CN110224203A - Aircraft battery group heating system - Google Patents
Aircraft battery group heating system Download PDFInfo
- Publication number
- CN110224203A CN110224203A CN201910599809.3A CN201910599809A CN110224203A CN 110224203 A CN110224203 A CN 110224203A CN 201910599809 A CN201910599809 A CN 201910599809A CN 110224203 A CN110224203 A CN 110224203A
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- China
- Prior art keywords
- heating
- battery group
- aircraft
- power supply
- monitoring device
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Classifications
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- 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
- H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
- H01M10/486—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte for measuring temperature
-
- 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
- H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
- H01M10/488—Cells or batteries combined with indicating means for external visualization of the condition, e.g. by change of colour or of light density
-
- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/615—Heating or keeping warm
-
- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/62—Heating or cooling; Temperature control specially adapted for specific applications
-
- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/63—Control systems
- H01M10/633—Control systems characterised by algorithms, flow charts, software details or the like
-
- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/63—Control systems
- H01M10/635—Control systems based on ambient temperature
-
- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/657—Means for temperature control structurally associated with the cells by electric or electromagnetic means
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M2220/00—Batteries for particular applications
- H01M2220/20—Batteries in motive systems, e.g. vehicle, ship, plane
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Automation & Control Theory (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Secondary Cells (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The present invention proposes a kind of aircraft battery group heating system, belongs to battery field.Technical solution of the present invention main points are as follows: including monitoring device, heater, overtemperature protection device, hand push button, temperature sensor and indicator light, the heater, overtemperature protection device, hand push button, temperature sensor and indicator light are connected with monitoring device.Aircraft battery group of the present invention can not only carry out self-heating, also it can be heated using external power supply, so that battery group application scenarios are more abundant, increase the mobility of battery group, guarantee task execution, enough heated by maintain equipment, so that requirement of the battery group to maintenance environment substantially reduces, outfield, which does not need specially to control room temperature, can be completed the maintenance of battery group, so that the mobility of battery group, operational performance be made significantly to be promoted.
Description
Technical field
The present invention relates to battery technologies, the in particular to technology of aircraft battery group heating system.
Background technique
Battery group heating system is to form the important component of aircraft battery group, and it acts as in low temperature environment
In, can generate heat by itself makes aircraft battery group temperature be increased to suitable operating temperature, it is ensured that aircraft battery
Power supply performance meets requirement in group low temperature environment.Currently, aircraft battery group heating system is only capable of using power supply on machine, by
Aircraft is powered monitoring device, and control heating system works, and this heating method, which has seriously reduced battery pack, to be made
Mobility, if power supply is inactive or in the case where needing to heat battery in advance on machine, battery group not can be carried out heating, from
And task execution is influenced, additionally, due to maintenance environment there are low temperature condition, battery group safeguards in low temperature environment, charging work
It is very unfavorable, it will lead to the charging of battery pack low temperature, the service life falls sharply, and the charging security risk and later period for increasing battery pack use peace
Full blast danger, more reduces the operation of battery group.
Summary of the invention
The object of the present invention is to provide the aircraft battery group heating systems of a kind of high environmental suitability, high operational performance.
The present invention solves its technical problem, the technical solution adopted is that: aircraft battery group heating system, including monitoring dress
It sets, heater, overtemperature protection device, hand push button, temperature sensor and indicator light, the heater, overtemperature protection device, hand
Dynamic button, temperature sensor and indicator light are connected with monitoring device；
The heater provides electric energy production heat for generating heat, by battery group；
The temperature sensor is used to detect the temperature of aircraft battery group, and the temperature for the aircraft battery group that will test
It is transmitted to monitoring device；
The overtemperature protection device is for being connected in the circuit of monitoring device and heater, when monitoring device judges electric power storage
When the temperature of pond group is greater than defined threshold, is controlled by overtemperature protection device and disconnect heating；
The monitoring device is for detecting external power supply and self-heating power supply, when aircraft battery group and external power supply connect
It connects, monitoring device detects external power supply, then the heating power supply only with external power supply as aircraft battery group, and self-heating is not
It enables, when not having to detect external power supply, if temperature sensor uploads temperature display aircraft battery group temperature and reaches fire-bar
Part, presses hand push button, then can turn on the circuit of aircraft battery group and heater, carries out self-heating, lights heated condition and refer to
Show lamp and acquire aircraft battery group internal temperature, monitoring device cutting heating circuit stops adding when reaching stopping heating condition
Heat turns off status indicator lamp and cutting self-heating power supply.
Particularly, the monitoring device is able to achieve external heating power supply and self-heating isolated from power, and isolation uses two poles
Pipe is completed.
Further, the external power supply is aircraft power supply.
Particularly, under the premise of aircraft battery group is not electrically connected with aircraft power supply, operator triggers hand push button, stores
Battery pack provides working power and heating power supply to monitoring device, and monitoring device is obtained inside battery group using temperature sensor
Temperature simultaneously judges whether to meet self-heating condition, heater switch is connected if meeting condition and carries out self-heating, lights heated condition
Indicator light simultaneously acquires battery group internal temperature, and when reaching stopping heating condition, monitoring device cutting heating circuit stops adding
Heat turns off status indicator lamp and cutting working power；
Hand push button is pressed by operator's holding during self-heating and continues 3S or more termination heating.
Further, needing operator in host computer under the aircraft battery group and aircraft power supply connection
Starting heating.
Particularly, under the premise of the aircraft battery group is electrically connected with aircraft, external power supply can be mentioned to monitoring device
For working power and heating power supply, monitoring device obtains battery group internal temperature using temperature sensor and judges whether to meet
Heating condition is heated if meeting condition and is acquired battery group internal temperature, the monitoring when reaching stopping heating condition
Device cuts off heating circuit and stops heating.
Further, having external power supply detection and self-heating power detecting in the monitoring device, work as aircraft battery
Group is connect with aircraft power supply, and monitoring device detects external power supply by internal microprocessor, then only with aircraft power supply conduct
The heating power supply of aircraft battery group, self-heating do not enable, when detecting does not have external power supply, if temperature sensor uploads temperature
Degree display battery temperature reaches heating condition, presses hand push button, then can turn on the circuit of battery and heater, add certainly
Heat.
Particularly, the overtemperature protection device includes two temperature relays, is lost if monitoring device control heating disconnects
Effect, overtemperature protection device disconnection ensure aircraft battery group heating safety.
Further, low capacity defencive function is set in the monitoring device, when the capacity for detecting aircraft battery group
In the case where 60%, then do not start self heating function.
The invention has the advantages that it is full battery group can be suitable for by above-mentioned aircraft battery group heating system
In the usage scenario in face, especially self heating function can be in the case where not needing external power supply, by aircraft battery group
It is heated to required temperature, increases the mobility of aircraft battery group, guarantees task execution, is enough added by maintain equipment
Heat, so that requirement of the battery group to maintenance environment substantially reduces, outfield, which does not need specially to control room temperature, can be completed storage
So that the mobility of battery group, operational performance be made significantly to be promoted, while battery group has been effectively ensured in the maintenance of battery pack
Safety in utilization, maintenance safety and service life, especially suitable for industries such as Aeronautics and Astronautics.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aircraft battery of embodiment of the present invention group heating system.
Specific embodiment
Below with reference to examples and drawings, the technical schemes of the invention are described in detail.
Aircraft battery group heating system of the present invention, wherein the system includes monitoring device, heater, overtemperature guarantor
Protection unit, hand push button, temperature sensor and indicator light, the heater, overtemperature protection device, hand push button, temperature sensing
Device and indicator light are connected with monitoring device.
Wherein, heater provides electric energy production heat by battery group for generating heat；Temperature sensor is for examining
The temperature of aircraft battery group is surveyed, and the temperature for the aircraft battery group that will test is transmitted to monitoring device；Overtemperature protection device
For being connected in the circuit of monitoring device and heater, when monitoring device judges that the temperature of battery group is greater than defined threshold
When, it is controlled by overtemperature protection device and disconnects heating；Monitoring device is for detecting external power supply and self-heating power supply, when aviation stores
Battery pack is connect with external power supply, and monitoring device detects external power supply, then only with external power supply as aircraft battery group
Heating power supply, self-heating do not enable, when not having to detect external power supply, if temperature sensor uploads temperature display aviation electric power storage
Pond group temperature reaches heating condition, presses hand push button, then can turn on the circuit of aircraft battery group and heater, add certainly
Heat lights heated condition indicator light and acquires aircraft battery group internal temperature, the monitoring device when reaching stopping heating condition
It cuts off heating circuit and stops heating, turn off status indicator lamp and cutting self-heating power supply.
In above system, monitoring device is able to achieve external heating power supply and self-heating isolated from power, and isolation uses diode
It completes, battery system caused by heating circuit can be prevented surprisingly charge or short-circuit；External power supply is aircraft power supply.
Under the premise of aircraft battery group is not electrically connected with aircraft power supply, operator triggers hand push button, and battery group is given
Monitoring device provides working power and heating power supply, and monitoring device obtains battery group internal temperature using temperature sensor and sentences
It is disconnected whether to meet self-heating condition, heater switch is connected if meeting condition and carries out self-heating, lights heated condition indicator light simultaneously
Battery group internal temperature is acquired, monitoring device cutting heating circuit stops heating when reaching stopping heating condition, turns off
Status indicator lamp and cutting working power；It by operator keeps pressing hand push button during self-heating and continues 3S or more and terminate
Heating.
Under aircraft battery group and aircraft power supply connection, needs operator to start in host computer and heat.
Under the premise of aircraft battery group is electrically connected with aircraft, external power supply can provide working power and be added to monitoring device
Thermoelectric generator, monitoring device obtain battery group internal temperature using temperature sensor and judge whether to meet heating condition, if full
Sufficient condition is then heated and is acquired battery group internal temperature, and when reaching stopping heating condition, monitoring device cutting is heated back
Road stops heating.
There are external power supply detection and self-heating power detecting in monitoring device, when aircraft battery group and aircraft power supply connect
It connects, monitoring device detects external power supply by internal microprocessor, then only with aircraft power supply as aircraft battery group
Heating power supply, self-heating do not enable, when detecting does not have external power supply, if temperature sensor uploads temperature display battery temperature
Reach heating condition, press hand push button, then can turn on the circuit of battery and heater, carries out self-heating.
Overtemperature protection device includes two temperature relays, if monitoring device control heating disconnects failure, overtemperature prote dress
Setting disconnection ensures aircraft battery group heating safety.
Low capacity defencive function is set in monitoring device, when detecting the case where capacity of aircraft battery group is lower than 60%
Under, then do not start self heating function.
Embodiment
Aircraft battery group heating system of the embodiment of the present invention, structural schematic diagram is referring to Fig. 1, wherein 1 is monitoring dress
Set, 2 be heater, 3 be overtemperature protection device, 4 be hand push button, 5 be temperature sensor, 6 be indicator light, 1-1 is micro process
Device, 1-2 are heater switch, 1-3 is electric control in self-heating, 1-4 is power detecting.
In the present embodiment, monitoring device 1, heater 2, overtemperature protection device 3 and hand push button 4 constitute entire heating and are
System, the energy that can not only be stored using battery group itself carry out self-heating, moreover it is possible to be heated using external power supply.
The present embodiment is in integrated aircraft battery group heating system, first according to the monitoring of the Functional Design of self-heating control
Then device 1 is attached with aircraft battery group output end, carries out overtemperature protection device 3 and heater 2 in heating circuit
Series connection, status indicator lamp 6 used is connected on monitoring device 1, and can be gone out/bright state observation battery by indicator light 6
The state of group, the microprocessor 1-1 of monitoring device 1 install software, can be executed according to condition warm-up strategy and to each component into
Row control and is communicated data processing with host computer.
Specifically, having microprocessor 1-1, heater switch 1-2, electric control 1-3, power supply in self-heating inside monitoring device 1
Detect 1-4, microprocessor 1-1 assume responsibility for signal processing, control, signal sampling, communication, storage function, self-heating circuit with
External power supply circuit has diode to be isolated, can prevent battery system caused by heating circuit surprisingly charge or short circuit,
And can prevent external power supply and electricity is gone here and there mutually in self-heating circuit, when power detecting 1-4 detects that external power supply accesses, signal is passed
Give microprocessor 1-1, by microprocessor 1-1 control self-heating on electric control 1-3 be off state, cut off battery group and
The connection of heating circuit, if temperature sensor 5 is uploaded to microprocessor 1-1 and shows to reach heating condition, micro process through processing
Device 1-1 that battery temperature is too low information reporting host computer is heated by manually determination, after heating instructions are assigned, is passed through
Heater switch 1-2 is connected in microprocessor 1-1 control, and battery heating is opened, in this case, only providing the electricity of heating by external circuit
Can, battery group temperature is heated to after assigned temperature, is disconnected by microprocessor 1-1 control heater switch 1-2, cutting adds
Heat is disconnected by overtemperature protection device 3 and being added if heating process software and control failure and circuit occurs still in heated condition
Hot loop avoids battery group from heating overtemperature.In the case that external power supply disconnects, hand push button 4 is manually pressed, activation adds certainly
Electric control 1-3 in heat, monitoring device 1 carry out self-test since battery group obtains power supply, and discovery temperature reaches in process of self-test
Heating condition is then connected by microprocessor 1-1 control heater switch 1-2, and heater 2 is started to work, and battery group temperature is added
After heat to assigned temperature, disconnected by microprocessor 1-1 control heater switch 1-2, cutting heating, if software occurs in heating process
And control is failed and circuit is still in heated condition, then disconnects heating circuit by overtemperature protection device 3, battery group is avoided to add
Hot overtemperature.
Claims (9)
1. aircraft battery group heating system, which is characterized in that including monitoring device, heater, overtemperature protection device, manually press
Button, temperature sensor and indicator light, the heater, overtemperature protection device, hand push button, temperature sensor and indicator light with
Monitoring device is connected；
The heater provides electric energy production heat for generating heat, by battery group；
The temperature sensor is used to detect the temperature of aircraft battery group, and the temperature transmission for the aircraft battery group that will test
To monitoring device；
The overtemperature protection device is for being connected in the circuit of monitoring device and heater, when monitoring device judges battery group
Temperature be greater than defined threshold when, pass through overtemperature protection device control disconnect heating；
The monitoring device is for detecting external power supply and self-heating power supply, when aircraft battery group is connect with external power supply, supervises
Control device detects external power supply, then the heating power supply only with external power supply as aircraft battery group, self-heating do not enable,
When not having to detect external power supply, if temperature sensor uploads temperature display aircraft battery group temperature and reaches heating condition, press
Dynamic hand push button, then can turn on the circuit of aircraft battery group and heater, carries out self-heating, lights heated condition indicator light simultaneously
Aircraft battery group internal temperature is acquired, when reaching stopping heating condition, monitoring device cutting heating circuit stops heating, then
Closed state indicator light and cutting self-heating power supply.
2. aircraft battery group heating system according to claim 1, which is characterized in that the monitoring device is able to achieve outer
Portion's heating power supply and self-heating isolated from power, isolation are completed using diode.
3. aircraft battery group heating system according to claim 1, which is characterized in that the external power supply is aircraft electricity
Source.
4. aircraft battery group heating system according to claim 3, which is characterized in that aircraft battery group not with aircraft
Under the premise of power electric connection, operator triggers hand push button, and battery group provides working power and heating electricity to monitoring device
Source, monitoring device obtains battery group internal temperature using temperature sensor and judges whether to meet self-heating condition, if meeting
Condition then connects heater switch and carries out self-heating, lights heated condition indicator light and acquires battery group internal temperature, when reaching
Stop monitoring device cutting heating circuit when heating condition and stop heating, turns off status indicator lamp and cutting working power；
Hand push button is pressed by operator's holding during self-heating and continues 3S or more termination heating.
5. aircraft battery group heating system according to claim 3, which is characterized in that the aircraft battery group and fly
Under electromechanical source connection, needs operator to start in host computer and heat.
6. aircraft battery group heating system according to claim 3, which is characterized in that the aircraft battery group and fly
Under the premise of mechatronics, external power supply can provide working power and heating power supply to monitoring device, and monitoring device utilizes temperature
Sensor obtains battery group internal temperature and judges whether to meet heating condition, be heated if meeting condition and acquire storage
Internal battery pack temperature, when reaching stopping heating condition, monitoring device cutting heating circuit stops heating.
7. aircraft battery group heating system according to claim 3, which is characterized in that have outside in the monitoring device
Power detecting and self-heating power detecting, when aircraft battery group is connect with aircraft power supply, monitoring device passes through internal micro process
Device detects external power supply, then the heating power supply only with aircraft power supply as aircraft battery group, self-heating do not enable, and works as inspection
It measures when there is no external power supply, if temperature sensor uploads temperature display battery temperature and reaches heating condition, presses hand push button,
It then can turn on the circuit of battery and heater, carry out self-heating.
8. aircraft battery group heating system according to claim 1, which is characterized in that the overtemperature protection device includes
Two temperature relays, if monitoring device control heating disconnects failure, overtemperature protection device disconnection ensures that aircraft battery group adds
Thermal safety.
9. aircraft battery group heating system according to claim 1, which is characterized in that set low appearance in the monitoring device
Defencive function is measured, in the case that the capacity for detecting aircraft battery group is lower than 60%, does not then start self heating function.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910599809.3A CN110224203A (en) | 2019-07-04 | 2019-07-04 | Aircraft battery group heating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910599809.3A CN110224203A (en) | 2019-07-04 | 2019-07-04 | Aircraft battery group heating system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110224203A true CN110224203A (en) | 2019-09-10 |
Family
ID=67812204
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910599809.3A Pending CN110224203A (en) | 2019-07-04 | 2019-07-04 | Aircraft battery group heating system |
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| CN (1) | CN110224203A (en) |
Cited By (3)
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| CN110661047A (en) * | 2019-10-08 | 2020-01-07 | 上海华氪企业管理有限公司 | Multifunctional energy storage battery with GPS positioning function |
| CN111916865A (en) * | 2020-07-23 | 2020-11-10 | 柳州市智甲金属科技有限公司 | Temperature control system and control method for battery pack |
| CN112599889A (en) * | 2020-12-14 | 2021-04-02 | 天津市捷威动力工业有限公司 | Self-heating control method for lithium ion battery |
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Application publication date: 20190910 |