine,
The power of engine is distributed according to need onto four ducted fans by complicated transmission mechanism, such scheme, a basis
The transmission mechanism of theory of mechanics design is necessarily extremely complex and the larger weight of attachment of band and higher failure rate, and two
Carry out 1/10th of the power output deficiency full power when unmanned plane is in flat winged, the efficiency of dynamical system will be extremely low；Such as adopt
With pure electric vehicle engine options, since unmanned plane requires VTOL, inevitable requirement configures powerful motor, however, electric
The power to weight ratio of dynamic engine is only 1/the tens of the dynamic engine of oil, it means that, for the unmanned plane of same Gross Weight Takeoff,
Genemotor weight will be far above the dynamic engine weight of oil, further, since unmanned plane requires long endurance (when small more than 10), need
Want genemotor to be equipped with substantial amounts of battery, add the weight of whole unmanned plane, and it is difficult to realize.
Thus, it is desirable to have a kind of technical solution is come at least one above problem for overcoming or at least mitigating the prior art.
The content of the invention
It is an object of the invention to provide a kind of vertical take-off and landing drone oil electric mixed dynamic system to overcome or at least subtract
Light at least one above problem of the prior art.
To achieve the above object, the present invention provides a kind of vertical take-off and landing drone oil electric mixed dynamic system, for hanging down
Straight landing unmanned plane, the vertical take-off and landing drone include fuselage, the first lift ducted fan being arranged on fuselage, second liter
Power ducted fan, postposition thrust ducted fan and preposition trim ducted fan, the vertical take-off and landing drone oil electricity mixing are dynamic
Force system includes：Turboshaft engine, the turboshaft engine respectively with the first lift ducted fan, the second lift ducted fan with
And postposition thrust ducted fan is sequentially connected；Genemotor, the genemotor are passed with the preposition trim ducted fan
Dynamic connection；Wherein, the turboshaft engine be used for drive the first lift ducted fan, the second lift ducted fan and after
Put the work of thrust ducted fan；The genemotor is used to drive the preposition trim ducted fan work.
Preferably, the vertical take-off and landing drone oil electric mixed dynamic system further comprises component force device, the component
Device has an input terminal and three output terminals, and the input terminal of the component force device connects with turboshaft engine transmission
Connect, the output terminal of the component force device is contained with the first lift ducted fan, the second lift ducted fan, postposition thrust respectively
Road fan is sequentially connected；The component force device is used to the power of the turboshaft engine is respectively allocated to institute according to preset ratio
State in the first lift ducted fan, the second lift ducted fan, postposition thrust ducted fan.
Preferably, the component force device makes the first lift ducted fan and the acquisition of the second lift ducted fan make unmanned plane
Lift needed for the VTOL stage, the ratio for accounting for gravity suffered by unmanned plane are not less than 85%；On the other hand, the component force device
Make postposition thrust ducted fan obtain make unmanned plane obtain maximal rate put down it is needed for the winged stage, for overcome aerodynamic drag to
Forward thrust, the ratio for accounting for gravity suffered by unmanned plane are 8%.
Preferably, the vertical take-off and landing drone oil electric mixed dynamic system further comprises power battery pack, described dynamic
Power battery pack is used to be arranged in the fuselage, and is connected with the genemotor, and power supply is provided for the genemotor.
Preferably, generator is provided with the turboshaft engine, the generator is used to connect with the power battery pack
Connect, so as to charge for the power battery pack.
Preferably, the genemotor can provide for the preposition trim ducted fan makes unmanned plane obtain vertical rise
Lift needed for depression of order section, the ratio which accounts for gravity suffered by unmanned plane are less than 15%.
The vertical take-off and landing drone oil electric mixed dynamic system of the present invention passes through transmission mechanism using a turboshaft engine
Two lift ducted fans and postposition thrust ducted fan are driven respectively, and a preposition trim is driven using a genemotor
Ducted fan；In this way, so as to meet demand of the VTOL stage to dynamical system maximum power output, and relative to
Powerful engine is used in the prior art, and transmission mechanism of the invention is relatively fewer, relative in the prior art using pure
Genemotor mode, using the teaching of the invention it is possible to provide the enough power of unmanned plane.
Brief description of the drawings
Fig. 1 is the structural representation of vertical take-off and landing drone oil electric mixed dynamic system according to a first embodiment of the present invention
Figure.
Reference numeral：
| 1 | First lift ducted fan | 6 | Genemotor |
| 2 | Second lift ducted fan | 7 | Power battery pack |
| 3 | Postposition thrust ducted fan | 51 | Generator |
| 4 | Preposition trim ducted fan | ||
| 5 | Turboshaft engine |
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
Fig. 1 is the structural representation of vertical take-off and landing drone oil electric mixed dynamic system according to a first embodiment of the present invention
Figure.
Existing vertical take-off and landing drone, some vertical take-off and landing drone include fuselage, first liter be arranged on fuselage
Power ducted fan 1, the second lift ducted fan 2, postposition thrust ducted fan 3 and preposition trim ducted fan 4.
The vertical take-off and landing drone oil electric mixed dynamic system as shown in Figure 1 includes turboshaft engine 5, motor
Machine 6, component force device and power battery pack 7.
Referring to Fig. 1, in the present embodiment, turboshaft engine 5 respectively with the first lift ducted fan 1, the second lift duct
Fan 2 and postposition thrust ducted fan 3 are sequentially connected；Genemotor 6 is sequentially connected with preposition trim ducted fan 4；Its
In, turboshaft engine 5 is used to drive the first lift ducted fan 1, the second lift ducted fan 2 and postposition thrust duct
Fan 3 works；Genemotor 6 is used to drive preposition trim ducted fan 4 to work.
The vertical take-off and landing drone oil electric mixed dynamic system of the present invention passes through transmission mechanism using a turboshaft engine
Two lift ducted fans and postposition thrust ducted fan are driven respectively, and a preposition trim is driven using a genemotor
Ducted fan；In this way, so as to meet demand of the VTOL stage to dynamical system maximum power output, and relative to
Powerful engine is used in the prior art, and transmission mechanism of the invention is relatively fewer, relative in the prior art using pure
Genemotor mode, using the teaching of the invention it is possible to provide the enough power of unmanned plane.
In the present embodiment, component force device has an input terminal and three output terminals, the input terminal of component force device with
Turboshaft engine 5 is sequentially connected, the output terminal of component force device respectively with the first lift ducted fan 1, the second lift ducted fan
2nd, postposition thrust ducted fan 3 is sequentially connected；Component force device is used to divide the power of turboshaft engine 5 respectively according to preset ratio
It is assigned in the first lift ducted fan 1, the second lift ducted fan 2, postposition thrust ducted fan 3., can be with by component force device
The power for controlling each ducted fan to be distributed.
In a preferred embodiment, component force device obtains the first lift ducted fan 1 and the second lift ducted fan 2
It must make the lift needed for the unmanned plane VTOL stage, the ratio for accounting for gravity suffered by unmanned plane is more than or equal to 85%；On the other hand,
Component force device make postposition thrust ducted fan 3 obtain make unmanned plane obtain maximal rate put down it is needed for the winged stage, for overcoming gas
The forward thrust of dynamic resistance, the ratio for accounting for gravity suffered by unmanned plane are 8%.
It is understood that above-mentioned mix proportion scheme is a preferred solution, according to the species of unmanned plane it is different or
Its structure is different, can use other mix proportion schemes.For example, component force device makes the first lift ducted fan 1 and the second lift
Ducted fan 2 obtains the lift made needed for the unmanned plane VTOL stage, and the ratio for accounting for gravity suffered by unmanned plane is more than or equal to
75%；On the other hand, component force device, which obtains postposition thrust ducted fan 3, makes unmanned plane acquisition maximal rate put down needed for the winged stage
, forward thrust for overcoming aerodynamic drag, the ratio for accounting for gravity suffered by unmanned plane is 10% etc..
Referring to Fig. 1, in the present embodiment, power battery pack 7 is used to be arranged in fuselage, and is connected with genemotor 6,
Power supply is provided for genemotor 6.
Advantageously, in the present embodiment, generator 51 is provided with turboshaft engine 5, generator 51 is used for and power
Battery pack 7 connects, so as to charge for power battery pack 7.Using this structure, whirlpool can be not required in cruise etc. in unmanned plane again
Shaft generator 5 works with all strength when, power is converted into electric energy by engine.
In a preferred embodiment, genemotor 6 can be that the offer of preposition trim ducted fan 4 obtains unmanned plane
Lift needed for the VTOL stage, the ratio which accounts for gravity suffered by unmanned plane are less than 15%.
It is understood that above-mentioned mix proportion scheme is a preferred solution, according to the species of unmanned plane it is different or
Its structure is different, can use other mix proportion schemes.Make for example, genemotor 6 can be the offer of preposition trim ducted fan 4
Unmanned plane obtains the lift needed for the VTOL stage, and the ratio which accounts for gravity suffered by unmanned plane is less than 10%.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution described in foregoing embodiments, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical solution
God and scope.
Claims (6)
1. a kind of vertical take-off and landing drone oil electric mixed dynamic system, described vertical take-off and landing unmanned for vertical take-off and landing drone
Machine includes fuselage, the first lift ducted fan (1) being arranged on fuselage, the second lift ducted fan (2), postposition thrust duct
Fan (3) and preposition trim ducted fan (4), it is characterised in that the vertical take-off and landing drone oil electric mixed dynamic system
Including：
Turboshaft engine (5), the turboshaft engine (5) respectively with the first lift ducted fan (1), the second lift ducted fan
(2) and postposition thrust ducted fan (3) is sequentially connected；
Genemotor (6), the genemotor (6) are sequentially connected with the preposition trim ducted fan (4)；Wherein,
The turboshaft engine (5) be used for drive the first lift ducted fan (1), the second lift ducted fan (2) and
Postposition thrust ducted fan (3) works；The genemotor (6) is used to drive preposition trim ducted fan (4) work.
2. vertical take-off and landing drone oil electric mixed dynamic system as claimed in claim 1, it is characterised in that the VTOL
Unmanned plane oil electric mixed dynamic system further comprises component force device, and the component force device is defeated with an input terminal and three
Outlet, the input terminal of the component force device are sequentially connected with the turboshaft engine (5), the output terminal difference of the component force device
It is sequentially connected with the first lift ducted fan (1), the second lift ducted fan (2), postposition thrust ducted fan (3)；Institute
Component force device is stated to be used to the power of the turboshaft engine (5) is respectively allocated to the first lift duct according to preset ratio
In fan (1), the second lift ducted fan (2), postposition thrust ducted fan (3).
3. vertical take-off and landing drone oil electric mixed dynamic system as claimed in claim 2, it is characterised in that the component force device
The first lift ducted fan (1) and the second lift ducted fan (2) is set to obtain the liter made needed for the unmanned plane VTOL stage
Power, the ratio for accounting for gravity suffered by unmanned plane are more than or equal to 85%；On the other hand, the component force device makes postposition thrust ducted fan
(3) obtaining, which makes unmanned plane obtain maximal rate, equals forward thrust needed for the winged stage, for overcoming aerodynamic drag, accounts for unmanned plane
The ratio of suffered gravity is 8%.
4. vertical take-off and landing drone oil electric mixed dynamic system as claimed in claim 2, it is characterised in that the VTOL
Unmanned plane oil electric mixed dynamic system further comprises power battery pack (7), and the power battery pack (7) is used to be arranged on described
In fuselage, and it is connected with the genemotor (6), power supply is provided for the genemotor (6).
5. vertical take-off and landing drone oil electric mixed dynamic system as claimed in claim 4, it is characterised in that the whirlpool axis starts
Generator (51) is provided with machine (5), the generator (51) is used to be connected with the power battery pack (7), so as to be described
Power battery pack (7) charges.
6. vertical take-off and landing drone oil electric mixed dynamic system as claimed in claim 5, it is characterised in that the motor
Machine (6) can be that the preposition trim ducted fan (4) provides the lift made needed for the unmanned plane acquisition VTOL stage, the liter
The ratio that power accounts for gravity suffered by unmanned plane is less than 15%.
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| CN201510834126.3A CN105329448B (en) | 2015-11-24 | 2015-11-24 | A kind of vertical take-off and landing drone oil electric mixed dynamic system |
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| CN201510834126.3A CN105329448B (en) | 2015-11-24 | 2015-11-24 | A kind of vertical take-off and landing drone oil electric mixed dynamic system |
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| CN105329448B true CN105329448B (en) | 2018-04-13 |
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| CN109383782B (en) * | 2018-08-31 | 2022-07-26 | 辽宁同心圆科技有限公司 | Danger-escaping energy-saving power-assisting system of aero-engine |
| CN109383783B (en) * | 2018-08-31 | 2022-07-26 | 辽宁同心圆科技有限公司 | Energy-saving power-assisting system of aero-engine |
| CN109204797B (en) * | 2018-08-31 | 2022-07-26 | 辽宁同心圆科技有限公司 | Energy-saving power assisting device of aero-engine |
| CN111356638B (en) * | 2018-11-30 | 2023-07-21 | 深圳市大疆创新科技有限公司 | Power component, power system and unmanned aerial vehicle |
| CN109738602A (en) * | 2018-12-12 | 2019-05-10 | 河南科技学院 | A kind of early warning system and method for water pollution |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205203397U (en) * | 2015-11-24 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | VTOL unmanned aerial vehicle oil -electricity hybrid vehicle system |
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| US10124890B2 (en) * | 2014-04-11 | 2018-11-13 | Dronetechuav Corporation | Modular nacelles to provide vertical takeoff and landing (VTOL) capabilities to fixed wing aerial vehicles, and associated systems and methods |
| CN204264457U (en) * | 2014-11-08 | 2015-04-15 | 河南摩西机械制造有限公司 | A kind of hybrid power unmanned plane |
| CN204527630U (en) * | 2015-04-10 | 2015-08-05 | 桂林航龙科讯电子技术有限公司 | A kind of oil electric mixed dynamic fixed-wing VUAV system |
| CN104743107B (en) * | 2015-04-24 | 2017-12-15 | 北京双飞伟业科技有限公司 | Multi-rotor aerocraft |
| CN104859853A (en) * | 2015-06-01 | 2015-08-26 | 姚龙江 | Six-rotor hybrid aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205203397U (en) * | 2015-11-24 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | VTOL unmanned aerial vehicle oil -electricity hybrid vehicle system |
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Effective date of registration: 20201103 Address after: Building B, building 28, Jiangsu information service industry base, Guangling New Town, Yangzhou City, Jiangsu Province, 225002 Patentee after: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co., Ltd Address before: Thavorn street in Huanggu District of Shenyang city of Liaoning Province, No. 40 110035 Patentee before: SHENYANG AIRCRAFT DESIGN INSTITUTE, AVIATION INDUSTRY CORPORATION OF CHINA |
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