CN105329448A - Oil-electricity mixed power system of vertical taking-off and landing unmanned aerial vehicle - Google Patents
Oil-electricity mixed power system of vertical taking-off and landing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105329448A CN105329448A CN201510834126.3A CN201510834126A CN105329448A CN 105329448 A CN105329448 A CN 105329448A CN 201510834126 A CN201510834126 A CN 201510834126A CN 105329448 A CN105329448 A CN 105329448A
- Authority
- CN
- China
- Prior art keywords
- ducted fan
- lift
- vuav
- unmanned plane
- dynamic system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an oil-electricity mixed power system of a vertical taking-off and landing unmanned aerial vehicle. The system comprises a turboshaft engine (5), and an electric engine (6), wherein the turboshaft engine (5) is connected with a first lift force ducted fan (1), a second lift force ducted fan (2) and a post-positioned lift force ducted fan (3) in a transmission manner; the electric engine (6) is connected with a pre-positioned balancing ducted fan (4) in the transmission manner; the turboshaft engine (5) is used for driving the first lift force ducted fan (1), the second lift force ducted fan (2) and the post-positioned lift force ducted fan (3) to work; the electric engine (6) is used for driving the pre-positioned balancing ducted fan (4) to work. By using the structure, compared with an engine with the largest power in the prior art, for the oil-electricity mixed power system, transmission mechanisms are relatively small in number; compared with that a pure electric engine is adopted in the prior art, the oil-electricity mixed power system can provide enough power for the unmanned aerial vehicle.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, be specifically related to a kind of VUAV oil electric mixed dynamic system.
Background technology
In order to realize boat-carrying unmanned plane configure the driving of four ducted fans, need on unmanned plane, configure corresponding power system; Conveniently, power system can adopt the dynamic driving engine of oil and genemotor two class allocation plan; Engine options is moved as adopted pure oil, because the inner space of unmanned plane is limited, the most real scheme is: adopt a high-performance driving engine, by the transmission device of complexity, the power of driving engine is distributed according to need on four ducted fans, such scheme, one according to the transmission device of theory of machines design inevitable very complicated and with larger accessory weight and higher fault rate, / 10th of two not enough full powers of Power output when unmanned plane is in flat flying, the efficiency of power system is by extremely low; As adopted pure genemotor scheme, because unmanned plane requires vertical takeoff and landing, inevitable requirement configures high-performance electrical motor, but, the power to weight ratio of genemotor is only 1/tens of the dynamic driving engine of oil, this means, for the unmanned plane of same Gross Weight Takeoff, genemotor weight will move engine weight far above oil, in addition, due to unmanned plane to rectificate boat time (more than 10 hours), need genemotor to be equipped with a large amount of batteries, add the weight of whole unmanned plane, and be difficult to realize.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one the problems referred to above of prior art.
Summary of the invention
The object of the present invention is to provide a kind of VUAV oil electric mixed dynamic system to overcome or at least alleviate at least one the problems referred to above of the prior art.
For achieving the above object, the invention provides a kind of VUAV oil electric mixed dynamic system, for VUAV, described VUAV comprises fuselage, the first lift ducted fan be arranged on fuselage, the second lift ducted fan, rearmounted thrust ducted fan and preposition trim ducted fan, described VUAV oil electric mixed dynamic system comprises: turboshaft engine, and described turboshaft engine is in transmission connection with the first lift ducted fan, the second lift ducted fan and rearmounted thrust ducted fan respectively; Genemotor, described genemotor and described preposition trim ducted fan are in transmission connection; Wherein, described turboshaft engine is for driving described first lift ducted fan, the second lift ducted fan and the work of rearmounted thrust ducted fan; Described genemotor is for driving the work of described preposition trim ducted fan.
Preferably, described VUAV oil electric mixed dynamic system comprises component force device further, described component force device has an input end and three mouths, input end and the described turboshaft engine of described component force device are in transmission connection, and the mouth of described component force device is in transmission connection with described first lift ducted fan, the second lift ducted fan, rearmounted thrust ducted fan respectively; Described component force device is used for being respectively allocated in described first lift ducted fan, the second lift ducted fan, rearmounted thrust ducted fan by the power of described turboshaft engine according to preset ratio.
Preferably, described component force device makes the first lift ducted fan and the second lift ducted fan obtain the lift made needed for the unmanned plane vertical takeoff and landing stage, and the ratio of gravity suffered by unmanned plane that accounts for is not less than 85%; On the other hand, described component force device make rearmounted thrust ducted fan obtain make unmanned plane obtain maximum speed put down needed for the stage of flying, for overcoming the forward thrust of aerodynamic drag, the ratio accounting for gravity suffered by unmanned plane is 8%.
Preferably, described VUAV oil electric mixed dynamic system comprises power battery pack further, and described power battery pack is used for being arranged in described fuselage, and is connected with described genemotor, for described genemotor provides power supply.
Preferably, be provided with electrical generator in described turboshaft engine, described driving engine is used for being connected with described power battery pack, thus is the charging of described power battery pack.
Preferably, described genemotor can provide for described preposition trim ducted fan the lift made needed for the unmanned plane acquisition vertical takeoff and landing stage, and this lift accounts for the ratio of gravity suffered by unmanned plane and is less than 15%.
VUAV oil electric mixed dynamic system of the present invention adopts a turboshaft engine to drive two lift ducted fans and rearmounted thrust ducted fan respectively by transmission device, adopts a genemotor to drive a preposition trim ducted fan; Like this, thus the demand of vertical takeoff and landing stage to power system maximum power output can be met, and relative to adopting high-performance driving engine in prior art, transmission device of the present invention is relatively less, relative to adopting pure genemotor mode in prior art, the power that unmanned plane is enough can be provided.
Accompanying drawing explanation
Fig. 1 is the structural representation of VUAV oil electric mixed dynamic system according to a first embodiment of the present invention.
Reference numeral:
| 1 | First lift ducted fan | 6 | Genemotor |
| 2 | Second lift ducted fan | 7 | Power battery pack |
| 3 | Rearmounted thrust ducted fan | 51 | Electrical generator |
| 4 | Preposition trim ducted fan | ||
| 5 | Turboshaft engine |
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Fig. 1 is the structural representation of VUAV oil electric mixed dynamic system according to a first embodiment of the present invention.
Existing VUAV, some VUAV comprises fuselage, is arranged on the first lift ducted fan 1, second lift ducted fan 2 on fuselage, rearmounted thrust ducted fan 3 and preposition trim ducted fan 4.
Described VUAV oil electric mixed dynamic system as shown in Figure 1 comprises turboshaft engine 5, genemotor 6, component force device and power battery pack 7.
See Fig. 1, in the present embodiment, turboshaft engine 5 is in transmission connection with the first lift ducted fan 1, second lift ducted fan 2 and rearmounted thrust ducted fan 3 respectively; Genemotor 6 and preposition trim ducted fan 4 are in transmission connection; Wherein, turboshaft engine 5 works for driving described first lift ducted fan 1, second lift ducted fan 2 and rearmounted thrust ducted fan 3; Genemotor 6 works for driving preposition trim ducted fan 4.
VUAV oil electric mixed dynamic system of the present invention adopts a turboshaft engine to drive two lift ducted fans and rearmounted thrust ducted fan respectively by transmission device, adopts a genemotor to drive a preposition trim ducted fan; Like this, thus the demand of vertical takeoff and landing stage to power system maximum power output can be met, and relative to adopting high-performance driving engine in prior art, transmission device of the present invention is relatively less, relative to adopting pure genemotor mode in prior art, the power that unmanned plane is enough can be provided.
In the present embodiment, component force device has an input end and three mouths, input end and the turboshaft engine 5 of component force device are in transmission connection, and the mouth of component force device is in transmission connection with the first lift ducted fan 1, second lift ducted fan 2, rearmounted thrust ducted fan 3 respectively; Component force device is used for being respectively allocated in the first lift ducted fan 1, second lift ducted fan 2, rearmounted thrust ducted fan 3 by the power of turboshaft engine 5 according to preset ratio.By component force device, the power that each ducted fan distributes can be controlled.
In a preferred embodiment, component force device makes the first lift ducted fan 1 and the second lift ducted fan 2 obtain the lift made needed for the unmanned plane vertical takeoff and landing stage, and the ratio of gravity suffered by unmanned plane that accounts for is more than or equal to 85%; On the other hand, component force device make rearmounted thrust ducted fan 3 obtain make unmanned plane obtain maximum speed put down needed for the stage of flying, for overcoming the forward thrust of aerodynamic drag, the ratio accounting for gravity suffered by unmanned plane is 8%.
Be understandable that, above-mentioned mix proportion scheme is a preferred version, and according to the kind of unmanned plane, different or its structure difference, can adopt other mix proportion schemes.Such as, component force device makes the first lift ducted fan 1 and the second lift ducted fan 2 obtain the lift made needed for the unmanned plane vertical takeoff and landing stage, and the ratio of gravity suffered by unmanned plane that accounts for is more than or equal to 75%; On the other hand, component force device rearmounted thrust ducted fan 3 is obtained make unmanned plane obtain maximum speed put down needed for the stage of flying, for overcoming the forward thrust of aerodynamic drag, the ratio accounting for gravity suffered by unmanned plane is 10% etc.
See Fig. 1, in the present embodiment, power battery pack 7 for being arranged in fuselage, and is connected with genemotor 6, for genemotor 6 provides power supply.
Advantageously, in the present embodiment, be provided with electrical generator 51 in turboshaft engine 5, driving engine 51 for being connected with power battery pack 7, thus charges for power battery pack 7.Adopt this structure, can unmanned plane again to cruise etc. do not need turboshaft engine 5 to work with all strength time, convert power to electric energy by driving engine.
In a preferred embodiment, genemotor 6 can provide for preposition trim ducted fan 4 lift made needed for the unmanned plane acquisition vertical takeoff and landing stage, and this lift accounts for the ratio of gravity suffered by unmanned plane and is less than 15%.
Be understandable that, above-mentioned mix proportion scheme is a preferred version, and according to the kind of unmanned plane, different or its structure difference, can adopt other mix proportion schemes.Such as, genemotor 6 can provide for preposition trim ducted fan 4 lift made needed for the unmanned plane acquisition vertical takeoff and landing stage, and this lift accounts for the ratio of gravity suffered by unmanned plane and is less than 10%.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (6)
1. a VUAV oil electric mixed dynamic system, for VUAV, described VUAV comprises fuselage, the first lift ducted fan (1) be arranged on fuselage, the second lift ducted fan (2), rearmounted thrust ducted fan (3) and preposition trim ducted fan (4), it is characterized in that, described VUAV oil electric mixed dynamic system comprises:
Turboshaft engine (5), described turboshaft engine (5) is in transmission connection with the first lift ducted fan (1), the second lift ducted fan (2) and rearmounted thrust ducted fan (3) respectively;
Genemotor (6), described genemotor (6) and described preposition trim ducted fan (4) are in transmission connection; Wherein,
Described turboshaft engine (5) works for driving described first lift ducted fan (1), the second lift ducted fan (2) and rearmounted thrust ducted fan (3); Described genemotor (6) is for driving described preposition trim ducted fan (4) work.
2. VUAV oil electric mixed dynamic system as claimed in claim 1, it is characterized in that, described VUAV oil electric mixed dynamic system comprises component force device further, described component force device has an input end and three mouths, input end and the described turboshaft engine (5) of described component force device are in transmission connection, and the mouth of described component force device is in transmission connection with described first lift ducted fan (1), the second lift ducted fan (2), rearmounted thrust ducted fan (3) respectively; Described component force device is used for being respectively allocated in described first lift ducted fan (1), the second lift ducted fan (2), rearmounted thrust ducted fan (3) by the power of described turboshaft engine (5) according to preset ratio.
3. VUAV oil electric mixed dynamic system as claimed in claim 2, it is characterized in that, described component force device makes the first lift ducted fan (1) and the second lift ducted fan (2) obtain the lift made needed for the unmanned plane vertical takeoff and landing stage, and the ratio of gravity suffered by unmanned plane that accounts for is more than or equal to 85%; On the other hand, described component force device make rearmounted thrust ducted fan (3) obtain make unmanned plane obtain maximum speed put down needed for the stage of flying, for overcoming the forward thrust of aerodynamic drag, the ratio accounting for gravity suffered by unmanned plane is 8%.
4. VUAV oil electric mixed dynamic system as claimed in claim 2, it is characterized in that, described VUAV oil electric mixed dynamic system comprises power battery pack (7) further, described power battery pack (7) is for being arranged in described fuselage, and be connected with described genemotor (6), for described genemotor (6) provides power supply.
5. VUAV oil electric mixed dynamic system as claimed in claim 4, it is characterized in that, electrical generator (51) is provided with in described turboshaft engine (5), described driving engine (51) for being connected with described power battery pack (7), thus is described power battery pack (7) charging.
6. VUAV oil electric mixed dynamic system as claimed in claim 5, it is characterized in that, described genemotor (6) can provide for described preposition trim ducted fan (4) lift made needed for the unmanned plane acquisition vertical takeoff and landing stage, and this lift accounts for the ratio of gravity suffered by unmanned plane and is less than 15%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510834126.3A CN105329448B (en) | 2015-11-24 | 2015-11-24 | A kind of vertical take-off and landing drone oil electric mixed dynamic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510834126.3A CN105329448B (en) | 2015-11-24 | 2015-11-24 | A kind of vertical take-off and landing drone oil electric mixed dynamic system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105329448A true CN105329448A (en) | 2016-02-17 |
| CN105329448B CN105329448B (en) | 2018-04-13 |
Family
ID=55280284
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510834126.3A Active CN105329448B (en) | 2015-11-24 | 2015-11-24 | A kind of vertical take-off and landing drone oil electric mixed dynamic system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105329448B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109204797A (en) * | 2018-08-31 | 2019-01-15 | 辽宁同心圆科技有限公司 | Aero-engine energy-saving power-assisting device |
| CN109383782A (en) * | 2018-08-31 | 2019-02-26 | 辽宁同心圆科技有限公司 | Aero-engine is escaped danger energy-saving power-boost system |
| CN109383783A (en) * | 2018-08-31 | 2019-02-26 | 辽宁同心圆科技有限公司 | Aero-engine energy-saving power-boost system |
| 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 |
| WO2020107373A1 (en) * | 2018-11-30 | 2020-06-04 | 深圳市大疆创新科技有限公司 | Power assembly, power system and unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104743107A (en) * | 2015-04-24 | 2015-07-01 | 北京双飞伟业科技有限公司 | Multi-rotor type aircraft |
| 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 |
| CN104859853A (en) * | 2015-06-01 | 2015-08-26 | 姚龙江 | Six-rotor hybrid aircraft |
| WO2015157114A1 (en) * | 2014-04-11 | 2015-10-15 | Sada-Salinas Jaime G | Modular nacelles to provide vertical takeoff and landing (vtol) capabilities to fixed wing aerial vehicles, and associated systems and methods |
| 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 |
-
2015
- 2015-11-24 CN CN201510834126.3A patent/CN105329448B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015157114A1 (en) * | 2014-04-11 | 2015-10-15 | Sada-Salinas Jaime G | 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 |
| CN104743107A (en) * | 2015-04-24 | 2015-07-01 | 北京双飞伟业科技有限公司 | Multi-rotor type aircraft |
| CN104859853A (en) * | 2015-06-01 | 2015-08-26 | 姚龙江 | Six-rotor hybrid aircraft |
| 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 |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109204797A (en) * | 2018-08-31 | 2019-01-15 | 辽宁同心圆科技有限公司 | Aero-engine energy-saving power-assisting device |
| CN109383782A (en) * | 2018-08-31 | 2019-02-26 | 辽宁同心圆科技有限公司 | Aero-engine is escaped danger energy-saving power-boost system |
| CN109383783A (en) * | 2018-08-31 | 2019-02-26 | 辽宁同心圆科技有限公司 | Aero-engine energy-saving power-boost system |
| 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 |
| 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 |
| 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 |
| WO2020107373A1 (en) * | 2018-11-30 | 2020-06-04 | 深圳市大疆创新科技有限公司 | Power assembly, 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105329448B (en) | 2018-04-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105329448A (en) | Oil-electricity mixed power system of vertical taking-off and landing unmanned aerial vehicle | |
| CN205203397U (en) | VTOL unmanned aerial vehicle oil -electricity hybrid vehicle system | |
| JP2015137092A (en) | Parallel hybrid multi-rotor aircraft | |
| WO2016085610A4 (en) | High speed multi-rotor vertical takeoff and landing aircraft | |
| CN106586001A (en) | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration | |
| CN108001677B (en) | Falling off tethered vertical take-off and landing fixed wing unmanned aerial vehicle | |
| US20210276723A1 (en) | Power assembly, power system and unmanned aerial vehicle | |
| EP3312085B1 (en) | Electric taxiing system of aircraft and method for controlling the system | |
| CN104276284A (en) | Tandem type fan wing aircraft layout | |
| CN106005386A (en) | Ducted unmanned aerial vehicle for combinable clusters | |
| CN105691621A (en) | aircraft and method of fitting out such an aircraft | |
| CN105109695A (en) | Multifunctional aircraft with hybrid of oil and electricity | |
| CN106585964A (en) | Aircraft and flying method thereof | |
| CN105035328A (en) | Hybrid-power flight vehicle | |
| US20240051670A1 (en) | Aircraft equipped with a distributed propulsion system having suction and pressure fans | |
| CN206719540U (en) | Tilting rotor type VUAV based on Flying-wing | |
| RU2532672C1 (en) | Heavy convertible electric drone | |
| RU2554043C1 (en) | Hybrid short takeoff and landing electric aircraft | |
| CN210793660U (en) | Single rotor tail seat type vertical take-off and landing unmanned aerial vehicle | |
| CN111792027A (en) | Aircraft with double-fuselage tandem wing vertical take-off and landing layout | |
| CN110683046A (en) | Aircraft with a flight control device | |
| CN206218223U (en) | A kind of polymorphic unmanned plane | |
| CN109606623A (en) | Intelligent modularized solar energy unmanned plane | |
| CN205168890U (en) | Energy -conserving aircraft of VTOL | |
| CN114802742A (en) | Vertical and horizontal dual-purpose aircraft based on tilting power |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
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 |