CN205790082U - The battery structure of multiple-way supply, battery system and aircraft - Google Patents
The battery structure of multiple-way supply, battery system and aircraft Download PDFInfo
- Publication number
- CN205790082U CN205790082U CN201620480433.6U CN201620480433U CN205790082U CN 205790082 U CN205790082 U CN 205790082U CN 201620480433 U CN201620480433 U CN 201620480433U CN 205790082 U CN205790082 U CN 205790082U
- Authority
- CN
- China
- Prior art keywords
- battery
- aircraft
- battery structure
- power
- attaching plug
- 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
-
- 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
- Battery Mounting, Suspending (AREA)
Abstract
The disclosure is directed to the battery structure of a kind of multiple-way supply, battery system and aircraft, this battery structure includes: battery container；The battery core group being built in described battery container, described battery core group forms multiple power supply port；Multiple power connectors, are respectively electrically connected to the plurality of power supply port, and described power connector is fixed on the default opening part on described battery container, to be electrically connected to the attaching plug in aircraft battery storehouse by described default opening.By the technical scheme of the disclosure, the confession electrical stability between battery and aircraft can be promoted.
Description
Technical field
It relates to flight control technique field, particularly relate to the battery structure of a kind of multiple-way supply, battery system
System and aircraft.
Background technology
In the related in the battery structure of aircraft, by the electric wire that battery core is drawn and flight
After metal connector (such as banana plug) in device battery compartment connects, it is achieved supply to the cooperation of aircraft
Electricity, and it is screwed the door of battery compartment.
But, on the one hand, the connection between electric wire and metal connector excessively fastens so that user is more
It is easy to when changing battery occur to pull energetically, thus causes the plug weld quilt of electric wire or metal connector
Pull apart.On the other hand, the battery core in correlation technique is by the output power supply of unique electric wire, then due to this
Electric wire and metal connector are easy to be torn and damage, and cause battery to the power supply of aircraft the most also
Unstable, it is likely that power-off in flight course and cause aircraft to crash, exist strong dangerous because of
Element.
Utility model content
The disclosure provides the battery structure of a kind of multiple-way supply, battery system and aircraft, relevant to solve
Deficiency in technology.
First aspect according to disclosure embodiment, it is provided that the battery structure of a kind of multiple-way supply, including:
Battery container；
The battery core group being built in described battery container, described battery core group forms multiple power supply port；
Multiple power connectors, are respectively electrically connected to the plurality of power supply port, and described power connector is fixed
Default opening part on described battery container, to be electrically connected to aircraft battery by described default opening
The attaching plug in storehouse.
Optionally, described battery structure is formed even number power connector, is respectively symmetrically described in being arranged at
The side edge of battery container.
Optionally, described battery container includes:
Upper shell, lower house, described upper shell and described lower house assemble after side to described battery core group
Wrap up with bottom；
Lid, when assembling with described upper shell, described lower house, closes the top of described battery core group；
Wherein, described power connector is positioned at the top side edge of described battery core group.
Optionally, the end of described upper shell and described lower house forms shirt rim the most laterally, to coordinate
Inner face in described lid；Wherein, described default opening is formed at described upper shell and described lower house
Junction, shirt rim.
Second aspect according to disclosure embodiment, it is provided that the battery system of a kind of multiple-way supply, including:
The battery structure of the multiple-way supply as described in arbitrary in above-described embodiment；
Aircraft battery storehouse, including:
Battery fixed frame, is used for accommodating and fix described battery structure；
At least one attaching plug, for being connected with the power connector on described battery structure, with to flying
Row device is powered.
Optionally, the attaching plug in described aircraft battery storehouse is connected with the power supply on described battery structure
Device one_to_one corresponding；Wherein, when described battery structure is fixed on described battery fixed frame, each power supply is inserted
Head is respectively electrically connected to corresponding power connector.
Optionally, described battery fixed frame is provided with on the battery container of Access Division, described battery structure and sets
Having snap-fit engagement portion, described battery structure is by coordinating between described Access Division with described snap-fit engagement portion
It is fixed in described aircraft battery storehouse.
Optionally, described battery structure, described aircraft battery storehouse are symmetrical set respectively.
Optionally, also include:
Power supply test section, for connecting with the multiple power supplys on described battery structure respectively when multiple attaching plugs
Connect device when being connected, detect the electric power thus supplied at each attaching plug respectively；
Power switching portion, when described aircraft exists for electrical anomaly, is cut by the attaching plug currently powered
Shift to other attaching plugs being in normal power supply state.
The third aspect according to disclosure embodiment, it is provided that a kind of aircraft, including:
The battery system of the multiple-way supply as described in arbitrary in above-described embodiment.
Embodiment of the disclosure that the technical scheme of offer can include following beneficial effect:
From above-described embodiment, the disclosure is by presetting of being fixed on battery container by power connector
Opening part, and avoid by the attaching plug being individually wired to aircraft battery storehouse, it can be ensured that two
The firm connection of person, and prevent the damages such as when dismounting or replacing battery, user causes that electric wire etc. is pulled apart.
Meanwhile, by arranging multiple power connector so that even if partial power adapter is damaged, still
Power supply can be attached by other power connectors, contribute to extending the service life of battery structure.
Especially, when being connected simultaneously to the attaching plug in aircraft battery storehouse by multiple power connectors, can
To realize the battery structure multiple-way supply to aircraft, then even if part line powering lost efficacy, still
The effective power supply to aircraft can be realized by All other routes, thus avoid the meanings such as aircraft generation crash
Outward.
It should be appreciated that it is only exemplary and explanatory that above general description and details hereinafter describe
, the disclosure can not be limited.
Accompanying drawing explanation
Accompanying drawing herein is merged in description and constitutes the part of this specification, it is shown that meet these public affairs
The embodiment opened, and for explaining the principle of the disclosure together with description.
Fig. 1 is the decomposition texture of the battery structure according to a kind of multiple-way supply shown in an exemplary embodiment
Schematic diagram.
Fig. 2 is the perspective view according to a kind of power connector shown in an exemplary embodiment.
Fig. 3 is the stereochemical structure of the battery structure according to a kind of multiple-way supply shown in an exemplary embodiment
Schematic diagram.
Fig. 4 is coordinating according to a kind of battery structure shown in an exemplary embodiment and aircraft battery storehouse
Structural representation.
Fig. 5 is according to the aircraft battery storehouse under a kind of decomposition texture shown in an exemplary embodiment and electricity
The fit structure schematic diagram of pool structure.
Detailed description of the invention
Here will illustrate exemplary embodiment in detail, its example represents in the accompanying drawings.Following
When description relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawings represents same or analogous
Key element.Embodiment described in following exemplary embodiment does not represent the institute consistent with the disclosure
There is embodiment.On the contrary, they only with as appended claims describes in detail, the one of the disclosure
The example of the apparatus and method that a little aspects are consistent.
Fig. 1 is the decomposition texture of the battery structure according to a kind of multiple-way supply shown in an exemplary embodiment
Schematic diagram, as it is shown in figure 1, this battery structure 1 may include that battery container 11；It is built in this battery
Battery core group 12 in housing 11, this battery core group 12 forms multiple power supply port (not shown)；Multiple
Power connector 13, is respectively electrically connected to above-mentioned multiple power supply ports so that this battery structure 1 can be same
Time or realized the transmission of multi-channel electric signal respectively by the plurality of power connector 13.
In one exemplary embodiment, as it is shown in figure 1, battery container 11 may include that upper shell 111,
Lower house 112 and lid 113.Wherein, to above-mentioned after this upper shell 111 assembles with this lower house 112
The side of battery core group 12 and bottom wrap up, and lid 113 and this upper shell 111, this lower house
112 when assembling, and can close the top of this battery core group 12, thus battery core group 12 is closed in electricity
Pond housing 11 is internal.
Wherein, in the top side edge of battery core group 12, i.e. upper shell 111 shown in Fig. 1, lower house 112
With the junction of lid 113, default opening (not indicating in figure) can be formed so that power connector
13 can stretch out battery container 11 from this default opening.
And as in figure 2 it is shown, the side up and down of power connector 13 can be respectively equipped with locating dowel 131, make
Obtain this power connector 13 can with respectively with upper shell 111, lower house 112 by modes such as such as screws
It is attached fixing；Meanwhile, power connector 13 can be by being positioned at slot 132 and figure below of end
Attaching plug 22 grafting in aircraft battery storehouse 2 shown in 4-5.Complete in conjunction with the assembling shown in Fig. 3
Battery structure 1 understand: by power connector 13 is fixed on battery container 11 so that power supply
Connection line etc. between the power supply port of adapter 13 and battery core group 12 is all housed inside battery container 11
Internal, then battery structure 1 is being unloaded from aircraft or carrying out this battery structure 1 more by user
When changing, can avoid this connection line etc. is caused pullling, thus prevent from causing circuit to damage, contribute to
Extend the service life of battery structure 1.
As shown in figures 1 and 3, upper shell 111, lower house 112 are combined as rectangular structure substantially,
To accommodate the battery core group 12 of essentially rectangular structure, and the end face of this rectangular structure is less than lid 113,
Thus so that the inner face of lid 113 can enter with the outer face of upper shell 111, lower house 112
Row is closed, to realize encapsulation to battery core group 12, upper shell 111, lower house 112 outer face at
Can form shirt rim (not indicating in figure) the most laterally, and the skirt of upper shell 111 and lower house 112
Junction, limit can form above-mentioned default opening so that power connector 13 can be stretched by this default opening
Go out, form the battery structure 1 shown in Fig. 3.
Understand it practice, combine Fig. 4: in the technical scheme of the disclosure, when battery structure 1 is assembled
During unmanned plane battery compartment 2 to unmanned plane 3, use the lid 113 of battery container 11 outwardly, upper casing
Battery structure 1 is inserted in aircraft battery storehouse 2 by direction inwardly, the bottom of body 111 and lower house 112,
Thus when power connector 13 stretches out at the shirt rim that upper shell 111 and lower house 112 are formed, can
Power connector 13 is made to arrange along this battery structure 1 direction of insertion to aircraft battery storehouse 2, then power supply
The slot 132 (see Fig. 2) of adapter 13 can just inside to aircraft battery storehouse 2, in order to should
Docking between slot 132 with the attaching plug 22 within aircraft battery storehouse 2.
By coordinating between the battery structure 1 of above-mentioned multiple-way supply and aircraft battery storehouse 2, permissible
Obtain the battery system of the multiple-way supply that the disclosure proposes, to realize the multiple-way supply to aircraft.Such as figure
Shown in 5, this aircraft battery storehouse 2 may include that battery fixed frame 21, is used for accommodating and fix this electricity
Pool structure 1；At least one attaching plug 22, is used for and the power connector 13 on this battery structure 1
It is connected, to power to aircraft 3.
Wherein, battery fixed frame 21 is provided with on the battery container 11 of Access Division 24, this battery structure 1
Being provided with snap-fit engagement portion 14, this battery structure 1 is by between this Access Division 24 and this snap-fit engagement portion 14
Cooperation be fixed in this aircraft battery storehouse 2, consequently facilitating realize quickly tearing open this battery structure 1
Dress.Certainly, battery fixed frame 21 can also pass through other any form of self-locking structures, it is achieved to battery
The fixing connection of structure 1, this is not limited by the disclosure.
As an exemplary embodiment, the attaching plug 22 in aircraft battery storehouse 2 and this battery structure 1
On power connector 13 one_to_one corresponding；Wherein, it is fixed on this battery fixed frame when this battery structure 1
When 21, each attaching plug 22 is respectively electrically connected to corresponding power connector 13.In other words, flight
Device 3 can realize Multi-path electricity with battery structure 2 simultaneously be connected, and there is left and right two-way electricity in such as Fig. 5
Connect, then even if the power connector 13 of any of which road abnormal electrical power supply, such as left side and attaching plug
22 loose contacts, then it is right still can be realized by the power connector 13 on right side and attaching plug 22
The normal power supply of aircraft 3.
Further, aircraft battery storehouse 2 can also include: power supply test section (not shown),
For when multiple attaching plugs 22 are connected with the multiple power connectors 13 on this battery structure 1 respectively,
Detect the electric power thus supplied at each attaching plug 22 respectively；Power switching portion (not shown), when this
When aircraft 3 exists for electrical anomaly, the attaching plug 22 currently powered switch to other and be in normal confession
The attaching plug 22 of electricity condition.So, especially when aircraft 3 is in state of flight, by confession
The timely switching of electric line, it can be ensured that aircraft 3 is maintained all the time normal power supply, thus avoids flight
There is the accidents such as crash in device 3.
As another exemplary embodiment, attaching plug 22 quantity in aircraft battery storehouse 2 can be less than
Power connector 13 quantity on battery structure 1, such as battery structure 1 is provided with two power connectors
13, aircraft battery storehouse 2 is provided only with an attaching plug 22, then if battery structure 1, this flight
Device battery compartment 2 is symmetrical set respectively, can be when certain power connector 13 damages, by by battery
After structure 1 upset, in mating connection with attaching plug 22 by another power connector 13.Wherein,
More power connector 13, and preferably even number power connector 13 can be comprised on battery structure 1,
And it is respectively symmetrically the side edge being arranged at battery container 11, such as respectively can arrange multiple in arranged on left and right sides
Power connector 13 etc..
Certainly, in the case of the attaching plug 22 quantity one_to_one corresponding with power connector 13, battery
Structure 1, this aircraft battery storehouse 2 are symmetrical set the most respectively, thus at power connector 13
When docking with attaching plug 22, symmetrical grafting can be provided to battery structure 1 and aircraft battery storehouse 2
Combining ability so that battery structure 1 is more stablized, is securely mounted in aircraft battery storehouse 2.
In the technical scheme of the disclosure, battery container 11, power connector 13 etc. all can use to be moulded
Glue material, can be in the case of guaranteeing sufficient intensity, it is provided that lighter weight, to reduce aircraft
The loading demand of 3, and be easy to realize quickly by modes such as such as injection mo(u)ldings, produce in enormous quantities.When
So, power connector 13 is internal by such as copper pipe etc., for realizing the transmission performance of excellence.
Additionally, battery structure 1 is provided with on and off switch (not indicating in figure), battery structure 1 is being filled
After being assigned to aircraft battery storehouse 2, by triggering this on and off switch, battery structure 1 can be started to flight
The power supply of device 3.
Those skilled in the art, after considering description and putting into practice disclosure disclosed herein, will readily occur to this
Other embodiment disclosed.The application is intended to any modification, purposes or the adaptability of the disclosure
Change, these modification, purposes or adaptations are followed the general principle of the disclosure and include these public affairs
Open undocumented common knowledge in the art or conventional techniques means.Description and embodiments only by
Being considered as exemplary, the true scope of the disclosure and spirit are pointed out by claim below.
It should be appreciated that the disclosure be not limited to described above and illustrated in the accompanying drawings accurately
Structure, and various modifications and changes can carried out without departing from the scope.The scope of the present disclosure is only by institute
Attached claim limits.
Claims (10)
1. the battery structure of a multiple-way supply, it is characterised in that including:
Battery container；
The battery core group being built in described battery container, described battery core group forms multiple power supply port；
Multiple power connectors, are respectively electrically connected to the plurality of power supply port, and described power connector is fixed
Default opening part on described battery container, to be electrically connected to aircraft battery by described default opening
The attaching plug in storehouse.
Battery structure the most according to claim 1, it is characterised in that formed on described battery structure
Even number power connector, is respectively symmetrically the side edge being arranged at described battery container.
Battery structure the most according to claim 1, it is characterised in that described battery container includes:
Upper shell, lower house, described upper shell and described lower house assemble after side to described battery core group
Wrap up with bottom；
Lid, when assembling with described upper shell, described lower house, closes the top of described battery core group；
Wherein, described power connector is positioned at the top side edge of described battery core group.
Battery structure the most according to claim 3, it is characterised in that described upper shell and described under
The end of housing forms shirt rim the most laterally, to be matched with the inner face of described lid；Wherein, described
Default opening is formed at the junction, shirt rim of described upper shell and described lower house.
5. the battery system of a multiple-way supply, it is characterised in that including:
The battery structure of the multiple-way supply as according to any one of claim 1-4；
Aircraft battery storehouse, including:
Battery fixed frame, is used for accommodating and fix described battery structure；
At least one attaching plug, for being connected with the power connector on described battery structure, with to flying
Row device is powered.
Battery system the most according to claim 5, it is characterised in that in described aircraft battery storehouse
Attaching plug and described battery structure on power connector one_to_one corresponding；Wherein, tie when described battery
When structure is fixed on described battery fixed frame, each attaching plug is respectively electrically connected to corresponding power connector.
Battery system the most according to claim 5, it is characterised in that set on described battery fixed frame
Having Access Division, the battery container of described battery structure to be provided with snap-fit engagement portion, described battery structure passes through
Coordinating between described Access Division with described snap-fit engagement portion is fixed in described aircraft battery storehouse.
Battery system the most according to claim 5, it is characterised in that described battery structure, described
Aircraft battery storehouse is symmetrical set respectively.
Battery system the most according to claim 5, it is characterised in that also include:
Power supply test section, for connecting with the multiple power supplys on described battery structure respectively when multiple attaching plugs
Connect device when being connected, detect the electric power thus supplied at each attaching plug respectively；
Power switching portion, when described aircraft exists for electrical anomaly, is cut by the attaching plug currently powered
Shift to other attaching plugs being in normal power supply state.
10. an aircraft, it is characterised in that including:
The battery system of the multiple-way supply as according to any one of claim 5-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620480433.6U CN205790082U (en) | 2016-05-24 | 2016-05-24 | The battery structure of multiple-way supply, battery system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620480433.6U CN205790082U (en) | 2016-05-24 | 2016-05-24 | The battery structure of multiple-way supply, battery system and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205790082U true CN205790082U (en) | 2016-12-07 |
Family
ID=58113241
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620480433.6U Active CN205790082U (en) | 2016-05-24 | 2016-05-24 | The battery structure of multiple-way supply, battery system and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205790082U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105826488A (en) * | 2016-05-24 | 2016-08-03 | 北京小米移动软件有限公司 | Multi-channel power supply cell structure, cell system and air vehicle |
-
2016
- 2016-05-24 CN CN201620480433.6U patent/CN205790082U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105826488A (en) * | 2016-05-24 | 2016-08-03 | 北京小米移动软件有限公司 | Multi-channel power supply cell structure, cell system and air vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5576675B2 (en) | Power supply control device | |
| CN105048682B (en) | The compressor of motor drive with electric terminal block component | |
| CN202405549U (en) | Charging connector and charging connecting device | |
| CN106531953B (en) | Lead-acid accumulator and battery pack | |
| CN109075299A (en) | The method of battery pack and assembled battery group | |
| JP2014054162A (en) | Electric vehicle charger | |
| JP6361808B2 (en) | battery pack | |
| CN203204041U (en) | Novel electric energy meter inserter | |
| CN103935236A (en) | Transmission for a vehicle | |
| CN205790082U (en) | The battery structure of multiple-way supply, battery system and aircraft | |
| US10840490B2 (en) | Manual service disconnect for battery system | |
| CN109546064A (en) | Electrical storage device | |
| CN105826488A (en) | Multi-channel power supply cell structure, cell system and air vehicle | |
| JP6641602B2 (en) | Wiring module | |
| US9787040B2 (en) | Energy-saving power strip | |
| CN205452674U (en) | Power supply plugging device | |
| CN208257344U (en) | Bus duct joint protective device | |
| US20170117527A1 (en) | Battery module cover provided with an electrical connection clip | |
| CN206332576U (en) | Starter-generator | |
| CN205051081U (en) | Novel plug subassembly structure | |
| CN209328811U (en) | Earth leakage circuit breaker | |
| CN208849113U (en) | A kind of eight needle connectors | |
| CN208385718U (en) | A kind of cylindrical connector harness | |
| CN205523751U (en) | A connect formula busbar soon for electric automobile fills electric pile | |
| CN205488269U (en) | Electronic equipment and battery compartment thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Multi-channel power supply cell structure, cell system and air vehicle Effective date of registration: 20180211 Granted publication date: 20161207 Pledgee: Silicon Valley Bank Co., Ltd. Pledgor: GUANGZHOU FEIMI ELECTRONIC TECHNOLOGY CO., LTD. Registration number: 2018310000006 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |