CN108155319A - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN108155319A CN108155319A CN201711440881.9A CN201711440881A CN108155319A CN 108155319 A CN108155319 A CN 108155319A CN 201711440881 A CN201711440881 A CN 201711440881A CN 108155319 A CN108155319 A CN 108155319A
- Authority
- CN
- China
- Prior art keywords
- heating member
- inner casing
- heat
- heating
- temperature
- 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
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
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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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/613—Cooling or keeping cold
-
- 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
- H01M10/63—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
- H01M10/659—Means for temperature control structurally associated with the cells by heat storage or buffering, e.g. heat capacity or liquid-solid phase changes or transition
-
- 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
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Secondary Cells (AREA)
- Automation & Control Theory (AREA)
Abstract
The present invention relates to a kind of aircraft, and including battery modules, battery modules include：Inner casing and shell, the inner casing limits battery cell installation space, heat-conductive assembly and ice chest are provided between the inner casing and the shell, setting phase-change material in the ice chest, for absorbing or for discharging heat, the inner casing is connected with the first heating member, to be heated to the inner casing, the heat-conductive assembly is connected with the second heating member, to be heated to the heat-conductive assembly, further include the temperature sensor and control unit of interconnection, wherein, the temperature sensor is used to detect the temperature of the inner casing, and temperature signal is generated according to the temperature of detection, the control unit is electrically connected first heating member, second heating member, the control unit controls first heating member and second heating member to work according to the temperature signal.The battery module structure is simple, good heat dissipation effect and performance are stable, service life is long, security performance is high.
Description
Technical field
The present invention relates to a kind of aircraft.
Background technology
Battery is affected for the flight of aircraft, and temperature has battery performance vital influence, battery temperature
Otherness decide the service life, stability and security performance of battery.Power battery module in the relevant technologies, no matter
Hot environment or low temperature environment, radiator all radiate for power battery, and the radiator structure of power battery is complicated and radiates
Efficiency can not be satisfactory, leads to cost increase and battery modules service life, the stability in use and safety of battery modules
Property cannot be guaranteed.
Invention content
The present invention provides a kind of aircraft, it is intended to the technical issues of solving in the relevant technologies at least to a certain extent it
One.
A kind of aircraft according to embodiments of the present invention, including battery modules, battery modules include：Inner casing and shell, institute
It states inner casing and limits battery cell installation space, heat-conductive assembly and ice chest are provided between the inner casing and the shell, it is described
Setting phase-change material in ice chest, for absorbing or for discharging heat, the inner casing is connected with the first heating member, to institute
It states inner casing to be heated, the heat-conductive assembly is connected with the second heating member, to heat the heat-conductive assembly, further includes mutually
The temperature sensor and control unit of connection, wherein, the temperature sensor is used to detect the temperature of the inner casing, and according to inspection
The temperature of survey generates temperature signal, and the control unit is electrically connected first heating member, the second heating member, the control
Component controls first heating member and second heating member to work according to the temperature signal.
In some preferred embodiments, the ice chest is set along the shell inner circumferential.
In some preferred embodiments, the heating power of first heating member is less than the heating of second heating member
Power.
In some preferred embodiments, the heat-conductive assembly includes multigroup, and multigroup heat-conductive assembly is along the inner casing
Circumferential direction or short transverse be arranged at intervals.
In some preferred embodiments, first heating member and/or second heating member are heating plate or heating
Film or semiconductor heating plate.
Beneficial effects of the present invention：The temperature of inner casing, when the temperature is low, Ke Yitong are detected by set temperature sensor
Crossing control unit controls the first heating member to heat inner casing, and the second heating member heats heat-conductive assembly, and by heat transfer
To inner casing, meanwhile, the phase-change material in ice chest can improve the heating properties to inner casing；When internal case temperature is higher, control unit
The first heating member and the second heating member is controlled to stop heating, and passes through the phase-change material in ice chest and conducts heat outward, ensures electricity
The safety in pond further ensures the flight safety of aircraft.
Description of the drawings
Fig. 1 is the structure diagram of the battery modules of aircraft according to embodiments of the present invention.
Specific embodiment
The embodiment of the present invention is described below in detail, the example of the embodiment is shown in the drawings.Below with reference to
The embodiment of attached drawing description is exemplary, it is intended to for explaining the present invention, and is not considered as limiting the invention.
Shown in Figure 1, a kind of aircraft of the embodiment of the present invention, including battery modules, battery modules include：Inner casing
1 and shell 2, the inner casing 1 limits battery cell installation space, and heat conduction group is provided between the inner casing 1 and the shell 2
Part 6 and ice chest 3, setting phase-change material in the ice chest 3, for absorbing or for discharging heat, the inner casing 1 is connected with the
One heating member 4, to be heated to the inner casing 1, the heat-conductive assembly 6 is connected with the second heating member 7, to be led to described
Hot component 6 heats, and further includes the temperature sensor of interconnection and control unit 5, wherein, the temperature sensor is used to detect
The temperature of the inner casing 1, and temperature signal is generated according to the temperature of detection, the control unit 5 is electrically connected described first
Heating member 4, the second heating member 7, the control unit 5 control first heating member 4 and described the according to the temperature signal
Two heating members 7 work.
In some preferred embodiments, the ice chest 3 is set along 2 inner circumferential of shell.
In some preferred embodiments, the heating power of first heating member 4 is less than adding for second heating member 7
Thermal power.
In some preferred embodiments, the heat-conductive assembly 6 includes multigroup, and multigroup heat-conductive assembly 6 is along described interior
The circumferential direction or short transverse of shell 1 are arranged at intervals.
In some preferred embodiments, first heating member 4 and/or second heating member 7 for heating plate or add
Hotting mask or semiconductor heating plate.
Beneficial effects of the present invention：The temperature of inner casing, when the temperature is low, Ke Yitong are detected by set temperature sensor
Crossing control unit controls the first heating member to heat inner casing, and the second heating member heats heat-conductive assembly, and by heat transfer
To inner casing, meanwhile, the phase-change material in ice chest can improve the heating properties to inner casing；When internal case temperature is higher, control unit
The first heating member and the second heating member is controlled to stop heating, and passes through the phase-change material in ice chest and conducts heat outward, ensures electricity
The safety in pond further ensures the flight safety of aircraft.
Claims (5)
1. a kind of aircraft, including battery modules, which is characterized in that the battery modules include：Inner casing and shell, the inner casing
Battery cell installation space is limited, is provided with heat-conductive assembly and ice chest between the inner casing and the shell, in the ice chest
Phase-change material is set, and for absorbing or for discharging heat, the inner casing is connected with the first heating member, to the inner casing
It is heated, the heat-conductive assembly is connected with the second heating member, to be heated to the heat-conductive assembly, further includes interconnection
Temperature sensor and control unit, wherein, the temperature sensor is used to detect the temperature of the inner casing, and according to the temperature of detection
Degree generates temperature signal, and the control unit is electrically connected first heating member, the second heating member, the control unit root
First heating member and second heating member work are controlled according to the temperature signal.
2. aircraft according to claim 1, which is characterized in that the ice chest is set along the shell inner circumferential.
3. aircraft according to claim 1, which is characterized in that the heating power of first heating member is less than described the
The heating power of two heating members.
4. aircraft according to claim 1, which is characterized in that the heat-conductive assembly includes multigroup, multigroup heat conduction
Component is arranged at intervals along the circumferential direction or short transverse of the inner casing.
5. aircraft according to claim 1, which is characterized in that first heating member and/or second heating member
For heating plate or heating film or semiconductor heating plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711440881.9A CN108155319A (en) | 2017-12-27 | 2017-12-27 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711440881.9A CN108155319A (en) | 2017-12-27 | 2017-12-27 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108155319A true CN108155319A (en) | 2018-06-12 |
Family
ID=62462428
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711440881.9A Pending CN108155319A (en) | 2017-12-27 | 2017-12-27 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108155319A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106252785A (en) * | 2016-09-18 | 2016-12-21 | 广东工业大学 | A kind of lithium battery module radiator structure |
| CN206349470U (en) * | 2016-12-02 | 2017-07-21 | 广州极飞科技有限公司 | Battery modules and with its unmanned plane |
| CN107112609A (en) * | 2016-07-01 | 2017-08-29 | 深圳市大疆创新科技有限公司 | Battery and the mobile platform using the battery |
| CN107403973A (en) * | 2016-12-02 | 2017-11-28 | 广州极飞科技有限公司 | Unmanned plane, battery modules and charge/discharge control method |
-
2017
- 2017-12-27 CN CN201711440881.9A patent/CN108155319A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107112609A (en) * | 2016-07-01 | 2017-08-29 | 深圳市大疆创新科技有限公司 | Battery and the mobile platform using the battery |
| CN106252785A (en) * | 2016-09-18 | 2016-12-21 | 广东工业大学 | A kind of lithium battery module radiator structure |
| CN206349470U (en) * | 2016-12-02 | 2017-07-21 | 广州极飞科技有限公司 | Battery modules and with its unmanned plane |
| CN107403973A (en) * | 2016-12-02 | 2017-11-28 | 广州极飞科技有限公司 | Unmanned plane, battery modules and charge/discharge control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180612 |
|
| WD01 | Invention patent application deemed withdrawn after publication |