CN106410086A - Heat dissipation device for battery of aircraft - Google Patents
Heat dissipation device for battery of aircraft Download PDFInfo
- Publication number
- CN106410086A CN106410086A CN201611022205.5A CN201611022205A CN106410086A CN 106410086 A CN106410086 A CN 106410086A CN 201611022205 A CN201611022205 A CN 201611022205A CN 106410086 A CN106410086 A CN 106410086A
- Authority
- CN
- China
- Prior art keywords
- battery
- protective cover
- aircraft
- battery case
- heat abstractor
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- 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
- H01M10/62—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
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/653—Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- 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)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Battery Mounting, Suspending (AREA)
Abstract
The invention discloses a heat dissipation device for a battery of an aircraft. The heat dissipation device comprises protecting covers and a battery container, wherein the protecting covers are used for protecting paddles of the aircraft, and the battery container is used for distributing batteries; the protecting covers and the battery container are made of heat conducting materials and are in contact with each other to transfer heat of the batteries from the battery container to the protecting covers. According to the heat dissipation device, the heat conducting materials are arranged under the batteries and are integrated with the protecting covers below or above the paddles, and heat of the batteries are conducted to the protecting covers below or above the paddles by virtue of the heat conducting materials; the aircraft is propelled by virtue of wind power generated by the paddles during the flight, and meanwhile, the protecting covers are cooled by virtue of wind, so that a good cooling effect is achieved without the loss of energy sources.
Description
Technical field
The present invention relates to unmanned plane field and radiator field；More particularly it relates to a kind of aircraft battery
Heat abstractor.
Background technology
The battery performance of aircraft seriously constrains the development of aircraft in every respect, such as battery-heating etc..
The long-time excessive heating of battery can lead to internal works temperature to raise, the normal work of impact parts；When battery is long
Between heating the heat of battery itself can be made to increase, if sealing battery its inner air can be made acutely to expand, lead to battery
As outer process, serious meeting makes battery explosion；The long-term excessive heating of battery can accelerate the ager process of product itself, shortens its longevity
Life.
Use battery to provide power more domestic civilian Multi-axis aircraft, in traditional Flight Vehicle Design, battery is dissipated
Heat condition, all excludes overall design objective.
Most of aircraft, does not have the solution of complete set in terms of radiating, and battery is installed directly into electricity
Pond container, battery case is using the structure sealing it is impossible to reach effective cooling-down effect.To electric-controlled plate near battery case etc.
Electric elements, all have a negative impact.
In the recent period, domestic start the radiating of aircraft is paid close attention to.The well-known producer of certain aircraft, just devises a band logical
The Multi-axis aircraft in air port.When aircraft is in motion, air quantity enters through the wind mouth opening up on fuselage, enters in fuselage
Portion, blows in battery and plate surfaces, reaches wind cooling temperature lowering effect.But, the radiating effect of this heat sink conception is unsatisfactory.
Therefore, those skilled in the art is devoted to developing one kind and can play good under conditions of not energy loss
Cooling-down effect technical scheme.
Content of the invention
In view of the drawbacks described above of prior art, the technical problem to be solved is to provide one kind can not damage
Under conditions of power consumption source, play good cooling-down effect aircraft battery heat abstractor.
For achieving the above object, the invention provides a kind of aircraft battery heat abstractor is it is characterised in that include：For
The protective cover of protection aircraft blade and the battery case for arranging battery；Wherein, protective cover and battery case are by heat conduction
Material is made, and protective cover contacts with battery case and makes it possible to the heat transfer of battery from battery case to protective cover.
Preferably, protective cover and battery case are integrally formed.
Preferably, protective cover and battery case are made by metal material.
Preferably, protective cover and battery case are all made of copper.
Preferably, protective cover includes：Upper protective cover, middle housing and lower protective cover；Upper protective cover comprises and aircraft oar
Cover structure on the upside of multiple hollow outs that what leaf position was corresponding link together, under screw, protective cover comprises and aircraft blade position
Put cover structure on the downside of the corresponding multiple hollow outs linking together；Middle housing includes the hollow out for accommodating aircraft blade
Part.
Preferably, battery case and one or more of upper protective cover, middle housing and lower protective cover form as one
Formula structure.
Preferably, battery case includes battery case and battery cover.
It is further preferred that one or more of battery case and battery cover and upper protective cover, middle housing and lower protection
One or more of the cover formula structure that forms as one.
With respect to the mode of the ventilating opening cooling belonging to passive cooling of prior art, prior art can not be according to actively
Demand is lowered the temperature whenever and wherever possible, and technical scheme belongs to active cooling, is not affected by any condition.Its
Secondary, the mode of the ventilating opening cooling of prior art increased air drag, produces unfavorable factor to flight.The technical side of the present invention
Case will not increase air drag, does not produce any unfavorable factor.And, technical scheme will not increase any loss.
Technique effect below with reference to design, concrete structure and generation to the present invention for the accompanying drawing is described further, with
It is fully understood from the purpose of the present invention, feature and effect.
Brief description
Fig. 1 is the overall schematic perspective view of aircraft battery heat abstractor according to the preferred embodiment of the invention.
Fig. 2 is the general plane schematic diagram of aircraft battery heat abstractor according to the preferred embodiment of the invention.
Fig. 3 is the schematic diagram of the protective cover of aircraft battery heat abstractor according to the preferred embodiment of the invention.
It should be noted that accompanying drawing is used for the present invention is described, and the unrestricted present invention.Note, represent that the accompanying drawing of structure can
Can be not necessarily drawn to scale.And, in accompanying drawing, same or like element indicates same or like label.
Specific embodiment
In the present invention, in battery arranged beneath Heat Conduction Material (as copper), Heat Conduction Material is anti-with blade below or above
Guard shield is integral type structure, by Heat Conduction Material, cell heat is conducted to the protective cover of blade below or above.Due to flight
The device air feed that blade produces in flight, blows cooling to protective cover simultaneously.Under conditions of not energy loss, rise
To good cooling-down effect.
Particularly preferred embodiment of the invention is described below.
Fig. 1 is the overall schematic perspective view of aircraft battery heat abstractor according to the preferred embodiment of the invention, and Fig. 2
It is the general plane schematic diagram of aircraft battery heat abstractor according to the preferred embodiment of the invention.
As depicted in figs. 1 and 2, aircraft battery heat abstractor according to the preferred embodiment of the invention includes：For protecting
The protective cover 1 of aircraft blade and the battery case 2 for arranging battery；Wherein, protective cover 1 and battery case 2 are by heat conduction
Material is made, and protective cover 1 contacts with battery case 2 and makes it possible to the heat transfer of battery from battery case 2 to protection
Cover 1.
Preferably, protective cover 1 and battery case 2 are integrally formed, and that is, protective cover 1 and battery case 2 are a global facility.
For example, protective cover 1 and battery case 2 are made up of metal material.
For example, protective cover 1 and battery case 2 are all made of copper.
The example of the protective cover that the present invention can use is described below.
Fig. 3 is the schematic diagram of the protective cover of aircraft battery heat abstractor according to the preferred embodiment of the invention.
As shown in figure 3, protective cover according to the preferred embodiment of the invention includes：Upper protective cover 100, middle housing 200 and
Lower protective cover 300；Upper protective cover 100 comprises side cover in the multiple hollow outs linking together corresponding with aircraft blade position
Structure, under screw, protective cover 300 comprises side cover under the multiple hollow outs linking together corresponding with aircraft blade position
Structure；Middle housing 200 includes the openwork part for accommodating aircraft blade.Thus, upper protective cover 100, middle housing 200
Can be assembled to accommodate aircraft blade for overall protective cover with lower protective cover 300.
It is thus preferable that battery case is formed as with one or more of upper protective cover, middle housing and lower protective cover
Integral structure.
Preferably, battery case includes battery case and battery cover.Thus, it is further preferred that in battery case and battery cover
One or more with upper protective cover, one or more of middle housing and lower protective cover formula structure that forms as one.
With respect to the mode of the ventilating opening cooling belonging to passive cooling of prior art, prior art can not be according to actively
Demand is lowered the temperature whenever and wherever possible, and technical scheme belongs to active cooling, is not affected by any condition.Its
Secondary, the mode of the ventilating opening cooling of prior art increased air drag, produces unfavorable factor to flight.The technical side of the present invention
Case will not increase air drag, does not produce any unfavorable factor.And, technical scheme will not increase any loss.
Described above illustrate and describes the preferred embodiments of the present invention, as previously mentioned it should be understood that the present invention not office
Be limited to form disclosed herein, be not to be taken as the exclusion to other embodiment, and can be used for various other combinations, modification and
Environment, and can be changed by the technology or knowledge of above-mentioned teaching or association area in invention contemplated scope described herein
Dynamic.And the change that those skilled in the art are carried out and change without departing from the spirit and scope of the present invention, then all should be appended by the present invention
In scope of the claims.
Claims (8)
1. a kind of aircraft battery heat abstractor is it is characterised in that include：For protecting the protective cover of aircraft blade and being used for
The battery case of arrangement battery；Wherein, protective cover and battery case are all made from a material that be thermally conductive, and protective cover and battery case
Contact makes it possible to the heat transfer of battery from battery case to protective cover.
2. aircraft battery heat abstractor as claimed in claim 1 is it is characterised in that protective cover and battery case entirety shape
Become.
3. aircraft battery heat abstractor as claimed in claim 1 or 2, protective cover and battery case are by metal material system
Become.
4. aircraft battery heat abstractor as claimed in claim 1 or 2 it is characterised in that protective cover and battery case by
Copper becomes.
5. aircraft battery heat abstractor as claimed in claim 1 or 2 is it is characterised in that protective cover includes：Upper protective cover,
Middle housing and lower protective cover；Upper protective cover comprises in the multiple hollow outs linking together corresponding with aircraft blade position
Side cover structure, under screw, protective cover comprises side cover under the multiple hollow outs linking together corresponding with aircraft blade position
Structure；Middle housing includes the openwork part for accommodating aircraft blade.
6. aircraft battery heat abstractor as claimed in claim 5 is it is characterised in that battery case and upper protective cover, middle part
One or more of shell and lower protective cover form as one formula structure.
7. the aircraft battery heat abstractor as described in claim 1 or 6 it is characterised in that battery case include battery case and
Battery cover.
8. aircraft battery heat abstractor as claimed in claim 7 it is characterised in that one of battery case and battery cover or
Multiple with upper protective cover, one or more of middle housing and lower protective cover formula structure that forms as one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611022205.5A CN106410086A (en) | 2016-11-16 | 2016-11-16 | Heat dissipation device for battery of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611022205.5A CN106410086A (en) | 2016-11-16 | 2016-11-16 | Heat dissipation device for battery of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106410086A true CN106410086A (en) | 2017-02-15 |
Family
ID=58068587
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611022205.5A Pending CN106410086A (en) | 2016-11-16 | 2016-11-16 | Heat dissipation device for battery of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106410086A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828953A (en) * | 2017-04-10 | 2017-06-13 | 上海未来伙伴机器人有限公司 | A kind of unmanned plane safety protection net cover |
| CN106864743A (en) * | 2017-04-10 | 2017-06-20 | 上海未来伙伴机器人有限公司 | A kind of safety protection net cover and unmanned plane |
| CN106882368A (en) * | 2017-04-10 | 2017-06-23 | 上海未来伙伴机器人有限公司 | A kind of unmanned plane safety device |
| CN107235144A (en) * | 2017-07-17 | 2017-10-10 | 上海未来伙伴机器人有限公司 | A kind of aircraft protective cover and aircraft |
| CN110077579A (en) * | 2019-05-16 | 2019-08-02 | 唐曾美 | Unmanned vehicle |
-
2016
- 2016-11-16 CN CN201611022205.5A patent/CN106410086A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828953A (en) * | 2017-04-10 | 2017-06-13 | 上海未来伙伴机器人有限公司 | A kind of unmanned plane safety protection net cover |
| CN106864743A (en) * | 2017-04-10 | 2017-06-20 | 上海未来伙伴机器人有限公司 | A kind of safety protection net cover and unmanned plane |
| CN106882368A (en) * | 2017-04-10 | 2017-06-23 | 上海未来伙伴机器人有限公司 | A kind of unmanned plane safety device |
| CN107235144A (en) * | 2017-07-17 | 2017-10-10 | 上海未来伙伴机器人有限公司 | A kind of aircraft protective cover and aircraft |
| CN110077579A (en) * | 2019-05-16 | 2019-08-02 | 唐曾美 | Unmanned vehicle |
| CN110077579B (en) * | 2019-05-16 | 2020-11-06 | 观典防务技术股份有限公司 | Unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170215 |
|
| WD01 | Invention patent application deemed withdrawn after publication |