CN221438363U - Battery box assembly and aircraft - Google Patents
Battery box assembly and aircraft Download PDFInfo
- Publication number
- CN221438363U CN221438363U CN202323231057.6U CN202323231057U CN221438363U CN 221438363 U CN221438363 U CN 221438363U CN 202323231057 U CN202323231057 U CN 202323231057U CN 221438363 U CN221438363 U CN 221438363U
- Authority
- CN
- China
- Prior art keywords
- battery box
- battery
- hanging frame
- aircraft
- assembly
- 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
- 238000009434 installation Methods 0.000 claims abstract description 31
- 230000005484 gravity Effects 0.000 claims description 12
- 238000000429 assembly Methods 0.000 description 4
- 230000000712 assembly Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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 application provides a battery box assembly, which is characterized in that the battery box assembly is applied to an aircraft and comprises: the battery box hanging frame is provided with a detachable battery box, and a battery is arranged in the battery box; the battery box hanging frame comprises a bottom plate and a plurality of first installation components and second installation components which are arranged on the bottom plate; the battery box hanging frame is connected to the aircraft through a first mounting assembly; a third installation component matched with the second installation component is arranged at the top of the battery box; the battery box is connected with the battery box hanging frame through the second installation component and the third installation component. Through the detachable battery box structure on the battery box stores pylon, realize according to the nimble quantity of adjusting the installation battery of specific flight task, reduce the load loss that unnecessary battery brought to the maximize, further optimize the work efficiency of aircraft.
Description
Technical Field
The utility model relates to the field of aircrafts, in particular to a battery box assembly and an aircraft.
Background
As aircraft have evolved, the fuselage of aircraft has been designed to be smaller and smaller in order to reduce the flight drag experienced during flight. In order for an aircraft to normally execute a flight mission, the flight efficiency is improved, and a sufficient energy source is required to be provided for the aircraft.
The batteries currently used to power aircraft are placed in the aircraft fuselage and are typically mounted in a fixed installation in the aircraft fuselage, further resulting in difficult handling when the batteries are removed. In addition, there are also some battery modules for aircraft which are designed to accommodate more flight tasks, choosing as many batteries as possible, which results in a battery pack weight that may be up to 30% or more of the fuselage dead weight; however, not all of the electricity is needed to perform each flight mission; this design therefore results in the majority of cases in the aircraft being flown with redundant batteries, further resulting in energy waste and affecting the flight performance of the aircraft.
There is a need for a battery case assembly that can flexibly mount batteries to solve the above-described problems.
Disclosure of utility model
In view of the foregoing, it is desirable to provide a battery pack assembly and an aircraft.
In a first aspect, the present utility model provides a battery compartment assembly for use in an aircraft, the battery compartment assembly comprising:
The battery box hanging frame is provided with a detachable battery box, and a battery is arranged in the battery box;
the battery box hanging frame comprises a bottom plate and a plurality of first installation components and second installation components which are arranged on the bottom plate;
The battery box hanger is connected to the aircraft through the first mounting assembly;
A third mounting assembly matched with the second mounting assembly is arranged at the top of the battery box;
the battery box is connected with the battery box hanging frame through the second installation component and the third installation component.
In some embodiments, the battery compartment assembly further comprises a baffle;
The second mounting assembly comprises a plurality of connecting blocks arranged on the bottom plate;
the baffle detachably with the connecting block is connected, just baffle and connecting block parallel arrangement.
In some embodiments, the baffle is connected to the connection block by a mortise and tenon structure;
And/or the number of the groups of groups,
The baffle is connected with the connecting block through a bolt structure.
In some embodiments, the second mounting assemblies are arranged on the base plate at a preset pitch and the preset pitch matches the width of the battery case; a step of
The third installation component comprises raised strips arranged on the left side and the right side of the top of the battery box;
Grooves are formed in two sides of the connecting block;
The battery box is connected with the battery box hanging frame through the convex strips and the grooves.
In some embodiments, the second mounting assembly includes a plurality of first stop blocks disposed at an edge of the base plate, the first stop blocks disposed between two adjacent connection blocks;
the third mounting assembly comprises second limiting blocks arranged at the front end and the rear end of the top of the battery box;
The battery box is connected with the battery box hanging frame through the first limiting block and the second limiting block.
In some embodiments, the first mounting assembly includes a third stopper disposed at an edge of the battery compartment hanger;
the battery box hanging frame is connected with the aircraft through the third limiting block.
In some embodiments, the battery case is provided with one or more openings on four sides and at the bottom;
One or more openings are arranged on the baffle plate.
In some embodiments, the number of installations of the battery compartment is an even number;
The battery box is symmetrically arranged on the battery box hanging frame by taking the center of the battery box hanging frame as a datum line.
In some embodiments, the number of installations of the battery compartment is an odd number;
The battery box is arranged at the center of the battery box hanging frame, and the battery box hanging frame is symmetrically arranged on the battery box hanging frame by taking the center of the battery box hanging frame as a datum line.
In a second aspect, the present utility model provides an aircraft comprising a fuselage, further comprising a battery compartment assembly as described above removably mounted to the bottom of the fuselage; and
The longitudinal axis where the center of gravity of the battery box hanging frame is located coincides with the longitudinal axis where the center of gravity of the aircraft is located.
The beneficial effects achieved by the utility model are as follows: the number of installed batteries is flexibly adjusted according to specific flight tasks through a detachable battery box structure on the battery box hanging frame, so that the load loss caused by redundant batteries is reduced to the maximum extent, and the working efficiency of the aircraft is further optimized; in addition, the detachable battery box structure is more convenient to maintain, and the battery can be directly replaced under the condition of the shortage of charging time so as to meet the requirements of flight tasks; furthermore, the battery box structure with the holes disclosed by the utility model is used for radiating heat for the working battery, so that dangerous situations possibly caused by overheat of the battery are avoided; in addition, the battery box is reinforced by the detachable baffles, the detachable baffles are arranged according to the number of the battery boxes while shaking is prevented, and the load pressure of the aircraft is reduced to the maximum degree so as to further increase the load capacity of the aircraft.
Drawings
For a clearer description of the technical solutions of the embodiments of the present utility model, the drawings that are needed in the description of the embodiments will be briefly introduced below, it being obvious that the drawings in the description below are only some embodiments of the present utility model, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art, wherein:
Fig. 1 is a schematic view of a battery case assembly according to an embodiment of the present utility model;
Fig. 2 is a schematic view of a battery case according to an embodiment of the present utility model;
Fig. 3 is a schematic view of a baffle according to an embodiment of the present utility model.
Description of the specification reference numerals:
100. A battery box hanger; 200. a battery case; 300. a baffle; 110. a bottom plate; 120. a first mounting assembly; 130. a second mounting assembly; 131. a connecting block; 132. a first limiting block; 210. a third mounting assembly; 211. a convex strip; 212. a second limiting block; 310. a first connection portion; 320. a second connecting portion; 330. a main body.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are only some embodiments of the present utility model, not all embodiments of the present utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
It should be understood that throughout this specification and the claims, unless the context clearly requires otherwise, the words "comprise", "comprising", and the like, are to be construed in an inclusive sense as opposed to an exclusive or exhaustive sense; that is, it is the meaning of "including but not limited to".
It should also be appreciated that the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Furthermore, in the description of the present utility model, unless otherwise indicated, the meaning of "a plurality" is two or more.
It should be noted that the terms "S1", "S2", and the like are used for the purpose of describing the steps only, and are not intended to be construed to be specific as to the order or sequence of steps, nor are they intended to limit the present utility model, which is merely used to facilitate the description of the method of the present utility model, and are not to be construed as indicating the sequence of steps. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present utility model.
As described in the background, since the batteries mounted on an aircraft are typically mounted in a fixed manner, the batteries cannot be easily removed; in order to consider more flight tasks, the scheme with the largest number of batteries is usually selected as much as possible during design; thereby causing a problem of heavy load.
The embodiment provides a battery case assembly detachably mounted on an aircraft, as shown in fig. 1, the battery case assembly includes:
the battery box hanging frame 100, a detachable battery box 200 is arranged on the battery box hanging frame 100, and a battery is arranged in the battery box 200;
The battery case hanger 100 includes a base plate 110, and a plurality of first and second mounting assemblies 120 and 130 disposed on the base plate 110;
The battery compartment pylon 100 is connected to the aircraft by a first mounting assembly 120;
The top of the battery case is provided with a third mounting assembly 210 matched with the second mounting assembly 130;
the battery case is coupled to the battery case hanger 100 through the second mounting assembly 130 and the third mounting assembly 210.
Specifically, the battery box assembly provided by the utility model is detachably mounted at the bottom of the aircraft through the first mounting assembly 120, and the power supply of the aircraft by using the battery mounted in the battery box 200 through the designed PCB is realized.
In one embodiment, the first mounting assembly 120 includes a third stopper disposed at an edge of the battery compartment hanger 100; the battery box hanger 100 is connected with the aircraft through a third limiting block. Specifically, a threaded hole or a through hole is formed in the third limiting block, a threaded hole corresponding to the threaded hole in the third limiting block in position is formed in the bottom of the aircraft, and the third limiting block is connected with the aircraft through a bolt. The four sides of the bottom plate 110 are all provided with third limiting blocks, and specific positions are not limited, and only need to be distinguished from the first limiting blocks 132, and the number of the third limiting blocks can be set according to the edge length of the bottom plate 110.
In one embodiment, to reduce the impact of the battery box hanger 100 on the aircraft, the longitudinal axis of the center of gravity of the battery box hanger 100 coincides with the longitudinal axis of the center of gravity of the aircraft. Specifically, firstly, determining the position of the center of gravity of the aircraft, projecting the center of gravity of the aircraft at the bottom, and determining the position of a first projection point; determining the position of the center of gravity of the battery box hanger 100, projecting the same on the upper surface, and determining the position of a second projection point; when the device is installed, the first projection point and the second projection point are overlapped, and the longitudinal axes of the first projection point and the second projection point are parallel. Therefore, the center of gravity of the aircraft can be finely adjusted only in the upper and lower positions, and can not be changed in the front, rear, left and right directions, and the aircraft is still in a balanced state after the battery box hanger 100 is installed, so that the control of the aircraft is facilitated.
In one embodiment, the second mounting assemblies 130 are arranged at a preset interval on the base plate 110 and the preset interval is matched with the width of the battery case 200, and as shown in fig. 2, the third mounting assemblies 210 include protrusions 211 provided at the left and right sides of the top of the battery case 200; grooves are formed on two sides of the connecting block 131; the battery case 200 is connected with the battery case hanger 100 through the convex strips 211 and the grooves; specifically, the corresponding protruding strips 211 of the battery case 200 are slid onto the bottom plate 110 of the battery case hanger 100 along the sliding grooves to realize the mounting of the battery case 200 on the battery case hanger 100.
In one embodiment, the second mounting assembly 130 includes a plurality of first stoppers 132 disposed at an edge of the base plate 110, the first stoppers 132 being disposed between two adjacent connection blocks 131; the third mounting assembly 210 includes second stoppers 212 provided at the front and rear ends of the top of the battery case 200; the battery case 200 is connected with the battery case hanger 100 through the first stopper 132 and the second stopper 212. In a specific implementation process, the first limiting block 132 and the second limiting block 212 may be connected by a mortise and tenon structure and/or a bolt structure; when the first limiting block 132 is connected with the second limiting block 212 through a mortise and tenon structure, a mortise and tenon structure is arranged on the first limiting block 132, and a mortise and tenon structure is arranged at a corresponding position on the second limiting block 212; or the first limiting block 132 is provided with a mortise-tenon structure, and the second limiting block 212 is provided with a tenon-tenon structure at a corresponding position, so that the first limiting block 132 is connected with the second limiting block 212 through the mortise-tenon structure, and the battery box 200 is further fixed on the battery box hanging frame 100. When the first limiting block 132 is connected with the second limiting block 212 through a bolt structure, a threaded hole is formed in a corresponding position on the first limiting block 132, a threaded hole or a through hole is formed in the second limiting block 212, after the threaded hole on the first limiting block 132 is overlapped with the threaded hole or the through hole on the second limiting block 212, the first limiting block 132 is connected with the second limiting block through a bolt, and the battery box 200 is further fixed to the battery box hanger 100.
It can be appreciated that, in order to improve the stability of the battery case 200 mounted on the battery case hanger 100, the battery case 200 may be further fixed by combining the connection manner of the first stopper 132 and the second stopper 212 on the basis that the battery case 200 is connected with the battery case hanger 100 through the raised line 211 and the groove. In this case, the function of the stopper is to make the connection between the battery case 200 and the battery case hanger 100 more firm, and the reinforcement function can be achieved when the number of stoppers provided on the battery case hanger 100 and the number of stoppers provided on the top of the battery case 200 are set to one, respectively, but may be set to two for better reinforcement effect.
In one embodiment, the battery compartment assembly further includes a baffle 300; the second mounting assembly 130 includes a plurality of connection blocks 131 disposed on the base plate 110; the baffle 300 is detachably connected with the connection block 131, and the baffle 300 is disposed in parallel with the connection block 131. Specifically, the baffle 300 is connected with the connecting block 131 through a mortise and tenon structure; and/or, the baffle 300 is connected with the connection block 131 by a bolt structure. Specifically, as shown in fig. 3, the baffle 300 is integrally formed and includes a main body, a first connecting portion 310 and a second connecting portion 320. It is to be understood that the present utility model is not limited to the shape of the main body portion, the first connecting portion 310 and the second connecting portion 320, and may be as shown in the figure, or may be in other shapes such as triangle.
When the baffle 300 is connected with the connecting block 131 through the mortise and tenon structure, the first connecting part 310 and the second connecting part 320 are provided with mortise and tenon structures, and the corresponding positions of the connecting block 131 are provided with mortise and tenon structures; or the first connecting part 310 and the second connecting part 320 are provided with mortise-shaped structures, and the corresponding positions on the connecting blocks 131 are provided with tenon-shaped structures so as to realize that the baffle 300 is connected with the connecting blocks 131 through the mortise-tenon structures, and further the baffle 300 is installed on the battery box hanger 100. When the baffle 300 is connected with the connection block 131 through the bolt structure, a threaded hole or a through hole is formed in the first connection portion 310 and the second connection portion 320, a threaded hole is formed in a corresponding position on the connection block 131, and after the threaded hole on the connection block 131 is overlapped with the threaded holes or the through holes on the first connection portion 310 and the second connection portion 320, the baffle 300 is fixed to the connection block 131 through bolts.
In the embodiment, the number of the baffles 300 is determined by the number of the cartridges 200 mounted on the cartridge hanger 100, and one cartridge 200 requires two baffles 300, specifically, one cartridge 200 requires the baffles 300 to be mounted at the connection blocks 131 at both sides of the cartridge 200, and the baffles 300 are disposed parallel to the connection blocks 131. The baffles 300 are arranged at the two sides of the battery box 200, so that the battery box 200 is further fixed, and shaking is avoided; only the fixing of the baffles 300 on both sides of each battery case 200 is ensured, and the rest of the baffles 300 which are not used can be removed to reduce the total weight, thereby further reducing the load pressure of the aircraft.
In one embodiment, the battery case 200 is provided with one or more openings on four sides and at the bottom; the baffle 300 is provided with one or more openings. So that the air flow generated during flying is used for cooling the battery, the battery is ensured not to overheat and generate danger, and meanwhile, the load weight is reduced through the opening. It will be appreciated that the openings may be square, circular, triangular, etc. in any shape.
In a specific implementation process, when the number of the batteries to be mounted is determined, a corresponding number of battery cartridges 200 need to be mounted on the battery cartridge hanger 100; at this time, the battery case 200 is mounted to the battery case hanger 100 according to the corresponding second mounting assembly 130 at the determined mounting position and the third mounting assembly 210 at the battery case hanger 100. The flexible installation of the battery is further realized, only the battery meeting the requirements is installed, and the load pressure of the aircraft is reduced while the flight performance is ensured.
In one embodiment, when it is determined that the number of battery cartridges 200 to be mounted is an even number, the battery cartridges 200 are symmetrically disposed on the battery cartridge hanger 100 with the center of the battery cartridge hanger 100 as a reference line. Specifically, the battery case 200 may be symmetrically mounted on the battery case hanger 100 in a direction away from the reference line; the battery case 200 may be symmetrically mounted to the battery case hanger 100 in a direction approaching the reference line. Preferably, in order to ensure the heat dissipation effect of the battery, the interval installation is performed at the time of installation, and the specific interval is not limited in this embodiment.
In one embodiment, when it is determined that the number of battery cartridges 200 to be mounted is an odd number, after one battery cartridge 200 is mounted at the center of the battery cartridge hanger 100, the battery cartridges 200 are symmetrically disposed on the battery cartridge hanger 100 with the center of the battery cartridge hanger 100 as a reference line. Specifically, the battery case 200 may be symmetrically mounted on the battery case hanger 100 in a direction away from the reference line; the battery case 200 may be symmetrically mounted to the battery case hanger 100 in a direction approaching the reference line. Preferably, in order to ensure the heat dissipation effect of the battery, the interval installation is performed at the time of installation, and the specific interval is not limited in this embodiment. When the number of the battery cases 200 to be mounted is 1, only the battery and the hanger are required to be mounted at the center.
The installation number is given by a battery allocation algorithm of the ground station, and specifically, the installation number of the battery boxes 200 is determined according to the current flight scene factors and a preset electric quantity correlation table; wherein the current flight scenario factors include flight weight, current wind speed, estimated altitude, current ambient temperature, and estimated speed of flight; the preset electric quantity association table comprises actual flight scene factors obtained through testing, corresponding electric quantity consumption values under different actual flight scene factors and association relations thereof. In a specific test, different factors are arranged and combined at appropriate intervals to measure battery consumption values corresponding to all flight missions. The current power consumption value corresponding to the current flight scene factor is obtained through inquiring in the preset power correlation table, the required battery installation number is obtained through calculation according to the current power consumption value, the emergency power value and the power reserve value of one battery, and the battery installation number= (current power consumption value+emergency power value)/the power reserve value is rounded up if decimal exists.
It can be understood that the voltage of a single battery can meet the requirement of load working voltage such as a propeller motor, all batteries are connected into an aircraft load circuit in a parallel manner, and all load circuits such as the propeller motor are connected into an on-board power supply in a parallel manner.
According to the utility model, the number of the installed batteries is flexibly adjusted according to the specific flight task conditions, so that the load loss caused by redundant batteries is reduced to the maximum extent, and the working efficiency of the unmanned aerial vehicle is optimized; further, the battery box 200 is convenient to detach and maintain, and under the condition of the shortage of charging time, the battery can be directly replaced to meet the task requirement; the battery can generate heat when discharging, the larger the current is, the more serious the heat is, the battery box 200 is hung outside the machine body, and the side wall and the bottom are provided with holes, so that the battery can be cooled conveniently by utilizing the air flow during flying, and the battery can not be overheated and dangerous; the saved battery weight can increase the load of the corresponding weight, and the load capacity of the unmanned aerial vehicle is increased maximally.
In one embodiment, the utility model also discloses an aircraft comprising a fuselage, the aircraft further comprising a battery compartment assembly as in the above embodiment removably mounted to the bottom of the fuselage; and the longitudinal axis of the center of gravity of the battery and the battery compartment pylon 100 in the assembly coincides with the longitudinal axis of the center of gravity of the aircraft.
The foregoing describes in detail preferred embodiments of the present utility model. It should be understood that numerous modifications and variations can be made in accordance with the concepts of the utility model by one of ordinary skill in the art without undue burden. Therefore, all technical solutions which can be obtained by logic analysis, reasoning or limited experiments based on the prior art by the person skilled in the art according to the inventive concept shall be within the scope of protection defined by the claims.
Claims (10)
1. A battery compartment assembly for use in an aircraft, the battery compartment assembly comprising:
The battery box hanging frame is provided with a detachable battery box, and a battery is arranged in the battery box;
the battery box hanging frame comprises a bottom plate and a plurality of first installation components and second installation components which are arranged on the bottom plate;
The battery box hanger is connected to the aircraft through the first mounting assembly;
A third mounting assembly matched with the second mounting assembly is arranged at the top of the battery box;
the battery box is connected with the battery box hanging frame through the second installation component and the third installation component.
2. The battery compartment assembly of claim 1, wherein,
The battery box assembly further comprises a baffle;
The second mounting assembly comprises a plurality of connecting blocks arranged on the bottom plate;
the baffle detachably with the connecting block is connected, just baffle and connecting block parallel arrangement.
3. The battery compartment assembly of claim 2, wherein,
The baffle is connected with the connecting block through a mortise and tenon structure;
And/or the number of the groups of groups,
The baffle is connected with the connecting block through a bolt structure.
4. The battery compartment assembly of claim 2, wherein,
The second installation components are arranged on the bottom plate according to preset intervals, and the preset intervals are matched with the width of the battery box;
The third installation component comprises raised strips arranged on the left side and the right side of the top of the battery box;
Grooves are formed in two sides of the connecting block;
The battery box is connected with the battery box hanging frame through the convex strips and the grooves.
5. The battery compartment assembly of claim 2, wherein,
The second installation component comprises a plurality of first limiting blocks arranged at the edge of the bottom plate, and the first limiting blocks are arranged between two adjacent connecting blocks;
the third mounting assembly comprises second limiting blocks arranged at the front end and the rear end of the top of the battery box;
The battery box is connected with the battery box hanging frame through the first limiting block and the second limiting block.
6. The battery compartment assembly of any one of claims 1-5, wherein,
The first mounting assembly comprises a third limiting block arranged at the edge of the battery box hanging frame;
the battery box hanging frame is connected with the aircraft through the third limiting block.
7. The battery compartment assembly of claim 2, wherein,
One or more openings are formed in the four sides and the bottom of the battery box;
One or more openings are arranged on the baffle plate.
8. The battery compartment assembly of any one of claims 1-5, wherein,
The number of the battery boxes is even;
The battery box is symmetrically arranged on the battery box hanging frame by taking the center of the battery box hanging frame as a datum line.
9. The battery compartment assembly of any one of claims 1-5, wherein,
The number of the battery boxes is an odd number;
The battery box is arranged at the center of the battery box hanging frame, and the battery box hanging frame is symmetrically arranged on the battery box hanging frame by taking the center of the battery box hanging frame as a datum line.
10. An aircraft comprising a fuselage, further comprising a battery compartment assembly as defined in any one of claims 1-9 removably mounted to the bottom of the fuselage; and
The longitudinal axis where the center of gravity of the battery box hanging frame is located coincides with the longitudinal axis where the center of gravity of the aircraft is located.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323231057.6U CN221438363U (en) | 2023-11-29 | 2023-11-29 | Battery box assembly and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323231057.6U CN221438363U (en) | 2023-11-29 | 2023-11-29 | Battery box assembly and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221438363U true CN221438363U (en) | 2024-07-30 |
Family
ID=92061842
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323231057.6U Active CN221438363U (en) | 2023-11-29 | 2023-11-29 | Battery box assembly and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221438363U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118578856A (en) * | 2024-08-02 | 2024-09-03 | 宁德时代新能源科技股份有限公司 | Vehicle and vehicle battery replacement method |
-
2023
- 2023-11-29 CN CN202323231057.6U patent/CN221438363U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118578856A (en) * | 2024-08-02 | 2024-09-03 | 宁德时代新能源科技股份有限公司 | Vehicle and vehicle battery replacement method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR102806907B1 (en) | Battery thermal management system and method | |
| CN221438363U (en) | Battery box assembly and aircraft | |
| Damiano et al. | Batteries for aerospace: a brief review | |
| CN208637494U (en) | Power supply module | |
| CN211844896U (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN207800697U (en) | Logistic car Battery case and logistic car battery system | |
| US20240372201A1 (en) | Battery pack and electrical apparatus | |
| US20240304930A1 (en) | Battery pack and electrical apparatus | |
| CN218334100U (en) | Replaceable battery box | |
| CN219393555U (en) | Box, battery and power consumption device | |
| CN217805303U (en) | Range extender and aircraft comprising same | |
| US11851198B2 (en) | Electrically propelled aircraft with partially rated converter | |
| CN216581046U (en) | Composite wing unmanned aerial vehicle with multiple power supplies for discrete power supply | |
| CN205376602U (en) | Unmanned aerial vehicle's external battery securing device | |
| JP2768290B2 (en) | Aerial moving object | |
| CN210653666U (en) | Big load unmanned aerial vehicle electrical system and big load unmanned aerial vehicle | |
| CN214216155U (en) | An easy-to-carry drone | |
| CN211700379U (en) | Household energy storage battery box | |
| CN221163405U (en) | Unmanned aerial vehicle battery mounting structure | |
| CN210325884U (en) | Unmanned aerial vehicle battery mounting structure and unmanned aerial vehicle | |
| CN209818168U (en) | Range extender for model airplane engine | |
| CN208848967U (en) | Electric automobile battery box cover plate unit | |
| CN118107815A (en) | Many rotors are unmanned aerial vehicle that moors | |
| CN222953249U (en) | On-board power supply for charging pile maintenance vehicles | |
| CN218022153U (en) | Unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |