CN105620765A - Co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system - Google Patents
Co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system Download PDFInfo
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- CN105620765A CN105620765A CN201511003358.0A CN201511003358A CN105620765A CN 105620765 A CN105620765 A CN 105620765A CN 201511003358 A CN201511003358 A CN 201511003358A CN 105620765 A CN105620765 A CN 105620765A
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- energy
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- storage units
- hybrid power
- power system
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- 238000004146 energy storage Methods 0.000 claims description 44
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 41
- 239000003990 capacitor Substances 0.000 claims description 10
- 238000010586 diagram Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 206010033799 Paralysis Diseases 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
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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
- B64U50/19—Propulsion using electrically powered motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention provides a co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system, and relates to the technical field of UAV aviation. The co-axis dual-rotor UAV hybrid power system comprises a power supply unit, a motor, a driving shaft, a main wing propeller and at least four aileron propellers, wherein the main wing propeller is co-axis type; the power supply unit provides energy for the motor; the motor provides power for the driving shaft so as to drive the main wing propeller; the co-axis dual-rotor UAV hybrid power system further comprises a power generator and a power storage system; the power supply unit, the power generator and the power storage system are sequentially connected; and the aileron propellers are electrically connected with the power storage system. By adopting the co-axis dual-rotor UAV hybrid power system, when the power of the power supply unit is exhausted, or the motor fails, continuous voyage can be realized, so that safety of a UAV body is ensured.
Description
Technical field
The present invention relates to without man-machine technical field of aerospace, particularly relate to a kind of coaxial double-rotary wing without man-machine hybrid power system.
Background technology
At present, it is possible to the aircraft of VTOL, the most common, it is exactly rotor vertiplane (being called for short " vertiplane "). Vertiplane is primarily of compositions such as body and lift system (containing main rotor and tail-rotor), power system, transmission system three digest journals and machine load flight equipments. The main rotor of vertiplane is generally driven by the mechanical transmission system being made up of transmission shaft, speed reduction unit etc. by turboaxle motor or piston engine, it is possible to drive by the reactive force of the oar jet generation of point. Vertiplane engine driven main rotor provides lift, vertiplane is lifted aloft, the structure of coaxial formula is that two rotors are arranged above and below, reverse rotation on same axis, rotor moment is offset with this, keeping organism balance, it changes lift by changing the rotating speed of each rotor, and then changes attitude and the position of quadrotor. Often the sense of rotation of two rotors in group is contrary, and to cancel out each other, single rotor rotates the moment produced, and regulates the rotating speed respectively organizing rotor all around, so that it may to regulate flight attitude and the speed of aircraft. Existing without man-machine all exist boat time short, the shortcoming that Energy Efficiency Ratio is low, and once entire machine will face paralysis when supply unit depleted of energy or engine break down, make to fall in the air without man-machine, damage without man-machine body, needing to spend a large amount of maintenance costs, the serious whole airplane that causes is scrapped for this reason.
Summary of the invention
It is an object of the invention to provide a kind of coaxial without man-machine hybrid power system so that it is can continue flight when supply unit depleted of energy or engine break down, ensure without man-machine safe land.
For achieving the above object, the present invention provides a kind of coaxial double-rotary wing without man-machine hybrid power system, described coaxial double-rotary wing comprises without man-machine hybrid power system: supply unit, engine, drive shaft, main wing water screw, at least 4 aileron water screws, described main wing water screw is coaxial formula, wherein supply unit provides energy for engine, described engine supplies power to drive shaft thus drives main wing water screw, described coaxial double-rotary wing also comprises generator without man-machine hybrid power system, accumulating system, described supply unit, generator, accumulating system connects successively, the drive end of described aileron water screw is electrically connected with described accumulating system.
Described supply unit is the dynamic energy supply of oil or electronic energy supply.
Described accumulating system is electrically connected with without other man-machine electrical equipments, for powering without other electrical equipments on man-machine.
As a further improvement on the present invention, described accumulating system comprises charging control unit, energy-storage units, the electrical input of described charging control unit connects the electric output terminal of described generator, the electric output terminal of described charging control unit connects energy-storage units, the electric current output terminal of described energy-storage units is electrically connected with described aileron water screw drive end, and described energy-storage units is power cell or super capacitor.
As a further improvement on the present invention, described accumulating system can also be made up of multiple energy-storage units, the quantity of energy-storage units is identical with the quantity of described aileron water screw, and with described aileron water screw one_to_one corresponding, described energy-storage units comprises power cell, super capacitor.
As a further improvement on the present invention, also comprise power supply arbitration unit, described energy-storage units is connected with aileron water screw by power supply arbitration unit, when described supply unit breaks down or during depleted of energy, it is aileron water screw offer electric energy that energy-storage units described in unit control is arbitrated in described power supply.
As a further improvement on the present invention, also comprise energy-storage units for subsequent use, described energy-storage units for subsequent use is connected with described generator, the electric output terminal of described energy-storage units for subsequent use is connected with the electrical input without other electrical equipments on man-machine, and described energy-storage units for subsequent use comprises power cell, super capacitor.
Present invention also offers a kind of without man-machine, comprise the coaxial double-rotary wing described in technique scheme without man-machine hybrid power system.
Compared with prior art, the invention has the beneficial effects as follows: when the coaxial double-rotary wing of the present invention can ensure that supply unit depleted of energy or engine break down without man-machine hybrid power system, it is possible to continue continuation of the journey, at least can ensure without man-machine safe land.
Accompanying drawing explanation
Fig. 1 is a kind of structure block diagram of implementing mode of coaxial double-rotary wing without man-machine hybrid power system of the present invention;
Fig. 2 is the structural representation of accumulating system in Fig. 1;
Fig. 3 is that the coaxial double-rotary wing of the present invention is without a kind of structure block diagram implementing mode of man-machine hybrid power system;
Fig. 4 is the structure block diagram of coaxial double-rotary wing without man-machine hybrid power system another kind of enforcement mode of the present invention.
Embodiment
Below in conjunction with each enforcement mode shown in the drawings, the present invention is described in detail; but it should what illustrate is; these implement mode not limitation of the present invention; those of ordinary skill in the art implement mode institute work energy, method or structural equivalent transformation or replacement according to these, all belong within protection scope of the present invention.
Coaxial double-rotary wing of the present invention comprises without man-machine hybrid power system: supply unit, engine, drive shaft, main wing water screw, at least 4 aileron water screws, described main wing water screw is coaxial formula, wherein supply unit provides energy for engine, described engine supplies power to drive shaft thus drives main wing water screw, described coaxial double-rotary wing also comprises generator without man-machine hybrid power system, accumulating system, described supply unit, generator, accumulating system connects successively, the drive end of described aileron water screw is electrically connected with described accumulating system, its concrete enforcement mode is set forth below for 4 secondary propeller aircrafts.
Embodiment 1
As shown in Figure 1, described coaxial double-rotary wing comprises without man-machine hybrid power system: supply unit 1, engine 2, drive shaft 4, main wing water screw 5, 4 aileron water screws 60, described main wing water screw 5 is coaxial formula, wherein supply unit 1 provides energy for engine 2, described engine 2 supplies power to drive shaft 3 thus drives main wing water screw 5, described coaxial double-rotary wing also comprises generator 3 without man-machine hybrid power system, accumulating system 6, described supply unit 1, engine 2, generator 3, accumulating system 6 connects successively, the drive end of described aileron water screw 60 is electrically connected with described accumulating system 6. described supply unit 1 is the dynamic energy supply of oil or electronic energy supply, supply unit 1 provides energy for engine 2, drive generator 3, give accumulating system 6 with electric energy by generator 3, accumulating system 6 can be single power cell or super capacitor, (as shown in Figure 2) described accumulating system 6 comprises charging control unit 61 as a further improvement on the present invention, energy-storage units 62, the input terminus of described charging control unit 61 connects the output terminal of described generator 3, the output terminal of described charging control unit 61 connects energy-storage units 62, the electric current output terminal of described energy-storage units 62 is electrically connected with the drive end of described aileron water screw 60, described energy-storage units 62 is power cell or super capacitor, described accumulating system 6 can be electrically connected with without other man-machine electrical equipments 8, for powering (as shown in Figure 3) without other electrical equipments 8 on man-machine. described coaxial double-rotary wing also comprises energy-storage units 7 for subsequent use without man-machine hybrid power system as a further improvement on the present invention, described energy-storage units for subsequent use 7 is connected with described engine 3, the electric output terminal of described energy-storage units for subsequent use 7 is connected with the electrical input without other electrical equipments 8 on man-machine, for without other man-machine equipment electricity consumptions, described energy-storage units 7 for subsequent use comprises power cell, super capacitor.
Its another kind of enforcement mode is set forth below for 4 secondary propeller aircrafts.
Embodiment 2
As shown in Figure 4, described coaxial double-rotary wing comprises without man-machine hybrid power system: supply unit 1, engine 2, drive shaft 4, main wing water screw 5, 4 aileron water screws 60, described main wing water screw 5 is coaxial formula, wherein supply unit 1 provides energy for engine 2, described engine 2 supplies power to drive shaft 3 thus drives main wing water screw 5, described coaxial double-rotary wing also comprises generator 3 without man-machine hybrid power system, accumulating system (accumulating system is made up of multiple energy-storage units 601), described supply unit 1, engine 2, generator 3, accumulating system (accumulating system is made up of multiple energy-storage units 601) connects successively, the drive end of described aileron water screw 60 is electrically connected with described accumulating system (accumulating system is made up of multiple energy-storage units 601), described supply unit 1 is the dynamic energy supply of oil or electronic energy supply, supply unit 1 provides energy for engine 2, drive generator 3, give accumulating system with electric energy by generator 3, the quantity of energy-storage units 601 is identical with the quantity of described aileron water screw 60, and with described aileron water screw 60 one_to_one corresponding, also comprise power supply arbitration unit 602, described energy-storage units is connected with the drive end of aileron water screw 60 by power supply arbitration unit 602, when described supply unit breaks down or during depleted of energy, energy-storage units described in described power supply arbitration unit control provides electric energy for aileron water screw 60. described coaxial double-rotary wing also comprises energy-storage units for subsequent use without man-machine hybrid power system, described energy-storage units for subsequent use 7 is connected with described generator 3, the electric output terminal of described energy-storage units for subsequent use 3 is connected with the electrical input without other electrical equipments 8 on man-machine, and described energy-storage units 7 for subsequent use comprises power cell, super capacitor.
It should be noted that, the coaxial double-rotary wing of the above the present invention just sets forth its concrete enforcement mode for 4 secondary propeller aircrafts without man-machine hybrid power system, and the coaxial double-rotary wing for more than 4 aileron water screws is suitable for equally without man-machine.
Compared with prior art, the invention has the beneficial effects as follows: when the coaxial double-rotary wing of the present invention can ensure that supply unit depleted of energy or engine break down without man-machine hybrid power system, it is possible to continue continuation of the journey, at least can ensure without man-machine safe land.
To those skilled in the art, it is clear that the invention is not restricted to the details of above-mentioned one exemplary embodiment, and when not deviating from spirit or the essential characteristic of the present invention, it is possible to realize the present invention in other specific forms. Therefore, no matter from which point, embodiment all should be regarded as exemplary, and right and wrong are restrictive, the scope of the present invention is limited by claims instead of above-mentioned explanation, it is intended that all changes in the implication of the equivalent important document dropping on claim and scope included in the present invention. Any Reference numeral in claim should be considered as the claim involved by limiting.
In addition, it is to be understood that, although this specification sheets is described according to enforcement mode, but not each enforcement mode only comprises an independent technical scheme, this kind of narrating mode of specification sheets is only for clarity sake, those skilled in the art should by specification sheets integrally, and the technical scheme in each embodiment through appropriately combined, can also form other enforcement modes that it will be appreciated by those skilled in the art that.
Claims (8)
1. a coaxial double-rotary wing is without man-machine hybrid power system, it is characterized in that, described coaxial double-rotary wing comprises without man-machine hybrid power system: supply unit, engine, drive shaft, main wing water screw, at least 4 aileron water screws, described main wing water screw is coaxial formula, wherein supply unit provides energy for engine, described engine supplies power to drive shaft thus drives main wing water screw, described coaxial double-rotary wing also comprises generator without man-machine hybrid power system, accumulating system, described supply unit, generator, accumulating system connects successively, the drive end of described aileron water screw is electrically connected with described accumulating system.
2. coaxial double-rotary wing according to claim 1 is without man-machine hybrid power system, it is characterised in that, described supply unit is the dynamic energy supply of oil or electronic energy supply.
3. coaxial double-rotary wing according to claim 1 is without man-machine hybrid power system, it is characterised in that, described accumulating system is electrically connected with without other man-machine electrical equipments.
4. coaxial double-rotary wing according to claim 1 is without man-machine hybrid power system, it is characterized in that, described accumulating system comprises charging control unit, energy-storage units, the electrical input of described charging control unit connects the electric output terminal of described generator, the electric output terminal of described charging control unit connects energy-storage units, the electric current output terminal of described energy-storage units is electrically connected with described aileron water screw drive end, and described energy-storage units is power cell or super capacitor.
5. coaxial double-rotary wing according to claim 1 is without man-machine hybrid power system, it is characterized in that, described accumulating system is made up of multiple energy-storage units, the quantity of energy-storage units is identical with the quantity of described aileron water screw, and with described aileron water screw one_to_one corresponding, described energy-storage units comprises power cell, super capacitor.
6. coaxial double-rotary wing according to claim 5 is without man-machine hybrid power system, it is characterized in that, also comprise power supply arbitration unit, described energy-storage units is connected with aileron water screw by power supply arbitration unit, when described supply unit breaks down or during depleted of energy, energy-storage units described in described power supply arbitration unit control is that aileron water screw provides electric energy.
7. coaxial double-rotary wing according to claim 1 is without man-machine hybrid power system, it is characterized in that, also comprise energy-storage units for subsequent use, described energy-storage units for subsequent use is connected with described generator, the electric output terminal of described energy-storage units for subsequent use is connected with the electrical input without other electrical equipments on man-machine, and described energy-storage units for subsequent use comprises power cell, super capacitor.
8. one kind without man-machine, it is characterised in that, comprising: the coaxial double-rotary wing described in the arbitrary item of claim 1 to 7 is without man-machine hybrid power system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511003358.0A CN105620765A (en) | 2015-12-29 | 2015-12-29 | Co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201511003358.0A CN105620765A (en) | 2015-12-29 | 2015-12-29 | Co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system |
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| CN105620765A true CN105620765A (en) | 2016-06-01 |
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| CN201511003358.0A Pending CN105620765A (en) | 2015-12-29 | 2015-12-29 | Co-axis dual-rotor UAV (Unmanned Aerial Vehicle) hybrid power system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018006439A1 (en) * | 2016-07-04 | 2018-01-11 | 深圳市龙云创新航空科技有限公司 | Integrated power multi-axis unmanned aerial vehicle |
| CN108082497A (en) * | 2016-11-22 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of multi-purpose unmanned aerial vehicle of hybrid power |
| CN109204841A (en) * | 2017-06-30 | 2019-01-15 | 通用电气公司 | Method for the hybrid electric propulsion system of aircraft and for operating turbine |
| CN110048498A (en) * | 2019-02-11 | 2019-07-23 | 南京工业职业技术学院 | A kind of uninterrupted long unmanned plane battery charging and discharging device and method of continuing a journey |
| CN111262322A (en) * | 2018-12-03 | 2020-06-09 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle electrical system and control method |
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| CN203005746U (en) * | 2012-12-20 | 2013-06-19 | 北京航空航天大学 | Composite type multi-rotor aircraft |
| CN103552686A (en) * | 2013-10-21 | 2014-02-05 | 北京航空航天大学 | Combined type ducted aerial reconnaissance robot |
| CN104163241A (en) * | 2014-08-12 | 2014-11-26 | 中国航空工业经济技术研究院 | Unmanned logistics helicopter |
| CN204750571U (en) * | 2015-05-29 | 2015-11-11 | 沈阳航空航天大学 | A flight machine people for high -rise building fire control is put out a fire |
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| DE102012005208A1 (en) * | 2011-03-19 | 2012-09-20 | Tomislav Duvnjak | Vehicle e.g. life boat, has solar plant producing electrical power from sunlight and feeding power into storage unit, and wind power generator plant producing electrical power from wind energy and feeding power into storage unit |
| CN203005746U (en) * | 2012-12-20 | 2013-06-19 | 北京航空航天大学 | Composite type multi-rotor aircraft |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018006439A1 (en) * | 2016-07-04 | 2018-01-11 | 深圳市龙云创新航空科技有限公司 | Integrated power multi-axis unmanned aerial vehicle |
| CN108082497A (en) * | 2016-11-22 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of multi-purpose unmanned aerial vehicle of hybrid power |
| CN109204841A (en) * | 2017-06-30 | 2019-01-15 | 通用电气公司 | Method for the hybrid electric propulsion system of aircraft and for operating turbine |
| CN109204841B (en) * | 2017-06-30 | 2022-06-17 | 通用电气公司 | Hybrid electric propulsion system for an aircraft and method for operating a turbine |
| CN111262322A (en) * | 2018-12-03 | 2020-06-09 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle electrical system and control method |
| CN110048498A (en) * | 2019-02-11 | 2019-07-23 | 南京工业职业技术学院 | A kind of uninterrupted long unmanned plane battery charging and discharging device and method of continuing a journey |
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Application publication date: 20160601 |