CN106130151A - A kind of Aircraft Electrical System and method of supplying power to thereof - Google Patents
A kind of Aircraft Electrical System and method of supplying power to thereof Download PDFInfo
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- CN106130151A CN106130151A CN201610545820.8A CN201610545820A CN106130151A CN 106130151 A CN106130151 A CN 106130151A CN 201610545820 A CN201610545820 A CN 201610545820A CN 106130151 A CN106130151 A CN 106130151A
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- WBJZTOZJJYAKHQ-UHFFFAOYSA-K iron(3+) phosphate Chemical compound [Fe+3].[O-]P([O-])([O-])=O WBJZTOZJJYAKHQ-UHFFFAOYSA-K 0.000 claims description 3
- 229910000399 iron(III) phosphate Inorganic materials 0.000 claims description 3
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- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L50/00—Electric propulsion with power supplied within the vehicle
- B60L50/40—Electric propulsion with power supplied within the vehicle using propulsion power supplied by capacitors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L50/00—Electric propulsion with power supplied within the vehicle
- B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B61—RAILWAYS
- B61C—LOCOMOTIVES; MOTOR RAILCARS
- B61C5/00—Locomotives or motor railcars with IC engines or gas turbines
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01G—CAPACITORS; CAPACITORS, RECTIFIERS, DETECTORS, SWITCHING DEVICES, LIGHT-SENSITIVE OR TEMPERATURE-SENSITIVE DEVICES OF THE ELECTROLYTIC TYPE
- H01G11/00—Hybrid capacitors, i.e. capacitors having different positive and negative electrodes; Electric double-layer [EDL] capacitors; Processes for the manufacture thereof or of parts thereof
- H01G11/08—Structural combinations, e.g. assembly or connection, of hybrid or EDL capacitors with other electric components, at least one hybrid or EDL capacitor being the main component
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
- H01M10/4207—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells for several batteries or cells simultaneously or sequentially
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0013—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries acting upon several batteries simultaneously or sequentially
- H02J7/0014—Circuits for equalisation of charge between batteries
-
- H02J7/0026—
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/0036—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits using connection detecting circuits
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0047—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with monitoring or indicating devices or circuits
-
- H02J7/0086—
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/02—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from ac mains by converters
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/345—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering using capacitors as storage or buffering devices
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P1/00—Arrangements for starting electric motors or dynamo-electric converters
- H02P1/02—Details of starting control
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/00302—Overcharge protection
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/00304—Overcurrent protection
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
- H02J7/00306—Overdischarge protection
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
-
- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/70—Energy storage systems for electromobility, e.g. batteries
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Sustainable Development (AREA)
- Manufacturing & Machinery (AREA)
- General Chemical & Material Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Electrochemistry (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
- Transceivers (AREA)
Abstract
The present invention relates to a kind of Aircraft Electrical System and method of supplying power to thereof, the electrical equipment of the aircraft with internal combustion engine as power is made a distinction by the present invention according to power characteristic, it is divided into power-type power unit and non-power type power unit, by energy supply side and the coupling of energy requirement side and balance.The Aircraft Electrical System of the present invention includes energy unit and power cell, connect between energy unit and power cell outfan and have isolated location, energy unit outfan is for electrically connecting airborne power device, power cell outfan starts motor for electrical connection, isolated location is for when power cell is powered for starting motor, disconnecting the current path of power cell and energy unit.The present invention is powered for starting motor by power cell, solve current Aircraft Electrical System and cause accumulator " excess configuration " owing to using accumulator to power for startup motor, to battery current impact greatly, cause the life of storage battery to reduce, other power unit powers the problems such as shakiness.
Description
Technical field
The present invention relates to a kind of Aircraft Electrical System and method of supplying power to thereof, belong to Circuits System applied technical field.
Background technology
Various aircrafts have become as the daily traffic of people, transport and the tool of production, such as manned large, medium and small type passenger plane,
The transporter of transport goods and various special use aircraft, engine power unmanned plane etc..Electrical system is that aircraft is essential
A part, aircraft conventional electrical system as it is shown in figure 1, be mainly made up of onboard generators, voltage regulator, accumulator etc.,
Electrical equipment is broadly divided into according to power characteristic to be needed transient state powerful startup motor and continues other airborne use low power
Electric installation, aircraft accumulator is one of requisite power supply of electric power system, when the internal combustion engine start of aircraft to starting motor
Power supply；When electromotor does not works or electromotor works under the highest rotating speed, accumulator is powered to aircraft power consumer apparatus；In power consumption
When rating of set exceedes its TRT power, accumulator is powered to power consumer apparatus with generator combined.Accumulator in aircraft
Should be responsible for providing airborne power device (as instrument show, program self-inspection, the little merit such as glittering, sound equipment short-term operation of signal lights
Rate device) energy, again be responsible for provide engine start moment powerful energy, in operative practice, this scheme is sudden and violent
Expose problems with:
1. aircraft engine starts system electrical characteristics different with other power device to accumulator property requirement difference very
Big: starting system requirements battery discharging high rate performance excellent, other power consumer apparatus then requires that accumulator possesses certain capacity
Can, high rate performance less demanding, this situation causes accumulator to be the big merit of the transient state needed for meeting aircraft engine cold start-up
Rate, it has to " excess configuration ", makes battery the biggest but also heavy, had both wasted resource the most uneconomical.
2. external when using under the electric equipment in use aircraft long-time under aircraft engine flameout state, flameout state
Forget to close the situations such as current consuming apparatus after power-supply device, shutdown, discharged or defective battery will be caused cannot to complete aircraft engine
Next time starts.
3. aircraft engine cold start-up electric current is relatively big, relatively big to the rush of current of lead-acid accumulator, causes positive plate activity
Material comes off so that lead-acid battery pool-size declines very fast, service life shorter (generally 2～3 years), changes more frequent,
Increase subscriber equipment maintenance workload and use cost；During aircraft accumulator uses, due to user of service or attendant
Cannot accurately confirm that accumulator uses state, generally using the aircraft phenomenon having some setbacks that starts afterwards overnight as judging the life of storage battery
The standard of termination rather than cannot electric power storage or cannot regular supply aircraft power consumer apparatus electricity consumption scrap as accumulator using accumulator
Standard, causes accumulator " to be sentenced useless too early ".
4., when aircraft engine starts (particularly cold start-up), accumulator instantaneous voltage drop is relatively big, causes aircraft voltage quick
Sense equipment (computer system, programmable logic controller (PLC), electronic equipment etc.) cannot normally work, and easily occurs that computer is disorderly
The faults such as unrest, loss of data and equipment are out of service, even cause the accidental damage of airborne equipment time serious.
To this end, it has been proposed that accumulator two ends parallel connection super capacitor mode jointly be start motor power, although
This scheme extends the service life of accumulator to a certain extent, but accumulator is also intended to undertake the startup starting motor
Task, does not the most fundamentally solve accumulator and powers cause battery current impact big for starting motor, cause accumulator
The problems such as service life reduction.
Summary of the invention
It is an object of the invention to provide a kind of Aircraft Electrical System and method of supplying power to thereof, with solution employing accumulator be at present
Aircraft starts motor to be provided and starts energy and cause accumulator " excess configuration " and be vulnerable to heavy current impact and affect asking of life-span
Topic.
The present invention solves that above-mentioned technical problem provides a kind of Aircraft Electrical System, including starting motor, airborne generating
Machine and airborne power device, this electrical system also includes energy unit and power cell, energy unit and power cell outfan
Between connect and have an isolated location, energy unit outfan is for electrically connecting airborne power device, and power cell outfan is for electrical connection
Starting motor, described isolated location is for when power cell is powered for starting motor, disconnecting power cell and energy unit
Current path, described energy unit is energy storage device, and described power cell is the energy storage device of high-multiplying power discharge.
Described isolated location is switching tube, catalyst or relay.
Described isolated location also includes that control circuit, described control circuit include controlling interface and the first detection connects
Mouthful, described first detection interface is used for detecting whether startup motor starts, and described control interface is in the first detection interface inspection
Measure startup motor to be started time, disconnect the electrical connection of power cell and energy unit.
Described control circuit also includes for detecting the second detection interface that power cell electricity is the most sufficient, when first
Detection interface detects that startup motor does not works and the second detection interface is when power cell electricity deficiency being detected, power cell with
Energy unit is not by isolated location connecing, the most not and connect.
Described power cell be ultracapacitor monomer, by ultracapacitor monomer connection in series-parallel composition module or
Array of capacitors.
Described energy unit be lead-acid battery, Ni-MH battery, lithium manganate battery, ferric phosphate lithium cell, ternary battery and
Any one in lithium titanate battery.
Present invention also offers the method for supplying power to of a kind of Aircraft Electrical System, the method by the electrical equipment of aircraft according to merit
Rate characteristic makes a distinction, and is divided into power-type power unit and non-power type power unit, and power-type power unit is by power cell
Power supply, non-power type power unit is powered by energy unit, carries out electricity by isolated location between power cell and energy unit
Air bound from, power cell be power-type power unit power time, isolated location disconnect the company of power cell and energy unit
Connecing, power cell be individually for power-type power unit and power, described power cell is the energy storage device of high-multiplying power discharge.
Described isolated location is connected between energy unit and power cell outfan.
When power-type power unit does not works, isolated location judges that power cell electricity is the most sufficient, if electricity is not enough,
Power cell and energy unit are not by isolated location and connect, energy unit be its charging, the most not and connect.
Described power cell be ultracapacitor monomer, by ultracapacitor monomer connection in series-parallel composition module or
Array of capacitors.
The invention has the beneficial effects as follows: aircraft electrical power supply system of the present invention uses combination type superbattery to provide electric energy, combination
Formula superbattery includes energy unit and power cell, and connecting between energy unit and power cell outfan has isolated location,
Energy unit outfan is for electrically connecting airborne power device, and power cell outfan starts motor for electrical connection, and isolated location is used
In time powering for starting motor at power cell, disconnecting the current path of power cell and energy unit, energy unit is energy storage
Device, power cell is can the energy storage device of high-multiplying power discharge.The present invention is by only with the merit in combination type superbattery
Rate unit is powered for starting motor, prevents from can not starting because accumulator over-discharge causes starting motor, affects the normal work of aircraft
Making, energy unit no longer undertakes the high-power job task of transient state, does not haves the situation of instantaneous bigger voltage drop, it is ensured that aircraft
Electrical system can steady operation, decrease the damage caused by electric loading because of quality of power supply shakiness.
Accompanying drawing explanation
Fig. 1 is conventional airplane electrical system architecture block diagram；
Fig. 2 is Aircraft Electrical System structured flowchart of the present invention；
Fig. 3 is Aircraft Electrical System structured flowchart of the present invention；
Fig. 4 is the isolated location structure chart that Aircraft Electrical System of the present invention is used.
Detailed description of the invention
Below in conjunction with the accompanying drawings the detailed description of the invention of the present invention is described further.
A kind of embodiment of the aircraft electrical power supply system of the present invention
Aircraft has become as the daily traffic of people, transport and the tool of production, and aircraft is in start-up course, it is generally required to open
The drive of galvanic electricity machine, startup motor, as power-type power unit, needs transient state high-power on startup, and the present invention uses power
Unit is its power supply.In same electrical system, power-type power unit is relative concept with non-power type power unit.Merit
Rate type power unit possesses lasting electricity consumption time short (less than 10 seconds), high-power (rated current is typically more than tens amperes)
With electrical feature, in the electrical system of aircraft, internal combustion engine start motor is exactly the power-type power unit in this electrical system；Non-
Power-type power unit possesses that the lasting electricity consumption time is changeable, the use of small-power (rated current is typically below tens amperes)
Electrical feature, in the electrical system of aircraft, instrument shows, program self-inspection, the small-power such as glittering, sound equipment short-term operation of signal lights
Device is energy type power unit.
Aircraft Electrical System in the present embodiment, as shown in Figures 2 and 3, including onboard generators 7, starts motor 1, machine
Carrying power device 6 and combination type superbattery, combination type superbattery includes power cell 4, isolated location 3 and energy unit 5,
Isolated location 3 is connected between energy unit and power cell outfan, and energy unit 5 outfan is for electrically connecting airborne Denso
Putting 6, power cell 4 outfan starts motor 1 by activate switch 2 for electrical connection, and the voltage of onboard generators 7 is by voltage-regulation
Device 8 regulates, for realizing the stable output of onboard generators 7 voltage.When the internal combustion engine starts up, closing activate switch 2, isolation is single
Unit 3 disconnects the current path between power cell 4 and energy unit 5, is only powered for starting motor by power cell 4.Energy list
Unit 5 no longer undertakes the high-power job task of transient state, and the lasting energy supply of the most responsible low-power load, energy unit does not haves instantaneous
The situation of bigger voltage drop, it is ensured that airborne electric power system can stably export, and energy unit is not damaged by heavy current impact, the longevity
Order longer, it is to avoid energy unit is sentenced useless by " too early ", causes waste.Can be according to the energy of airborne power consumer apparatus by energy unit
Require configuration capacity, suitably reduce its volume and weight, type selection realizes " weight reducing " thus economizes on resources, reduce ring
Environment pollution；Only relying on power cell to start, the startability making aircraft is more preferable, especially at low-temperature startup, prevents because flying
Machine battery electric discharge excessively causes the situation that aircraft engine can not start.
Power cell 4 can be ultracapacitor monomer, the module consisted of connection in series-parallel ultracapacitor monomer, or
Person's traditional capacitor array, as shown in Figure 2.Power cell 4 may be used without the energy storage device of high rate performance and low temperature performance excellent,
As it is shown on figure 3, energy storage device can be to possess high-multiplying-power discharge performance accumulator, such as lithium ion battery (ferric phosphate lithium, ternary
System, LiMn2O4 system, lithium titanate system etc.) and coiled high-rate lead-acid battery, it is also possible to it is low temperature high-rate lithium battery and low temperature
High magnification lead-acid battery.Energy unit 5 can be lead-acid battery, it is also possible to be Ni-MH battery, it is also possible to be lithium manganate battery, phosphorus
Acid lithium iron battery, ternary battery, lithium titanate battery etc. therein any one.Power cell storage energy specific energy unit storage
Energy is much smaller, but efficiency for charge-discharge and power characteristic are the most much higher.
Isolated location has control function, it is possible to starts according to power-type power unit and realizes energy unit and power cell
Isolation.The isolated location of the present invention is switching tube, catalyst or relay, includes control circuit, and control circuit is arranged
Having control interface and the first detection interface, the first detection interface is used for detecting whether startup motor starts, and controls interface and is used for controlling
Whether isolated location processed disconnects the current path between power cell and energy unit, when the first detection interface detects startup electricity
When machine starts, isolation power cell and the electrical connection of energy unit.In order to prevent when energy unit discharges, power cell and
Energy unit discharges together, adversely affects power cell, and the control circuit of the present invention also includes for detecting power
The second detection interface that unit electricity is the most sufficient, when the first detection interface detects that startup motor does not works and the second detection connects
When mouthful power cell electricity deficiency being detected, power cell does not passes through isolated location with energy unit and connects, the most not and connect.This
Bright used isolated location also can use the implementation of hand switch, is operated with manual switches and realizes power cell and energy list
The isolation of unit.
Additionally, as required, Dynamic Test Transient activity of force compensator also includes peripheral circuit, and this peripheral circuit includes and power list
Testing circuit, protection and equalizing circuit that unit connects and management and display module, as shown in Figure 4, examined in real time by testing circuit
The electricity of power scale unit, by protection and equalizing circuit realize the balance protection of power cell, charge protection, discharge prevention,
Overvoltage protection, under-voltage protection, overcurrent protection, overheat protector and short-circuit protection function etc., it is right to be realized by management and display module
Management and the parameter of power cell show.Testing circuit, protection and equalizing circuit and management and display module can be real as required
Existing function is designed, and the realization of each functional circuit belongs to routine techniques means to those skilled in the art, here
No longer provide concrete circuit explanation.
A kind of embodiment of the method for supplying power to of the Aircraft Electrical System of the present invention
The present embodiment method of supplying power to is directed to Aircraft Electrical System, and the method is special according to power by the electrical equipment of aircraft
Property makes a distinction, and is divided into power-type power unit and non-power type power unit, and in the present embodiment, power-type power unit refers to
Being to start motor, non-power type power unit refers to other the airborne power device in addition to starting motor.Power-type electricity consumption
Unit is only powered by the power cell in Dynamic Test Transient activity of force compensator, when the internal combustion engine starts up, and power cell and energy unit
Electrical connection disconnected by isolated location, only with power cell for start motor power；Non-power type power unit
By the energy unit in parallel with Dynamic Test Transient activity of force compensator or generator powered, when power-type power unit does not works, by
Energy unit provides electric energy for other power consuming device, and isolated location judges that power cell electricity is the most sufficient simultaneously, if electricity is not
During foot, power cell and energy unit are not by isolated location and connect, energy unit be that it is powered, the most not and connect.
The method is as follows for the power supply process of electrical system in system embodiment: when aircraft engine starts, Guan Bi opens
Dynamic switch 2, controls isolated location and disconnects the electrical connection between power cell 4 and energy unit 5, make power cell 4 to startup
Motor 1 discharges；After engine start completes, activate switch 2 disconnects, and isolated location 3 turns on, and power cell 4 is with energy unit 5 even
Logical, onboard generators 7 starts to power to airborne power device 6, and charges to energy unit 5 and power cell 4, and airborne
When electromotor cannot meet airborne power device, energy unit power for airborne power device together with onboard generators；When
When onboard generators 7 quits work, control isolated location and disconnect the electrical connection between power cell 4 and energy unit 5, if machine
Carrying power device 6 to work on, the most required electric energy is provided by energy unit 5 completely, controls isolated location and disconnects power list
Electrical connection between unit 4 and energy unit 5, isolated location 3 stops power cell 4 to discharge, thus guaranteed output unit 4 can
Carry out follow-up startup.
Aircraft electrical power supply system of the present invention uses combination type superbattery to provide energy for it, utilizes combination type superbattery
Power cell provides for power-type power unit and starts electric energy, makes energy unit no longer undertake the high-power job task of transient state, energy
Amount unit is only responsible for the lasting energy supply of low-power load, it is to avoid energy unit, by heavy current impact, can be effectively improved it and uses
Life-span.Meanwhile, energy unit type selection can " be reduced weight ", it is achieved miniaturization, lightweight.Additionally, power cell is only used
In powering for starting motor, when energy unit be power consumer apparatus power time, isolated location disconnect power cell and energy unit it
Between the path of electric current, it is to avoid power cell discharges to energy unit, has certain protective effect to power cell.Rely on simultaneously
The Dynamic Test Transient activity of force compensator of the present invention starts, and internal combustion engine start is more preferable, and especially low-temperature startup is more preferable, energy
Unit does not haves the situation of instantaneous bigger voltage drop, it is ensured that aircraft electrical power supply system can stably export, and reduces non-power type and uses
The damage that electric unit causes because of quality of power supply shakiness.Aircraft electrical equipment is divided into power-type power unit and non-power by the present invention
Type power unit, power-type power unit only powered by the power cell in Dynamic Test Transient activity of force compensator, non-power type electricity consumption
Unit, by the energy unit in parallel with Dynamic Test Transient activity of force compensator or generator powered, reaches energy supply side and energy requirement
The coupling of side and balance, make Aircraft Electrical System be optimized, and extends the life-span, improves performance, reduces the wasting of resources and system dimension
Protect workload, and by lightweight and the employing of the power cell of higher efficiency, it is achieved energy-saving and emission-reduction.
Claims (10)
1. an Aircraft Electrical System, including starting motor, onboard generators and airborne power device, it is characterised in that this electricity
Gas system also includes energy unit and power cell, and connecting between energy unit and power cell outfan has isolated location, energy
Amount unit outfan is for electrically connecting airborne power device, and power cell outfan starts motor, described isolated location for electrical connection
For when power cell is powered for starting motor, disconnecting the current path of power cell and energy unit, described energy list
Unit is energy storage device, and described power cell is the energy storage device of high-multiplying power discharge.
Aircraft Electrical System the most according to claim 1, it is characterised in that described isolated location is switching tube, contact
Device or relay.
Aircraft Electrical System the most according to claim 1, it is characterised in that described isolated location also includes controlling electricity
Road, described control circuit includes controlling interface and the first detection interface, and described first detection interface is used for detecting startup motor
Whether start, described control interface for first detection interface detect startup motor to be started time, disconnect power cell with
The electrical connection of energy unit.
Aircraft Electrical System the most according to claim 3, it is characterised in that described control circuit also includes for detecting
The second detection interface that power cell electricity is the most sufficient, when the first detection interface detects that startup motor does not works and the second inspection
Surveying interface when power cell electricity deficiency being detected, power cell does not passes through isolated location with energy unit and connects, the most not and connect.
Aircraft Electrical System the most according to claim 1, it is characterised in that described power cell is ultracapacitor list
Body, the module formed by ultracapacitor monomer connection in series-parallel or array of capacitors.
Aircraft Electrical System the most according to claim 1, it is characterised in that described energy unit is lead-acid battery, nickel
Any one in hydrogen battery, lithium manganate battery, ferric phosphate lithium cell, ternary battery and lithium titanate battery.
7. the method for supplying power to of an Aircraft Electrical System, it is characterised in that the method is special according to power by the electrical equipment of aircraft
Property makes a distinction, and is divided into power-type power unit and non-power type power unit, and power-type power unit is powered by power cell,
Non-power type power unit is powered by energy unit, between power cell and energy unit by isolated location carry out electrically every
From, power cell be power-type power unit power time, isolated location disconnect the connection of power cell and energy unit, by
Power cell is individually for power-type power unit and powers, and described power cell is the energy storage device of high-multiplying power discharge.
The method of supplying power to of Aircraft Electrical System the most according to claim 7, it is characterised in that described isolated location connects
Between energy unit and power cell outfan.
9. according to the method for supplying power to of the Aircraft Electrical System described in claim 7 or 8, it is characterised in that when power-type electricity consumption list
When unit does not works, isolated location judges that power cell electricity is the most sufficient, if electricity is not enough, power cell passes through with energy unit
Isolated location also connects, energy unit be not its charging, the most not and connect.
The method of supplying power to of Aircraft Electrical System the most according to claim 7, it is characterised in that described power cell is
Ultracapacitor monomer, the module formed by ultracapacitor monomer connection in series-parallel or array of capacitors.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2016102439262 | 2016-04-18 | ||
| CN201610243926.2A CN105790365A (en) | 2016-04-18 | 2016-04-18 | Electrical system of internal-combustion-engine powered vehicle and power supply method thereof |
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| CN106130151A true CN106130151A (en) | 2016-11-16 |
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| CN201610243926.2A Pending CN105790365A (en) | 2016-04-18 | 2016-04-18 | Electrical system of internal-combustion-engine powered vehicle and power supply method thereof |
| CN201610546111.1A Pending CN106130152A (en) | 2016-04-18 | 2016-07-12 | A kind of naval electric systems and method of supplying power to thereof |
| CN201620731178.8U Active CN205945194U (en) | 2016-04-18 | 2016-07-12 | Electric system of wireless data transmission device |
| CN201610545819.5A Pending CN106042967A (en) | 2016-04-18 | 2016-07-12 | Electrical system of electric vehicle and power supply method |
| CN201610544332.5A Pending CN106058997A (en) | 2016-04-18 | 2016-07-12 | Internal combustion generator electrical system and power supply method thereof |
| CN201610544359.4A Pending CN106059046A (en) | 2016-04-18 | 2016-07-12 | Combined emergency guarantee power source and power supply method thereof |
| CN201620728734.6U Active CN206099484U (en) | 2016-04-18 | 2016-07-12 | Aircraft electric system |
| CN201610544357.5A Pending CN106100090A (en) | 2016-04-18 | 2016-07-12 | A kind of internal-combustion engine vehicle electrical system and method for supplying power to thereof |
| CN201610546112.6A Pending CN106059035A (en) | 2016-04-18 | 2016-07-12 | Electrical system for wireless data transmission device and power supply method |
| CN201610544335.9A Pending CN106058998A (en) | 2016-04-18 | 2016-07-12 | Diesel locomotive electrical system and a power supply method thereof |
| CN201620728737.XU Active CN206099485U (en) | 2016-04-18 | 2016-07-12 | Naval vessel electric system |
| CN201610545820.8A Pending CN106130151A (en) | 2016-04-18 | 2016-07-12 | A kind of Aircraft Electrical System and method of supplying power to thereof |
| CN201620731179.2U Active CN205945204U (en) | 2016-04-18 | 2016-07-12 | Modular emergent guarantee power |
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| CN201610243926.2A Pending CN105790365A (en) | 2016-04-18 | 2016-04-18 | Electrical system of internal-combustion-engine powered vehicle and power supply method thereof |
| CN201610546111.1A Pending CN106130152A (en) | 2016-04-18 | 2016-07-12 | A kind of naval electric systems and method of supplying power to thereof |
| CN201620731178.8U Active CN205945194U (en) | 2016-04-18 | 2016-07-12 | Electric system of wireless data transmission device |
| CN201610545819.5A Pending CN106042967A (en) | 2016-04-18 | 2016-07-12 | Electrical system of electric vehicle and power supply method |
| CN201610544332.5A Pending CN106058997A (en) | 2016-04-18 | 2016-07-12 | Internal combustion generator electrical system and power supply method thereof |
| CN201610544359.4A Pending CN106059046A (en) | 2016-04-18 | 2016-07-12 | Combined emergency guarantee power source and power supply method thereof |
| CN201620728734.6U Active CN206099484U (en) | 2016-04-18 | 2016-07-12 | Aircraft electric system |
| CN201610544357.5A Pending CN106100090A (en) | 2016-04-18 | 2016-07-12 | A kind of internal-combustion engine vehicle electrical system and method for supplying power to thereof |
| CN201610546112.6A Pending CN106059035A (en) | 2016-04-18 | 2016-07-12 | Electrical system for wireless data transmission device and power supply method |
| CN201610544335.9A Pending CN106058998A (en) | 2016-04-18 | 2016-07-12 | Diesel locomotive electrical system and a power supply method thereof |
| CN201620728737.XU Active CN206099485U (en) | 2016-04-18 | 2016-07-12 | Naval vessel electric system |
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| WO2022095059A1 (en) * | 2020-11-09 | 2022-05-12 | 深圳市大疆创新科技有限公司 | Internal combustion charging system |
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| CN105790365A (en) * | 2016-04-18 | 2016-07-20 | 洛阳尹太科智能科技有限公司 | Electrical system of internal-combustion-engine powered vehicle and power supply method thereof |
| CN106876816B (en) * | 2017-03-17 | 2020-03-27 | 奇酷互联网络科技（深圳）有限公司 | Charging method and charging system |
| EP3425766B1 (en) * | 2017-07-03 | 2022-08-24 | Ningbo Geely Automobile Research & Development Co., Ltd. | A capacitor module |
| CN108482130A (en) * | 2018-03-27 | 2018-09-04 | 吉利汽车研究院（宁波）有限公司 | Energy regenerating control device, vehicle energy recovery system and automobile |
| EP3640074B1 (en) * | 2018-10-16 | 2022-12-21 | Ningbo Geely Automobile Research & Development Co. Ltd. | An electric power system |
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- 2016-04-18 CN CN201610243926.2A patent/CN105790365A/en active Pending
- 2016-07-12 CN CN201610546111.1A patent/CN106130152A/en active Pending
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- 2016-07-12 CN CN201610545819.5A patent/CN106042967A/en active Pending
- 2016-07-12 CN CN201610544332.5A patent/CN106058997A/en active Pending
- 2016-07-12 CN CN201610544359.4A patent/CN106059046A/en active Pending
- 2016-07-12 CN CN201620728734.6U patent/CN206099484U/en active Active
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| WO2022095059A1 (en) * | 2020-11-09 | 2022-05-12 | 深圳市大疆创新科技有限公司 | Internal combustion charging system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN205945194U (en) | 2017-02-08 |
| CN106100090A (en) | 2016-11-09 |
| CN105790365A (en) | 2016-07-20 |
| CN106058998A (en) | 2016-10-26 |
| CN106130152A (en) | 2016-11-16 |
| CN205945204U (en) | 2017-02-08 |
| CN106059046A (en) | 2016-10-26 |
| CN106058997A (en) | 2016-10-26 |
| CN106059035A (en) | 2016-10-26 |
| CN206099485U (en) | 2017-04-12 |
| CN106042967A (en) | 2016-10-26 |
| CN206099484U (en) | 2017-04-12 |
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