CN106654086A - Multifunctional structure battery for aircraft - Google Patents
Multifunctional structure battery for aircraft Download PDFInfo
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- CN106654086A CN106654086A CN201610885536.5A CN201610885536A CN106654086A CN 106654086 A CN106654086 A CN 106654086A CN 201610885536 A CN201610885536 A CN 201610885536A CN 106654086 A CN106654086 A CN 106654086A
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- Prior art keywords
- battery
- lithium ion
- ion single
- single battery
- electric connector
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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
- 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
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
-
- 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
- H01M50/50—Current conducting connections for cells or batteries
- H01M50/502—Interconnectors for connecting terminals of adjacent batteries; Interconnectors for connecting cells outside a battery casing
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a multifunctional structure battery for an aircraft, and relates to the field of cabin structures and battery devices on aircrafts. The multifunctional structure battery comprises an I-shaped beam, an I-shaped beam cover plate, a control battery, a power battery, an electric connector and screws. A bearing structure beam of the used aircraft and a power supply battery are integrated, a battery pack, cables, damping components and the electric connector are implanted into a bearing structure of the used aircraft, parasitism parts and components such as battery shells, a battery installation support and connecting cables between batteries are effectively decreased, weight of a power supply system and a structure system is reduced, installation spaces and assembly workload are effectively decreased, a 'Z'-shaped overlapped design is achieved in an installation mode of lithium ion monomer battery packs in the control battery and the power battery, the battery packs are effectively implanted into abnormal-shape small space, serial and parallel connection is achieved by the aid of an alternating-current welding mode, tin soldering points are omitted, welding process is simplified, and reliability of the battery packs is improved.
Description
Technical field
The present invention relates to a kind of carry-on section structure is applied to aircraft with battery apparatus field, particularly one kind
On multifunction structure battery.
Background technology
Power-supply system generally comprises the equipment such as supplying cell, distributor, cable system, section structure include main force support structure,
Equipment supporter etc..Traditional power-supply system number of devices is more, unit volume big, and the installation that equipment occupies instrument bay section is empty
Between, make Flight Vehicle Structure it is too fat to move, connect up in disorder, weight it is larger, constrain the lifting of aircraft performance.
At present, the section structure that uses in conventional aircraft, power-supply system are two independent systems.Reducing aircraft
The approach aspect of own wt, typically starts with respectively in terms of Flight Vehicle Structure and instrument and equipment two, but this method is
Jing gradually exposes its limitation.For instrument and equipment, the miniaturization of its own can no doubt mitigate some quality, but not
The parasitic elements such as associated equipment cabinets, cable can be reduced, and these parasitic elements can account for instrument and equipment gross mass
50% or so.Therefore, how to greatest extent the parasitism such as abatement apparatus cabinet, cable, connector parts just become one
New technical task.
《The spacecraft progress of lithium-ions battery accumulation power supply》For imitating with high-energy-density, low-heat
Should, the lithium-ions battery of memory-less effect, carry out in terms of reaction mechanism, Seal Design, life performance, management of charging and discharging etc.
Discuss, give the Primary Study scheme of power subsystem on aircraft.《Ground based on the multifunction structure scheme of pyroelectric technology
Study carefully》Carry out the project study and mechanical analysis, analysis of Heat Transfer, heat to electricity conversion point based on the multifunction structure of thermoelectric generation technology
The target of electric energy is started and is provided in analysis, realization using flight vehicle aerodynamic heat.《The present Research of spacecraft multifunction structure and its should
Use prospect》It is that multifunction structure is reviewed in spaceborne present Research and application prospect, provides multifunction structure
Method for designing.
In above-mentioned document, aircraft electrical origin system is still designed as independent power-supply system, and main direction of studying is
Safe high energy density cells material newly and battery system, and in terms of multifunction structure, analysis of mainly advancing a theory
Method and method for designing, are given at the application forecast of different field, are not given and can be applicable to carry-on multifunction structure
Battery.
The content of the invention
It is an object of the invention to overcome the above-mentioned deficiency of prior art, there is provided one kind is applied to carry-on multi-functional
Structure battery, effectively reduces the parasitism parts such as battery container, battery mounting bracket, intercell connection cable, realizes power supply
The loss of weight of system and structural system, and effectively reduce installing space and assembly work amount.
The above-mentioned purpose of the present invention is achieved by following technical solution：
One kind is applied to carry-on multifunction structure battery, including I-beam, I-beam cover plate, control battery, work(
Rate battery, the first electric connector, the second electric connector, the 3rd electric connector and the 4th electric connector；Wherein, I-beam is fixed on
On external flight device section structure, as the support beam structure of external flight device；Control battery is vertically installed at the one of I-beam
End；Capacity cell is vertically installed at the other end of I-beam；First electric connector and the second electric connector distinguish axially vertical peace
It is mounted on the outer surface on the inside of control battery；3rd electric connector and the 4th electric connector are axially vertical installed in power electricity respectively
On outer surface on the inside of pond；The shape of I-beam cover plate is consistent with I-beam horizontal cross sectional geometry, the fixed installation of I-beam cover plate
In the upper surface of I-beam.
Carry-on multifunction structure battery is applied in above-mentioned one kind, the I-beam horizontal cross-section is I-shaped
Type, the outer side edges at I shape horizontal cross-section two ends are circular shape；One end of I-beam is vertically provided with deep trouth, that is, control
Battery installing space processed, the other end of I-beam is vertically provided with deep trouth, i.e. capacity cell installing space；Control battery
It is vertically installed in control battery installing space, capacity cell is vertically installed in capacity cell installing space.
Carry-on multifunction structure battery is applied in above-mentioned one kind, the control battery includes 90 lithium ions
Cell, cable and connection strap and epoxy plate；90 lithium ion single batteries are uniformly divided into 9 row's lithium ion single battery packs, and 9
The equidistant horizontal parallel of row's lithium ion single battery pack is placed；The lithium ion single battery often arranged in lithium ion single battery pack passes through
Connection strap positioning is fixedly connected, and the lithium ion single battery often arranged in lithium ion single battery pack is parallel connection；Per 3 row's lithium ions
Cell group constitute lithium ion battery layer, the arrangement mode per 3 row's lithium ion single battery packs be " Z " word folding mode, phase
Epoxy plate is provided between adjacent lithium ion battery layer；The corresponding lithium ion single battery of adjacent row is fixedly connected by cable, is led to
The lithium ion single battery for crossing cable connection is series connection；The connection in series-parallel connected mode for controlling lithium ion single battery in battery is 9
String 10 is simultaneously.
Carry-on multifunction structure battery is applied in above-mentioned one kind, the control battery also includes thermal conductive silicon
Glue；It is fixedly connected by heat conductive silica gel between adjacent lithium ion single battery；Control battery is fixedly mounted on by heat conductive silica gel
The upper surface of control battery installing space bottom.
Carry-on multifunction structure battery is applied in above-mentioned one kind, the capacity cell includes 72 lithium ions
Cell, cable and connection strap and epoxy plate；72 lithium ion single batteries are uniformly divided into 9 row's lithium ion single battery packs, and 9
The equidistant horizontal parallel of row's lithium ion single battery pack is placed；The lithium ion single battery often arranged in lithium ion single battery pack passes through
Connection strap positioning is fixedly connected, and the lithium ion single battery often arranged in lithium ion single battery pack is parallel connection；Per 3 row's lithium ions
Cell group constitute lithium ion battery layer, the arrangement mode per 3 row's lithium ion single battery packs be " Z " word folding mode, phase
Epoxy plate is provided between adjacent lithium ion battery layer；The corresponding lithium ion single battery of adjacent row is fixedly connected by cable, is led to
The lithium ion single battery for crossing cable connection is series connection；The connection in series-parallel connected mode of lithium ion single battery is 9 in capacity cell
String 8 is simultaneously.
Carry-on multifunction structure battery is applied in above-mentioned one kind, the capacity cell also includes thermal conductive silicon
Glue；It is fixedly connected by heat conductive silica gel between adjacent lithium ion single battery；Capacity cell is fixedly mounted on by heat conductive silica gel
The upper surface of capacity cell installing space bottom.
Carry-on multifunction structure battery is applied in above-mentioned one kind, described lithium ion single battery is adopted
LiFePO4 battery systems, battery energy density is 115Wh/Kg, voltage 3.15V, capacity 2.5Ah.
Carry-on multifunction structure battery is applied in above-mentioned one kind, each lithium ion single battery two ends leads to
Cable extraction is crossed, the two ends for controlling all lithium ion single batteries in battery are drawn out on the first electric connector 5, in capacity cell
The two ends of all lithium ion single batteries are drawn out on the 3rd electric connector；By electricity after 9 groups of lithium ion single battery pack series connection
Cable is drawn, and is drawn out on the second electric connector 6 by cable after 9 groups of lithium ion single battery pack series connection in control battery, power
It is drawn out on the 4th electric connector 8 by cable after 9 groups of lithium ion single battery pack series connection in battery.
Carry-on multifunction structure battery is applied in above-mentioned one kind, described I-beam, I-beam cover plate
Material is aluminium alloy.
The present invention has the advantage that compared with prior art：
(1) present invention adopts the bearing structure beam of aircraft and the integrated placement scheme of supplying cell, by battery
Group, cable, damping part, electric connector are implanted in aircraft bearing structure, mutually discrete with bearing structure, supplying cell
Traditional scheme is compared, and effectively reduces the parasitism parts such as battery container, battery mounting bracket, intercell connection cable, is realized
The loss of weight of electric power system and structural system, and effectively reduce installing space and assembly work amount；
(2) employ " Z " in lithium ion single battery pack mounting means of the present invention in control battery and capacity cell
Type stack design, realizes effective implantation of the battery pack in special-shaped little space, and connection in series-parallel all adopts AC welding, without soldering
Point, simplifies welding procedure, improves the reliability of battery pack.
Description of the drawings
Fig. 1 is multifunction structure battery composition schematic diagram of the present invention；
Fig. 2 is I-beam schematic diagram of the present invention；
Fig. 3 is I-beam upper cover plate schematic diagram of the present invention；
Fig. 4 is present invention control battery lithium ions cell connection in series-parallel connection figure；
Fig. 5 is capacity cell lithium ion single battery series-parallel connection connection figure of the present invention；
Fig. 6 is present invention control battery and capacity cell assembled inside figure；
Fig. 7 is present invention control battery and capacity cell electrical connection schematic diagram.
Specific embodiment
Below in conjunction with the accompanying drawings the present invention is described in further detail with specific embodiment：
One kind proposed by the present invention is applied to carry-on multifunction structure battery, using Electromechanical Design skill
Art, battery pack, cable, damping part, electric connector are implanted in aircraft bearing structure, realize structural support, system
For electrical integrated multifunction structure system.The multifunction structure battery tradition mutually discrete with bearing structure, supplying cell
Scheme is compared, and effectively reduces the parasitism parts such as battery container, battery mounting bracket, intercell connection cable, realizes power supply
The loss of weight of system and structural system, and effectively reduce installing space and assembly work amount.
As shown in figure 1, the multifunction structure battery that the present invention is provided, including：I-beam 1, I-beam cover plate 2, control electricity
Pond 3, capacity cell 4, electric connector 5, electric connector 6, electric connector 7, electric connector 8 and screw 9；Wherein, I-beam 1 is fixed
On outside aircraft section structure, as the support beam structure of external flight device；Control battery 3 is vertically installed at I-beam 1
One end；Capacity cell 4 is vertically installed at the other end of I-beam 1；First electric connector 5 and the difference axle of the second electric connector 6
To on the outer surface being vertically mounted on the inside of control battery 3；3rd electric connector 7 and the 4th electric connector 8 distinguish axially vertical
On the outer surface of the inner side of capacity cell 4；I-beam cover plate 2 is fixedly mounted on the upper surface of I-beam 1 by screw 9.
Described I-beam 1, the material of I-beam cover plate 2 are aluminium alloy.
I-beam schematic diagram is illustrated in figure 2, as seen from the figure, the horizontal cross-section of I-beam 1 is I shape, and I shape level is cut
The outer side edges at face two ends are circular shape；One end of I-beam 1 is vertically provided with deep trouth, that is, control battery installing space
10, the other end of I-beam 1 is vertically provided with deep trouth, i.e. capacity cell installing space 11；Control battery 3 is vertically-mounted
In control battery installing space 10, capacity cell 4 is vertically installed in capacity cell installing space 11.
I-beam upper cover plate schematic diagram is illustrated in figure 3, as seen from the figure, shape and the level of I-beam 1 of I-beam cover plate 2
Cross sectional shape is consistent, and I-beam cover plate 2 is fixedly mounted on the upper surface of I-beam 1.
Be illustrated in figure 4 control battery lithium ions cell connection in series-parallel connection figure, be illustrated in figure 5 capacity cell lithium from
Sub- cell connection in series-parallel connection figure, such as Fig. 6 is control battery and capacity cell assembled inside figure, as seen from the figure, controls battery 3
Including 90 lithium ion single batteries 12, cable 13 and connection strap 14 and epoxy plate 15；90 lithium ion single batteries 12 are uniform
It is divided into 9 row's lithium ion single battery packs, the equidistant horizontal parallel of 9 row's lithium ion single battery packs is placed；Often arrange lithium ion single electricity
The lithium ion single battery 12 of Chi Zuzhong by connection strap 14 positioning be fixedly connected, often arrange lithium ion single battery pack in lithium from
Sub- cell 12 is parallel connection；Lithium ion battery layer is constituted per 3 row's lithium ion single battery packs, the electricity per 3 row's lithium ion singles
The arrangement mode of pond group is " Z " word folding mode, and epoxy plate 15 is provided between adjacent lithium ion battery layer；Adjacent row is corresponding
Lithium ion single battery 12 is fixedly connected by cable 13, and the lithium ion single battery 12 connected by cable 13 is series connection；Control
The connection in series-parallel connected mode of lithium ion single battery 12 goes here and there 10 simultaneously for 9 in battery processed 3.
Control battery 3 also includes heat conductive silica gel 16；Fixed by heat conductive silica gel 16 between adjacent lithium ion single battery 12
Connection；Control battery 3 is fixedly mounted on the upper surface of the bottom of control battery installing space 10 by heat conductive silica gel 16.
Capacity cell 4 includes 72 lithium ion single batteries 12, cable 13 and connection straps 14 and epoxy plate 15；72 lithiums from
Sub- cell 12 is uniformly divided into 9 row's lithium ion single battery packs, and the equidistant horizontal parallel of 9 row's lithium ion single battery packs is placed；
The lithium ion single battery 12 often arranged in lithium ion single battery pack is fixedly connected by the positioning of connection strap 14, often arranges lithium ion list
Lithium ion single battery 12 in body battery pack is parallel connection；Lithium ion battery layer is constituted per 3 row's lithium ion single battery packs, often
The arrangement mode of 3 row's lithium ion single battery packs is " Z " word folding mode, and between adjacent lithium ion battery layer epoxy plate is provided with
15；The corresponding lithium ion single battery 12 of adjacent row is fixedly connected by cable 13, the lithium ion single connected by cable 13
Battery 12 is series connection；The connection in series-parallel connected mode of lithium ion single battery 12 goes here and there 8 simultaneously for 9 in capacity cell 4.
Capacity cell 4 also includes heat conductive silica gel 16；Fixed by heat conductive silica gel 16 between adjacent lithium ion single battery 12
Connection；Capacity cell 4 is fixedly mounted on the upper surface of the bottom of capacity cell installing space 11 by heat conductive silica gel 16.
Control battery 3, electric connector 5, electric connector 6 provide the output of flying vehicles control electric flux jointly, control battery
Voltage is 28.5V, capacity is 23Ah.Capacity cell 4, electric connector 7, electric connector 8 provide craft power electric flux jointly
Output, it is 18Ah that the voltage of capacity cell is 28.5V, capacity.
It is illustrated in figure 7 control battery and capacity cell electrical connection schematic diagram, as seen from the figure, each lithium ion single electricity
The two ends of pond 12 are drawn by cable 13, and the two ends of all lithium ion single batteries 12 are drawn out to first and are electrically connected in control battery 3
Connect on device 5, the two ends of all lithium ion single batteries 12 are drawn out on the 3rd electric connector 7 in capacity cell 4；9 groups of lithium ions
Drawn by cable 13 after the series connection of cell group, cable 13 is passed through after 9 groups of lithium ion single battery pack series connection in control battery 3
It is drawn out on the second electric connector 6, the is drawn out to by cable 13 after the series connection of 9 groups of lithium ion single battery packs in capacity cell 4
On four electric connectors 8.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (9)
1. one kind is applied to carry-on multifunction structure battery, it is characterised in that：Including I-beam (1), I-beam cover plate
(2), control battery (3), capacity cell (4), the first electric connector (5), the second electric connector (6), the 3rd electric connector (7) and
4th electric connector (8)；Wherein, I-beam (1) is fixed on external flight device section structure, as the support of external flight device
Girder construction；Control battery (3) is vertically installed at one end of I-beam (1)；Capacity cell (4) is vertically installed at I-beam (1)
The other end；First electric connector (5) and the second electric connector (6) are axially vertical outer on the inside of control battery (3) respectively
On surface；3rd electric connector (7) and the 4th electric connector (8) are axially vertical outer on the inside of capacity cell (4) respectively
On surface；The shape of I-beam cover plate (2) is consistent with I-beam (1) horizontal cross sectional geometry, and I-beam cover plate (2) is fixedly mounted on
The upper surface of I-beam (1).
2. one kind according to claim 1 is applied to carry-on multifunction structure battery, it is characterised in that：The work
Word beam (1) horizontal cross-section is I shape, and the outer side edges at I shape horizontal cross-section two ends are circular shape；One end of I-beam (1)
Deep trouth is vertically provided with, that is, controls battery installing space (10), the other end of I-beam (1) is vertically provided with
Deep trouth, i.e. capacity cell installing space (11)；Control battery (3) is vertically installed in control battery installing space (10), power
Battery (4) is vertically installed in capacity cell installing space (11).
3. one kind according to claim 2 is applied to carry-on multifunction structure battery, it is characterised in that：The control
Battery (3) processed includes 90 lithium ion single batteries (12), cable (13) and connection strap (14) and epoxy plate (15)；90 lithiums from
Sub- cell (12) is uniformly divided into 9 row's lithium ion single battery packs, and the equidistant horizontal parallel of 9 row's lithium ion single battery packs is put
Put；The lithium ion single battery (12) often arranged in lithium ion single battery pack is fixedly connected by connection strap (14) positioning, is often arranged
Lithium ion single battery (12) in lithium ion single battery pack is parallel connection；Per 3 row's lithium ion single battery packs constitute lithium from
Sub- battery layers, the arrangement mode per 3 row's lithium ion single battery packs is " Z " word folding mode, between adjacent lithium ion battery layer
It is provided with epoxy plate (15)；The corresponding lithium ion single battery (12) of adjacent row is fixedly connected by cable (13), by cable
(13) the lithium ion single battery (12) of connection is series connection；The connection in series-parallel of lithium ion single battery (12) in control battery (3) connects
Connect mode and go here and there 10 simultaneously for 9.
4. one kind according to claim 3 is applied to carry-on multifunction structure battery, it is characterised in that：The control
Battery (3) processed also includes heat conductive silica gel (16)；Connect by the way that heat conductive silica gel (16) is fixed between adjacent lithium ion single battery (12)
Connect；Control battery (3) is fixedly mounted on the upper surface of control battery installing space (10) bottom by heat conductive silica gel (16).
5. one kind according to claim 2 is applied to carry-on multifunction structure battery, it is characterised in that：The work(
Rate battery (4) includes 72 lithium ion single batteries (12), cable (13) and connection strap (14) and epoxy plate (15)；72 lithiums from
Sub- cell (12) is uniformly divided into 9 row's lithium ion single battery packs, and the equidistant horizontal parallel of 9 row's lithium ion single battery packs is put
Put；The lithium ion single battery (12) often arranged in lithium ion single battery pack is fixedly connected by connection strap (14) positioning, is often arranged
Lithium ion single battery (12) in lithium ion single battery pack is parallel connection；Per 3 row's lithium ion single battery packs constitute lithium from
Sub- battery layers, the arrangement mode per 3 row's lithium ion single battery packs is " Z " word folding mode, between adjacent lithium ion battery layer
It is provided with epoxy plate (15)；The corresponding lithium ion single battery (12) of adjacent row is fixedly connected by cable (13), by cable
(13) the lithium ion single battery (12) of connection is series connection；The connection in series-parallel of lithium ion single battery (12) in capacity cell (4) connects
Connect mode and go here and there 8 simultaneously for 9.
6. one kind according to claim 5 is applied to carry-on multifunction structure battery, it is characterised in that：The work(
Rate battery (4) also includes heat conductive silica gel (16)；Connect by the way that heat conductive silica gel (16) is fixed between adjacent lithium ion single battery (12)
Connect；Capacity cell (4) is fixedly mounted on the upper surface of capacity cell installing space (11) bottom by heat conductive silica gel (16).
7. the one kind according to one of claim 3-6 is applied to carry-on multifunction structure battery, it is characterised in that：
Using LiFePO4 battery systems, battery energy density is 115Wh/Kg, voltage 3.15V to described lithium ion single battery (12),
Capacity 2.5Ah.
8. one kind according to claim 1 is applied to carry-on multifunction structure battery, it is characterised in that：Each lithium
Ion battery cell (12) two ends are drawn by cable (13), control all lithium ion single batteries (12) in battery (3)
Two ends are drawn out on the first electric connector 5, and the two ends of all lithium ion single batteries (12) are drawn out to the 3rd in capacity cell (4)
On electric connector (7)；Drawn by cable (13) after the series connection of 9 groups of lithium ion single battery packs, control in battery (3) 9 groups of lithiums from
It is drawn out on the second electric connector 6 by cable (13) after sub- cell group series connection, 9 groups of lithium ion lists in capacity cell (4)
It is drawn out on the 4th electric connector 8 by cable (13) after the series connection of body battery pack.
9. one kind according to claim 1 is applied to carry-on multifunction structure battery, it is characterised in that：Described
I-beam (1), the material of I-beam cover plate (2) are aluminium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610885536.5A CN106654086B (en) | 2016-10-10 | 2016-10-10 | One kind being applied to carry-on multifunction structure battery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610885536.5A CN106654086B (en) | 2016-10-10 | 2016-10-10 | One kind being applied to carry-on multifunction structure battery |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106654086A true CN106654086A (en) | 2017-05-10 |
| CN106654086B CN106654086B (en) | 2019-03-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610885536.5A Active CN106654086B (en) | 2016-10-10 | 2016-10-10 | One kind being applied to carry-on multifunction structure battery |
Country Status (1)
| Country | Link |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109760819A (en) * | 2018-12-24 | 2019-05-17 | 中国兵器工业导航与控制技术研究所 | A kind of structure battery component of aircraft and aircraft |
| CN112531257A (en) * | 2020-12-16 | 2021-03-19 | 北方特种能源集团有限公司西安庆华公司 | Telescopic thermal battery assembly for rocket projectile |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4614405A (en) * | 1982-09-28 | 1986-09-30 | The Boeing Company | Wide angle laser window |
| US5285986A (en) * | 1991-04-18 | 1994-02-15 | Luftschiffbau Zeppelin Gmbh | Rigid airship with a carrier frame of ribs and beams enclosed by skin sections forming an envelope |
| CN2490052Y (en) * | 2001-06-13 | 2002-05-08 | 上海皮恩斯电讯电子有限公司 | Framework of parasol |
| CN204464338U (en) * | 2014-12-15 | 2015-07-08 | 昆山优力电能运动科技有限公司 | For aircraft battery component and comprise its aircraft |
-
2016
- 2016-10-10 CN CN201610885536.5A patent/CN106654086B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4614405A (en) * | 1982-09-28 | 1986-09-30 | The Boeing Company | Wide angle laser window |
| US5285986A (en) * | 1991-04-18 | 1994-02-15 | Luftschiffbau Zeppelin Gmbh | Rigid airship with a carrier frame of ribs and beams enclosed by skin sections forming an envelope |
| CN2490052Y (en) * | 2001-06-13 | 2002-05-08 | 上海皮恩斯电讯电子有限公司 | Framework of parasol |
| CN204464338U (en) * | 2014-12-15 | 2015-07-08 | 昆山优力电能运动科技有限公司 | For aircraft battery component and comprise its aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109760819A (en) * | 2018-12-24 | 2019-05-17 | 中国兵器工业导航与控制技术研究所 | A kind of structure battery component of aircraft and aircraft |
| CN112531257A (en) * | 2020-12-16 | 2021-03-19 | 北方特种能源集团有限公司西安庆华公司 | Telescopic thermal battery assembly for rocket projectile |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106654086B (en) | 2019-03-22 |
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