CN113955081A - Aircraft battery compartment structure - Google Patents
Aircraft battery compartment structure Download PDFInfo
- Publication number
- CN113955081A CN113955081A CN202111121784.XA CN202111121784A CN113955081A CN 113955081 A CN113955081 A CN 113955081A CN 202111121784 A CN202111121784 A CN 202111121784A CN 113955081 A CN113955081 A CN 113955081A
- Authority
- CN
- China
- Prior art keywords
- battery compartment
- quick
- aircraft
- release flap
- connector
- 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
Links
- 230000003014 reinforcing effect Effects 0.000 claims description 5
- 239000000428 dust Substances 0.000 abstract description 3
- 238000005192 partition Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000011324 bead Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/22—Other structures integral with fuselages to facilitate loading, e.g. cargo bays, cranes
-
- 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
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Battery Mounting, Suspending (AREA)
Abstract
This application belongs to battery compartment (1) and quick-release flap (3), and battery compartment (1) wholly is the triangular prism form, including bottom surface, top surface, side and both ends face, battery compartment (1) low face opening forms box structure, battery compartment (1) bottom surface opening is connected with quick-release flap (3) and is formed seal structure, provides a relatively sealed environment for the battery, can make the battery less receive the influence of temperature and dust, and aircraft battery compartment structural strength is high, and the battery is installed inside aircraft battery compartment box, has the bearing stress ability of a plurality of directions, avoids the battery to damage at operational environment's mechanics.
Description
Technical Field
The application belongs to the field of aircraft structural design, and particularly relates to an aircraft storage battery compartment structure.
Background
Most of storage batteries on the airplane are installed in a fairing, but the storage batteries are heavy in weight, and the batteries need to have good load resistance in the flying process of the airplane, so that accidents such as falling off of the storage batteries and the like caused by the fact that the storage batteries have large mass in the process of taking off or landing of the airplane are avoided, and meanwhile, the storage batteries have more circuits, so that good dust separation capacity is needed, and the circuits are prevented from being corroded and aged. The use and the maintenance of battery are frequent, and the battery needs to have the installation environment of easy change and dismouting, and the work efficiency of battery receives the temperature influence great, consequently need provide a relatively more heat retaining, dustless environment for the battery.
Disclosure of Invention
In order to solve the problem, the application provides an aircraft battery compartment structure, include, battery compartment and quick-release flap, the battery compartment wholly is the triangular prism form, including bottom surface, top surface, side and both ends face, battery compartment low face opening forms box structure, battery compartment bottom surface opening and quick-release flap are connected and are formed seal structure.
Preferably, the battery compartment has a reinforcing profile on its side.
Preferably, the two end faces of the storage battery compartment respectively comprise two connectors, each connector comprises a connector end cover and a connector edge strip, the connector end covers seal the two end faces of the storage battery compartment, the connector edge strips are arranged at the top ends of the connector end covers, and the connector edge strips are connected with the wall plate of the machine body.
Preferably, the junction of the battery compartment and the quick release flap has a spacing of 0.5mm to 1.5 mm.
Preferably, the space between the battery compartment and the connection of the quick release cover is provided with a Gole seal tape.
Preferably, the quick-release cover cap is integrally L-shaped, the quick-release cover cap comprises a cover face and inner edge strips of the partition frame at two ends of the cover face, and the inner edge strips of the partition frame are L-shaped and connected with the lower end of the joint.
Preferably, the quick release flap has a movable door, which is hinged to the quick release flap.
Preferably, the top surface of the battery compartment is connected with the connector through a connecting angle, and the connector flange is connected with the fuselage wall panel through a connecting angle.
The advantages of the present application include: 1. the storage battery is provided with a relatively sealed environment, so that the storage battery is less influenced by temperature and dust; 2. the aircraft storage battery compartment has high structural strength, and the battery is arranged inside the aircraft storage battery compartment box, has bearing capacity in multiple directions, and avoids mechanical damage of the storage battery in a working environment.
Drawings
FIG. 1 is a schematic view of an aircraft battery compartment structure installation.
Fig. 2 is a schematic view of the construction of the quick release flap.
Fig. 3 is a schematic view of an aircraft battery compartment configuration.
Fig. 4 is a schematic view of a joint structure.
The battery compartment comprises 1-a storage battery compartment, 2-a partition frame inner edge strip, 3-a quick-release opening cover, 4-a connector, 6-a reinforcing section bar and 7-a connecting angle bar.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
As the application of the figure provides an aircraft battery compartment structure, include, battery compartment 1 and quick-release flap 3, battery compartment 1 wholly is the triangular prism form, including bottom surface, top surface, side and both ends face, battery compartment 1 low face opening forms box structure, and box structure can hold the battery, and the box-packed structure of triangular prism form has higher stability for the structure of quadrangular, can make the battery can have better protection.
The bottom opening of the storage battery compartment 1 is connected with the quick-release cover cap 3 to form a sealing structure.
In some possible embodiments, the side of the battery compartment 1 has the reinforcing profile 6, the side of the battery compartment 1 needs to be provided with the battery inside, and no other parts generate support for the side force in the side direction, therefore, two reinforcing ribs need to be arranged on the side to improve the strength of the side. The two end faces of the storage battery compartment 1 are respectively composed of two connectors 4, each connector 4 comprises a connector end cover and a connector edge strip, the connector end covers seal the two end faces of the storage battery compartment 1, and the connector end covers extend upwards;
in some possible embodiments, the two end faces of the battery compartment 1 are respectively composed of two connectors 4, the connectors 4 include connector end covers and connector flanges, the connector end covers close the two end faces of the battery compartment 1, the connector flanges are arranged at the top ends of the connector end covers, and the connector flanges are connected with the fuselage wall panels.
In some possible embodiments, the connection of the battery compartment 1 and the quick release flap 3 has a spacing of 0.5mm to 1.5 mm.
In some possible embodiments, the space at the junction of the battery compartment 1 and the quick release flap 3 has a gore seal.
In some possible embodiments, the quick-release flap 3 is integrally "L" shaped, the quick-release flap 3 includes a covering surface and a bulkhead inner edge 2 at both ends of the covering surface, and the bulkhead inner edge 2 is "L" shaped and connected to the lower end of the joint 4.
In some possible embodiments, the quick-release flap 3 has a movable hatch door hinged to the quick-release flap 3, which is freely openable and closable, and can be freely replaced after the accumulator has been installed.
In some possible embodiments, the top surface of the battery compartment 1 is connected to the terminal 4 by a connecting angle 7, the terminal bead is connected to the fuselage panel by a connecting angle 7, and the shape of the angle 7 provides a good sealing effect at the connection.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides an aircraft battery compartment structure, its characterized in that includes, battery compartment (1) and quick-release flap (3), and battery compartment (1) wholly is the triangular prism form, including bottom surface, top surface, side and both ends face, battery compartment (1) low face opening forms box structure, battery compartment (1) the bottom surface opening is connected with quick-release flap (3) and is formed seal structure.
2. An aircraft battery compartment structure according to claim 1, characterised in that the sides of the battery compartment (1) are provided with reinforcing profiles (6).
3. An aircraft battery compartment structure according to claim 2, characterised in that the battery compartment (1) is formed on both end faces by two respective connectors (4), the connectors (4) comprising connector end caps and connector flanges, the connector end caps closing both end faces of the battery compartment (1), the connector flanges being at the top ends of the connector end caps, the connector flanges being connected to fuselage panels.
4. An aircraft battery compartment structure according to claim 1, characterised in that the connection of the battery compartment (1) to the quick-release flap (3) has a spacing of 0.5mm to 1.5 mm.
5. An aircraft battery compartment structure according to claim 4, characterised in that the distance between the battery compartment (1) and the connection of the quick-release flap (3) is provided with a Gore seal.
6. An aircraft battery compartment structure as claimed in claim 1, characterised in that the quick release flap (3) is entirely "L" shaped, the quick release flap (3) comprising a covering surface and a bulkhead inner edge strip (2) at both ends of said covering surface, the bulkhead inner edge strip (2) being "L" shaped and connected to the lower end of the connector (4).
7. An aircraft battery compartment structure according to claim 1, characterised in that the quick-release flap (3) has a movable door which is hinged to the quick-release flap (3).
8. An aircraft battery compartment structure according to claim 2, characterised in that the top side of the battery compartment (1) is connected to the terminal (4) by means of a connection angle (7), and the terminal strip is connected to the fuselage panel by means of a connection angle (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111121784.XA CN113955081B (en) | 2021-09-24 | 2021-09-24 | Aircraft battery cabin structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111121784.XA CN113955081B (en) | 2021-09-24 | 2021-09-24 | Aircraft battery cabin structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113955081A true CN113955081A (en) | 2022-01-21 |
| CN113955081B CN113955081B (en) | 2023-11-28 |
Family
ID=79462717
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111121784.XA Active CN113955081B (en) | 2021-09-24 | 2021-09-24 | Aircraft battery cabin structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113955081B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3738506A1 (en) * | 1987-11-13 | 1989-06-01 | Dornier System Gmbh | ANTENNA STRUCTURE |
| JP2002134084A (en) * | 2000-10-27 | 2002-05-10 | Fuji Heavy Ind Ltd | Structure of vehicle battery box |
| US20100193271A1 (en) * | 2007-07-09 | 2010-08-05 | Renault S.A.S. | Arrangement for mounting a battery in a motor vehicle |
| DE102011106090A1 (en) * | 2011-06-30 | 2013-01-03 | Audi Ag | Arrangement of battery modules in a vehicle and vehicle |
| CN204895353U (en) * | 2015-08-31 | 2015-12-23 | 中国重汽集团成都王牌商用车有限公司 | Machineshop car accumulator jar protector |
| CN205203357U (en) * | 2015-12-11 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | Outer covering system of aircraft pressure cabin controls an airtight mounting structure |
| CN108110149A (en) * | 2017-11-09 | 2018-06-01 | 广德宝达精密电路有限公司 | A kind of omniseal battery box for nano silica-magnesia solid state battery |
| CN113054285A (en) * | 2021-03-29 | 2021-06-29 | 安徽师范大学 | Preparation method of lithium battery pack with collision protection and heat dissipation functions |
| CN213948747U (en) * | 2020-11-03 | 2021-08-13 | 深圳市蜉飞科技有限公司 | Streamlined low resistance aircraft that load capacity is big |
-
2021
- 2021-09-24 CN CN202111121784.XA patent/CN113955081B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3738506A1 (en) * | 1987-11-13 | 1989-06-01 | Dornier System Gmbh | ANTENNA STRUCTURE |
| JP2002134084A (en) * | 2000-10-27 | 2002-05-10 | Fuji Heavy Ind Ltd | Structure of vehicle battery box |
| US20100193271A1 (en) * | 2007-07-09 | 2010-08-05 | Renault S.A.S. | Arrangement for mounting a battery in a motor vehicle |
| DE102011106090A1 (en) * | 2011-06-30 | 2013-01-03 | Audi Ag | Arrangement of battery modules in a vehicle and vehicle |
| CN204895353U (en) * | 2015-08-31 | 2015-12-23 | 中国重汽集团成都王牌商用车有限公司 | Machineshop car accumulator jar protector |
| CN205203357U (en) * | 2015-12-11 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | Outer covering system of aircraft pressure cabin controls an airtight mounting structure |
| CN108110149A (en) * | 2017-11-09 | 2018-06-01 | 广德宝达精密电路有限公司 | A kind of omniseal battery box for nano silica-magnesia solid state battery |
| CN213948747U (en) * | 2020-11-03 | 2021-08-13 | 深圳市蜉飞科技有限公司 | Streamlined low resistance aircraft that load capacity is big |
| CN113054285A (en) * | 2021-03-29 | 2021-06-29 | 安徽师范大学 | Preparation method of lithium battery pack with collision protection and heat dissipation functions |
Non-Patent Citations (1)
| Title |
|---|
| 葛宗义, 邓尧: "飞机雷达舱大口盖开启困难的改善与解决", 飞机设计, no. 01, pages 31 - 35 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113955081B (en) | 2023-11-28 |
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