CN114234836B - Method for assembling large complex sealed cabin structure of space station in part - Google Patents
Method for assembling large complex sealed cabin structure of space station in part Download PDFInfo
- Publication number
- CN114234836B CN114234836B CN202111351748.2A CN202111351748A CN114234836B CN 114234836 B CN114234836 B CN 114234836B CN 202111351748 A CN202111351748 A CN 202111351748A CN 114234836 B CN114234836 B CN 114234836B
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- horizontal plate
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- cabin body
- mounting
- plate
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000000926 separation method Methods 0.000 claims abstract description 16
- 125000006850 spacer group Chemical group 0.000 claims abstract description 11
- 238000012360 testing method Methods 0.000 claims abstract description 6
- 238000001514 detection method Methods 0.000 claims description 12
- 230000003287 optical effect Effects 0.000 claims description 12
- 238000005259 measurement Methods 0.000 claims description 9
- 239000000853 adhesive Substances 0.000 claims description 5
- 230000001070 adhesive effect Effects 0.000 claims description 5
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 238000003698 laser cutting Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 3
- 238000007789 sealing Methods 0.000 abstract 1
- 108010066057 cabin-1 Proteins 0.000 description 11
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 210000004899 c-terminal region Anatomy 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/24—Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes
Abstract
The invention relates to a method for assembling a large complex sealed cabin structure of a space station, which comprises the following steps: a. sequentially installing the cementing support (2), the vertical beam (4) and the angle separation beam system (3) on the cabin body (1); b. mounting a pull rod (7) on the corner spacer system (3); c. and (3) sequentially installing the horizontal plate (5) and the vertical plate (6) on the cabin body (1), and performing a cabin-whole test. The invention can efficiently realize the projects of assembly, debugging, cementing, testing and the like of the cabin body assembly of the large sealing structure.
Description
Technical Field
The invention relates to a method for assembling a large complex sealed cabin structure of a space station.
Background
Space stations are the base for human access to space, and their sealed cabins generally include working cabins and large column sections, etc. The sealed cabin is a place where the astronaut works and lives in the space, and various devices for the astronaut are arranged in the sealed cabin, so that the sealed cabin becomes an important component part in the space station task, and the performance of the sealed cabin directly influences the life safety of the astronaut and the success and failure of the space station task. Sealed enclosures typically have a large number of parts, however, there is no mature set of solutions in the prior art to complete the assembly of these parts.
Disclosure of Invention
The invention aims to provide a method for assembling a large complex sealed cabin structure of a space station.
In order to achieve the above object, the present invention provides a method for assembling a structure of a sealed cabin, comprising the steps of:
a. sequentially installing the cementing support, the vertical beam and the angle separation beam system on the cabin body;
b. mounting the tie rod to the corner spacer beam system;
c. and installing the horizontal plate and the vertical plate on the cabin body in sequence, and performing a cabin-whole test.
According to one aspect of the invention, in said step a, a reference plane of the nacelle is determined and a nacelle coordinate system is established;
for a cementing support arranged on the outer wall of the cabin column section, measuring by utilizing optical detection equipment according to the coordinates of the cementing support, and drawing the contour line of the cementing support on the cabin by taking the cementing support as a line drawing positioning reference;
for the cementing support installed on the inner wall of the cabin column section, the number of the cementing support is more than three in the range of 1500mm multiplied by 1000mm, and the two distances at the outermost end are less than 1500mm multiplied by 1000mm, the contour line is drawn by using a template.
According to one aspect of the invention, drawing a contour line using a template includes the steps of:
manufacturing outline hole sites of the cementing support on the sample plate by using a laser cutting method;
measuring the corresponding position of the cabin body by utilizing optical detection equipment, drawing contour lines of two glue-joint supports to serve as positioning references of a template, and taking the drawn contour lines as positioning references by the rest glue-joint supports, wherein the positioning precision is smaller than 0.3mm;
and positioning the template on the cabin body, and drawing the contour lines of the rest glue-joint supports through contour hole sites on the template.
According to one aspect of the invention, the adhesive support is adhered in the contour line on the cabin by using the adhesive, and the positioning precision of the adhesive support and the contour line is less than 0.3mm.
According to one aspect of the present invention, the gauge is an aluminum alloy sheet having a thickness within 0.3.+ -. 0.1 mm;
the four corners of the sample plate are rounded by R20, and the hole position of the outline hole position is phi 0.3.
According to one aspect of the invention, in the step a, a combined trial-and-fit allowance of 2mm-3mm is reserved on two mounting surfaces of the vertical beam;
performing distance actual measurement on two mounting surfaces of a vertical beam mounting part on the cabin body, and symmetrically processing the two mounting surfaces of the vertical beam according to the actual measurement distance;
the actual distance between the two mounting surfaces of the vertical beam is 0.08mm-0.1mm smaller than the actual distance between the two mounting surfaces of the mounting part of the vertical beam on the cabin.
According to one aspect of the present invention, in the step b, a pin hole of one mounting end of the tie rod is firstly processed, and the end is mounted to the corner spacer beam train;
and the pin hole of the other mounting end of the pull rod is matched with the pin hole on the mounting seat corresponding to the other mounting end of the pull rod, and then the end is mounted.
According to one aspect of the invention, in said step c, the horizontal plate is placed on the nacelle such that the mounting face of the horizontal plate is perpendicular to the axis of the nacelle;
measuring parallelism between the mounting surface of the horizontal plate and the reference surface of the cabin body by using optical detection equipment;
the method comprises the steps of taking a precision measuring point on the plate surface of a horizontal plate, wherein the taking point is located within a range of 40mm away from the plate edge, and each corner takes a point;
the required increased shim thickness was calculated using the formula:
wherein Deltat is the distance from the actual position of the mounting surface of the horizontal plate to the theoretical position, t is the increased thickness of the gasket, x is the width dimension of the horizontal plate, and Deltat is the distance from the lower edge of the horizontal plate to the position of the mounting gasket;
the gasket is added at the position, close to the cabin body datum plane, of the upper end or the lower end of the threaded hole of the horizontal plate;
the method comprises the steps of measuring at the edge of a horizontal plate by utilizing optical detection equipment, taking at least three precision measuring points at the edge of the horizontal plate, balancing out a straight line by utilizing the precision measuring points, evaluating and comparing the straight line with a quadrant line of a cabin body, and adjusting the upper and lower positions of the horizontal plate through a connecting hole position of the horizontal plate and the cabin body.
According to one aspect of the invention, when the precise point is taken on the plate surface of the horizontal plate, a point is taken in the middle of the long side with the length of 1500 mm-2000 mm, a point is taken in the 45-degree direction, and a point is taken in the middle of the short side with the length of less than 1500 mm;
when the edge of the horizontal plate is used for taking the accurate measuring point, two ends are respectively provided with one point, and the middle part is provided with at least one point.
The sealed cabin structure comprises a cabin body, a cementing support, an angle separation beam system, a vertical beam, a horizontal plate, a vertical plate and a pull rod;
the cementing supports are adhered to the cabin body and are discretely distributed in and out of the cabin;
the angle separation beam system, the vertical beam and the horizontal plate are all connected with the cabin body through threaded fasteners;
the vertical plate is connected with the horizontal plate and the vertical beam through threaded fasteners and is positioned between the two layers of horizontal plates;
the pull rod is connected with the angle separation beam system through a threaded fastener, is positioned between the two layers of the angle separation beam systems, and two ends of the pull rod are connected through shaft holes in a matched manner;
the angle separation beam is a V-shaped angle separation beam system and is provided with a cabinet adapter.
According to the conception of the invention, the assembly method of the structure part of the sealed cabin body is provided to solve the difficult problems of low mixing efficiency of multiple items such as assembly, debugging, gluing, testing and the like of the assembly of the structure part of the large sealed cabin body, realize digital adjustment in the assembly process, and can timely check the problems in the assembly process so as to improve the production efficiency and shorten the development period. The invention can be applied to space missions such as deep space exploration, manned lunar climbing and the like, and has good application prospect and economic benefit.
Drawings
FIG. 1 schematically illustrates a flow chart of a method of assembling a sealed enclosure structure according to one embodiment of the invention;
FIG. 2 is a schematic view showing the constitution of a sealed capsule according to an embodiment of the present invention;
FIG. 3 schematically illustrates a block diagram of a template in accordance with one embodiment of the present invention;
FIG. 4 is a schematic view showing a construction of a vertical beam according to an embodiment of the present invention;
FIG. 5 schematically illustrates an assembly and disassembly of a vertical beam in accordance with one embodiment of the present invention;
FIG. 6 schematically illustrates a drawbar assembly according to an embodiment of the invention;
FIG. 7 schematically illustrates a horizontal plate assembly layout of one embodiment of the present invention;
FIG. 8 schematically illustrates a horizontal plate fine survey point location map of one embodiment of the present invention;
fig. 9 schematically shows a horizontal plate sizing diagram according to an embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
In describing embodiments of the present invention, the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in terms of orientation or positional relationship shown in the drawings for convenience of description and simplicity of description only, and do not denote or imply that the devices or elements in question must have a particular orientation, be constructed and operated in a particular orientation, so that the above terms are not to be construed as limiting the invention.
The present invention will be described in detail below with reference to the drawings and the specific embodiments, which are not described in detail herein, but the embodiments of the present invention are not limited to the following embodiments.
Referring to fig. 1 and 2, the assembly method of the large complex sealed cabin structure part of the space station of the invention firstly establishes a cabin coordinate system by taking the A surface of the cabin 1 as a reference surface, and installs a cementing support 2 on the cabin 1. Then, the mounting surface of the vertical beam 4 is processed, and the vertical beam 4 is mounted on the cabin 1. The corner spacer system 3 is then mounted to the hull 1 and the tie rods 7 are mounted to the corner spacer system 3. Subsequently, a horizontal plate 5 is mounted on the cabin 1, and the parallelism of the horizontal plate 5 and the reference surface of the cabin 1 is adjusted. The vertical plate 6 is mounted on the cabin body 1, and the whole cabin test is performed.
In the invention, the assembly and debugging process of the cementing support 2 and the cabin body 1 is divided into two steps, namely drawing the contour line of the cementing support 2 and installing the cementing support 2. In the step of drawing the contour line, auxiliary accurate measurement is needed for the glue-joint support 2 arranged on the outer wall of the column section of the cabin body 1 by utilizing optical detection equipment, mainly the measurement is carried out according to the coordinate data of each glue-joint support 2, and the contour line of the glue-joint support 2 is drawn at the corresponding position on the cabin body 1 by taking a real object of the glue-joint support 2 as a drawing line positioning reference. For the cementing support 2 arranged on the inner wall of the column section of the cabin body 1, the number of the cementing support is more than three in the range of 1500mm multiplied by 1000mm, and the two distances at the outermost end are less than 1500mm multiplied by 1000mm, the coordinate points are relatively close, so that the contour lines are drawn by using the template 8 for assisting in drawing the contour lines.
As shown in fig. 3, when the template 8 is used to draw the contour line, the contour hole sites of all the positions of the glue joint support 2 in the range are manufactured on the template 8 by adopting a laser cutting method according to the coordinate points. And then carrying out auxiliary accurate measurement on the corresponding position of the cabin body 1 by utilizing optical detection equipment, drawing out contour lines of the two glue-bonded supports 2 to serve as positioning references of the template 8, wherein the rest glue-bonded supports 2 in the position range take the drawn contour lines as the positioning references, and the positioning precision is better than (smaller than) 0.3mm. And positioning the template 8 on the cabin body 1, and drawing the contour lines of the rest glue-joint supports 2 through the contour hole sites of the glue-joint supports 2 on the template 8. Wherein, the template 8 is an aluminum alloy plate with the thickness within 0.3+/-0.1 mm, four corners of the aluminum alloy plate are rounded by R20, and the hole position of the profile hole position is phi 0.3.
After the drawing of the contour line is completed, the cementing support 2 can be stuck in the contour line on the bulkhead of the cabin body 1 by using the adhesive. In the invention, the positioning precision of the cementing support 2 and the contour line is better than 0.3mm.
Referring to fig. 4 and 5, the vertical beam 4 and the cabin 1 are processed and assembled by adopting a combined trial-and-fit method. In the component state (i.e., the uninstalled state), a combined trial fit allowance of 2mm to 3mm should be provided on both installation surfaces (i.e., the a surface and the B surface) of the vertical beam 4. The distance between the two mounting surfaces of the vertical beam mounting part on the cabin body 1 is actually measured by a tool, and the two mounting surfaces of the vertical beam 4 are symmetrically processed according to the actually measured distance, so that the actual distance between the two mounting surfaces of the vertical beam 4 is 0.08mm-0.1mm smaller than the actual distance between the two mounting surfaces of the vertical beam mounting part on the cabin body 1, and the vertical beam 4 and the cabin body 1 can be assembled after the processing is finished.
Referring to fig. 6, the tie rod 7 and the corner spacer system 3 are assembled and adjusted in a combined and trial manner. Specifically, in the part machining process, the pin hole of one mounting end (i.e., the C-end) of the tie rod 7 is machined first, while the pin hole of the other mounting end (the D-end) is not machined. Subsequently, the C-terminal is mounted to the corner spacer 3. And then, the D end is subjected to trial matching, namely, the pin hole of the D end is matched through the pin hole on the mounting seat H corresponding to the D end, and then the D end is mounted.
Referring to fig. 7 to 9, the assembly and debugging process of the horizontal plate 5 and the cabin 1 is divided into two steps, namely, the debugging of the plate surface parallelism and the edge parallelism. Specifically, the horizontal plate 5 is placed at a corresponding position on the cabin 1, and the mounting surface (D surface) of the horizontal plate 5 is perpendicular to the axis of the cabin 1 (coarse adjustment by visual inspection may be adopted). And then the parallelism between the mounting surface of the horizontal plate 5 and the reference surface of the cabin body 1 is accurately detected in an auxiliary manner by using optical detection equipment. The precise point G is taken on the plate surface of the horizontal plate 5, the point is within 40mm from the plate edge, and each corner is taken at one point. Specifically, one point can be taken at the middle part of a long side with the length of 1500 mm-2000 mm, one point can be taken at each 45 DEG direction (based on the long side), and one point can be taken at the middle part of a short side with the length of less than 1500 mm. After the distance delta t from the actual position to the theoretical position of the horizontal plate mounting surface is obtained, the thickness of the gasket to be increased can be calculated by using the following formula by combining the width dimension x of the horizontal plate 5:
wherein Δt is the distance from the actual position to the theoretical position of the mounting surface of the horizontal plate 5, t is the increased thickness of the gasket, x is the width dimension of the horizontal plate 5, and Δx is the distance from the lower edge of the horizontal plate 5 to the position where the gasket is mounted. Then, if the upper end surface of the horizontal plate 5 is close to the reference surface of the cabin 1, a gasket with corresponding thickness is added at the position of the upper end of the threaded hole of the horizontal plate 5 close to the reference surface of the cabin 1; if the upper end surface of the horizontal plate 5 is far away from the reference surface of the cabin body 1, a gasket with corresponding thickness is added at the position where the lower end of the threaded hole of the horizontal plate 5 is close to the reference surface of the cabin body 1.
Then, auxiliary accurate measurement is performed on the edge of the horizontal plate 5 by utilizing optical detection equipment, at least three accurate measurement points G are taken on the edge of the horizontal plate 5, and specifically, one point can be taken at each of two ends, and at least one point is taken in the middle. A straight line can be balanced by utilizing the precision measuring points, and is compared with the II-IV/I-III quadrant line of the cabin body 1 by the evaluation ratio, and the upper and lower positions of the horizontal plate 5 are adjusted by the connecting hole positions of the horizontal plate 5 and the cabin body 1, so that the adjustment of the parallelism is realized.
As shown in fig. 2, the sealed cabin structure comprises a cabin body 1, a cementing support 2, an angle beam system 3, a vertical beam 4, a horizontal plate 5, a vertical plate 6 and a pull rod 7. The cementing supports 2 are adhered to the cabin body 1 and are distributed in the cabin and outside the cabin, and the coordinates of the centers of the cementing supports 2 on the cabin body 1 are (x 1, y1, z1 … … xn, yn, zn). The angle beam system 3, the vertical beam 4 and the horizontal plate 5 are all connected with the cabin body 1 through threaded fasteners. The parallelism of the mounting surface of the horizontal plate 5 and the reference surface of the cabin body 1 is t1, and the parallelism of the upper edge of the horizontal plate 5 and the central quadrant line of the cabin body 1 is t2. The vertical plate 6 is connected with the horizontal plate 5 and the vertical beam 4 through threaded fasteners and is positioned between the two layers of horizontal plates 5. The pull rod 7 is connected with the corner separation beam system 3 through a threaded fastener and is positioned between the two layers of corner separation beam systems 3, and two ends of the pull rod are connected through shaft holes in a matching mode. The corner spacer system 3 is a V-shaped corner spacer system and has a cabinet adapter with a hole position of phi m.
The above description is only one embodiment of the present invention and is not intended to limit the present invention, and various modifications and variations of the present invention will be apparent to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A part assembly method of a large complex sealed cabin structure of a space station comprises the following steps:
a. sequentially installing the cementing support (2), the vertical beam (4) and the angle separation beam system (3) on the cabin body (1);
b. mounting a pull rod (7) on the corner spacer system (3);
c. the horizontal plate (5) and the vertical plate (6) are sequentially installed on the cabin body (1), and the whole cabin test is carried out;
in the step a, a reference plane of the cabin (1) is determined and a cabin coordinate system is established;
for a cementing support (2) arranged on the outer wall of a column section of the cabin body (1), measuring by utilizing optical detection equipment according to the coordinates of the cementing support (2), and drawing the contour line of the cementing support (2) on the cabin body (1) by taking the cementing support (2) as a line drawing positioning reference;
for the cementing support (2) arranged on the inner wall of the column section of the cabin body (1), the number of the cementing support is more than three in the range of 1500mm multiplied by 1000mm, and the two distances at the outermost end are less than 1500mm multiplied by 1000mm, the contour line is drawn by using the template (8).
2. A method according to claim 1, characterized in that drawing the contour line with a template (8) comprises the steps of:
manufacturing outline hole sites of the cementing support (2) on the template (8) by utilizing a laser cutting method;
measuring the corresponding position of the cabin body (1) by utilizing optical detection equipment, drawing contour lines of two glue-joint supports (2) to serve as positioning references of a template (8), and taking the drawn contour lines of the rest glue-joint supports (2) as positioning references, wherein the positioning precision is smaller than 0.3mm;
and positioning the template (8) on the cabin body (1), and drawing the contour lines of the rest glue-joint supports (2) through contour hole sites on the template (8).
3. Method according to claim 1 or 2, characterized in that the glue-bonded support (2) is glued in the contour line on the cabin (1) with an adhesive, the positioning accuracy of the glue-bonded support (2) and the contour line being less than 0.3mm.
4. A method according to claim 3, characterized in that the template (8) is an aluminium alloy plate with a thickness of within 0.3 ± 0.1 mm;
four corners of the sample plate (8) are rounded by R20, and the hole site degree of the contour hole site is phi 0.3.
5. Method according to claim 1, characterized in that in said step a, a combined trial-and-fit allowance of 2-3 mm is reserved at both mounting faces of the vertical beams (4);
performing distance actual measurement on two mounting surfaces of a vertical beam mounting part on the cabin body (1), and symmetrically processing the two mounting surfaces of the vertical beam (4) according to the actual measurement distance;
the actual distance between the two mounting surfaces of the vertical beam (4) is 0.08mm-0.1mm smaller than the actual distance between the two mounting surfaces of the vertical beam mounting part on the cabin body (1).
6. A method according to claim 1, characterized in that in said step b, the pin hole of one mounting end of the tie rod (7) is first machined and this end is mounted to the corner spacer system (3);
and a pin hole at the other mounting end of the pull rod (7) is matched with a pin hole on a mounting seat corresponding to the other mounting end of the pull rod (7), and then the end is mounted.
7. Method according to claim 1, characterized in that in said step c a horizontal plate (5) is placed on the nacelle (1) with the mounting surface of the horizontal plate (5) perpendicular to the axis of the nacelle (1);
measuring parallelism between the mounting surface of the horizontal plate (5) and the reference surface of the cabin (1) by using optical detection equipment;
the precise measuring point is taken on the plate surface of the horizontal plate (5), the point taking point is within 40mm from the plate edge, and each corner takes one point;
the required increased shim thickness was calculated using the formula:
wherein Deltat is the distance from the actual position to the theoretical position of the mounting surface of the horizontal plate (5), t is the increased thickness of the gasket, x is the width dimension of the horizontal plate (5), and Deltat is the distance from the lower edge of the horizontal plate (5) to the position of the mounting gasket;
the gasket is added at the position of the upper end or the lower end of the threaded hole of the horizontal plate (5) close to the reference surface of the cabin body (1);
the method comprises the steps of measuring at the edge of a horizontal plate (5) by utilizing optical detection equipment, taking at least three precise measuring points at the edge of the horizontal plate (5), balancing out a straight line by utilizing the precise measuring points, evaluating and comparing the straight line with a quadrant line of a cabin body (1), and adjusting the upper and lower positions of the horizontal plate (5) through a connecting hole site of the horizontal plate (5) and the cabin body (1).
8. A method according to claim 7, wherein when the accurate measuring point is taken on the plate surface of the horizontal plate (5), a point is taken in the middle of the long side with the length of 1500 mm-2000 mm, a point is taken in the 45-degree direction, and a point is taken in the middle of the short side with the length of less than 1500 mm;
when the edge of the horizontal plate (5) is used for taking the precision measuring point, two ends are respectively provided with one point, and the middle part is provided with at least one point.
9. A sealed cabin structure assembled by the assembly method of the sealed cabin structure part of any one of claims 1-8, characterized by comprising a cabin (1), a cementing support (2), an angle beam system (3), a vertical beam (4), a horizontal plate (5), a vertical plate (6) and a pull rod (7);
the cementing support (2) is adhered to the cabin body (1) and is discretely distributed in and out of the cabin;
the angle separation beam system (3), the vertical beam (4) and the horizontal plate (5) are connected with the cabin body (1) through threaded fasteners;
the vertical plate (6) is connected with the horizontal plate (5) and the vertical beam (4) through threaded fasteners and is positioned between the two layers of horizontal plates (5);
the pull rod (7) is connected with the corner separation beam system (3) through a threaded fastener, and is positioned between the two layers of the corner separation beam systems (3), and two ends of the pull rod are connected through shaft holes in a matched mode;
the angle separation beam system (3) is a V-shaped angle separation beam system and is provided with a cabinet adapter.
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| CN202111351748.2A CN114234836B (en) | 2021-11-16 | 2021-11-16 | Method for assembling large complex sealed cabin structure of space station in part |
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| CN202111351748.2A CN114234836B (en) | 2021-11-16 | 2021-11-16 | Method for assembling large complex sealed cabin structure of space station in part |
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