Space pipeline and cabin section and installation method of space pipeline

Abstract

The application discloses a space pipeline and a cabin section and a mounting method of the space pipeline, relates to the technical field of space pipelines, and comprises at least two spliced pipes, the circumferential section of the spliced pipe is an arc-shaped rigid pipe, and the spliced pipes are spliced to form an annular pipeline which is sleeved on the outer wall of the cabin section; the two end portions of the spliced pipe are provided with connecting grooves, and adjacent two spliced pipes are fixedly connected through the connecting grooves; and a cover plate is sealed and fixed in the connecting groove after the spliced pipes are spliced, so that the annular pipeline becomes a closed pipeline. The annular pipeline is formed by splicing the spliced pipes at the mounting positions of the cabin section, the technical problem that a finished pipeline cannot be sleeved and mounted due to the change of the outer diameter size of the cabin section is avoided, meanwhile, the connecting grooves are arranged at the end portions of the spliced pipes, the spliced pipes are welded through the connecting grooves, and the cover plate is welded on the connecting grooves, so that the normal pressure resistance requirement of the welded structure can be ensured.

Description

Technical Field

[0001] This application belongs to the field of aerospace piping technology, specifically relating to an aerospace piping and module and an installation method for the aerospace piping. Background Technology

[0002] Aerospace piping is a crucial component of aerospace products, used for the transport of fluids or gases. Piping is installed on the module structure and connected by welding, which helps ensure the strength and sealing of the connection. In open spaces, piping can be assembled and welded without restrictions on the angle of the welding torch, allowing for normal welding. However, some piping is limited by installation space and needs to be laid close to (or against) the outer wall of the module. During welding, the side of the outer circumference of the mating part of the piping closest to the module is too close for the welding torch to operate within, making welding impossible and affecting the successful connection. Summary of the Invention

[0003] This application provides a space pipeline and module, as well as a method for installing the space pipeline, which aims to at least partially solve the technical problem that the current space pipeline is inconvenient to install due to space limitations.

[0004] To solve the above-mentioned technical problems, this application adopts the following technical solution:

[0005] A first aspect of this application provides an aerospace pipeline, which is fitted onto the outer wall of a cabin section for the transmission of fluids or gases. The aerospace pipeline includes: at least two splicing pipes, each splicing pipe having a rigid pipe with an arc-shaped circumferential cross-section, the splicing pipes being spliced ​​together to form an annular pipeline fitted onto the outer wall of the cabin section; connecting grooves are provided at both ends of the splicing pipes, and adjacent splicing pipes are connected through the connecting grooves; and a cover plate, which is sealed and fixed to the connecting grooves after the splicing pipes are assembled, so that the annular pipeline becomes a closed pipeline.

[0006] In some embodiments, there are two splicing pipes, and the circumferential cross-section of the splicing pipes is semi-circular.

[0007] In some embodiments, the splicing pipe is made of stainless steel or other weldable materials.

[0008] In some embodiments, the cover plate is made of stainless steel or other weldable materials.

[0009] A second aspect of this application provides a module, the module comprising: a module body and a space pipeline as described in any one of claims 1 to 4, the space pipeline being sleeved on the outer wall of the module body.

[0010] In some embodiments, a mounting boss is fixed on the outer wall of the main body of the module, and the aerospace pipeline is installed on the mounting boss.

[0011] A third aspect of this application provides a method for installing aerospace piping, comprising the following steps:

[0012] Processing and splicing pipes;

[0013] The splicing pipe is connected to the outer wall of the compartment to form a ring-shaped pipeline;

[0014] Fix the cover plate onto the connecting groove of the ring pipeline to complete the installation.

[0015] In some embodiments, the specific steps of processing the splicing pipe are as follows: according to the outer wall size of the compartment, two or more splicing pipes are set, and splicing grooves are processed at both ends of the splicing pipes.

[0016] In some embodiments, the specific steps of connecting the splicing pipe to the outer wall of the compartment to form a ring pipeline are as follows: the splicing pipe is assembled onto the mounting boss on the outer wall of the compartment, the splicing pipes are connected by connecting grooves, and the adjacent connecting grooves are welded from the inner surface of the splicing pipes to achieve a connection seal between the connecting grooves.

[0017] In some embodiments, the specific steps for fixing the cover plate on the connecting groove of the annular pipeline are as follows: placing the cover plate on the splicing groove to form a complete annular pipeline, and then welding and sealing it from the outer surface of the cover plate to complete the installation.

[0018] As can be seen from the above technical solution, this application has at least the following advantages and positive effects:

[0019] This application discloses an aerospace pipeline system that uses splicing pipes to form a ring pipeline at the installation location of the cabin section. This avoids the technical problem that finished pipelines cannot be fitted into the installation due to changes in the outer diameter of the cabin section. At the same time, connecting grooves are provided at the ends of each splicing pipe, and the splicing pipes are welded together through the connecting grooves. Then, cover plates are welded on the connecting grooves, which ensures good weldability and guarantees the normal pressure resistance requirements of the welded structure.

[0020] One type of compartment in this application uses splicing pipes to form a ring-shaped pipeline at the installation location of the compartment. This avoids the technical problem that finished pipelines cannot be fitted into the installation due to changes in the outer diameter of the compartment. At the same time, connecting grooves are provided at the ends of each splicing pipe, and the splicing pipes are welded together through the connecting grooves. Then, cover plates are welded on the connecting grooves. The welding accessibility is good, which can solve the problem that it is impossible to achieve full circumferential welding when directly splicing two pipe sections (i.e. without connecting grooves and cover plates) due to limited operating space. Moreover, the method adopted in this application can ensure the normal pressure resistance requirements of the welded structure.

[0021] This application discloses an installation method for aerospace pipelines. By setting splicing pipes at the installation location of the cabin section to form a ring pipeline, it avoids the technical problem that finished pipelines cannot be fitted into the installation due to changes in the outer diameter of the cabin section. At the same time, a connecting groove is set at the end of each splicing pipe, and the splicing pipes are welded together through the connecting groove. Then, a cover plate is welded on the connecting groove. The welding accessibility is good, which can ensure the normal pressure resistance requirements of the welded structure. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the installation of an aerospace pipeline according to an embodiment of this application;

[0024] Figure 2 This is a schematic diagram of the structure of a splicing pipe for aerospace pipelines in an embodiment of this application;

[0025] Figure 3 This is a partial structural diagram of an aerospace pipeline during splicing, as described in an embodiment of this application.

[0026] Figure 4 This is a schematic diagram of the structure of a cover plate for an aerospace pipeline in an embodiment of this application;

[0027] Figure 5 This is a cross-sectional view of one compartment in an embodiment of this application;

[0028] Figure 6 This is a flowchart illustrating an installation method for aerospace piping in an embodiment of this application.

[0029] The reference numerals in the attached drawings are explained as follows: 1. Compartment; 12. Mounting boss; 13. Flange; 2. Splicing pipe; 21. Connecting groove; 3. Cover plate. Detailed Implementation

[0030] To enable those skilled in the art to more clearly understand this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0031] Please see Figure 1 and Figure 2 ;

[0032] Figure 1 This is a schematic diagram of the installation of an aerospace pipeline according to an embodiment of this application. Figure 2 This is a schematic diagram of the structure of a splicing pipe for aerospace pipelines in an embodiment of this application, as shown below. Figure 1 and Figure 2 As shown, the aerospace pipeline is fitted onto the outer wall of section 1 for the transmission of fluids or gases. The aerospace pipeline includes: at least two splicing pipes 2, each with a rigid, arc-shaped circumferential cross-section, joined to form an annular pipeline fitted onto the outer wall of section 1; connecting grooves 21 at both ends of each splicing pipe 2, with adjacent splicing pipes 2 fixedly connected via these grooves; and a cover plate 3, which, after the splicing of the splicing pipes 2 is completed, seals and fixes them to the connecting grooves 21, thus transforming the annular pipeline into a closed pipeline. By splicing the splicing pipes 2 at the installation location of section 1 to form an annular pipeline, the technical problem of finished pipelines being unable to be fitted into the end of section 1 due to changes in the outer diameter of section 1 is avoided. Furthermore, connecting grooves 21 are provided at the ends of each splicing pipe 2, and the splicing pipes 2 are welded together on the inner semicircle via these grooves. The cover plate 3 is then welded onto the connecting grooves 21, ensuring good weld accessibility and guaranteeing the welding connection requirements and normal pressure resistance requirements of the welded structure.

[0033] In some embodiments, there are two splicing pipes 2, and the circumferential cross-section of the splicing pipe 2 is semi-circular.

[0034] In other embodiments, three, four, or five splicing pipes 2 may be provided, and multiple splicing pipes 2 may be spliced ​​together to form a ring pipeline when connected.

[0035] In some embodiments, the splicing pipe 2 and the cover plate 3 are made of stainless steel or other weldable materials. (See also...) Figure 3 , Figure 3 This is a partial structural diagram of an aerospace pipeline during splicing, as described in an embodiment of this application.

[0036] like Figure 3 As shown, the connecting groove 21 is the shape of the splicing pipe 2, which only retains the lower half of the pipe. During splicing, the ends of the two connecting grooves 21 are spliced ​​together, and then the upper surface of the splicing part is welded and fixed in the inner semicircle. As can be seen from the figure, the welding on the upper surface of the splicing part of the connecting groove 21 has good openness. If the two pipe sections do not have connecting grooves and cover plates and are directly connected, welding will be required on the outer circumference of the pipes. Due to the limited operating space, welding on the side of the outer circumference of the pipes near the compartment section cannot be carried out.

[0037] Please see Figure 4 , Figure 4This is a schematic diagram of the structure of a cover plate 3 for an aerospace pipeline in an embodiment of this application;

[0038] like Figure 4 As shown, in some embodiments, the shape of the cover plate 3 is the same as the shape of the upper half of the splicing pipe 2, and the splicing groove is welded and sealed by the cover plate 3 to form a sealed pipeline.

[0039] Please see Figure 5 , Figure 5 This is a cross-sectional view of one of the compartments 1 in an embodiment of this application;

[0040] like Figure 5 As shown, a second aspect of this application provides a module 1, which includes a module 1 body and the aforementioned aerospace piping. Since flanges 13 are provided at both ends of the module 1, if the aerospace piping is formed into a ring, it cannot be fitted into the designated position of the module 1. Therefore, the aforementioned aerospace piping is used for installation, avoiding the technical problem that the finished piping cannot be fitted into the module due to changes in the outer diameter of the module 1. At the same time, a connecting groove 21 is provided at the end of each splicing pipe 2, and each splicing pipe 2 is welded together through the connecting groove 21. Then, a cover plate 3 is welded on the connecting groove 21, which has good weldability and can ensure the welding connection requirements and normal pressure resistance requirements of the welded structure.

[0041] In some embodiments, a mounting boss 12 is fixed on the outer wall of the main body of the compartment 1, and the aerospace pipeline is installed on the mounting boss 12 and is limited by the mounting boss 12.

[0042] Please see Figure 6 , Figure 6 This is a flowchart illustrating an installation method for aerospace piping in an embodiment of this application.

[0043] like Figure 6 As shown, a third aspect of this application provides a method for installing aerospace piping, comprising the following steps:

[0044] S1: Processing and splicing pipe 2;

[0045] Specifically, the specific steps for processing the splicing pipe 2 are as follows: according to the outer wall dimensions of the compartment 1, two or more splicing pipe sections 2 are set, and splicing grooves are processed at both ends of the splicing pipe 2.

[0046] S2: Connect splicing pipe 2 to the outer wall of compartment 1 to form a ring pipeline;

[0047] Specifically, the steps for attaching the splicing pipe 2 to the outer wall of the compartment 1 to form a ring pipeline are as follows: the splicing pipe 2 is assembled onto the mounting boss 12 on the outer wall of the compartment 1, and the splicing pipes 2 are connected to each other through the connecting groove 21. The adjacent connecting grooves 21 are welded from the inner semi-circular position of the inner surface of the splicing pipe 2 to achieve a connection and seal between the connecting grooves 21.

[0048] S3: Fix the cover plate 3 on the connecting groove 21 of the annular pipeline to complete the installation.

[0049] Specifically, the steps for fixing the cover plate 3 on the connecting groove 21 of the annular pipeline are as follows: cover the cover plate 3 onto the splicing groove so that the annular pipeline forms a complete pipe, and then weld and seal it from the outer surface of the cover plate 3 to complete the installation.

[0050] This application discloses an installation method for aerospace pipelines. By setting splicing pipes 2 at the installation location of the compartment 1 to form a ring pipeline, the technical problem of finished pipelines being unable to be fitted and installed due to changes in the outer diameter of the compartment 1 is avoided. At the same time, connecting grooves 21 are set at the ends of each splicing pipe 2, and the splicing pipes 2 are welded together through the connecting grooves 21. Then, cover plates 3 are welded on the connecting grooves 21. The welding accessibility is good, which can ensure the welding connection requirements of the welded structure and the normal pressure resistance requirements after welding.

[0051] As can be seen from the above technical solution, this application has at least the following advantages and positive effects:

[0052] This application discloses an aerospace pipeline system that uses splicing pipes to form a ring pipeline at the installation location of the cabin section. This avoids the technical problem that finished pipelines cannot be fitted into the installation due to changes in the outer diameter of the cabin section. At the same time, connecting grooves are provided at the ends of each splicing pipe, and the splicing pipes are welded together through the connecting grooves. Then, cover plates are welded on the connecting grooves, which provides good weld accessibility and ensures that the welded structure meets the normal pressure resistance requirements.

[0053] One type of compartment in this application uses splicing pipes to form a ring pipeline at the installation location of the compartment, which avoids the technical problem that the finished pipeline cannot be fitted into the installation due to changes in the outer diameter of the compartment. At the same time, a connecting groove is set at the end of each splicing pipe, and the splicing pipes are welded together through the connecting groove. Then, a cover plate is welded on the connecting groove, which has good weld accessibility and can ensure the normal pressure resistance requirements of the welded structure.

[0054] This application discloses an installation method for aerospace pipelines. By setting splicing pipes at the installation location of the cabin section to form a ring pipeline, it avoids the technical problem that the finished pipeline cannot be fitted into the installation due to changes in the outer diameter of the cabin section. At the same time, a connecting groove is set at the end of each splicing pipe, and the splicing pipes are welded together through the connecting groove. Then, a cover plate is welded on the connecting groove. The welding accessibility is good, which can ensure the normal pressure resistance requirements of the welded structure.

[0055] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0056] Furthermore, the use of terms such as "first" and "second" in this application is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, features defined with "first" or "second" may explicitly or implicitly include one or more features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0057] Although embodiments of this application have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the claims and their equivalents.

Claims

1. A spacecraft piping system, wherein the spacecraft piping system is sleeved on the outer wall of a cabin section for the transmission of fluids or gases, characterized in that, The aerospace piping includes: At least two splicing pipes, the splicing pipes having a circumferential cross-section of an arc-shaped rigid pipe, the splicing pipes being spliced ​​together to form an annular pipeline fitted onto the outer wall of the compartment; the two ends of the splicing pipes are provided with connecting grooves, and adjacent splicing pipes are connected through the connecting grooves; The cover plate is used to seal and fix the splicing pipe to the connecting groove after the splicing is completed, so that the annular pipeline becomes a closed pipeline. The circumferential cross-section of the splicing pipe is semi-circular, and the splicing pipes are welded together on the inner semi-circle through connecting grooves.

2. The aerospace piping according to claim 1, characterized in that, The splicing pipe has two parts.

3. The aerospace piping according to claim 1, characterized in that, The splicing pipe is made of stainless steel or other weldable materials.

4. The aerospace piping according to claim 1, characterized in that, The cover plate is made of stainless steel or other weldable materials.

5. A compartment, characterized in that, The module includes: a module body and aerospace piping as described in any one of claims 1 to 4, wherein the aerospace piping is sleeved on the outer wall of the module body.

6. The compartment according to claim 5, characterized in that, The outer wall of the main body of the compartment is fixed with a mounting boss, and the aerospace pipeline is installed on the mounting boss.

7. The installation method for aerospace piping according to claim 1, characterized in that, Includes the following steps: Processing and splicing pipes; The splicing pipe is connected to the outer wall of the compartment to form a ring-shaped pipeline; Fix the cover plate onto the connecting groove of the ring pipeline to complete the installation.

8. The method for installing aerospace piping according to claim 7, characterized in that, The specific steps for processing and splicing the tubing are as follows: Depending on the outer wall dimensions of the compartment, two or more splicing pipes are installed, and splicing grooves are machined at both ends of the splicing pipes.

9. The method for installing aerospace piping according to claim 7, characterized in that, The specific steps for attaching the splicing pipe to the outer wall of the compartment to form a ring-shaped pipeline are as follows: The splicing pipes are assembled onto the mounting bosses on the outer wall of the compartment. The splicing pipes are connected by connecting grooves, and the adjacent connecting grooves are welded from the inner surface of the splicing pipes to achieve a connection and seal between the connecting grooves.

10. The method for installing aerospace piping according to claim 7, characterized in that, The specific steps for fixing the cover plate on the connecting groove of the annular pipeline are as follows: Place the cover plate onto the splicing groove to form a complete ring pipe, and then weld and seal it from the outer surface of the cover plate to complete the installation.

Images