CN110127064A - A kind of unmanned plane hybrid power system - Google Patents
A kind of unmanned plane hybrid power system Download PDFInfo
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- CN110127064A CN110127064A CN201910387612.3A CN201910387612A CN110127064A CN 110127064 A CN110127064 A CN 110127064A CN 201910387612 A CN201910387612 A CN 201910387612A CN 110127064 A CN110127064 A CN 110127064A
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- module
- unmanned plane
- charging
- management
- discharging
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- 238000007599 discharging Methods 0.000 claims abstract description 37
- 238000011105 stabilization Methods 0.000 claims abstract description 15
- 230000001052 transient effect Effects 0.000 claims abstract description 14
- 230000006641 stabilisation Effects 0.000 claims abstract description 13
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052744 lithium Inorganic materials 0.000 claims abstract description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 14
- 239000003990 capacitor Substances 0.000 claims description 9
- 238000011084 recovery Methods 0.000 claims description 9
- 229910052799 carbon Inorganic materials 0.000 claims description 8
- 238000003860 storage Methods 0.000 claims description 5
- 239000003792 electrolyte Substances 0.000 claims description 4
- 239000002041 carbon nanotube Substances 0.000 claims description 3
- 229910021393 carbon nanotube Inorganic materials 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 239000000446 fuel Substances 0.000 claims description 3
- 229910021389 graphene Inorganic materials 0.000 claims description 3
- 239000000178 monomer Substances 0.000 claims description 3
- 238000012856 packing Methods 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims description 3
- 239000007784 solid electrolyte Substances 0.000 claims description 3
- 238000007731 hot pressing Methods 0.000 claims description 2
- 239000003292 glue Substances 0.000 claims 1
- 229920000642 polymer Polymers 0.000 claims 1
- 238000004064 recycling Methods 0.000 claims 1
- 238000005183 dynamical system Methods 0.000 abstract description 9
- 230000008901 benefit Effects 0.000 abstract description 3
- 239000000203 mixture Substances 0.000 abstract description 2
- 230000000930 thermomechanical effect Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 7
- 239000002131 composite material Substances 0.000 description 5
- 239000000835 fiber Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 230000005611 electricity Effects 0.000 description 4
- 239000011521 glass Substances 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 230000004048 modification Effects 0.000 description 4
- 238000009413 insulation Methods 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 238000005538 encapsulation Methods 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 239000003822 epoxy resin Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229920000647 polyepoxide Polymers 0.000 description 2
- 239000005518 polymer electrolyte Substances 0.000 description 2
- 238000003672 processing method Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 244000045947 parasite Species 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/16—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like specially adapted for mounting power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/32—Wings specially adapted for mounting power plant
-
- B64D27/026—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
-
- 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
Abstract
A kind of unmanned plane hybrid power system, peak value transient dynamics output module and management of charging and discharging the module composition of stabilization power take-off module, high power density including high-energy density.The stabilization power take-off module and management of charging and discharging module of the high-energy density are arranged in fuselage, the peak value transient dynamics output module of the high power density is arranged in wing, and management of charging and discharging module is connected by harness with the peak value transient dynamics output module of the stabilization power take-off module of high-energy density and power density.The management of charging and discharging module is responsible for management of charging and discharging.The invention has the benefit that unmanned plane cruising ability can be improved, energy ecology is improved, will not influence unmanned plane topology layout and load；Supercapacitor can be processed into various unmanned thermomechanical components to match dynamical system demand；Supercapacitor provides unmanned plane power demand, and higher energy density lithium battery can be used, and meets long continuation of the journey while reducing battery cost.
Description
Technical field
The invention belongs to air vehicle technique fields, are related to a kind of unmanned plane hybrid power system.
Background technique
Traditional unmanned plane, which mostly uses, to be driven by electricity, and energy source is parasite power battery.And it by itself load limit and moves
The influence of Force system efficiency, the cruise duration of unmanned plane, course continuation mileage was usually no more than generally between 30min-60min
30km.In recent years, unmanned plane is in emergency management and rescue, environmental monitoring, power-line patrolling, mapping of taking photo by plane, agricultural plant protection and logistics distribution etc.
Multiple fields are used widely, and as global unmanned plane industry development is persistently raised speed, application popularization range is also constantly expanding
, unmanned plane cruising ability and loading problem also more highlight.
Supercapacitor has the application of considerable scale as the power source starting apparatus of unmanned plane, and by lithium battery and capacitor
The hybrid electrical storage device that device electric power storage principle combines also is put forward one after another.These are used in mixed way mode and meet to a certain extent
The performance requirement of unmanned aerial vehicle onboard dynamical system high-energy density, high output characteristic, but additional supercapacitor device also one
Determine the weight for increasing dynamical system in degree, affects the weight bearing and cruising ability of unmanned plane.
Summary of the invention
For above-mentioned problems of the prior art, the present invention provides a kind of unmanned plane hybrid power system, this is mixed
Continuation of the journey and load that dynamical system optimizes existing electronic unmanned plane to greatest extent are closed, in the premise for not increasing unmanned plane weight bearing
Under, realize the mutual supplement with each other's advantages of dynamical system high-energy density and high power density.
To achieve the goals above, the present invention adopts the following technical scheme that:
A kind of unmanned plane hybrid power system, the stabilization power take-off module including high-energy density, high power density
Peak value transient dynamics output module and management of charging and discharging module composition.
The stabilization power take-off module and management of charging and discharging module of the high-energy density are arranged in fuselage, the Gao Gong
The peak value transient dynamics output module of rate density is arranged in wing, and management of charging and discharging module passes through harness and high-energy density
Stablize power take-off module to be connected with the peak value transient dynamics output module of power density.The management of charging and discharging module is responsible for filling
Electric discharge management.
Further, the stabilization power take-off module of the high-energy density can be traditional storage battery, lithium battery,
The one or more of fuel cell or solar battery.
Further, the peak value transient dynamics output module of the high power density is by several supercapacitor monomer group moulds
It forms, the super capacitor module is set in wing or casing, by supercapacitor in a manner of the structural members such as wing or casing
It presents.
Further, several single supercapacitors can form respective mode group, super electricity in series or in parallel
The structure of container are as follows: the carbon cloth of the high-specific surface area of carbon nanotube and/or graphene modified is as electrode, solid electrolyte
Or structured packing (such as hollow glass micropearl, glass) preparation structure electrolyte is added in gel-form solid polymer electrolyte.Pass through heat
Pressure or other processing methods prepare " sandwich " structure supercapacitor.
Further, several single supercapacitors prepare mould group: positive and negative with epoxy resin or other insulation covering encapsulation
Pole tab is placed in encapsulating structure two sides, and is attached according to demand, and connection structure is insulated by plug-type mechanical device protects
Shield, the material of mechanical device are also preferred with carbon fibre composite.
Further, energy recovery module is equipped in the wing.
Further, the management of charging and discharging module is connected by conducting wire with supercapacitor, and the supercapacitor is logical
It crosses conducting wire and is connected with motor.
Further, the motor is connected with rotor.
Further, the management of charging and discharging module is connected with charging AM access module by conducting wire.
Further, the management of charging and discharging module is connected with electric machine controller by conducting wire, and the electric machine controller is logical
Conducting wire is crossed to be connected to the motor.The electric machine controller is DC communication converter unit.
Further, the motor is connected with brake by conducting wire, and the brake passes through conducting wire and energy regenerating mould
Block is connected, and the energy recovery module is connected by conducting wire with supercapacitor and management of charging and discharging module.
Further, the fuselage and wing are made of carbon fibre composite.
Further, power battery module is equipped in the fuselage.
When unmanned plane velocity-stabilization, that is, when stable energy being needed to input, management of charging and discharging module can control power electric
Chi Mo group conveys energy, is worked by electric machine controller driving motor.When unmanned plane starts or sharply accelerates, charge and discharge fulgurite
It manages module control high-power super capacitor and exports energy, driving motor operation.And unmanned plane when braking suddenly, is exactly brake fortune
When row, braking energy is had, energy is recovered to super by braking energy automatically by energy recovery module and management of charging and discharging module
Grade capacitor, energy is stored.On the one hand unmanned plane dynamical system capacity can be improved, improve unmanned plane cruising ability；Separately
On the one hand the energy loss that charge and discharge process is reduced by management of charging and discharging system, improves energy ecology.
The invention has the benefit that (1) fuselage and wing are all made of carbon fibre composite, structure will be had both and held
It carries and the structure supercapacitor of energy storage capacity incorporates unmanned aerial vehicle body or wing, unmanned plane dynamical system on the one hand can be improved
Capacity improves unmanned plane cruising ability；On the other hand the energy loss that charge and discharge process is reduced by management of charging and discharging system, mentions
High-energy service efficiency, and do not increase additional volume or weight, it will not influence unmanned plane topology layout and load.(2) structure
Supercapacitor can be processed into various unmanned thermomechanical components to match dynamical system demand by the workability of supercapacitor.(3)
Supercapacitor provides unmanned plane power demand, and higher energy density lithium battery can be used, and meets long continuation of the journey while reducing battery
Cost.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is unmanned plane cantilever energy storage device structure schematic diagram；
Fig. 3 is supercapacitor structures schematic diagram；
Fig. 4 is unmanned plane hybrid power system working principle diagram；
Fig. 5 is super capacitor module structural schematic diagram；
Fig. 6 is supercapacitor Parallel connection structure schematic diagram；
Fig. 7 is supercapacitor series arrangement schematic diagram.
Appended drawing reference: 1- fuselage, 2- wing, 3- management of charging and discharging module, 4- power battery module, 5- supercapacitor,
6- motor, 7- rotor, 8- energy recovery module, 9- charging AM access module, 10- electric machine controller, 11- brake, a- stablizes low
Load, the instantaneous high load capacity of b-.
Specific embodiment
In order to make it easy to understand, with reference to the accompanying drawing, by embodiment, the present invention will be described in detail:
A kind of unmanned plane hybrid power system, the stabilization power take-off module including high-energy density, high power density
Peak value transient dynamics output module and management of charging and discharging module 3.
The stabilization power take-off module and management of charging and discharging module 3 of high-energy density are set in fuselage 1.High power density
Peak value transient dynamics output module is set in wing 2.Fuselage 1 and wing 2 are made of carbon fibre composite.The end of wing
Equipped with motor 6.Motor 6 is connected with rotor 7.
The stabilization power take-off module of high-energy density can be traditional storage battery, lithium battery, fuel cell or solar energy
The one or more of battery.
The peak value transient dynamics output module of high power density is formed by several 5 monomer group moulds of supercapacitor；Super electricity
Container 5 is arranged in wing or casing, and supercapacitor 5 is presented in a manner of the structural members such as wing or casing.
Single supercapacitor 5 can form respective mode group in the way of string or parallel connection.
The structure of supercapacitor 5 are as follows: the carbon cloth of the high-specific surface area of carbon nanotube or graphene modified is as electricity
Structured packing (such as hollow glass micropearl, glass) preparation structure is added in pole, solid electrolyte or gel-form solid polymer electrolyte
Electrolyte." sandwich " structure supercapacitor is prepared by hot pressing or other processing methods.
Single supercapacitor 5 prepares mould group: being placed in envelope with epoxy resin or other insulation covering encapsulation, positive and negative anodes tab
Assembling structure two sides, and being attached according to demand, connection structure by plug-type mechanical device insulation protection, mechanical device
Material is also preferred with carbon fibre composite.
The peak value that management of charging and discharging module 3 passes through the stabilization power take-off module and power density of harness and high-energy density
Transient dynamics output module is connected.
Management of charging and discharging module 3 is connected by conducting wire with supercapacitor 5, and supercapacitor 5 passes through conducting wire and 6 phase of motor
Even.
Power battery module 4 is equipped in fuselage 1, charge AM access module 9, electric machine controller 10 and brake 11.
Management of charging and discharging module 3 connects charging AM access module 9 by conducting wire and electric machine controller 10, electric machine controller 10 are
DC communication converter unit.Electric machine controller 10 is connected by conducting wire with motor 6.
Energy recovery module 8 is equipped in wing 2.Motor 6 is connected by conducting wire with brake 11, and brake 11 passes through conducting wire
It is connected with energy recovery module 8, energy recovery module 8 is connected by conducting wire with supercapacitor 5 and management of charging and discharging module 3.
Management of charging and discharging module 3 is responsible for management of charging and discharging.Unmanned plane velocity-stabilization, that is, stable energy is needed to input,
I.e. in when stablizing underload a, management of charging and discharging module 3 can control power battery module 4 and convey energy, pass through electric machine controller
The work of 10 driving motors 6.
When unmanned plane starts or sharply accelerates, that is, is in instantaneous high load capacity b, management of charging and discharging module 3 controls big function
Rate super capacitor 5 exports energy, and driving motor 6 is run.
And unmanned plane when being exactly that brake 11 is run, has braking energy when braking suddenly, braking energy passes through energy and returns
It receives module 8 and energy is recovered to super capacitor 5 by management of charging and discharging module 3 automatically, energy is stored.On the one hand it can mention
High unmanned plane dynamical system capacity improves unmanned plane cruising ability；On the other hand charge and discharge are reduced by management of charging and discharging system
The energy loss of process improves energy ecology.
Above-described embodiment is the illustration or explanation to technical solution of the present invention, be but should not be understood as to skill of the present invention
The limitation of art scheme, it is clear that those skilled in the art can carry out various modifications the present invention and modification is without departing from the present invention
Spirit and scope.If these modifications and variations are within the scope of the claims of the present invention and its equivalent technology, then originally
Including invention also includes these modifications and variations.
Claims (10)
1. a kind of unmanned plane hybrid power system, it is characterised in that: stabilization power take-off module, height including high-energy density
The peak value transient dynamics output module and management of charging and discharging module of power density form, and the stabilization power of the high-energy density is defeated
Module and management of charging and discharging module are set in fuselage out, and the peak value transient dynamics output module of the high power density is set to wing
Peak value wink interior, that the management of charging and discharging module passes through the stabilization power take-off module and power density of harness and high-energy density
When power take-off module be connected.
2. a kind of unmanned plane hybrid power system according to claim 1, it is characterised in that: the high-energy density
Stablize the one or more that power take-off module is traditional storage battery, lithium battery, fuel cell or solar battery.
3. a kind of unmanned plane hybrid power system according to claim 1, it is characterised in that: the high power density
Peak value transient dynamics output module is formed by several supercapacitor monomer group moulds, and super capacitor module is set to wing or casing
It is interior.
4. a kind of unmanned plane hybrid power system according to claim 3, it is characterised in that: the management of charging and discharging mould
Block is connected by conducting wire with supercapacitor, and supercapacitor is connected with motor by conducting wire.
5. a kind of unmanned plane hybrid power system according to claim 1, it is characterised in that: the management of charging and discharging mould
Block is connected with electric machine controller by conducting wire, and the electric machine controller is connected to the motor by conducting wire.
6. a kind of unmanned plane hybrid power system according to claim 4, it is characterised in that: be equipped with energy in the wing
Measure recycling module.
7. a kind of unmanned plane hybrid power system according to claim 6, it is characterised in that: the motor passes through conducting wire
Be connected with brake, the brake is connected by conducting wire with energy recovery module, the energy recovery module pass through conducting wire and
Supercapacitor is connected with management of charging and discharging module.
8. a kind of unmanned plane hybrid power system according to claim 3, it is characterised in that: several single super capacitors
Device can form respective mode group in the way of string or parallel connection.
9. a kind of unmanned plane hybrid power system according to claim 3, it is characterised in that: the structure of supercapacitor
Are as follows: for the carbon cloth of the high-specific surface area of carbon nanotube and/or graphene modified as electrode, solid electrolyte or polymer are solidifying
Structured packing preparation structure electrolyte is added in glue electrolyte, passes through standby " sandwich " the structure supercapacitor of hot pressing.
10. a kind of unmanned plane hybrid power system according to claim 1 to 9, it is characterised in that: described
Management of charging and discharging module is connected with charging AM access module by conducting wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910387612.3A CN110127064A (en) | 2019-05-10 | 2019-05-10 | A kind of unmanned plane hybrid power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910387612.3A CN110127064A (en) | 2019-05-10 | 2019-05-10 | A kind of unmanned plane hybrid power system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110127064A true CN110127064A (en) | 2019-08-16 |
Family
ID=67577009
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910387612.3A Pending CN110127064A (en) | 2019-05-10 | 2019-05-10 | A kind of unmanned plane hybrid power system |
Country Status (1)
| Country | Link |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110696575A (en) * | 2019-10-25 | 2020-01-17 | 西北工业大学 | Amphibious observer for observing underwater environment |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108367685A (en) * | 2015-09-16 | 2018-08-03 | 高通股份有限公司 | Battery management system for the autonomous vehicles |
| CN210102008U (en) * | 2019-05-10 | 2020-02-21 | 费曼科技(青岛)有限公司 | Hybrid power system for unmanned aerial vehicle |
-
2019
- 2019-05-10 CN CN201910387612.3A patent/CN110127064A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108367685A (en) * | 2015-09-16 | 2018-08-03 | 高通股份有限公司 | Battery management system for the autonomous vehicles |
| CN210102008U (en) * | 2019-05-10 | 2020-02-21 | 费曼科技(青岛)有限公司 | Hybrid power system for unmanned aerial vehicle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110696575A (en) * | 2019-10-25 | 2020-01-17 | 西北工业大学 | Amphibious observer for observing underwater environment |
| CN110696575B (en) * | 2019-10-25 | 2021-07-27 | 西北工业大学 | Amphibious observer for observing underwater environment |
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