CN115632467A - Civil aviation electrodynamic type bulk cargo loader energy supply device - Google Patents

Civil aviation electrodynamic type bulk cargo loader energy supply device Download PDF

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Publication number
CN115632467A
CN115632467A CN202211652185.5A CN202211652185A CN115632467A CN 115632467 A CN115632467 A CN 115632467A CN 202211652185 A CN202211652185 A CN 202211652185A CN 115632467 A CN115632467 A CN 115632467A
Authority
CN
China
Prior art keywords
groove
supply device
box body
energy supply
civil aviation
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.)
Granted
Application number
CN202211652185.5A
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Chinese (zh)
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CN115632467B (en
Inventor
马海兵
马琼琼
沈亮
马列
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Jiangsu Tianyi Aviation Industry Co Ltd
Original Assignee
Jiangsu Tianyi Aviation Industry Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Jiangsu Tianyi Aviation Industry Co Ltd filed Critical Jiangsu Tianyi Aviation Industry Co Ltd
Priority to CN202211652185.5A priority Critical patent/CN115632467B/en
Publication of CN115632467A publication Critical patent/CN115632467A/en
Application granted granted Critical
Publication of CN115632467B publication Critical patent/CN115632467B/en
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0042—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60R—VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR
    • B60R16/00—Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for
    • B60R16/02—Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric constitutive elements
    • B60R16/03—Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric constitutive elements for supply of electrical power to vehicle subsystems or for
    • B60R16/033—Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric constitutive elements for supply of electrical power to vehicle subsystems or for characterised by the use of electrical cells or batteries
    • 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
    • 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
    • H01M50/50—Current conducting connections for cells or batteries
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0042—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction
    • H02J7/0045—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction concerning the insertion or the connection of the batteries
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/10—Energy storage using batteries

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Power Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Connector Housings Or Holding Contact Members (AREA)
  • Battery Mounting, Suspending (AREA)

Abstract

The invention relates to the technical field of energy supply of loaders, and discloses an energy supply device of a civil aviation electric bulk cargo loader, which comprises a bearing component, wherein the bearing component comprises a box body and a sealing cover, the box body is hollow, the sealing cover is arranged at an opening of the box body, a heat radiation opening is arranged at one side of the box body, and a power supply component and a centralized control box are arranged in the box body; the power supply assembly is arranged in the box body and is provided with a frame and a battery, and the battery is embedded in the frame; the side wall of the box body is provided with a wiring end, the wiring end is connected with the centralized control box, and a sealing cover is arranged on the wiring end; the invention is convenient for installation and disassembly and management and replacement of single batteries.

Description

Civil aviation electrodynamic type bulk cargo loader energy supply device
Technical Field
The invention relates to the technical field of energy supply of loaders, in particular to an energy supply device of an electric bulk cargo loader for civil aviation.
Background
Current cargo loader energy supply device is difficult to all batteries unified management and change, and unified wiring mouth adopts and relies on frictional force plug-in connection, and is firm inadequately, has jolt the hidden danger that drops in the transportation, has the grafting structure of utilizing the screw-thread tightening now, but in the narrow and small space of vehicle bottom, threaded connection's mode need utilize the instrument, is not convenient for overhaul the operation.
Disclosure of Invention
This section is for the purpose of summarizing some aspects of embodiments of the invention and to briefly introduce some preferred embodiments, and in this section as well as in the abstract and the title of the invention of this application some simplifications or omissions may be made to avoid obscuring the purpose of this section, the abstract and the title of the invention, and such simplifications or omissions are not intended to limit the scope of the invention.
The present invention has been made keeping in mind the above problems occurring in the prior art and/or the problems occurring in the prior art.
Therefore, the invention aims to solve the technical problems that the wiring structure of the existing functional device has falling risks and is difficult to disassemble and assemble.
In order to solve the technical problems, the invention provides the following technical scheme: an energy supply device of a civil aviation electrodynamic type bulk cargo loader comprises,
the bearing assembly comprises a box body and a sealing cover, the box body is hollow, the sealing cover is arranged at an opening of the box body, a heat dissipation opening is formed in one side of the box body, and a power supply assembly and a centralized control box are arranged in the box body;
the power supply assembly is arranged in the box body and is provided with a frame and a battery, and the battery is embedded in the frame;
the side wall of the box body is provided with a wiring end, the wiring end is connected with the centralized control box, and a sealing cover is arranged on the wiring end.
As a preferable aspect of the civil aviation electric bulk cargo loader energy supply device of the present invention, the following features: the frame is provided with a first groove and a second groove, the battery is arranged in the first groove, the second groove is provided with a transfer piece, and the transfer piece is connected with the battery and the centralized control box.
As a preferable aspect of the civil aviation electric bulk cargo loader energy supply device of the present invention, the following features: the wiring end comprises an outer frame plate and an inner groove, wherein a conductive column is arranged in the inner groove, and the conductive column is electrically connected with the centralized control box.
As a preferable aspect of the civil aviation electric bulk cargo loader power supply device of the present invention, wherein: the plug comprises an end plate and an end column, wherein a conductive groove is formed in the end column, a lead is arranged on one side of the end plate, and the conductive groove is electrically conducted with the lead.
As a preferable aspect of the civil aviation electric bulk cargo loader energy supply device of the present invention, the following features: the end post lateral wall is provided with side slot and kerve, the kerve set up in the side slot bottom.
As a preferable aspect of the civil aviation electric bulk cargo loader energy supply device of the present invention, the following features: a clamping block is arranged in the side groove, and a first inclined plane is arranged at one end of the clamping block.
As a preferable aspect of the civil aviation electric bulk cargo loader energy supply device of the present invention, the following features: the other end of the clamping block is provided with a limiting plate, the limiting plate is embedded in the bottom groove, and a first spring is arranged on the limiting plate and connected with the bottom of the bottom groove.
As a preferable aspect of the civil aviation electric bulk cargo loader energy supply device of the present invention, the following features: the inside groove lateral wall is provided with the draw-in groove, the outer deckle board is provided with the slot from the outside, the slot through run through the groove with the draw-in groove intercommunication.
As a preferable aspect of the civil aviation electric bulk cargo loader power supply device of the present invention, wherein: the detachable part comprises an inserting rod and a pushing block arranged at the end part of the inserting rod, the inserting rod is arranged in the inserting groove, and the pushing block is arranged in the through groove;
and a second inclined plane is arranged on the push block.
As a preferable aspect of the civil aviation electric bulk cargo loader energy supply device of the present invention, the following features: the end part of the inserted bar is provided with a push plate, and the push plate is connected with the outer frame plate through a second spring.
The invention has the beneficial effects that: the invention is convenient for installation and disassembly and management and replacement of single batteries.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise. Wherein:
fig. 1 is a schematic overall structure diagram of an energy supply device of an electric civil aviation bulk cargo loader according to an embodiment of the invention;
fig. 2 is a schematic structural view of a frame in the power supply device of the civil aviation electric bulk cargo loader according to an embodiment of the present invention;
fig. 3 is a schematic structural view of a terminal and a plug in the power supply device of the civil aviation electric bulk cargo loader according to the embodiment of the invention;
fig. 4 is a schematic structural view of a disassembly part of the power supply device of the civil aviation electric bulk cargo loader according to an embodiment of the invention.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways than those specifically described and will be readily apparent to those of ordinary skill in the art without departing from the spirit of the present invention, and therefore the present invention is not limited to the specific embodiments disclosed below.
Next, the present invention will be described in detail with reference to the drawings, wherein the cross-sectional views illustrating the structure of the device are not enlarged partially according to the general scale for convenience of illustration when describing the embodiments of the present invention, and the drawings are only examples, which should not limit the scope of the present invention. In addition, the three-dimensional dimensions of length, width and depth should be included in the actual fabrication.
Further, reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one implementation of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments.
Example 1
Referring to fig. 1 to 4, the embodiment provides an energy supply device for an electric bulk cargo loader for civil aviation, which includes a bearing assembly 100, wherein the bearing assembly 100 includes a box body 101 and a cover 102, the box body 101 is hollow, the cover 102 is arranged at an opening of the box body 101, a heat dissipation opening 103 is arranged at one side of the box body 101, and a power supply assembly 200 and a centralized control box 104 are arranged in the box body 101; the power supply assembly 200 is arranged in the box body 101, and is provided with a frame 201 and a battery 202, wherein the battery 202 is embedded in the frame 201; the side wall of the box body 101 is provided with a terminal 300, the terminal 300 is connected with the centralized control box 104, and a sealing cover is arranged on the terminal 300.
Further, a first groove 201a and a second groove 201b are formed in the frame 201, the battery 202 is disposed in the first groove 201a, and a relay member 201c is disposed in the second groove 201b, and the relay member 201c connects the battery 202 and the centralized control box 104.
In this embodiment, the bearing assembly 100 is a casing for placing and protecting the battery, and is used for integrating the battery into a whole and managing the battery in a unified manner, and a component for detecting and adjusting the temperature can be arranged in the bearing assembly for managing the internal temperature thereof, which is the prior art and is not described again, the frame 201 is arranged in the box 101 for placing the battery 202 and the transfer piece 201c, so as to maintain the distance between the batteries 202 and the fixed connection between the transfer piece 201c, the transfer piece 201c is fixedly arranged in the second groove 201b for connecting the battery 202 and the centralized control box 104, so that the single battery is convenient to replace, and the lead is arranged in the second groove 201b in a penetrating manner, and the battery replacement is not affected.
Further, a contact is arranged on the relay member 201c and connected with the positive electrode and the negative electrode of the battery 202, and a switch is arranged in the relay member 201c and used for connecting the battery 202 and the centralized control box 104.
The terminal 300 includes an outer frame plate 301 and an inner groove 302, wherein a conductive pillar 303 is disposed in the inner groove 302, and the conductive pillar 303 is electrically connected to the centralized control box 104.
It should be noted that the terminal 300 is disposed outside the case 101, and is mainly used for outputting electric power.
Further, the plug 400 is further included, the plug 400 includes an end plate 401 and an end post 402, a conductive groove 403 is disposed in the end post 402, a conductive wire 404 is disposed on one side of the end plate 401, and the conductive groove 403 is electrically connected to the conductive wire 404.
Further, the outer side wall of the end post 402 is provided with a side groove 402a and a bottom groove 402b, and the bottom groove 402b is arranged at the bottom of the side groove 402 a; a clamping block 405 is arranged in the side groove 402a, and a first inclined surface 405a is arranged at one end of the clamping block 405; the other end of the clamping block 405 is provided with a limiting plate 405b, the limiting plate 405b is embedded in the bottom groove 402b, and the limiting plate 405b is provided with a first spring 405c connected with the bottom of the bottom groove 402 b.
It should be noted that the size of the bottom groove 402b is larger than that of the side groove 402a for preventing the latch 405 from falling off, and specifically, the first spring 405c tends to make the latch 405 protrude out of the side groove 402a, and the latch 405 is pressed to enter the bottom groove 402b, and after the external force is removed, the latch 405 is returned by the first spring 405 c.
Plug 400 is used for with wiring end 300 plug connection, and both carry out the block through fixture block 405 and fix, have avoided the risk that drops, compare the mounting means in screw fastening simultaneously and be convenient for install, be applicable to narrow and small space.
Furthermore, the end plate 401 is used for limiting and is convenient for controlling the plug 400 to perform plugging operation, the end post 402 is inserted into the inner groove 302, the conductive post 303 is inserted into the conductive groove 403 to realize electrical conduction, the end post 402 is correspondingly inserted into the inner groove 302 during installation, the fixture block 405 is extruded into the bottom groove 402b due to the arrangement of the first inclined surface 405a in the process of installing the fixture block 405, and the first spring 405c ejects the fixture block 405 into the clamping groove 302a to complete installation when the position of the side groove 402a corresponds to the clamping groove 302a.
Further, a locking groove 302a is provided on a side wall of the inner groove 302, and a slot 301a is provided on the outer frame plate 301 from the outside, and the slot 301a communicates with the locking groove 302a through slot 301 b.
Note that the through groove 301b communicates with the inner groove 302.
Further, the dismounting device 304 is further included, the dismounting device 304 comprises an inserting rod 304a and a pushing block 304b arranged at the end part of the inserting rod 304a, the inserting rod 304a is arranged in the inserting groove 301a, and the pushing block 304b is arranged in the penetrating groove 301 b; the pushing block 304b is provided with a second inclined surface 304c.
The end of the insertion rod 304a is provided with a push plate 304d, and the push plate 304d is connected with the outer frame plate 301 through a second spring 304 e.
It should be noted that, in the detachment process of the present invention, the pushing plate 304d is pressed, the second inclined surface 304c on the pushing block 304b faces the latch 405, the second inclined surface 304c contacts the latch 405 and pushes the latch 405 to compress the first spring 405c to move, and specifically, one side surface of the pushing block 304b corresponds to one side surface of the inner groove 302, so as to push the latch 405 out of the latch groove 302a after the second inclined surface 304c is pushed in.
Preferably, the latch 405 has a third inclined surface facing the push plate 304d to facilitate the pushing of the push block 304 b.
It is important to note that the construction and arrangement of the present application as shown in the various exemplary embodiments is illustrative only. Although only a few embodiments have been described in detail in this disclosure, those skilled in the art who review this disclosure will readily appreciate that many modifications are possible (e.g., variations in sizes, dimensions, structures, shapes and proportions of the various elements, values of parameters (e.g., temperatures, pressures, etc.), mounting arrangements, use of materials, colors, orientations, etc.) without materially departing from the novel teachings and advantages of the subject matter recited in this application. For example, elements shown as integrally formed may be constructed of multiple parts or elements, the position of elements may be reversed or otherwise varied, and the nature or number of discrete elements or positions may be altered or varied. Accordingly, all such modifications are intended to be included within the scope of this invention. The order or sequence of any process or method steps may be varied or re-sequenced according to alternative embodiments. In the claims, any means-plus-function clause is intended to cover the structures described herein as performing the recited function and not only structural equivalents but also equivalent structures. Other substitutions, modifications, changes and omissions may be made in the design, operating conditions and arrangement of the exemplary embodiments without departing from the scope of the present inventions. Therefore, the present invention is not limited to a particular embodiment, but extends to various modifications that nevertheless fall within the scope of the appended claims.
Moreover, in an effort to provide a concise description of the exemplary embodiments, all features of an actual implementation may not be described (i.e., those unrelated to the presently contemplated best mode of carrying out the invention, or those unrelated to enabling the invention).
It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions may be made. Such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure, without undue experimentation.
It should be noted that the above-mentioned embodiments are only for illustrating the technical solutions of the present invention and not for limiting, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, which should be covered by the claims of the present invention.

Claims (10)

1. The utility model provides a civil aviation electrodynamic type bulk cargo loader energy supply device which characterized in that: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
the bearing assembly (100) comprises a box body (101) and a cover (102), the box body (101) is hollow, the cover (102) is arranged at an opening of the box body (101), a heat dissipation opening (103) is arranged on one side of the box body (101), and a power supply assembly (200) and a centralized control box (104) are arranged in the box body (101);
the power supply assembly (200) is arranged in the box body (101), a frame (201) and a battery (202) are arranged in the box body (101), and the battery (202) is embedded in the frame (201);
the side wall of the box body (101) is provided with a wiring terminal (300), the wiring terminal (300) is connected with the centralized control box (104), and a sealing cover is arranged on the wiring terminal (300).
2. Civil aviation electrodynamic bulk loader power supply device according to claim 1, characterized in that: a first groove (201 a) and a second groove (201 b) are formed in the frame (201), the battery (202) is arranged in the first groove (201 a), a transfer piece (201 c) is arranged in the second groove (201 b), and the transfer piece (201 c) is connected with the battery (202) and the centralized control box (104).
3. The electrodynamic civil aviation bulk loader energy supply device of claim 2, wherein: the terminal (300) comprises an outer frame plate (301) and an inner groove (302), wherein a conductive column (303) is arranged in the inner groove (302), and the conductive column (303) is electrically connected with the centralized control box (104).
4. Civil aviation electrodynamic bulk loader energy supply device according to claim 3, characterized in that: the connector comprises an end plate (401) and an end column (402), wherein the end column (402) is provided with a conductive groove (403), one side of the end plate (401) is provided with a lead (404), and the conductive groove (403) is electrically conducted with the lead (404).
5. Civil aviation electrodynamic bulk loader energy supply device according to claim 4, characterized in that: the outer side wall of the end post (402) is provided with a side groove (402 a) and a bottom groove (402 b), and the bottom groove (402 b) is arranged at the bottom of the side groove (402 a).
6. Civil aviation electrodynamic bulk loader energy supply device according to claim 5, characterized in that: a clamping block (405) is arranged in the side groove (402 a), and a first inclined surface (405 a) is arranged at one end of the clamping block (405).
7. Civil aviation electrodynamic bulk loader energy supply device according to claim 6, characterized in that: the other end of the clamping block (405) is provided with a limiting plate (405 b), the limiting plate (405 b) is embedded in the bottom groove (402 b), and a first spring (405 c) is arranged on the limiting plate (405 b) and connected with the bottom of the bottom groove (402 b).
8. Civil aviation electrodynamic bulk loader energy supply device according to claim 7, characterized in that: the side wall of the inner groove (302) is provided with a clamping groove (302 a), the outer frame plate (301) is provided with a slot (301 a) from the outer side, and the slot (301 a) is communicated with the clamping groove (302 a) through a penetrating groove (301 b).
9. Civil aviation electrodynamic bulk loader energy supply device according to claim 8, characterized in that: the dismounting part (304) comprises an inserting rod (304 a) and a pushing block (304 b) arranged at the end part of the inserting rod (304 a), the inserting rod (304 a) is arranged in the inserting groove (301 a), and the pushing block (304 b) is arranged in the through groove (301 b);
the push block (304 b) is provided with a second inclined surface (304 c).
10. Civil aviation electrodynamic bulk loader energy supply device according to claim 9, characterized in that: the end part of the inserted link (304 a) is provided with a push plate (304 d), and the push plate (304 d) is connected with the outer frame plate (301) through a second spring (304 e).
CN202211652185.5A 2022-12-22 2022-12-22 Civil aviation electrodynamic type bulk cargo loader energy supply device Active CN115632467B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211652185.5A CN115632467B (en) 2022-12-22 2022-12-22 Civil aviation electrodynamic type bulk cargo loader energy supply device

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Application Number Priority Date Filing Date Title
CN202211652185.5A CN115632467B (en) 2022-12-22 2022-12-22 Civil aviation electrodynamic type bulk cargo loader energy supply device

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CN115632467A true CN115632467A (en) 2023-01-20
CN115632467B CN115632467B (en) 2023-04-07

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106965761A (en) * 2016-01-13 2017-07-21 厦门雅迅网络股份有限公司 A kind of mobile unit system cut-off protection device
CN111834818A (en) * 2020-08-01 2020-10-27 曾缤 High stability wire harness connector
CN112820999A (en) * 2021-01-22 2021-05-18 姜婷婷 New forms of energy electric automobile lithium cell box assembly

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106965761A (en) * 2016-01-13 2017-07-21 厦门雅迅网络股份有限公司 A kind of mobile unit system cut-off protection device
CN111834818A (en) * 2020-08-01 2020-10-27 曾缤 High stability wire harness connector
CN112820999A (en) * 2021-01-22 2021-05-18 姜婷婷 New forms of energy electric automobile lithium cell box assembly

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Application publication date: 20230120

Assignee: Jiangsu Tianyi Airport Equipment Maintenance Service Co.,Ltd.

Assignor: Jiangsu Tianyi Aviation Industry Co.,Ltd.

Contract record no.: X2023980044219

Denomination of invention: An energy supply device for a civil aviation electric bulk cargo loader

Granted publication date: 20230407

License type: Common License

Record date: 20231024