CN106712202A - Aircraft power supply management system and aircraft - Google Patents
Aircraft power supply management system and aircraft Download PDFInfo
- Publication number
- CN106712202A CN106712202A CN201710050640.7A CN201710050640A CN106712202A CN 106712202 A CN106712202 A CN 106712202A CN 201710050640 A CN201710050640 A CN 201710050640A CN 106712202 A CN106712202 A CN 106712202A
- Authority
- CN
- China
- Prior art keywords
- battery bag
- aircraft
- voltage
- management system
- battery
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012544 monitoring process Methods 0.000 claims abstract description 20
- 238000001514 detection method Methods 0.000 claims abstract description 9
- 230000005611 electricity Effects 0.000 claims description 12
- 239000006185 dispersion Substances 0.000 claims description 5
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000178 monomer Substances 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- 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
- H02J7/0019—Circuits for equalisation of charge between batteries using switched or multiplexed charge circuits
-
- H02J7/0021—
-
- 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
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses an aircraft power supply management system comprising N battery packs, a detection module which acquires monitoring data of the N battery packs, a charger and a BMS host. The N battery packs are arranged in parallel, and N is greater than or equal to 2. The charger comprises N paths of charging loops which are correspondingly connected with the N battery packs so as to charge the battery packs. Each charging loop is provided with a charging switch. The charger is connected with the detection module so as to acquire total voltage of each battery pack and rank the total voltage of the N battery packs. The charging switch corresponding to the battery pack of the lowest total voltage is successively conducted until the N charging switches are conducted. The multiple battery packs are independently arranged, and all the battery packs are charged in turn by starting from the battery pack of the lowest voltage so as to enhance the charging efficiency.
Description
Technical field
The present invention relates to power-supply management system, more particularly to aircraft power-supply management system.
Background technology
Because existing aircraft battery bag is cascaded, when being charged to it, can only be while to multiple battery bags simultaneously
Charge, charge efficiency extreme difference, and the difference such as specific internal resistance due to battery bag, not only cause that the electricity between battery bag is difficult to
Weighing apparatus, and it is easily damaged battery bag when charging.
Therefore, it is badly in need of a kind of aircraft and power-supply management system for solving the above problems.
The content of the invention
It is an object of the invention to provide a kind of aircraft electrical management system and aircraft, when charging so that in charging
Each battery bag between voltage maximum possible keep in balance, and improve charge efficiency.
It is upper purposeful in order to realize, the invention discloses a kind of aircraft electrical management system, including N number of battery bag, adopt
Collect the detection module of N number of battery bag monitoring data, and charger, N number of battery bag is arranged in parallel, N is described more than or equal to 2
Charger includes that the N roads charge circuit of connection corresponding with N number of battery bag charges with to the battery bag, often charging described in road
Loop is provided with a charge switch, and the charger is connected to obtain the total voltage of each battery bag with the detection module
And N number of total voltage is ranked up, the corresponding charge switch of the minimum battery bag of total voltage is sequentially turned on, until N number of institute
State charge switch conducting.
Compared with prior art, the present invention charges to each battery bag successively from the minimum battery bag of voltage so that charge
In each battery bag between voltage maximum possible keep in balance, and improve charge efficiency.Wherein, aircraft of the invention
Can be unmanned plane, light-duty or sports type airborne vehicle, hovercar etc..
It is preferred that each battery bag includes more piece single battery core respectively, the detection module also detects N number of electricity
Single battery core magnitude of voltage is often saved in the bag of pond, the charger often saves single battery core magnitude of voltage in also obtaining each battery bag,
And when single battery core magnitude of voltage is often saved in corresponding to battery bag or battery bag total voltage reaches blanking voltage, disconnect corresponding charging
Switch, until N number of charge switch disconnects, increases the security for charging.
It is preferred that the charger calculates the number that the charge switch disconnects and/or turns on, and opened according to the charging
Total charging voltage and/or total charging current of number and/or charge circuit described in conducting number real-time adjustment N roads are opened in shut-off.
It is preferred that the aircraft electrical management system also include N number of BMS modules corresponding with N number of battery bag and
One BMS main frames, described BMS modules one end is connected with corresponding battery bag, gathers the monitoring data of the battery bag and to described
Battery bag carries out security monitoring management, and the BMS modules other end to be connected with BMS main frames and be delivered to institute with by the monitoring data
BMS main frames are stated, the monitoring data includes the total voltage of each battery bag, the charger and the BMS host communications
To obtain the total voltage of each battery bag.Be independently arranged for multiple battery bags by the present invention, and each battery bag has independently
Discharge loop, charge circuit and BMS modules, independent monitoring, charge independence can be not only carried out to each battery bag, increase electricity
The service life of Chi Bao and use degree of safety.
Specifically, the monitoring data also including the voltage of the battery bag, temperature, electricity, each single battery core it is interior
Resistance and the voltage of each single battery core.
More preferably, the aircraft electrical management system also includes N number of discharge loop corresponding with N number of battery bag, N
The individual separate setting of the discharge loop.This programme provides independent current supply circuit to aircraft multiple power source, improves and flies
The safety in utilization and control precision of row device.
More preferably, N number of battery bag dispersion is installed on aircraft and by the discharge loop to correspondence position
Motor is powered.
More preferably, the aircraft electrical management system also includes 4 reserve battery bags, four reserve battery bags point
Not She Yu aircraft four positions all around, and be connected to a standby discharge loop.Four redundancy backups can be maximum
When ensuring that aircraft all around locates the reasons such as battery bag damage, short of electricity and causes to be unable to normal power supply of limit, it is possible to provide standby
Power supply, it is ensured that aircraft regular descent.
It is preferred that N is more than or equal to 20.
The invention also discloses a kind of aircraft, including several motors and aircraft electrical management system, it is described
Aircraft electrical management system is as it appears from the above, the aircraft electrical management system also includes N corresponding with N number of battery bag
Individual discharge loop, N number of separate setting of discharge loop, N number of discharge loop connect several drivings respectively
Motor, and the motor powered respectively.
It is preferred that several described motor dispersions are located at the correspondence position of the aircraft, N number of battery bag is faced
The motor is closely corresponded to set.
It is preferred that the aircraft electric discharge management system also includes 4 reserve battery bags, four reserve battery bags point
Not She Yu aircraft four positions all around, and be connected to a standby discharge loop, the standby discharge loop point
Not Lian Jie correspondence position motor.
Brief description of the drawings
Fig. 1 is the structured flowchart of aircraft electrical management system described in first embodiment of the invention.
Fig. 2 is the structured flowchart of aircraft electrical management system described in second embodiment of the invention.
Fig. 3 is the part-structure block diagram of aircraft electrical management system described in third embodiment of the invention.
Specific embodiment
To describe technology contents of the invention, structural feature, the objects and the effects in detail, below in conjunction with implementation method
And coordinate accompanying drawing to be explained in detail.
With reference to Fig. 1, in the first embodiment of the present invention, a kind of aircraft, including several motors 50 are disclosed
With aircraft electrical management system 100, the aircraft electrical management system 100 is including described in 40 battery bags 30 and 40
Battery bag 30 corresponding 40 discharge loops, 31,40 BMS modules 20, and charger 40 and one BMS main frames, 10,40 electricity
Pond bag 30 is arranged in parallel, and the separate setting of 40 discharge loops 31, each battery bag 30 includes more piece list respectively
Body battery core, described one end of BMS modules 20 is connected with corresponding battery bag 30, gathers the monitoring data of the battery bag 30 and to institute
Stating battery bag 30 carries out security monitoring management, and the other end of BMS modules 20 is connected with by the monitoring data with BMS main frames 10
Be delivered to the BMS main frames 10, the monitoring data includes the total voltage of each battery bag, the charger 40 include with
40 road charge circuits 41 of 40 correspondence connections of the battery bag 30 charge with to the battery bag 30, charge circuit described in per road
41 are provided with a charge switch K, and the charger 40 communicates to obtain the total of 40 battery bags 30 with the BMS main frames 10
Voltage is simultaneously ranked up to 40 total voltages, sequentially turns on the minimum corresponding charge switch of battery bag 30 of total voltage, directly
To 40 charge switch K conductings.40 discharge loops 31 connect 40 motors 50 and respectively to 40 respectively
The motor 50 is powered.Certainly, the quantity of the battery bag can also be 2, the numbers such as 3, or 20,30 etc.
More than 20 numbers.Certainly, it is every by the direct access of a detection module 20 ' in the second embodiment of the present invention with reference to Fig. 2
The total voltage of battery bag described in is replacing BMS modules 20 and BMS main frames 10.
Wherein, the power of motor 50 is not described in detail again by flight control system control.
Wherein, the monitoring data also includes often saving single battery core magnitude of voltage in the battery bag, and the charger 10 is also
Obtain and often save in each battery bag 30 single battery core magnitude of voltage, and single battery core magnitude of voltage is often saved in correspondence battery bag 30
Or battery bag total voltage is when reaching blanking voltage, corresponding charge switch K is disconnected, until 40 charge switch K disconnect.Increase
Plus the security for charging.Wherein, the monitoring data also voltage including the battery bag 30, temperature, electricity and each monomer
The internal resistance of battery core.
Preferably, the charger 10 calculates the number that the charge switch K disconnects and/or turns on, and is filled described in
Electric switch K disconnects number and/or total charging voltage of charge circuit 41 and/or total charging described in the tunnel of conducting number real-time adjustment 40
Electric current.
Preferably, 40 motor dispersions are located at the correspondence position of the aircraft, and 40 battery bags are faced
The motor is closely corresponded to set.
With reference to Fig. 1, the operation principle of aircraft electric discharge management system 100 of the present invention is described, when charger 400 connects outer
When portion's power supply proceeds by charging, the total voltage of the collection battery bag 30 of BMS modules 20 is simultaneously reported to BMS main frames 10, BMS master
The total voltage of battery bag 30 is delivered to charger 10 by machine 10, charger 10 to the total voltage of all of battery bag 30 from low to high
Carrying out sort in real time, find out the minimum battery bag 30 of total voltage, such as battery bag 30 is arranged from low to high according to total voltage
Sequence is respectively：3rd battery bag, the 5th battery bag, the 2nd battery bag, the 6th battery bag etc. are until all of battery bag.
Therefore, charger 10 turns on the 3rd charge switch K of battery bag and is charged with to the 3rd battery bag, when the 3rd battery bag
When total voltage reaches the total voltage of the 5th battery bag, it is minimum that the 5th battery bag and the 3rd battery bag turn into total voltage simultaneously
Battery bag, charger turns on the 5th battery bag to be charged to the 3rd, 5 battery bags simultaneously, so as to sequentially turn on the 2nd battery
Bag, the 6th battery bag etc. are until all of battery bag.
While charging, BMS modules 20 also gather the magnitude of voltage of all single battery cores in each battery bag 30, and by its
Charger 40 is delivered to by BMS main frames 10, a full piezoelectric voltage is now set, in the present embodiment, it is stipulated that voltage in battery bag
The voltage of any single battery core reaches 4.20V, or the total voltage of battery bag 30 reaches single battery core section in the 4.2V* battery bags
Number.When the magnitude of voltage of any single battery core in the total voltage value of battery bag 30 or its reaches default full piezoelectric voltage, charge
Machine 10 controls the charge switch K of the battery bag 30 to disconnect, until disconnecting all of charge switch K.Wherein, judge in battery bag 30
Whether the voltage of any single battery core of voltage reaches full piezoelectric voltage, and judges whether the total voltage of the battery bag 30 reaches full
The execution unit of piezoelectric voltage can be BMS modules 20, or BMS main frames 10, or charger 40.
Wherein, in charging process, the charger 10 also calculates the number that the charge switch K disconnects and/or turns on, and
Disconnect number according to the charge switch K and/or total charging voltage of charge circuit described in the tunnel of conducting number real-time adjustment 40 and/
Or total charging current.Wherein, specific regulation rule is actually needed by those skilled in the art's foundation and is configured, and can be passed through
One table of comparisons is adjusted, it is also possible to be adjusted according to formula.The number of the charge switch K of conducting is more, total electricity that charges
Stream is bigger.The number of the charge switch K of disconnection is bigger, and total charging current is smaller.
With reference to Fig. 3, in third embodiment of the invention, the aircraft electrical management system 100a is also standby including 4
Battery bag 301, four reserve batteries 301 wrap four positions all around for being respectively arranged on aircraft, and are connected to
One standby discharge loop 32.Wherein, aircraft four positions all around are respectively provided with least a motor 50, four
At least one motor of position connects the standby discharge loop 32 of reserve battery bag 301.
Above disclosed is only the preferred embodiments of the present invention, can not limit the right of the present invention with this certainly
Scope, therefore the equivalent variations made according to scope of the present invention patent, still belong to the scope that the present invention is covered.
Claims (10)
1. a kind of aircraft electrical management system, it is characterised in that：Including N number of battery bag, gather N number of battery bag monitoring data
Detection module, and charger, N number of battery bag are arranged in parallel, and N is more than or equal to 2, and the charger includes and N number of electricity
The N roads charge circuit of Chi Bao correspondence connections charges with to the battery bag, and charge circuit described in per road is provided with a charge switch,
The charger is connected with the detection module and the total voltage to obtain each battery bag and N number of total voltage is carried out
Sequence, sequentially turns on the corresponding charge switch of the minimum battery bag of total voltage, until N number of charge switch conducting.
2. aircraft electrical management system as claimed in claim 1, it is characterised in that：Each battery bag includes many respectively
Section single battery core, the detection module often saves single battery core magnitude of voltage in also detecting N number of battery bag, and the charger is also obtained
Take and often save in each battery bag single battery core magnitude of voltage, and single battery core magnitude of voltage or battery are often saved in correspondence battery bag
When bag total voltage reaches blanking voltage, corresponding charge switch is disconnected, until N number of charge switch disconnects.
3. aircraft electrical management system as claimed in claim 1, it is characterised in that：The charger calculates the charging and opens
The number that shut-off is opened and/or turned on, and disconnected described in number and/or conducting number real-time adjustment N roads according to the charge switch
Total charging voltage and/or total charging current of charge circuit.
4. aircraft electrical management system as claimed in claim 1, it is characterised in that：Also include and N number of battery bag pair
The N number of BMS modules answered and a BMS main frames, described BMS modules one end are connected with corresponding battery bag, gather the battery bag
Monitoring data simultaneously carries out security monitoring management to the battery bag, and the BMS modules other end is connected with by described in BMS main frames
Monitoring data is delivered to the BMS main frames, and the monitoring data includes the total voltage of each battery bag, the charger with
The BMS host communications are obtaining the total voltage of each battery bag.
5. aircraft electrical management system as claimed in claim 4, it is characterised in that：The monitoring data also includes the electricity
The voltage of the voltage of Chi Bao, temperature, electricity, the internal resistance of each single battery core and each single battery core.
6. aircraft electrical management system as claimed in claim 4, it is characterised in that：Also include and N number of battery bag pair
N number of discharge loop, the N number of separate setting of discharge loop answered.
7. aircraft electrical management system as claimed in claim 6, it is characterised in that：N number of battery bag dispersion is installed on
The motor of correspondence position is powered on aircraft and by the discharge loop.
8. aircraft electrical management system as claimed in claim 7, it is characterised in that：Also include 4 reserve battery bags, four
The reserve battery bag is respectively arranged on four positions all around of aircraft, and is connected to a standby discharge loop.
9. a kind of aircraft, it is characterised in that：Including several motors and aircraft electrical management system, the aircraft
As shown in any one of claim 1-8, the aircraft electrical management system also includes and N number of electricity power-supply management system
Corresponding N number of discharge loop, N number of separate setting of discharge loop are wrapped in pond, and N number of discharge loop connects some respectively
The individual motor, and the motor powered respectively.
10. aircraft as claimed in claim 9, it is characterised in that：Several described motor dispersions are located at the flight
The correspondence position of device, N number of battery bag is closed on the correspondence motor and is set.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710050640.7A CN106712202A (en) | 2017-01-23 | 2017-01-23 | Aircraft power supply management system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710050640.7A CN106712202A (en) | 2017-01-23 | 2017-01-23 | Aircraft power supply management system and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106712202A true CN106712202A (en) | 2017-05-24 |
Family
ID=58910191
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710050640.7A Pending CN106712202A (en) | 2017-01-23 | 2017-01-23 | Aircraft power supply management system and aircraft |
Country Status (1)
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| CN (1) | CN106712202A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109065988A (en) * | 2018-07-05 | 2018-12-21 | 北京长城华冠汽车科技股份有限公司 | Multiple gradients utilize the method and device of battery pack charge and discharge |
| WO2019109951A1 (en) * | 2017-12-08 | 2019-06-13 | 南京德朔实业有限公司 | Portable electric energy system, and measurement method for remaining electric quantity of battery pack |
| WO2021168769A1 (en) * | 2020-02-28 | 2021-09-02 | 东莞新能源科技有限公司 | Battery pack management system, battery pack, vehicle and management method |
| CN113517733A (en) * | 2021-05-07 | 2021-10-19 | 广东汇天航空航天科技有限公司 | Charging control device, charging control method and aircraft |
| CN114567028A (en) * | 2021-09-13 | 2022-05-31 | 惠州市乐亿通科技有限公司 | Battery system and parallel operation method and device thereof |
| CN115071453A (en) * | 2022-06-07 | 2022-09-20 | 六安智梭无人车科技有限公司 | Power supply system and method for unmanned logistics vehicle |
| CN115101840A (en) * | 2022-08-22 | 2022-09-23 | 如果新能源科技(江苏)股份有限公司 | Battery system and battery pack connection state identification method |
| WO2023009631A3 (en) * | 2021-07-27 | 2023-03-09 | Electric Power Systems, Inc. | Cross-compatible battery modules for microgrid systems |
| WO2024022031A1 (en) * | 2022-07-27 | 2024-02-01 | 亿航智能设备（广州）有限公司 | Aircraft power battery, aircraft, and aircraft power battery integrated power supply method |
| WO2024021823A1 (en) * | 2022-07-26 | 2024-02-01 | 亿航智能设备（广州）有限公司 | Method and device for collaborative charging of battery packs, and computer-readable storage medium |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2019109951A1 (en) * | 2017-12-08 | 2019-06-13 | 南京德朔实业有限公司 | Portable electric energy system, and measurement method for remaining electric quantity of battery pack |
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| CN114567028A (en) * | 2021-09-13 | 2022-05-31 | 惠州市乐亿通科技有限公司 | Battery system and parallel operation method and device thereof |
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| CN115071453A (en) * | 2022-06-07 | 2022-09-20 | 六安智梭无人车科技有限公司 | Power supply system and method for unmanned logistics vehicle |
| WO2024021823A1 (en) * | 2022-07-26 | 2024-02-01 | 亿航智能设备（广州）有限公司 | Method and device for collaborative charging of battery packs, and computer-readable storage medium |
| WO2024022031A1 (en) * | 2022-07-27 | 2024-02-01 | 亿航智能设备（广州）有限公司 | Aircraft power battery, aircraft, and aircraft power battery integrated power supply method |
| WO2024040972A1 (en) * | 2022-08-22 | 2024-02-29 | 如果新能源科技(江苏)股份有限公司 | Battery system and battery pack connection state identification method |
| CN115101840A (en) * | 2022-08-22 | 2022-09-23 | 如果新能源科技(江苏)股份有限公司 | Battery system and battery pack connection state identification method |
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| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170524 |