CN117489866A - Space pipeline, cabin section and installation method of space pipeline - Google Patents
Space pipeline, cabin section and installation method of space pipeline Download PDFInfo
- Publication number
- CN117489866A CN117489866A CN202311692051.0A CN202311692051A CN117489866A CN 117489866 A CN117489866 A CN 117489866A CN 202311692051 A CN202311692051 A CN 202311692051A CN 117489866 A CN117489866 A CN 117489866A
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- Prior art keywords
- pipeline
- splicing
- pipes
- cabin section
- connecting grooves
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- 238000009434 installation Methods 0.000 title claims abstract description 38
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000003466 welding Methods 0.000 claims abstract description 31
- 238000007789 sealing Methods 0.000 claims abstract description 10
- 239000000463 material Substances 0.000 claims description 5
- 229910001220 stainless steel Inorganic materials 0.000 claims description 5
- 239000010935 stainless steel Substances 0.000 claims description 5
- 239000012530 fluid Substances 0.000 claims description 4
- 210000001503 joint Anatomy 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 5
- 239000007789 gas Substances 0.000 description 3
- 230000008092 positive effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L1/00—Laying or reclaiming pipes; Repairing or joining pipes on or under water
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L1/00—Laying or reclaiming pipes; Repairing or joining pipes on or under water
- F16L1/024—Laying or reclaiming pipes on land, e.g. above the ground
- F16L1/06—Accessories therefor, e.g. anchors
Abstract
The application discloses a space pipeline and cabin section and space pipeline's installation method relates to space pipeline technical field, space pipeline includes: the circumferential sections of the splicing pipes are arc-shaped rigid pipelines, and the splicing pipes are spliced to form annular pipelines sleeved on the outer wall of the cabin section; the two ends of the spliced pipes are provided with connecting grooves, and two adjacent spliced pipes are fixedly connected through the connecting grooves; and after the splicing of the spliced pipes is completed, the cover plate is fixed in the connecting groove in a sealing manner, so that the annular pipeline is changed into a closed pipeline. The annular pipeline is formed by splicing the splicing pipes at the installation part of the cabin section, so that the technical problem that a finished pipeline cannot be sleeved and installed due to the change of the outer diameter size of the cabin section is avoided, meanwhile, the connecting grooves are formed at the end parts of the splicing pipes, the splicing pipes are welded through the connecting grooves, and then the cover plate is welded on the connecting grooves, so that the pressure-resistant requirement of the normal welding structure can be ensured.
Description
Technical Field
The application belongs to the technical field of aerospace pipelines, and particularly relates to an aerospace pipeline, a cabin section and an installation method of the aerospace pipeline.
Background
Aerospace pipelines are an important component of aerospace products for the transport of fluids or gases. The pipeline is arranged on the cabin section structure and is connected in a welding mode, so that the strength and the tightness of the connection are guaranteed. The pipeline is welded in a combined way under the condition that the space is opened, the angle of the welding gun is not limited, and normal welding can be realized. However, some pipelines are limited by the installation space and need to be laid against the outer wall of the cabin section (or very close to the outer wall of the cabin section), and when in welded connection, the welding gun cannot weld due to the fact that the welding gun does not have an operation space due to the fact that the outer circumference of the joint part of the pipelines is close to one side of the cabin section, and connection realization of the pipelines is affected.
Disclosure of Invention
The application provides a space pipeline, a cabin section and a method for installing the space pipeline, and aims to solve the technical problem that the existing space pipeline is limited by an installation space and is inconvenient to install to at least a certain extent.
In order to solve the technical problems, the application adopts the following technical scheme:
a first aspect of the embodiments of the present application provides an aerospace pipeline, the aerospace pipeline is sleeved on an outer wall of a cabin section, and is used for conveying fluid or gas, and the aerospace pipeline includes: the circumferential sections of the splicing pipes are arc-shaped rigid pipelines, and the splicing pipes are spliced to form annular pipelines sleeved on the outer wall of the cabin section; the two ends of the spliced pipes are provided with connecting grooves, and two adjacent spliced pipes are connected through the connecting grooves; and after the splicing of the spliced pipes is completed, the cover plate is fixed in the connecting groove in a sealing manner, so that the annular pipeline is changed into a closed pipeline.
In some embodiments, the splice tube is provided with two, and the circumferential cross section of the splice tube is semicircular.
In some embodiments, the splice is made of stainless steel or other weldable material.
In some embodiments, the cover plate is made of stainless steel or other weldable material.
A second aspect of embodiments of the present application provides a cabin segment comprising: a cabin body and the aerospace pipeline as claimed in any one of claims 1 to 4, wherein the aerospace pipeline is sleeved on the outer wall of the cabin body.
In some embodiments, a mounting boss is fixed to an outer wall of the cabin body, and the space pipeline is mounted to the mounting boss.
A third aspect of the embodiments of the present application provides a method for installing a space pipeline, including the following steps:
processing the splicing pipe;
sleeving the splicing pipe to the outer wall of the cabin section to form an annular pipeline;
and fixing a cover plate on the connecting groove of the annular pipeline to finish the installation.
In some embodiments, the specific steps of machining the splice are: according to the outer wall size of the cabin section, two or more splicing pipes are arranged, and splicing grooves are processed at two ends of each splicing pipe.
In some embodiments, the specific steps of connecting the splice tube to the outer wall of the cabin segment to form a loop are: the splicing pipes are combined to the installation bosses on the outer wall of the cabin section, the splicing pipes are in butt joint through the connecting grooves, and the adjacent connecting grooves are welded from the inner surfaces of the splicing pipes, so that the connecting sealing is realized among the connecting grooves.
In some embodiments, the specific steps of fixing the cover plate on the connecting groove of the annular pipeline are as follows: and covering the cover plate on the splicing groove to form a whole pipe of the annular pipeline, and then welding and sealing the outer surface of the cover plate to finish the installation.
According to the technical scheme, the application has at least the following advantages and positive effects:
according to the space pipeline, the annular pipeline is formed by splicing the splicing pipes at the installation part of the cabin section, so that the technical problem that a finished pipeline cannot be sleeved in for installation due to the change of the outer diameter and the size of the cabin section is avoided, meanwhile, the connecting grooves are formed at the end parts of the splicing pipes, the splicing pipes are welded through the connecting grooves, the cover plate is welded on the connecting grooves, and the welding accessibility is good, so that the normal pressure-resistant requirement of the welding structure can be guaranteed.
According to the cabin section, the annular pipeline is formed by splicing the splicing pipes at the installation part of the cabin section, the technical problem that a finished pipeline cannot be sleeved in for installation due to the change of the outer diameter size of the cabin section is avoided, meanwhile, the connecting grooves are formed at the end parts of the splicing pipes, the splicing pipes are welded through the connecting grooves, the cover plate is welded on the connecting grooves, the welding accessibility is good, the problem that the whole circumferential welding cannot be achieved due to the fact that the operation space is limited due to the fact that two sections of pipes are directly spliced (namely, the connecting grooves and the cover plate are not arranged) can be solved, and the normal pressure-resistant requirement of a welding structure can be guaranteed in the mode adopted by the application.
According to the installation method of the space pipeline, the annular pipeline is formed by splicing the splicing pipes at the installation part of the cabin section, so that the technical problem that a finished pipeline cannot be sleeved and installed due to the change of the outer diameter size of the cabin section is avoided, meanwhile, the end parts of the splicing pipes are provided with the connecting grooves, the splicing pipes are welded through the connecting grooves, and then the cover plate is welded on the connecting grooves, so that the welding accessibility is good, and the normal pressure-resistant requirement of the welding structure can be ensured.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of the installation of a space pipeline in an embodiment of the present application;
FIG. 2 is a schematic view of a splice of aerospace lines according to an embodiment of the present application;
FIG. 3 is a schematic view of a partial structure of an aerospace pipeline during splicing according to an embodiment of the present application;
FIG. 4 is a schematic structural view of a cover plate of an aerospace pipeline according to an embodiment of the present application;
FIG. 5 is a cross-sectional view of a pod according to an embodiment of the present application;
FIG. 6 is a block flow diagram of a method of installing a space pipeline in an embodiment of the present application.
The reference numerals are explained as follows: 1. a cabin section; 12. a mounting boss; 13. a flange; 2. splicing pipes; 21. a connecting groove; 3. and a cover plate.
Detailed Description
In order to make the present application more clearly understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
Please refer to fig. 1 and 2;
fig. 1 is an installation schematic diagram of an aerospace pipeline in an embodiment of the present application, and fig. 2 is a structural schematic diagram of a splicing pipe of an aerospace pipeline in an embodiment of the present application, as shown in fig. 1 and fig. 2, where the aerospace pipeline is sleeved on an outer wall of a cabin segment 1, and is used for conveying fluid or gas, and the aerospace pipeline includes: the circumferential sections of the splicing pipes 2 are arc-shaped rigid pipelines, and the splicing pipes 2 are spliced to form annular pipelines sleeved on the outer wall of the cabin section 1; the two ends of the spliced pipes 2 are provided with connecting grooves 21, and two adjacent spliced pipes 2 are fixedly connected through the connecting grooves 21; and a cover plate 3, wherein after the splicing of the splicing tube 2 is completed, the cover plate 3 is fixed in the connecting groove 21 in a sealing way so that the annular pipeline becomes a closed pipeline. Through setting up the concatenation of concatenation pipe 2 at the installation site of cabin section 1, form annular pipeline, avoided the finished product pipeline because cabin section 1 external diameter size changes and can't embolia the technical problem of installation from cabin section tip, set up spread groove 21 at each tip of concatenation pipe 2 simultaneously, weld on half circumference in through spread groove 21 between each concatenation pipe 2, weld apron 3 on spread groove 21 again, the welding accessibility is good, can guarantee welded connection requirement and the normal withstand voltage requirement of welded structure.
In some embodiments, two splice tubes 2 are provided, and the circumferential cross section of the splice tubes 2 is semicircular.
In other embodiments, three, four or five splicing pipes 2 may be further disposed, and when connected, a plurality of splicing pipes 2 are spliced to form a ring pipeline.
In some embodiments, the spliced tube 2 and the cover plate 3 are made of stainless steel or other weldable materials, refer to fig. 3, and fig. 3 is a schematic partial structure diagram of a aerospace pipeline in the embodiment of the present application;
as shown in fig. 3, the connecting groove 21 has the shape of only half pipe for the splicing pipe 2, when the two connecting grooves 21 are spliced, the upper surfaces of the spliced parts are welded and fixed in the inner half circumference, and as shown in the figure, the upper surfaces of the spliced parts of the connecting grooves 21 are welded and have good openness, if the two sections of pipes are directly butted without the connecting groove and the cover plate, the two sections of pipes need to be welded on the outer circumference of the pipeline involution, and the welding of the outer circumference of the pipeline involution close to one side of the cabin section cannot be performed due to the limited operation space.
Referring to fig. 4, fig. 4 is a schematic structural diagram of a cover plate 3 of an aerospace pipeline according to an embodiment of the present disclosure;
as shown in fig. 4, in some embodiments, the shape of the cover plate 3 is the same as the shape of the upper half section of the spliced tube 2, and the splice groove is welded and sealed by the cover plate 3 to form a sealed pipeline.
Referring to fig. 5, fig. 5 is a cross-sectional view of a cabin segment 1 according to an embodiment of the present application;
as shown in fig. 5, a second aspect of the embodiments of the present application provides a cabin segment 1, the cabin segment 1 comprising: the main body of the cabin section 1 and the space pipeline are provided with the flanges 13 at the two ends of the cabin section 1, if the space pipeline is formed into a circular ring and then cannot be sleeved at the designated position of the cabin section 1, the space pipeline is used for installation, the technical problem that a finished pipeline cannot be sleeved for installation due to the change of the outer diameter and the size of the cabin section 1 is avoided, meanwhile, the connecting grooves 21 are formed at the end parts of the splicing pipes 2, the splicing pipes 2 are welded through the connecting grooves 21, and then the cover plate 3 is welded on the connecting grooves 21, so that the welding accessibility is good, and the welding connection requirement of a welding structure and the normal pressure resistance requirement can be ensured.
In some embodiments, a mounting boss 12 is fixed on the outer wall of the main body of the cabin section 1, the space pipeline is mounted on the mounting boss 12, and limiting is performed through the mounting boss 12.
Referring to fig. 6, fig. 6 is a flow chart of an installation method of an aerospace pipeline according to an embodiment of the present application.
As shown in fig. 6, a third aspect of the embodiments of the present application provides a method for installing an aerospace pipeline, including the following steps:
s1: machining the splicing pipe 2;
specifically, the specific steps of processing the splicing pipe 2 are as follows: according to the outer wall size of the cabin section 1, two or more sections of splicing pipes 2 are arranged, and splicing grooves are processed at two ends of the splicing pipes 2.
S2: sleeving the splicing pipe 2 on the outer wall of the cabin section 1 to form an annular pipeline;
specifically, the specific steps of sleeving the splicing pipe 2 on the outer wall of the cabin section 1 to form an annular pipeline are as follows: the splicing tubes 2 are combined on the installation boss 12 of the outer wall of the cabin section 1, the splicing tubes 2 are in butt joint through the connecting grooves 21, and the adjacent connecting grooves 21 are welded from the inner half circumference position of the inner surface of the splicing tube 2, so that the connecting sealing between the connecting grooves 21 is realized.
S3: the cover plate 3 is fixed on the connecting groove 21 of the annular pipeline, and the installation is completed.
Specifically, the specific steps of fixing the cover plate 3 on the connecting groove 21 of the annular pipeline are as follows: and covering the cover plate 3 on the splicing groove to form a whole pipe of the annular pipeline, and then welding and sealing the outer surface of the cover plate 3 to finish the installation.
According to the installation method of the space pipeline, the splicing pipes 2 are arranged at the installation part of the cabin section 1 to splice the annular pipeline, so that the technical problem that a finished pipeline cannot be sleeved and installed due to the change of the outer diameter size of the cabin section 1 is solved, meanwhile, the connecting grooves 21 are formed in the end parts of the splicing pipes 2, the splicing pipes 2 are welded through the connecting grooves 21, the cover plate 3 is welded on the connecting grooves 21, the welding accessibility is good, and the welding connection requirement of a welding structure and the normal pressure-resistant requirement after welding can be guaranteed.
According to the technical scheme, the application has at least the following advantages and positive effects:
according to the space pipeline, the annular pipeline is formed by splicing the splicing pipes at the installation part of the cabin section, so that the technical problem that a finished pipeline cannot be sleeved in installation due to the change of the outer diameter size of the cabin section is avoided, meanwhile, the connecting grooves are formed at the end parts of the splicing pipes, the splicing pipes are welded through the connecting grooves, the cover plate is welded on the connecting grooves, and the welding accessibility is good, so that the normal pressure-resistant requirement of the welding structure can be guaranteed.
According to the cabin section, the annular pipeline is formed by splicing the splicing pipes at the installation part of the cabin section, so that the technical problem that a finished pipeline cannot be sleeved in installation due to the change of the outer diameter size of the cabin section is avoided, meanwhile, the connecting grooves are formed at the end parts of the splicing pipes, the splicing pipes are welded through the connecting grooves, the cover plate is welded on the connecting grooves, and the welding accessibility is good, so that the normal pressure-resistant requirement of a welding structure can be guaranteed.
According to the installation method of the space pipeline, the annular pipeline is formed by splicing the splicing pipes at the installation part of the cabin section, so that the technical problem that a finished pipeline cannot be sleeved and installed due to the change of the outer diameter of the cabin section is avoided, meanwhile, the end parts of the splicing pipes are provided with the connecting grooves, the splicing pipes are welded through the connecting grooves, and then the cover plate is welded on the connecting grooves, so that the welding accessibility is good, and the normal pressure-resistant requirement of the welding structure can be ensured.
In this application, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, and may also include the first and second features not being in direct contact but being in contact with each other by way of additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In addition, descriptions such as those related to "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated in this application. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more features. In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
While embodiments of the present application have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the application, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. The utility model provides a space flight pipeline, space flight pipeline cover is located cabin section outer wall for carry out the transmission of fluid or gas, its characterized in that, space flight pipeline includes:
the circumferential sections of the splicing pipes are arc-shaped rigid pipelines, and the splicing pipes are spliced to form annular pipelines sleeved on the outer wall of the cabin section; the two ends of the spliced pipes are provided with connecting grooves, and two adjacent spliced pipes are connected through the connecting grooves;
and after the splicing of the spliced pipes is completed, the cover plate is fixed in the connecting groove in a sealing manner, so that the annular pipeline is changed into a closed pipeline.
2. The space pipeline according to claim 1, wherein two splice tubes are provided, and the circumferential cross section of the splice tubes is semicircular.
3. The aerospace tube of claim 1, wherein the splice tube is made of stainless steel or other weldable material.
4. The space pipeline of claim 1, wherein the cover plate is made of stainless steel or other weldable material.
5. A pod segment, the pod segment comprising: a cabin body and the aerospace pipeline as claimed in any one of claims 1 to 4, wherein the aerospace pipeline is sleeved on the outer wall of the cabin body.
6. The pod according to claim 5, wherein a mounting boss is secured to an outer wall of the pod body, the aerospace tube being mounted to the mounting boss.
7. The installation method of the aerospace pipeline is characterized by comprising the following steps of:
processing the splicing pipe;
sleeving the splicing pipe to the outer wall of the cabin section to form an annular pipeline;
and fixing a cover plate on the connecting groove of the annular pipeline to finish the installation.
8. The method of installing a space pipeline according to claim 7, wherein the specific steps of machining the splice pipe are:
according to the outer wall size of the cabin section, two or more splicing pipes are arranged, and splicing grooves are processed at two ends of each splicing pipe.
9. The method for installing a space pipeline according to claim 7, wherein the specific step of sleeving the splice tube to the outer wall of the cabin section to form an annular pipeline is as follows:
the splicing pipes are combined to the installation bosses on the outer wall of the cabin section, the splicing pipes are in butt joint through the connecting grooves, and the adjacent connecting grooves are welded from the inner surfaces of the splicing pipes, so that the connecting sealing is realized among the connecting grooves.
10. The method for installing an aerospace pipeline according to claim 7, wherein the specific step of fixing the cover plate on the connection groove of the annular pipeline comprises the following steps:
and covering the cover plate on the splicing groove to form a whole pipe of the annular pipeline, and then welding and sealing the outer surface of the cover plate to finish the installation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311692051.0A CN117489866A (en) | 2023-12-11 | 2023-12-11 | Space pipeline, cabin section and installation method of space pipeline |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311692051.0A CN117489866A (en) | 2023-12-11 | 2023-12-11 | Space pipeline, cabin section and installation method of space pipeline |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117489866A true CN117489866A (en) | 2024-02-02 |
Family
ID=89680207
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311692051.0A Pending CN117489866A (en) | 2023-12-11 | 2023-12-11 | Space pipeline, cabin section and installation method of space pipeline |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117489866A (en) |
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2023
- 2023-12-11 CN CN202311692051.0A patent/CN117489866A/en active Pending
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