CN206422102U - A kind of aircraft electric power system - Google Patents
A kind of aircraft electric power system Download PDFInfo
- Publication number
- CN206422102U CN206422102U CN201621350042.9U CN201621350042U CN206422102U CN 206422102 U CN206422102 U CN 206422102U CN 201621350042 U CN201621350042 U CN 201621350042U CN 206422102 U CN206422102 U CN 206422102U
- Authority
- CN
- China
- Prior art keywords
- back box
- copper sheet
- battery case
- power system
- electric power
- 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.)
- Expired - Fee Related
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
Abstract
A kind of aircraft electric power system, including power supply and the fixed mount for fixed power source；The power supply includes battery case, the battery pack being arranged in battery case and arrangements of electric connection；The control circuit of the first copper sheet terminal and the second copper sheet terminal as the output end of battery pack by two flat spring shell fragments to aircraft on battery case is powered, this kind contact can be the contact of elastic sheet metal, the electrical connection for making the two is reliable, it can thus realize that power supply is powered, and conveniently say that power supply is removed；The flanged structure formation slide unit of battery case cover rim formation, coordinates, battery case can slip into chute, flange is supported by the supporting plate of chute so that battery case can be realized with aircraft and mechanically connected with the chute of fixed mount bottom.
Description
Technical field
The utility model is related to aircraft, the aircraft electric power system of especially a kind of replaceable power supply.
Background technology
Unmanned plane application technology is a upcoming technology.There are many new technologies on unmanned plane to be opened
Hair.Unmanned plane has very big potentiality to play a significant role in following logistics or monitoring activity.But still have some shortcomings.One
It is individual primary disadvantage is that the limitation of flight range, therefore a kind of technology should be developed to expand flight range.Allow unmanned plane during flying when
Between extension have many different methods.For example, unmanned plane can carry more or more preferable battery.This will extend the electricity of unmanned plane
Pond use time.However, it is not a nothing the matter to improve battery.Many companies are directed to improving the energy density of battery
Or the new battery technology of exploitation.However, in a short time, energy density does not have big improvement.If unmanned plane carries more
Battery, it can fly farther.But in a certain critical condition, the weight of battery becomes big, and flight range can decline again.So
The endurance of real improvement unmanned plane, in unmanned plane power technology is intelligently changed, power supply are can be only achieved by changing battery
Structure electrical cooperation between aircraft power fixed mount and mechanical engagement are most important.
The content of the invention
Technical problem to be solved in the utility model is to provide a kind of aircraft electric power system, and power supply is replaceable.
In order to solve the above technical problems, the technical solution of the utility model is：A kind of aircraft electric power system, including power supply
With the fixed mount for fixed power source；The power supply includes battery case, the battery pack being arranged in battery case and arrangements of electric connection；
The battery case includes back box and the upper lid coordinated with back box, the surrounding formation flange wider than back box of the upper lid, the back box
Side and bottom surface be equipped with heat emission hole, one end of the back box is provided with can be by the metal derby of magnetic；The arrangements of electric connection bag
Include the first copper sheet terminal and the second copper sheet terminal for being arranged on tops, the first copper sheet terminal and the second copper sheet terminal respectively with
The positive and negative electrode connection of battery pack；The fixed mount includes two blocks of symmetrically arranged side plates and between two blocks of side plates
Some crossbeams, the bottom of the side plate is provided with the supporting plate extended internally, is formed between the supporting plate, side plate and crossbeam
Chute；Wherein one crossbeam is provided with two panels spring copper sheet, and the spring copper sheet includes fixed part, contact site and guiding
Portion, the contact site is provided with screw, and contact site is bolted on crossbeam, and the contact site relative level is in downward
It is obliquely installed, the guide part relative level is in the setting that is inclined upwardly, and the fixed part, contact site and guide part are by spring copper
Piece bending forming.Utility model works principle：During normal operating conditions, the battery case of power supply is arranged in fixed mount, the two
Whole installation aircraft bottom position；The first copper sheet terminal and the second copper sheet terminal on battery case as battery pack output end
Control circuit by two flat spring shell fragments to aircraft is powered, and this kind contact can be the contact of elastic sheet metal, make the two
Electrical connection be reliable, can thus realize that power supply is powered, and conveniently say that power supply is removed；Battery case cover rim is formed
Flanged structure formation slide unit, coordinate with the chute of fixed mount bottom, battery case can be slipped into chute, pass through the branch of chute
Fagging is supported to flange so that battery case can be realized with aircraft and mechanically connected；When needing to change carry-on electricity
During source, electromagnet is held to the metal derby of battery case end, battery case is taken out from chute using magnetic force, then changes and is full of
The power supply of electricity.
As an improvement, the back box is rectangle, accommodating cavity, shape and the back box shape of the battery pack are formed in back box
Shape is similar, and battery pack is arranged in accommodating cavity body.
As an improvement, one end of the back box is provided with embedded hole, the metal derby is embedded in the embedded hole.
As an improvement, the upper lid is connected by bolt with back box.
As an improvement, the bottom of the side plate is provided with some projections, the side correspondence high spot of the supporting plate
Provided with groove, the described raised and groove coordinates.
As an improvement, the supporting plate is bolted on the bottom of side plate.
As an improvement, the top of the crossbeam is provided with mounting hole.
As an improvement, the two ends of the crossbeam are connected by bolt with side plate.
The beneficial effect that the utility model is brought compared with prior art is：
Quick electrical connection can be realized by being contacted by the copper sheet terminal at the top of battery case with the spring copper sheet on fixed mount；
Coordinated by the chute plug-in type on the flange and fixed mount of cover rim, can be achieved quickly to mechanically connect；Pass through battery case
The metal derby of end, can be achieved the quick-replaceable of battery.
Brief description of the drawings
Fig. 1 is the schematic diagram that power supply coordinates with fixed mount.
Fig. 2 is power supply decomposition view.
Fig. 3 is power supply architecture schematic diagram.
Fig. 4 is fixed rack structure schematic diagram.
Embodiment
With reference to Figure of description, the utility model is described in further detail.
As shown in figure 1, a kind of aircraft electric power system, including power supply 2 and the fixed mount 1 for fixed power source 2；It is described solid
Determine the bottom that frame 1 is arranged on aircraft, the power supply 2 is fixed in fixed mount 1.
As shown in Figure 2,3, the power supply 2 includes battery case, the battery pack 23 being arranged in battery case and arrangements of electric connection.
The battery case includes back box 21 and the upper lid 22 coordinated with back box 21.The back box 21 is steel box, and its totality is rectangle, bottom
Accommodating cavity is formed in box 21, the side and bottom surface of the back box 21 are equipped with heat emission hole；Heat emission hole 212 on side is in strip
Shape and it is obliquely installed, makes the aperture of heat emission hole bigger, the heat emission hole of the both sides of back box 21 is oppositely arranged, and convection current is more preferable；The bottom of back box 21
The heat emission hole in face is in shift to install.The battery pack 23 is Li-ion batteries piles 23, shape and the back box 21 of the battery pack 23
Shape is similar, and battery pack 23 is arranged in accommodating cavity body.The surrounding formation flange wider than back box 21 of the upper lid 22, it is described on
Lid 22 is connected by bolt with back box 21；The two ends width of upper lid 22 is gradually narrowed, and four corners of lid 22 is formed inwardly
Inclined-plane 222, this kind of structure can make lid 22 be easier import chute in.One end of the back box 1 is provided with embedded hole 211,
Embedded hole 211 is rounded or square, and metal derby 25 is provided with the embedded hole, and the metal derby 25 can pass through magnetic by magnetic
Whole back box 21 can be connected upper lid 22 and pulled together by the metal derby 25.The top of the upper lid 22 is provided with two storage tanks
221, the arrangements of electric connection includes the first copper sheet terminal 26 and the second copper sheet end being arranged in the top storage tank 221 of lid 22
The top surface of son 27, the first copper sheet terminal 26 and the second copper sheet terminal 27 is higher than upper lid 22, the first copper sheet terminal 26 and the second copper sheet
The bottom of terminal 27 is connected by cable with the positive and negative electrode of battery pack 23 respectively；One end of cable is welded with copper sheet terminal,
The other end is provided with connection sheet, and the connection sheet is electrically connected with by bolt and the output end of battery pack 23.
As shown in figure 4, the fixed mount 1 includes two blocks of symmetrically arranged side plates 11, between two blocks of side plates 11
Some crossbeams 12 and the supporting plate 13 located at the bottom of side plate 11.The crossbeam 12 equally be arranged in parallel, the horizontal stroke
The two ends of beam 12 respectively at both sides the contacts side surfaces of side plate 11 and be connected by bolt with side plate 11；The top of the crossbeam 12
Portion is provided with mounting hole, and the mounting hole is used to be connected with the bottom plate of aircraft, so that the entirely fixed bottom for being placed on aircraft.Institute
State supporting plate 13 to extend internally, the outside of supporting plate 13 is bolted on the bottom of side plate 11；The side plate 11
Bottom is provided with some raised 111, the side correspondence described raised 111 of the supporting plate 13 and is provided with groove 131, the projection
111 coordinate with the groove 131.Chute 14 is formed between the supporting plate 13, side plate 11 and crossbeam 12, the chute 14 is available for
The battery case of power supply is inserted and fixed.Wherein one crossbeam 12 is provided with two panels spring copper sheet 15, and the output end of power supply can
Control circuit by the spring copper sheet 15 to aircraft is powered.The spring copper sheet 15 includes fixed part 151, contact site 152
With guide part 153；The contact site 152 is provided with screw, and contact site 152 is bolted on crossbeam 12；The contact
The relative level of portion 152 forms the trend being pressed downward, the output end that the contact site 152 can be with power supply in setting is tilted down
Sub- reliable contacts；The relative level of guide part 153 enters after chute 14 in the setting that is inclined upwardly, the lead-out terminal of power supply,
Pass through the inclined-plane jack-up of the front end of guide part 153 guide part 153 and entrance contact site 152；The fixed part 151, contact site 152
With guide part 153 by the bending forming of spring copper sheet 15, certain elasticity is made it have.
Utility model works principle：During normal operating conditions, the battery case of power supply is arranged in fixed mount, the two entirety
Aircraft bottom position is set；The first copper sheet terminal and the second copper sheet terminal on battery case pass through as the output end of battery pack
Two flat spring shell fragments are powered to the control circuit of aircraft, and this kind contact can be the contact of elastic sheet metal, make the electricity of the two
Connection is reliable, can thus realize that power supply is powered, and conveniently say that power supply is removed；It is convex that battery case cover rim is formed
Edge structure formation slide unit, coordinates, battery case can be slipped into chute, pass through the supporting plate of chute with the chute of fixed mount bottom
Flange is supported so that battery case can be realized with aircraft and mechanically connected；When needing to change carry-on power supply,
Electromagnet is held to the metal derby of battery case end, battery case is taken out from chute using magnetic force, then changed fully charged
Power supply.
Claims (8)
1. a kind of aircraft electric power system, including power supply and the fixed mount for fixed power source；It is characterized in that：The power supply bag
Include battery case, the battery pack being arranged in battery case and arrangements of electric connection；What the battery case coordinated including back box and with back box
Upper lid, the surrounding formation flange wider than back box of the upper lid, the side and bottom surface of the back box are equipped with heat emission hole, the back box
One end provided with can be by the metal derby of magnetic；The arrangements of electric connection includes the first copper sheet terminal and for being arranged on tops
Two copper sheet terminals, the first copper sheet terminal and the second copper sheet terminal are connected with the positive and negative electrode of battery pack respectively；The fixed mount includes
Two blocks of symmetrically arranged side plates and some crossbeams between two blocks of side plates, the bottom of the side plate, which is provided with, inwardly prolongs
The supporting plate stretched, chute is formed between the supporting plate, side plate and crossbeam；Wherein one crossbeam is provided with two flat springs
Copper sheet, the spring copper sheet includes fixed part, contact site and guide part, and the contact site is provided with screw, and contact site passes through spiral shell
Bolt is fixed on crossbeam, and the contact site relative level is in setting is tilted down, and the guide part relative level is in upward
It is obliquely installed, the fixed part, contact site and guide part are by spring copper sheet bending forming.
2. a kind of aircraft electric power system according to claim 1, it is characterised in that：The back box is rectangle, back box
Interior to form accommodating cavity, the shape of the battery pack is similar to back box shape, and battery pack is arranged in accommodating cavity body.
3. a kind of aircraft electric power system according to claim 1, it is characterised in that：One end of the back box is provided with insertion
Hole, the metal derby is embedded in the embedded hole.
4. a kind of aircraft electric power system according to claim 1, it is characterised in that：The upper lid passes through bolt and back box
Connection.
5. a kind of aircraft electric power system according to claim 1, it is characterised in that：If the bottom of the side plate is provided with
Dry projection, the side correspondence high spot of the supporting plate is provided with groove, and the described raised and groove coordinates.
6. a kind of aircraft electric power system according to claim 5, it is characterised in that：The supporting plate is bolted
In the bottom of side plate.
7. a kind of aircraft electric power system according to claim 1, it is characterised in that：The top of the crossbeam is provided with installation
Hole.
8. a kind of aircraft electric power system according to claim 1, it is characterised in that：The two ends of the crossbeam pass through bolt
It is connected with side plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621350042.9U CN206422102U (en) | 2016-12-09 | 2016-12-09 | A kind of aircraft electric power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621350042.9U CN206422102U (en) | 2016-12-09 | 2016-12-09 | A kind of aircraft electric power system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206422102U true CN206422102U (en) | 2017-08-18 |
Family
ID=59575098
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621350042.9U Expired - Fee Related CN206422102U (en) | 2016-12-09 | 2016-12-09 | A kind of aircraft electric power system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206422102U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109275319A (en) * | 2018-11-09 | 2019-01-25 | 易蕾 | A kind of unmanned electromechanical source mounting box of good heat dissipation effect |
-
2016
- 2016-12-09 CN CN201621350042.9U patent/CN206422102U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109275319A (en) * | 2018-11-09 | 2019-01-25 | 易蕾 | A kind of unmanned electromechanical source mounting box of good heat dissipation effect |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104979503B (en) | Battery pack and battery operating system | |
| CN106575724B (en) | Battery module with insulation moulding part | |
| CN206569262U (en) | A kind of UAS | |
| KR101977454B1 (en) | Battery Pack | |
| CN105070951B (en) | Rectangular lithium ion battery component capacitive equipment | |
| CN107732063A (en) | A kind of detachable battery module | |
| EP3014692A1 (en) | Detection mechanism | |
| CN206422102U (en) | A kind of aircraft electric power system | |
| CN105070948A (en) | Formatting and grading equipment for soft package lithium-ion batteries | |
| CN205900633U (en) | Power battery and car that has it | |
| KR101791427B1 (en) | Battery Pack Comprising Cap Plate Having Inducing Portion of Electrolyte On Inner Surface Thereof | |
| CN206945922U (en) | A kind of accumulator electric quantity detection apparatus | |
| KR100829737B1 (en) | Clip for contacting electrode of charge and discharge system of battery | |
| CN107706332A (en) | A kind of battery modules | |
| CN206441781U (en) | A kind of aircraft power supply | |
| CN203406338U (en) | Battery cover and power battery pack containing same | |
| CN105024022B (en) | A kind of laminar soft bag lithium ionic cell module and its battery pack | |
| CN206388797U (en) | A kind of lithium battery group | |
| CN206417204U (en) | A kind of aircraft power fixed mount | |
| CN207021315U (en) | A kind of lithium battery group installation positioner | |
| CN209282340U (en) | Single string of batteries charge and discharge device in a kind of pair of cylindrical lithium ion battery mould group | |
| CN209472027U (en) | A kind of electronic automobile-used combined moving power lead-acid accumulator | |
| CN209045699U (en) | Balanced externally charging typed electric car lithium-ion-power cell mould group | |
| CN207572496U (en) | Battery modules | |
| CN207731871U (en) | High-voltage DC contactor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20171219 Address after: 519090 Guangdong province Zhuhai city Zhuhai town of Red Bay area, Shuanghu road Xihua Road on the north side of Xinrong Industrial Zone No. 6 building three Room 305 Patentee after: Zhuhai Luban automation equipment Co., Ltd. Address before: 510800 Guangzhou, Huadu District, Guangdong Province Road, No. 1 Patentee before: Guangzhou College of South China University of Technology |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170818 Termination date: 20191209 |