CN112849420B - Regional subdivision sealing structure - Google Patents
Regional subdivision sealing structure Download PDFInfo
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- CN112849420B CN112849420B CN202110151134.3A CN202110151134A CN112849420B CN 112849420 B CN112849420 B CN 112849420B CN 202110151134 A CN202110151134 A CN 202110151134A CN 112849420 B CN112849420 B CN 112849420B
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- 238000007789 sealing Methods 0.000 title claims abstract description 245
- 238000009434 installation Methods 0.000 claims abstract description 12
- 238000004891 communication Methods 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 10
- 238000012423 maintenance Methods 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 2
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 238000013316 zoning Methods 0.000 abstract description 2
- 230000000149 penetrating effect Effects 0.000 description 6
- 239000002775 capsule Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229920001971 elastomer Polymers 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229920000181 Ethylene propylene rubber Polymers 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 229910000963 austenitic stainless steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229920001973 fluoroelastomer Polymers 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/06—Hermetically-sealed casings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Pressure Vessels And Lids Thereof (AREA)
- Gasket Seals (AREA)
Abstract
The invention discloses a regional and cabin-dividing sealing structure which comprises a shell, wherein the shell is divided into N +1 sealing chambers in a single direction through N cabin-dividing sealing cover plates, wherein N is more than or equal to 1; at least one sealing structure for entering is arranged on the shell at each sealing cavity; a plurality of installation components are correspondingly installed in a plurality of sealed cavities, and wall-through sealed sockets are arranged on the sealing structures or the cabin-dividing sealed cover plates at the front end and the rear end. The invention controls and adjusts the cabin sealing and environment zoning of the internal installation space, and simultaneously improves the working environment in the sealed cabin of the aircraft and the environmental adaptability of the product by combining the good sealing property of the sealed cabin; the regional and cabin-divided sealing design structure has the advantages that the internal products are convenient to replace according to the maintenance period, the sealing effect is good, the structure is simple, the universality is high, and the regional and cabin-divided sealing design structure is suitable for the sealing design of the internal installation space of most aircrafts or other similar products.
Description
Technical Field
The invention relates to the technical field of sealed cabins, in particular to a regional and cabin-dividing sealing structure.
Background
In the design of complex equipment products such as aircrafts and the like, in order to adapt to the external variable pressure environment experienced in the processes of storage, launching flight, on-orbit operation and the like and provide a proper working environment for internal products, the internal space for installing the products is generally required to be subjected to sealing design. Without special requirements, the interior of the aircraft is generally designed as a unified capsule and various products are installed inside. When the type difference of products installed inside the aircraft is large, and especially when different products have inconsistent requirements on working environments (such as pressure, humidity, atmosphere environments with different gas contents and the like) and inconsistent maintenance and replacement periods, only one sealed cabin designed inside the aircraft cannot meet the use requirements.
The traditional aircraft internal sealed cabin only has one unified cabin body, can't control respectively pressure and atmosphere according to the operational environment requirement of internally mounted product and adjust, need open the sealed cabin completely when maintaining the change to the internally mounted product, can destroy the sealed environment of whole sealed cabin.
Therefore, it is necessary to develop a sealing structure for a compartment to solve the above problems.
Disclosure of Invention
The invention aims to solve the problems and designs a regional cabin sealing structure.
The invention realizes the purpose through the following technical scheme:
a regional and cabin-dividing sealing structure comprises a shell, wherein the shell is divided into N +1 sealing chambers in a single direction through N cabin-dividing sealing cover plates, wherein N is more than or equal to 1; at least one sealing structure for entering is arranged on the shell at each sealing cavity; a plurality of installation components are correspondingly installed in a plurality of sealed cavities, wall penetrating sealed sockets are arranged on sealing structures or cabin dividing sealing cover plates at the front end and the rear end, installation components in adjacent sealed cavities are electrically connected through the wall penetrating sealed sockets and wires, and installation components in the front end and rear end sealed cavities are electrically connected with the outside through the wall penetrating sealed sockets and the wires.
Specifically, an atmosphere control assembly is mounted within each sealed chamber.
Preferably, the atmosphere control member comprises a moisture absorbing member or a member absorbing a different gas.
Specifically, the through-wall sealing socket is connected to the sealing structure or the subdivision sealing cover plate through the adapter plate.
Specifically, each sealing structure is provided with a sealing valve, and two ends of each sealing valve are respectively communicated with the sealing chamber and the outside.
Specifically, seal structure all includes sealed lid and sealing washer, corresponds on the casing correspondingly be provided with the opening that seals the cavity intercommunication, and sealed lid covers the opening setting, is provided with the seal groove on sealed lid or casing, and the sealing washer is installed in the seal groove to a sealed of casing and sealed lid.
Specifically, the through-wall sealing socket is installed on the sealing cover through the adapter plate, a sealing groove is formed between the adapter plate and the sealing cover, and the sealing ring is installed in the sealing groove and used for sealing the adapter plate and the sealing cover.
Specifically, a sealing groove is formed in the position of the sub-cabin sealing cover plate, and the sealing ring is installed in the sealing groove and used for sealing the adapter plate and the sub-cabin sealing cover plate.
Preferably, an annular structure is arranged in the shell in a protruding mode, a sealing groove is arranged on the annular structure or the sub-chamber sealing cover plate, and a sealing ring is arranged in the sealing groove and used for sealing the annular structure or the sub-chamber sealing cover plate.
Preferably, a boss structure is provided projecting inwardly at each sealed chamber in the housing, the atmosphere control assembly and the mounting assembly being fixedly mounted on the boss structure.
The invention has the beneficial effects that:
the method controls and adjusts the cabin sealing and environment zoning of the internal installation space of the aircraft, and simultaneously improves the working environment in the sealed cabin of the aircraft and the environmental adaptability of products by combining the good sealing performance of the sealed cabin; the regional and cabin-divided sealing design structure has the advantages that the internal products are convenient to replace according to the maintenance period, the sealing effect is good, the structure is simple, the universality is high, and the regional and cabin-divided sealing design structure is suitable for the sealing design of the internal installation space of most aircrafts or other similar products.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of the present application;
FIG. 2 is an enlarged view of a portion a of the present application;
FIG. 3 isbase:Sub>A schematic sectional view taken along line A-A of FIG. 1;
FIG. 4 is a schematic sectional view taken along line B-B of FIG. 1;
FIG. 5 is a schematic view of the structure of the sealing port cover of the middle sealed cabin in the present application;
FIG. 6 is a schematic structural diagram of a second embodiment of the present application;
in the figure: 1-front sealing cover; 2-a shell; 3-a front mounting plate; 4-sealing cover plates in different cabins; 5, mounting a rear plate; 6-rear sealing cover; 7-an adapter plate; 8-a first through-wall sealed socket; 9-a first sealing valve; 10-a second through-wall sealed socket; 11-a first sealing ring; 12-a second sealing ring; 13-a third seal ring; 14-a fourth seal ring; 15-a fifth sealing ring; 16-an atmosphere control assembly; 17-a first mounting assembly; 18-a second mounting assembly; 19-sealing the flap; 20-cover plate; 21-sixth sealing ring; 22-a second sealing valve; 23-seventh sealing ring.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined or explained in subsequent figures.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "inside", "outside", "left", "right", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the present invention are conventionally placed in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is also to be noted that, unless otherwise explicitly stated or limited, the terms "disposed" and "connected" are to be interpreted broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The following detailed description of embodiments of the invention refers to the accompanying drawings.
A regional and cabin-dividing sealing structure comprises a shell 2, wherein the shell 2 is internally divided into N +1 sealing chambers in a single direction through N cabin-dividing sealing cover plates 4, wherein N is more than or equal to 1; at least one sealing structure for entering is arranged on the shell 2 at each sealing chamber; a plurality of installation components are correspondingly installed in a plurality of sealed cavities, wall penetrating sealed sockets are arranged on sealing structures or cabin dividing sealing cover plates 4 at the front end and the rear end, installation components in adjacent sealed cavities are electrically connected through the wall penetrating sealed sockets and wires, and installation components in the front end and rear end sealed cavities are electrically connected with the outside through the wall penetrating sealed sockets and the wires.
Specifically, an atmosphere control assembly 16 is mounted within each sealed chamber.
Preferably, the atmosphere control member 16 comprises a moisture absorbing member or a member that absorbs a different gas.
In particular, the through-wall sealing socket is connected to the sealing structure or the subdivision sealing cover plate 4 by an adapter plate 7.
Specifically, each sealing structure is provided with a sealing valve, and two ends of each sealing valve are respectively communicated with the sealing chamber and the outside.
Specifically, seal structure all includes sealed lid and sealing washer, corresponds on the casing 2 correspondingly be provided with the opening that seals the cavity intercommunication, and sealed lid covers the opening setting, is provided with the seal groove on sealed lid or casing 2, and the sealing washer is installed in the seal groove to a sealed of casing 2 and sealed lid.
Specifically, the through-wall sealing socket is installed on the sealing cover through the adapter plate 7, a sealing groove is formed between the adapter plate 7 and the sealing cover, and the sealing ring is installed in the sealing groove and used for sealing the adapter plate 7 and the sealing cover.
Specifically, a sealing groove is arranged on the sub-chamber sealing cover plate 4, and a sealing ring is installed in the sealing groove and used for sealing the adapter plate 7 and the sub-chamber sealing cover plate 4.
Preferably, an annular structure is provided in the housing 2 so as to protrude inward, and a sealing groove is provided in the annular structure or the capsule sealing cover plate 4, in which a sealing ring is mounted and used for sealing the annular structure or the capsule sealing cover plate 4.
Preferably, a boss structure is provided projecting inwardly at each sealed chamber in the housing 2, and the atmosphere control assembly 16 and the mounting assembly are fixedly mounted on the boss structure.
As shown in fig. 1, 2 and 6, the inside of the shell 2 is divided into two sealed chambers in a single direction by a compartment sealing cover plate 4; the sealing structure comprises a front end sealing structure and a rear end sealing structure, wherein the front end sealing structure comprises a front sealing cover 1 and a second sealing ring 12 (as shown in figure 1, a sealing groove is formed in the shell 2, and the second sealing ring 12 is arranged in the sealing groove; as shown in figure 6, a sealing groove is formed in the front sealing cover 1, and the second sealing ring 12 is arranged in the sealing groove), and the front sealing cover 1 is connected with the shell 2 through a plurality of bolts; the second through-wall sealing socket 10 is mounted on the front sealing cover 1 through the adapter plate 7, the adapter plate 7 is connected with the front sealing cover 1 through a plurality of bolts, a sealing groove is formed in the front sealing cover 1, and the first sealing ring 11 is mounted in the sealing groove; the rear end sealing structure comprises a rear sealing cover 6 and a seventh sealing ring 23 (as shown in figure 1, a sealing groove is formed in the shell 2, and the seventh sealing ring 23 is arranged in the sealing groove; as shown in figure 6, a sealing groove is formed in the rear sealing cover 6, and the seventh sealing ring 23 is arranged in the sealing groove), and the rear sealing cover 6 is connected with the shell 2 through a plurality of bolts; the first through-wall sealing socket 8 is mounted on the rear sealing cover 6 through the adapter plate 7, the adapter plate 7 is connected with the rear sealing cover 6 through a plurality of bolts, a sealing groove is formed in the rear sealing cover 6, and the fifth sealing ring 15 is mounted in the sealing groove; an atmosphere control assembly 16, a first mounting assembly 17 and a second mounting assembly 18 are arranged in each sealed cavity, and the atmosphere control assembly 16, the first mounting assembly 17 and the second mounting assembly 18 are all mounted on a mounting plate and fixedly connected to a protruding structure through bolts (a front mounting plate 3 is arranged in the front sealed cabin, and a rear mounting plate 5 is arranged in the rear sealed cabin); (as shown in fig. 1, a sealing groove is arranged on the annular structure in the shell 2, and a third sealing ring 13 is arranged in the sealing groove; as shown in fig. 6, a sealing groove is arranged on the capsule sealing cover plate 4, and the third sealing ring 13 is arranged in the sealing groove), and the capsule sealing cover plate 4 and the annular structure in the shell 2 are fixedly connected through a plurality of bolts; the second wall-penetrating sealing socket 10 is mounted on the sub-cabin sealing cover plate 4 through a connecting plate, the wall-penetrating sealing socket and the connecting plate are fixedly connected through a plurality of bolts, a sealing groove is formed in the sub-cabin sealing cover plate 4, and a fourth sealing ring 14 is mounted in the sealing groove; one first sealing valve 9 is arranged on the front sealing cover 1 and is used for controlling the on-off of the air inside and outside the front sealing cover 1, and the other first sealing valve 9 is arranged on the rear sealing cover 6; the sealing valves are generally used for controlling the initial atmosphere environment inside the sealed cabin after the assembly of the sealed cabin is finished (for example, the sealed cabin is vacuumized, dehumidified and filled with inert gas with certain pressure through the sealing valves), and the number of the sealing valves can be determined according to size constraints, atmosphere environment treatment modes and the like;
as shown in fig. 5, in the case that the casing 2 includes more than three sealing chambers, at this time, a groove is inwardly formed in the casing 2 of the sealing chamber located in the middle, an opening is formed at the bottom of the groove, a part of the sealing port cover 19 is placed in the sealing chamber, a part of the sealing chamber is placed at the bottom of the groove, a sealing groove is formed at the bottom of the groove, a sixth sealing ring 21 is installed in the groove and used for sealing the casing 2 and the sealing port cover 19, the cover plate 20 is covered in the groove above the sealing port cover 19, and a plurality of bolts pass through the cover plate 20 and the sealing port cover 19 and then are screwed into the casing 2; the second sealing valve 22 is arranged on the sealing opening cover 19 and is used for controlling the on-off of the air inside and outside the shell 2;
in some embodiments, the housing 2 is circular in cross-section, but may be designed as a rectangular, etc. regular shaped housing 2 or an irregular shaped housing 2 as desired;
in some embodiments, the sealing groove structure can be in the form of a rectangular groove, a trapezoidal groove or the like as required;
in some embodiments, the sealing parts of the front sealed cabin and the rear sealed cabin are generally rubber sealing rings, and can also be metal sealing rings. The rubber sealing ring is generally made of fluororubber, ethylene propylene rubber and other materials with good aging resistance, heat resistance, cold resistance and corrosion resistance. The metal sealing ring is generally made of austenitic stainless steel and other materials with good corrosion resistance and oil resistance. The through-wall sealing socket is generally selected to be an aviation socket with good sealing performance, high reliability and good environment resistance;
when the flow exchange direction of media in different sealed cabins under the long-time condition is required, the media with different pressures can be filled in each sealed cabin according to the requirement;
when the medium in the sealed cabin is gas, the atmosphere control assemblies 16 need to be arranged, and when the types of the atmosphere control assemblies 16 designed in each sealed cabin are different, the regional control of the atmosphere environment in a certain time can be realized;
except that the sealing surface or the sealing flange in the shell 2 needs to be designed into a complete ring shape due to the sealing design constraint, the mounting flange for fixing the mounting plate can be designed into a petal gap form (as shown in figure 4), and the mounting plate is arranged from the gap, so that the mounting plate can be conveniently mounted, the utilization rate of the internal space of the shell 2 is improved, and the quality of the shell 2 is reduced;
when the assembly installed in the sealed cabin needs to be replaced, the sealed cabin provided with the assembly can be opened only, and classified maintenance and replacement are realized. When the number of the sealed cabins is more than two, a sealed door 19 (shown in figure 3) can be designed on the side wall of the middle sealed cabin, so that the aim of replacing components in the sealed cabin without influencing the environment of other sealed cabins is fulfilled.
The technical solution of the present invention is not limited to the limitations of the above specific embodiments, and all technical modifications made according to the technical solution of the present invention fall within the protection scope of the present invention.
Claims (10)
1. A regional and cabin-dividing sealing structure comprises a shell and is characterized in that the shell is divided into N +1 sealing chambers in a single direction through N cabin-dividing sealing cover plates, wherein N is more than or equal to 1; at least one sealing structure for entering is arranged on the shell at each sealing cavity; the installation components in the front end sealed cavity and the rear end sealed cavity are electrically connected with the outside through the wall-penetrating sealed sockets and the leads; when the number of the sealing chambers is more than two, a sealing cover is arranged on the side wall of the middle sealing chamber.
2. A zoned compartmentalized containment structure as recited by claim 1 wherein an atmosphere control assembly is mounted within each containment chamber.
3. A zoned compartmentalized containment structure as recited by claim 2, wherein said atmosphere control component comprises a moisture absorbing component or a different gas absorbing component.
4. A zoned compartmentalized sealing arrangement as recited by claim 1, wherein the wall seal receptacle is attached to the sealing arrangement or the compartmentalized sealing cover by an adapter plate.
5. A zoned compartmentalized sealing structure as recited by claim 1, wherein a sealing valve is provided on each sealing structure, the two ends of the sealing valve being in communication with the sealed chamber and the outside, respectively.
6. The zoned subdivision sealing structure of claim 4, wherein the sealing structure comprises a sealing cover and a sealing ring, an opening communicated with the sealing chamber is correspondingly arranged on the housing, the sealing cover is arranged to cover the opening, a sealing groove is arranged on the sealing cover or the housing, and the sealing ring is arranged in the sealing groove and used for sealing the housing and the sealing cover.
7. The zoned subdivision sealing structure of claim 6, wherein the wall-through sealing socket is mounted on the sealing cover by an adapter plate, a sealing groove is provided between the adapter plate and the sealing cover, and a sealing ring is mounted in the sealing groove and used for sealing the adapter plate and the sealing cover.
8. The zoned subdivision sealing structure of claim 4, wherein a sealing groove is formed in the subdivision sealing cover plate, and a sealing ring is mounted in the sealing groove and used for sealing the adapter plate and the subdivision sealing cover plate.
9. A zoned and chambered sealing arrangement according to claim 1, wherein an annular structure projects inwardly in the housing, and wherein a sealing groove is provided in the annular structure or the chambered sealing cover, and wherein the sealing ring is mounted in the sealing groove and is used for sealing the annular structure or the chambered sealing cover.
10. A zoned compartmentalized sealing arrangement as recited by claim 1 wherein a boss structure is provided projecting inwardly at each sealed chamber in the housing, the atmosphere control assembly and the mounting assembly being fixedly mounted on the boss structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110151134.3A CN112849420B (en) | 2021-02-03 | 2021-02-03 | Regional subdivision sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110151134.3A CN112849420B (en) | 2021-02-03 | 2021-02-03 | Regional subdivision sealing structure |
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| Publication Number | Publication Date |
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| CN112849420A CN112849420A (en) | 2021-05-28 |
| CN112849420B true CN112849420B (en) | 2022-12-13 |
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| CN202110151134.3A Active CN112849420B (en) | 2021-02-03 | 2021-02-03 | Regional subdivision sealing structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114044176A (en) * | 2021-11-17 | 2022-02-15 | 北京航天发射技术研究所 | Pressure-bearing composite material cylinder |
| CN114323561B (en) * | 2021-12-30 | 2023-10-20 | 中国特种飞行器研究所 | Watertight hull test model device with gravity center inertia and high freedom degree adjustment |
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| CN112849420A (en) | 2021-05-28 |
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