CN114094266A - Modular aviation power battery system - Google Patents
Modular aviation power battery system Download PDFInfo
- Publication number
- CN114094266A CN114094266A CN202111471164.9A CN202111471164A CN114094266A CN 114094266 A CN114094266 A CN 114094266A CN 202111471164 A CN202111471164 A CN 202111471164A CN 114094266 A CN114094266 A CN 114094266A
- Authority
- CN
- China
- Prior art keywords
- layer
- modular
- power
- battery case
- battery system
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
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
- H01M50/244—Secondary casings; Racks; Suspension devices; Carrying devices; Holders characterised by their mounting method
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
- H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
- H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
- H01M10/486—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte for measuring temperature
-
- 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
- H01M50/233—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders characterised by physical properties of casings or racks, e.g. dimensions
- H01M50/24—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders characterised by physical properties of casings or racks, e.g. dimensions adapted for protecting batteries from their environment, e.g. from corrosion
-
- 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
- H01M50/249—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders specially adapted for aircraft or vehicles, e.g. cars or trains
-
- 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
- H01M50/271—Lids or covers for the racks or secondary casings
-
- 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
-
- 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
The invention relates to the technical field of aviation, in particular to a modular aviation power battery system. The technical scheme comprises the following steps: battery case, mounting panel and aircraft body, battery case's inside fixed mounting has the mounting panel, and the surface of mounting panel is provided with power module and collection module respectively, and the battery case surface mounting of mounting panel one end has the apron, and the fixed surface of apron installs the display screen. The output of the power module and the acquisition module of the invention adopts a quick-change connector mode, the weight of each module is controlled below 30kg, the installation and the replacement can be more convenient, and the whole system can realize two to more than ten power loops by adopting a serial or parallel mode, thereby realizing the functional redundancy and improving the safety performance, reducing the requirement of small modules on regular large-size space, realizing the installation in many flying places, completely meeting the requirement of zero fragmentation space of an aircraft and optimizing the use process.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a modular aviation power battery system.
Background
The aviation is a complex and strategic human activity, which refers to the flight activity of the aircraft in the earth atmosphere, and the aircraft engaged in the flight activity, also called aircraft, is divided into two types, namely lighter-than-air aircraft, such as balloon and airship, using air static buoyancy to lift, and heavier-than-air aircraft, such as airplane and helicopter, using aerodynamic to lift, and a power battery system is needed in the technical field of aviation.
Through retrieval, patent publication No. CN209183599U discloses an aviation power battery pack system, which includes a storage casing, the storage casing is a cylindrical structure, one end of the storage casing is closed, the other end of the storage casing is provided with an opening, an aviation power battery is arranged in the storage casing, the closed end of the storage casing is provided with a negative electrode triggering mechanism, the open end of the storage casing is sleeved with a casing cover, and the casing cover is provided with a positive electrode triggering mechanism.
The existing modular aviation power battery system has the following defects:
1. the existing modular aviation power battery system adopts an architecture mode which is similar to that of an automobile power battery system, and requires high power and high specific energy for the power system due to flight and load requirements, while the existing power batteries mostly adopt a high specific energy or high power mode, do not meet two types of power batteries simultaneously, are heavy in most cases, and are difficult to overhaul and maintain;
2. the existing modular aviation power battery system is large in size, large-size installation space cannot be found on an aircraft, the utilization rate of the space is greatly reduced, a power loop is single, redundancy is low, and safety performance is low.
Disclosure of Invention
The present invention is directed to a modular aero-power battery system that solves the problems set forth above in the background.
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a modular aviation power battery system, includes battery case, mounting panel and aircraft body, the inside of aircraft body all is provided with battery case, battery case's inside fixed mounting has the mounting panel, the surface of mounting panel is provided with power module and collection module respectively, the battery case surface mounting of mounting panel one end has the apron, the fixed surface of apron installs the display screen, battery case's periphery is provided with protective coating layer.
The device separates the function of the power battery system and realizes the function on different parts, firstly, the power distribution converging part is integrated with the power distribution part of the aircraft, only the power module and the acquisition module are reserved, the function is simplified, the voltage and the temperature of the device are acquired in real time through the acquisition module, the acquired data are displayed through a display screen, the observation by workers is facilitated, the charging control part is integrated with a charging cabinet or a battery replacing cabinet, the charging cabinet or the battery replacing cabinet can realize the functions of integral charging and single-cell charging, so that the power battery system can be separated from discharging and charging, the centralized battery charging maintenance is realized, the safety performance is improved, the device adopts a small module mode, the small module comprises the power module and the acquisition module, the output of the power module and the acquisition module adopts a quick-change connector mode, and the weight of each module is controlled below 30kg, the installation and the change that can be comparatively convenient to adopt series connection or parallelly connected mode, whole system can realize two ways to the power return circuit more than ten, realizes the function redundancy, improves the security performance, and the little module reduces regular jumbo size space requirement, can realize the installation in many places of flight, satisfies the requirement in zero fragmentation space of aircraft completely.
Preferably, an overhaul bolt is arranged between the cover plate and the battery shell, and the surface of the overhaul bolt is coated with an oxidation-resistant coating. The cover plate can be detached through the detaching overhaul bolt, so that workers can conveniently carry out dismounting and overhauling work, and the overhauling bolt can be prevented from rusting and damaging through the anti-oxidation coating.
Preferably, a nameplate is fixedly mounted on the surface of the other end of the battery shell, and a bolt is fixedly mounted between the nameplate and the battery shell. Can make things convenient for the staff to look over the model and the specification of device through the data plate, can install the data plate on battery case through the bolt, increase the stability of data plate.
Preferably, a buckle is installed on one side of the battery shell, and a clamping bolt is arranged inside the buckle. Can loosen the buckle through loosening the gim peg, make things convenient for the staff to dismantle battery case and carry out the work of dismouting maintenance.
Preferably, the surface of the other end of the battery shell is provided with heat dissipation holes, and dust screens are arranged inside the heat dissipation holes. The heat dissipation effect of the battery shell can be increased through the heat dissipation holes, and dust can be prevented from entering the battery shell through the heat dissipation holes through the dust screen.
Preferably, a first protective layer is arranged in the protective coating layer, and a waterproof layer is arranged in the first protective layer. The first protective layer can provide protection for the battery shell, and the waterproof layer can provide waterproof effect for the battery shell.
Preferably, a second protective layer is arranged inside the protective coating layer, and an anti-rust layer is arranged inside the second protective layer. The second protective layer can provide protection for the battery shell, and the antirust layer can provide antirust effect for the battery shell.
Preferably, the inside of protective paint layer is provided with the third protection layer, and the inside of third protection layer is provided with fire-retardant layer. The third protective layer can provide protection for the battery shell, and the flame-retardant layer can provide heat insulation and flame-retardant effects for the battery shell.
Preferably, a fourth protective layer is arranged inside the protective coating layer, and an insulating layer is arranged inside the fourth protective layer. Can provide the protection for battery case through the fourth inoxidizing coating, can provide insulating effect for battery case through the insulating layer, increase battery case's protective effect.
Compared with the prior art, the invention has the beneficial effects that:
1. through the surface at the mounting panel be provided with power module and collection module respectively, the fixed surface of apron installs the display screen, this device carries out the split to power battery system's function, realize on different parts, at first the distribution converges the part and is integrated with the distribution part of aircraft, only remain power module and collection module, the simplified function, carry out real-time acquisition to the voltage and the temperature of device through collection module, and show data collection through the display screen, make things convenient for the staff to observe, and it is integrated with the cabinet that charges or trade the battery box to charge the control part, the cabinet that charges or trade the battery box can realize wholly charge and the function that single electric core charges, thereby can realize that power battery system discharges and charges separately, and realize concentrated battery maintenance of charging, safety performance is improved, optimize the use process.
2. There is the mounting panel through the inside fixed mounting at battery case, the surface of mounting panel is provided with power module and collection module respectively, this device adopts little module mode, little module contains power module and collection module, and the output of power module and collection module adopts the quick change connector mode, every module weight control is below 30kg, installation and change that can be comparatively convenient, and adopt series connection or parallelly connected mode, entire system can realize two the way to the power return circuit more than ten ways, realize the function redundancy, improve the security performance, little module reduces regular jumbo size space requirement, can realize the installation in many places of flight, satisfy the zero requirement in fragmentation space of aircraft completely, optimize the use.
Drawings
FIG. 1 is a perspective view of the present invention;
FIG. 2 is a side view of the present invention;
FIG. 3 is a rear view of the present invention;
FIG. 4 is a schematic view of the internal structure of the present invention;
FIG. 5 is a front view of the present invention;
FIG. 6 is a schematic view of a partial structure of a protective coating layer according to the present invention;
fig. 7 is a schematic view of a partial structure of the aircraft body according to the invention.
In the figure: 1. a battery case; 2. an acquisition module; 3. mounting a plate; 4. a power module; 5. a cover plate; 6. a protective coating layer; 7. overhauling the bolt; 8. a display screen; 9. a nameplate; 10. a first protective layer; 1001. a waterproof layer; 11. a second protective layer; 1101. a rust-proof layer; 12. a third protection layer; 1201. a flame retardant layer; 13. a fourth protective layer; 1301. an insulating layer; 14. buckling; 15. heat dissipation holes; 16. an aircraft body.
Detailed Description
The technical solution of the present invention is further explained with reference to the accompanying drawings and specific embodiments.
Example one
As shown in fig. 1, 4, 5 and 7, the modular aviation power battery system provided by the invention comprises a battery shell 1, a mounting plate 3 and an aircraft body 16, wherein the battery shell 1 is arranged inside the aircraft body 16, the mounting plate 3 is fixedly arranged inside the battery shell 1, a power module 4 and an acquisition module 2 are respectively arranged on the surface of the mounting plate 3, a cover plate 5 is arranged on the surface of the battery shell 1 at one end of the mounting plate 3, a display screen 8 is fixedly arranged on the surface of the cover plate 5, a protective coating layer 6 is arranged on the periphery of the battery shell 1, an overhaul plug 7 is arranged between the cover plate 5 and the battery shell 1, the surface of the overhaul plug 7 is coated with an antioxidant coating, a buckle 14 is arranged on one side of the battery shell 1, and a clamping plug is arranged inside the buckle 14.
The working principle of the modular aviation power battery system based on the embodiment 1 is as follows: the device separates the function of the power battery system and realizes the function on different parts, firstly, the power distribution converging part is integrated with the power distribution part of the aircraft, only the power module 4 and the acquisition module 2 are reserved, the function is simplified, the voltage and the temperature of the device are acquired in real time through the acquisition module 2, the acquired data are displayed through the display screen 8, the observation by workers is facilitated, the charging control part is integrated with the charging cabinet or the battery replacing cabinet, the charging cabinet or the battery replacing cabinet can realize the functions of integral charging and single-cell charging, thereby realizing the separation of the discharging and the charging of the power battery system, realizing the charging maintenance of a centralized battery, improving the safety performance and optimizing the use process, in addition, the device adopts a small module mode, the small module comprises the power module 4 and the acquisition module 2, and the output of the power module 4 and the acquisition module 2 adopts a quick-change connector mode, every module weight control is below 30kg, installation and change that can be comparatively convenient, and adopt series connection or parallelly connected mode, entire system can realize two the way to the power return circuit more than ten ways, realize the function redundancy, the security performance is improved, little module is to regular jumbo size space requirement reduction, can realize the installation in many places of flight, satisfy the zero requirement in fragmentation space of aircraft completely, optimize the use process, can provide the protection for battery case 1 through protective coating layer 6, can dismantle apron 5 through dismantling maintenance bolt 7, make things convenient for the staff to carry out the work of dismouting maintenance, can avoid repairing bolt 7 to rust the damage through oxidation resistant coating, can loosen buckle 14 through loosening the bolt, make things convenient for the staff to dismantle battery case 1 and carry out the work of dismouting maintenance, optimize the use process.
Example two
As shown in fig. 2, 3 and 6, the present invention provides a modular aviation power battery system, compared to the first embodiment, the present embodiment further includes: fixed surface of the other end of battery case 1 installs data plate 9, and fixed mounting has the bolt between data plate 9 and the battery case 1, the surface of the other end of battery case 1 all is provided with louvre 15, and the inside of louvre 15 all is provided with the dust screen, the inside of protective coating layer 6 is provided with first inoxidizing coating 10, and the inside of first inoxidizing coating 10 is provided with waterproof layer 1001, the inside of protective coating layer 6 is provided with second inoxidizing coating 11, and the inside of second inoxidizing coating 11 is provided with antirust coat 1101, the inside of protective coating layer 6 is provided with third protective layer 12, and the inside of third protective layer 12 is provided with fire-retardant layer 1201, the inside of protective coating layer 6 is provided with fourth protective layer 13, and the inside of fourth protective layer 13 is provided with insulating layer 1301.
In this embodiment, the name plate 9 can facilitate the worker to check the model and specification of the device, the name plate 9 can be mounted on the battery case 1 through bolts, the stability of the name plate 9 is increased, the heat dissipation effect of the battery case 1 can be increased through the heat dissipation holes 15, the dust can be prevented from entering the battery case 1 through the heat dissipation holes 15 through the dust screen, the protection can be provided for the battery case 1 through the first protective layer 10, the waterproof effect can be provided for the battery case 1 through the waterproof layer 1001, the protection can be provided for the battery case 1 through the second protective layer 11, the antirust effect can be provided for the battery case 1 through the antirust layer 1101, the protection can be provided for the battery case 1 through the third protective layer 12, the heat insulation and flame retardation effects can be provided for the battery case 1 through the flame retardation layer 1201, the protection can be provided for the battery case 1 through the fourth protective layer 13, the insulation effect can be provided for the battery case 1 through the insulating layer 1301, the protective effect of the battery case 1 is increased.
The above embodiments are merely some preferred embodiments of the present invention, and those skilled in the art can make various alternative modifications and combinations of the above embodiments based on the technical solution of the present invention and the related teaching of the above embodiments.
Claims (9)
1. A modular aviation power battery system, includes battery case (1), mounting panel (3) and aircraft body (16), its characterized in that: the inside of aircraft body (16) all is provided with battery case (1), the inside fixed mounting of battery case (1) has mounting panel (3), the surface of mounting panel (3) is provided with power module (4) and collection module (2) respectively, battery case (1) surface mounting of mounting panel (3) one end has apron (5), the fixed surface of apron (5) installs display screen (8), the periphery of battery case (1) is provided with protective coating layer (6).
2. The modular aero-power battery system as claimed in claim 1, wherein: install between apron (5) and battery case (1) and overhaul bolt (7), and the surface coating of overhauing bolt (7) has anti-oxidant coating.
3. The modular aero-power battery system as claimed in claim 1, wherein: a nameplate (9) is fixedly arranged on the surface of the other end of the battery shell (1), and a bolt is fixedly arranged between the nameplate (9) and the battery shell (1).
4. The modular aero-power battery system as claimed in claim 1, wherein: a buckle (14) is installed on one side of the battery shell (1), and a clamping bolt is arranged inside the buckle (14).
5. The modular aero-power battery system as claimed in claim 1, wherein: the surface of the other end of the battery shell (1) is provided with heat dissipation holes (15), and dust screens are arranged inside the heat dissipation holes (15).
6. The modular aero-power battery system as claimed in claim 1, wherein: the interior of the protective coating layer (6) is provided with a first protective layer (10), and a waterproof layer (1001) is arranged in the first protective layer (10).
7. The modular aero-power battery system as claimed in claim 1, wherein: and a second protective layer (11) is arranged inside the protective coating layer (6), and an anti-rust layer (1101) is arranged inside the second protective layer (11).
8. The modular aero-power battery system as claimed in claim 1, wherein: the interior of the protective coating layer (6) is provided with a third protection layer (12), and the interior of the third protection layer (12) is provided with a flame-retardant layer (1201).
9. The modular aero-power battery system as claimed in claim 1, wherein: the interior of the protective coating layer (6) is provided with a fourth protective layer (13), and the interior of the fourth protective layer (13) is provided with an insulating layer (1301).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111471164.9A CN114094266A (en) | 2021-12-04 | 2021-12-04 | Modular aviation power battery system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111471164.9A CN114094266A (en) | 2021-12-04 | 2021-12-04 | Modular aviation power battery system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114094266A true CN114094266A (en) | 2022-02-25 |
Family
ID=80306446
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111471164.9A Pending CN114094266A (en) | 2021-12-04 | 2021-12-04 | Modular aviation power battery system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114094266A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115347336A (en) * | 2022-10-18 | 2022-11-15 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle distributed power battery |
-
2021
- 2021-12-04 CN CN202111471164.9A patent/CN114094266A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115347336A (en) * | 2022-10-18 | 2022-11-15 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle distributed power battery |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110032121A (en) | A kind of unmanned plane airport system | |
| CN114094266A (en) | Modular aviation power battery system | |
| CN208904083U (en) | A kind of box energy storage battery system of high integration | |
| WO2021077687A1 (en) | Modular standard battery box | |
| CN109148758A (en) | High-tension battery group and its assemble method | |
| CN216597822U (en) | Modular aviation power battery system | |
| CN112722289A (en) | Self-rotary wing aircraft combined with multi-shaft rotor wing | |
| CN203481666U (en) | Low-voltage distribution box with inner framework and outer shell separated from each other | |
| CN209471363U (en) | A kind of unmanned plane airport system | |
| CN203473249U (en) | Ground station system for unmanned helicopter safety routing inspection | |
| CN214138980U (en) | Self-rotary wing aircraft combined with multi-shaft rotor wing | |
| CN206558569U (en) | A kind of lithium battery module case | |
| CN211108019U (en) | Quick change power battery compartment of electric aircraft | |
| CN204822054U (en) | Unmanned aerial vehicle mounting disc | |
| WO2022177577A1 (en) | Modular electric powertrain conversion for aircraft | |
| CN211969424U (en) | Subway train lower box with convenient-to-overhaul inclined mounting plate | |
| CN220263066U (en) | Battery pack quick assembly and disassembly structure of eVTOL aircraft | |
| CN219658782U (en) | Centralized control type energy storage structure | |
| US20220177153A1 (en) | Conformal energy bay | |
| CN219134484U (en) | Fully modularized single-rotor helicopter with tail rotor | |
| CN219642913U (en) | Air-cooled energy storage module system of lithium ion battery | |
| US20190039714A1 (en) | Solar panel window assembly and method of forming the same | |
| CN211720096U (en) | Assembled transformer substation | |
| CN204263952U (en) | A kind of motor train unit accessory feed | |
| CN209258407U (en) | Electric power propulsion system |
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 |