CN106654086B - One kind being applied to carry-on multifunction structure battery - Google Patents
One kind being applied to carry-on multifunction structure battery Download PDFInfo
- Publication number
- CN106654086B CN106654086B CN201610885536.5A CN201610885536A CN106654086B CN 106654086 B CN106654086 B CN 106654086B CN 201610885536 A CN201610885536 A CN 201610885536A CN 106654086 B CN106654086 B CN 106654086B
- Authority
- CN
- China
- Prior art keywords
- battery
- lithium ion
- ion single
- single battery
- row
- 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.)
- Active
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
- 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
Abstract
One kind being applied to carry-on multifunction structure battery, is related to carry-on section structure and battery apparatus field；Multifunction structure battery includes: I-beam, I-beam cover board, control battery, capacity cell, electric connector, screw；The present invention is using the bearing structure beam of aircraft and the integrated placement scheme of supplying cell, battery pack, cable, damping part, electric connector are implanted in aircraft bearing structure, effectively reduce the parasitic components such as battery case, battery mounting bracket, intercell connection cable, it realizes the loss of weight of power supply system and structural system, and effectively reduces installation space and assembly work amount；" Z " type stack design is used in the lithium ion single battery pack mounting means in control battery and capacity cell simultaneously, realize effective implantation of the battery pack in special-shaped small space, in series and parallel all using AC welding, without tin welding spot, welding procedure is simplified, the reliability of battery pack is improved.
Description
Technical field
The present invention relates to a kind of carry-on section structures and battery apparatus field, especially a kind of to be applied to aircraft
On multifunction structure battery.
Background technique
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, single machine volume is big, and the installation that equipment occupies instrument bay section is empty
Between, make that Flight Vehicle Structure is too fat to move, wiring is in disorder, weight is larger, constrains the promotion of aircraft performance.
Currently, the section structure used in conventional aircraft, power-supply system are two independent systems.Reducing aircraft
In terms of the approach of own wt, usually start with respectively in terms of Flight Vehicle Structure is with instrument and equipment two, but this method is
Gradually exposed its limitation.For instrument and equipment, the miniaturization of its own can no doubt mitigate some quality, but not
It can be reduced the parasitic elements such as associated equipment cabinets, cable, and these parasitic elements can account for instrument and equipment gross mass
50% or so.Therefore, how to eliminate the parasitic components such as equipment cabinets, cable, connector to the maximum extent just becomes one
New technical task.
" progress of spacecraft lithium-ions battery accumulation power supply " is directed to imitates with high-energy-density, low-heat
It answers, the lithium-ions battery of memory-less effect, is carried out from reaction mechanism, Seal Design, life performance, management of charging and discharging etc.
It discusses, gives the Primary Study scheme of power subsystem on aircraft." the multifunction structure scheme based on pyroelectric technology is ground
Study carefully " carry out the project study and mechanical analysis, analysis of Heat Transfer, heat to electricity conversion point of the multifunction structure based on thermoelectric generation technology
Analysis, realization are started using flight vehicle aerodynamic heat and provide the target of electric energy.It " present Research of spacecraft multifunction structure and its answers
With prospect " it is to be reviewed to multifunction structure in spaceborne present Research and application prospect, provide multifunction structure
Design method.
In above-mentioned document, aircraft power system is still designed as independent power-supply system, and main direction of studying is
The high energy density cells material and battery system of new safety, and in terms of multifunction structure, analysis of mainly advancing a theory
Method and design method, are given at the application forecast of different field, do not provide and can be applied to carry-on multifunction structure
Battery.
Summary of the invention
It is an object of the invention to overcome the above-mentioned deficiency of the prior art, provide a kind of applied to carry-on multi-functional
Structure battery effectively reduces the parasitic components such as battery case, battery mounting bracket, intercell connection cable, realizes power supply
The loss of weight of system and structural system, and effectively reduce installation space and assembly work amount.
Above-mentioned purpose of the invention is achieved by following technical solution:
One kind being applied to carry-on multifunction structure battery, including I-beam, I-beam cover board, control battery, function
Rate battery, the first electric connector, the second electric connector, third electric connector and the 4th electric connector；Wherein, I-beam is fixed on
Support beam structure on external flight device section structure, as 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
On the outer surface on the inside of control battery；Third electric connector and the 4th electric connector are axially vertical respectively to be mounted on power electricity
On outer surface on the inside of pond；The shape of I-beam cover board is consistent with I-beam horizontal cross sectional geometry, and I-beam cover board is fixedly mounted
In the upper surface of I-beam.
It is applied to carry-on multifunction structure battery in above-mentioned one kind, the I-beam horizontal cross-section is I-shaped
Type, the outer side edges at I-shaped horizontal cross-section both ends are circular shape；One end of I-beam is provided with deep trouth along the vertical direction, that is, controls
Battery installation space processed, the other end of I-beam are provided with deep trouth, i.e. capacity cell installation space along the vertical direction；Control battery
It is vertically installed in control battery installation space, capacity cell is vertically installed in capacity cell installation space.
It is applied to carry-on multifunction structure battery in above-mentioned one kind, the control battery includes 90 lithium ions
Single battery, 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 lithium ion single battery pack is arranged to place；Lithium ion single battery in every row's lithium ion single battery pack passes through
Connection strap positioning is fixedly connected, and the lithium ion single battery in every row's lithium ion single battery pack is parallel connection；Every 3 row lithium ion
Single battery group forms lithium ion battery layer, and the arrangement mode of every 3 row lithium ion single battery pack is " 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 of cable connection is crossed as series connection；The series-parallel connection type for controlling lithium ion single battery in battery is 9
String 10 is simultaneously.
It is applied to carry-on multifunction structure battery in above-mentioned one kind, the control battery further includes thermal conductive silicon
Glue；It is fixedly connected between adjacent lithium ion single battery by heat conductive silica gel；Control battery is fixedly mounted on by heat conductive silica gel
Control the upper surface of battery installation space bottom end.
It is applied to carry-on multifunction structure battery in above-mentioned one kind, the capacity cell includes 72 lithium ions
Single battery, 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 lithium ion single battery pack is arranged to place；Lithium ion single battery in every row's lithium ion single battery pack passes through
Connection strap positioning is fixedly connected, and the lithium ion single battery in every row's lithium ion single battery pack is parallel connection；Every 3 row lithium ion
Single battery group forms lithium ion battery layer, and the arrangement mode of every 3 row lithium ion single battery pack is " 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 of cable connection is crossed as series connection；The series-parallel connection type of lithium ion single battery is 9 in capacity cell
String 8 is simultaneously.
It is applied to carry-on multifunction structure battery in above-mentioned one kind, the capacity cell further includes thermal conductive silicon
Glue；It is fixedly connected between adjacent lithium ion single battery by heat conductive silica gel；Capacity cell is fixedly mounted on by heat conductive silica gel
The upper surface of capacity cell installation space bottom end.
It is applied to carry-on multifunction structure battery in above-mentioned one kind, the lithium ion single battery uses
LiFePO4 battery system, battery energy density 115Wh/Kg, voltage 3.15V, capacity 2.5Ah.
It is applied to carry-on multifunction structure battery in above-mentioned one kind, each lithium ion single battery both ends are logical
Cable extraction is crossed, the both ends for controlling all lithium ion single batteries in battery are drawn out on the first electric connector 5, in capacity cell
The both ends of all lithium ion single batteries are drawn out on third electric connector；Pass through electricity after 9 groups of lithium ion single battery pack series connection
Cable is drawn, and is controlled in battery and is drawn out on the second electric connector 6 after 9 groups of lithium ion single battery pack series connection by cable, power
It is drawn out on the 4th electric connector 8 after 9 groups of lithium ion single battery pack series connection by cable in battery.
It is applied to carry-on multifunction structure battery, the I-beam, I-beam cover board in above-mentioned one kind
Material is aluminium alloy.
The invention has the following advantages over the prior art:
(1) present invention is using 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 is effectively reduced the parasitic components such as battery case, battery mounting bracket, intercell connection cable, is realized
The loss of weight of power supply system and structural system, and effectively reduce installation space and assembly work amount；
(2) present invention uses " Z " in the lithium ion single battery pack mounting means in control battery and capacity cell
Type stack design realizes effective implantation of the battery pack in special-shaped small space, in series and parallel all using AC welding, no soldering
Point, simplifies welding procedure, improves the reliability of battery pack.
Detailed description of the invention
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 the present invention control series-parallel connection figure of battery lithium ions single battery；
Fig. 5 is that capacity cell lithium ion single battery strings of the present invention are connected in parallel figure；
Fig. 6 is present invention control battery and capacity cell assembled inside figure；
Fig. 7 is that present invention control battery and capacity cell are electrically connected schematic diagram.
Specific embodiment
The present invention is described in further detail in the following with reference to the drawings and specific embodiments:
It is proposed by the present invention a kind of applied to carry-on multifunction structure battery, using Electromechanical Design skill
Battery pack, cable, damping part, electric connector are implanted in aircraft bearing structure by art, realize structural support, system
It powers integrated multifunction structure system.The multifunction structure battery and the mutual discrete tradition of bearing structure, supplying cell
Scheme is compared, and is effectively reduced the parasitic components such as battery case, battery mounting bracket, intercell connection cable, is realized power supply
The loss of weight of system and structural system, and effectively reduce installation space and assembly work amount.
As shown in Figure 1, multifunction structure battery provided by the invention, comprising: I-beam 1, I-beam cover board 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
Support beam structure on external aircraft section structure, as 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 second electric connector 6 distinguish axis
To on the outer surface being vertically mounted on the inside of control battery 3；Third electric connector 7 and the 4th electric connector 8 are distinguished axially vertical
It is mounted on the outer surface of 4 inside of capacity cell；I-beam cover board 2 is fixedly mounted on the upper surface of I-beam 1 by screw 9.
The material of the I-beam 1, I-beam cover board 2 is aluminium alloy.
It is illustrated in figure 2 I-beam schematic diagram, as seen from the figure, 1 horizontal cross-section of I-beam is I-shaped, I-shaped level section
The outer side edges at face both ends are circular shape；One end of I-beam 1 is provided with deep trouth along the vertical direction, i.e. control battery installation space
10, the other end of I-beam 1 is provided with deep trouth, i.e. capacity cell installation space 11 along the vertical direction；It is vertically-mounted to control battery 3
In control battery installation space 10, capacity cell 4 is vertically installed in capacity cell installation space 11.
It is illustrated in figure 3 I-beam upper cover plate schematic diagram, as seen from the figure, the shape and I-beam 1 of I-beam cover board 2 are horizontal
Cross sectional shape is consistent, and I-beam cover board 2 is fixedly mounted on the upper surface of I-beam 1.
Be illustrated in figure 4 control the series-parallel connection figure of battery lithium ions single battery, be illustrated in figure 5 capacity cell lithium from
The sub- series-parallel connection figure of single battery, if Fig. 6 is that control battery and capacity cell assembled inside figure control battery 3 as seen from the figure
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；Every row's lithium ion single electricity
The lithium ion single battery 12 of Chi Zuzhong by connection strap 14 positioning be fixedly connected, the lithium in every row's lithium ion single battery pack from
Sub- single battery 12 is parallel connection；Every 3 row lithium ion single battery pack forms lithium ion battery layer, every 3 row lithium ion single electricity
The arrangement mode of pond group is " Z " word folding mode, is provided with epoxy plate 15 between adjacent lithium ion battery layer；Adjacent row is corresponding
Lithium ion single battery 12 is fixedly connected by cable 13, is series connection by the lithium ion single battery 12 that cable 13 connects；Control
The series-parallel connection type of lithium ion single battery 12 goes here and there 10 simultaneously for 9 in battery 3 processed.
Controlling battery 3 further includes heat conductive silica gel 16；It is 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 control 10 bottom end of battery installation space by heat conductive silica gel 16.
Capacity cell 4 includes 72 lithium ion single batteries 12, cable 13 and connection strap 14 and epoxy plate 15；72 lithiums from
Sub- single battery 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；
Lithium ion single battery 12 in every row's lithium ion single battery pack is fixedly connected by the positioning of connection strap 14, every row's lithium ion list
Lithium ion single battery 12 in body battery pack is parallel connection；Every 3 row lithium ion single battery pack forms lithium ion battery layer, often
The arrangement mode of 3 row's lithium ion single battery packs is " Z " word folding mode, is provided with epoxy plate between adjacent lithium ion battery layer
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 series-parallel connection type of lithium ion single battery 12 goes here and there 8 simultaneously for 9 in capacity cell 4.
Capacity cell 4 further includes heat conductive silica gel 16；It is 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 11 bottom end of capacity cell installation space by heat conductive silica gel 16.
It controls battery 3, electric connector 5, electric connector 6 and the output of flying vehicles control electric flux is provided jointly, control battery
Voltage is 28.5V, capacity 23Ah.Capacity cell 4, electric connector 7, electric connector 8 provide craft power electric flux jointly
Output, the voltage of capacity cell is 28.5V, capacity 18Ah.
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
12 both ends of pond pass through cable 13 and draw, and the both ends for controlling all lithium ion single batteries 12 in battery 3 are drawn out to first and are electrically connected
It connects on device 5, the both ends of all lithium ion single batteries 12 are drawn out on third electric connector 7 in capacity cell 4；9 groups of lithium ions
It is drawn after the series connection of single battery group by cable 13, controls in battery 3 and pass through cable 13 after 9 groups of lithium ion single battery pack series connection
It is drawn out on the second electric connector 6, is drawn out to the 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 that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (8)
1. one kind is applied to carry-on multifunction structure battery, it is characterised in that: including I-beam (1), I-beam cover board
(2), control battery (3), capacity cell (4), the first electric connector (5), the second electric connector (6), third electric connector (7) and
4th electric connector (8)；Wherein, I-beam (1) is fixed on external flight device section structure, the support as 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) respectively it is axially vertical be mounted on it is outer on the inside of control battery (3)
On surface；Third electric connector (7) and the 4th electric connector (8) respectively it is axially vertical be mounted on it is outer on the inside of capacity cell (4)
On surface；The shape of I-beam cover board (2) is consistent with I-beam (1) horizontal cross sectional geometry, and I-beam cover board (2) is fixedly mounted on
The upper surface of I-beam (1)；
I-beam (1) horizontal cross-section be it is I-shaped, the outer side edges at I-shaped horizontal cross-section both ends are circular shape；I-beam
(1) one end is provided with deep trouth along the vertical direction, i.e. control battery installation space (10), and the other end of I-beam (1) is along vertical
Direction is provided with deep trouth, i.e. capacity cell installation space (11)；Control battery (3) is vertically installed at control battery installation space
(10) in, capacity cell (4) is vertically installed in capacity cell installation space (11).
2. according to claim 1 a kind of 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- single battery (12) is uniformly divided into 9 row's lithium ion single battery packs, and the 9 equidistant horizontal parallels of row's lithium ion single battery pack are put
It sets；Lithium ion single battery (12) in every row's lithium ion single battery pack is fixedly connected by connection strap (14) positioning, every row
Lithium ion single battery (12) in lithium ion single battery pack is parallel connection；Every 3 row lithium ion single battery pack composition lithium from
Sub- battery layers, the arrangement mode of every 3 row lithium ion single battery pack are " 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), passes through cable
(13) the lithium ion single battery (12) connected is series connection；Lithium ion single battery (12) connects in series and parallel in control battery (3)
It connects mode and goes here and there 10 simultaneously for 9.
3. according to claim 2 a kind of applied to carry-on multifunction structure battery, it is characterised in that: the control
Battery (3) processed further includes heat conductive silica gel (16)；Connect between adjacent lithium ion single battery (12) by the way that heat conductive silica gel (16) are fixed
It connects；Control battery (3) is fixedly mounted on the upper surface of control battery installation space (10) bottom end by heat conductive silica gel (16).
4. according to claim 3 a kind of applied to carry-on multifunction structure battery, it is characterised in that: the function
Rate battery (4) includes 72 lithium ion single batteries (12), cable (13) and connection strap (14) and epoxy plate (15)；72 lithiums from
Sub- single battery (12) is uniformly divided into 9 row's lithium ion single battery packs, and the 9 equidistant horizontal parallels of row's lithium ion single battery pack are put
It sets；Lithium ion single battery (12) in every row's lithium ion single battery pack is fixedly connected by connection strap (14) positioning, every row
Lithium ion single battery (12) in lithium ion single battery pack is parallel connection；Every 3 row lithium ion single battery pack composition lithium from
Sub- battery layers, the arrangement mode of every 3 row lithium ion single battery pack are " 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), passes through cable
(13) the lithium ion single battery (12) connected is series connection；Lithium ion single battery (12) connects in series and parallel in capacity cell (4)
It connects mode and goes here and there 8 simultaneously for 9.
5. according to claim 4 a kind of applied to carry-on multifunction structure battery, it is characterised in that: the function
Rate battery (4) further includes heat conductive silica gel (16)；Connect between adjacent lithium ion single battery (12) by the way that heat conductive silica gel (16) are fixed
It connects；Capacity cell (4) is fixedly mounted on the upper surface of capacity cell installation space (11) bottom end by heat conductive silica gel (16).
6. according to claim 5 a kind of applied to carry-on multifunction structure battery, it is characterised in that: described
Lithium ion single battery (12) uses LiFePO4 battery system, battery energy density 115Wh/Kg, voltage 3.15V, capacity
2.5Ah。
7. according to claim 6 a kind of applied to carry-on multifunction structure battery, it is characterised in that: each lithium
Ion battery cell (12) both ends pass through cable (13) extraction, all lithium ion single batteries (12) in control battery (3)
Both ends are drawn out on the first electric connector (5), and the both ends of all lithium ion single batteries (12) are drawn out in capacity cell (4)
On three electric connectors (7)；It is drawn after 9 groups of lithium ion single battery pack series connection by cable (13), 9 groups of lithiums in control battery (3)
Be drawn out on the second electric connector (6) after the series connection of ion battery cell group by cable (13), in capacity cell (4) 9 groups of lithiums from
It is drawn out on the 4th electric connector (8) after sub- single battery group series connection by cable (13).
8. according to claim 1 a kind of applied to carry-on multifunction structure battery, it is characterised in that: described
I-beam (1), I-beam cover board (2) material be 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 CN106654086A (en) | 2017-05-10 |
| CN106654086B true CN106654086B (en) | 2019-03-22 |
Family
ID=58853822
Family Applications (1)
| 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 |
|---|---|
| CN (1) | CN106654086B (en) |
Families Citing this family (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 |
| CN112531257B (en) * | 2020-12-16 | 2023-01-10 | 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 |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4614405A (en) * | 1982-09-28 | 1986-09-30 | The Boeing Company | Wide angle laser window |
| FR2675462A1 (en) * | 1991-04-18 | 1992-10-23 | Zeppelin Luftschiffbau | DIRECTION WHERE THE ENVELOPE SURROUNDING THE AIR CHAMBERS IS MOUNTED ON A CARRIER CHANNEL FORMED OF A SERIES OF TRANSVERSE COUPLES AND LONGITUDINAL BEAMS. |
| 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
Also Published As
| Publication number | Publication date |
|---|---|
| CN106654086A (en) | 2017-05-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20150044572A1 (en) | Electrical energy storage structures | |
| EP2959521B1 (en) | Aircraft including mitigation system for rechargeable batteries | |
| EP2962341B1 (en) | Rechargeable battery including battery cell separators | |
| CN106654086B (en) | One kind being applied to carry-on multifunction structure battery | |
| CN105990609A (en) | Battery pack | |
| CN107706325A (en) | Power module and vehicle | |
| CN205652370U (en) | Staying unmanned aerial vehicle | |
| Duy et al. | Review on the hybrid-electric propulsion system and renewables and energy storage for unmanned aerial vehicles | |
| CN110474130A (en) | A kind of Upper Stage Li-ion batteries piles | |
| CN106785215A (en) | A kind of battery modules and electrokinetic cell | |
| CN202189852U (en) | Power lithium ion battery pack | |
| CN206516728U (en) | Quick-inflating type long circulating electrokinetic cell system | |
| CN106410069B (en) | Removable lithium battery group | |
| EP4354618A1 (en) | Battery, electrical device, and method and device for fabricating battery | |
| CN105071545A (en) | Quantum physics storage battery and preparation method thereof | |
| CN107919810A (en) | A kind of aircraft electrostatic protection and Collection utilization system | |
| EP2535970A1 (en) | Component including a rechargeable battery | |
| CN106972194A (en) | A kind of lithium ion battery | |
| CN114633870A (en) | Load-bearing composite layer material structure for an aircraft component, aircraft component produced therewith and aircraft | |
| CN206087307U (en) | Unmanned aerial vehicle's distributed power supply unit and unmanned aerial vehicle | |
| Ohki | Commencement of operation of the world's largest storage battery facility [News from Japan] | |
| CN207303175U (en) | A kind of column lithium ion battery group | |
| CN111370806A (en) | Battery pack honeycomb topology heat conduction structure for underwater vehicle | |
| CN215955385U (en) | Battery module | |
| CN109560239A (en) | Extend cable type space lithium-ions battery group |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |