Satellite deck multifunctional auxiliary tool and satellite deck testing method

Abstract

The invention relates to a satellite deck multifunctional auxiliary tool and a satellite deck testing method.The satellite deck multifunctional auxiliary tool comprises a base platform, a lifting mechanism, a turnover driving mechanism, a cross-shaped sliding table, a bottom support and a profiling supporting frame, and the lifting mechanism is installed on the base platform in a left-right moving mode through a translation mechanism; the bottom support is hinged to the top lifting end of the lifting mechanism through a first hinge shaft, the bottom of the cross-shaped sliding table is installed on the bottom support, the profiling supporting frame is fixed to the top of the cross-shaped sliding table and can move front and back and left and right under driving of the cross-shaped sliding table, and the first hinge shaft extends in the front-back direction; the two ends of the turnover driving mechanism are hinged to the bottom of the cross-shaped sliding table and the top lifting end of the lifting mechanism respectively, and the turnover driving mechanism is used for driving the bottom support, the cross-shaped sliding table and the profiling supporting frame to turn over or reset around the first hinge shaft towards one side of the lifting mechanism.

Description

Technical Field

[0001] This invention relates to the field of spacecraft manufacturing and assembly technology, specifically to a multi-functional auxiliary tooling for satellite panels and a method for testing satellite panels. Background Technology

[0002] During satellite assembly, various instrument panels need to be frequently assembled with the satellite body for electrical performance testing. After testing or when problems are discovered, they need to be disassembled for troubleshooting or maintenance. Traditional operating methods require that each panel be fully installed onto the body structure using formal connectors (such as aerospace-grade bolts) for each test. This process has the following significant drawbacks: 1. Low operational efficiency: Each assembly and disassembly requires tightening and loosening of a large number of high-precision fasteners, which consumes a lot of manpower and time, and seriously restricts the overall assembly progress.

[0003] 2. Significant quality risks: Cable connectors and plugs are prone to signal attenuation, poor contact, or even physical damage due to mechanical wear during repeated plugging and unplugging; repeated disassembly and assembly of fasteners can easily cause thread wear and inaccurate preload, affecting the reliability of the final connection.

[0004] 3. High safety risks: The hatch panels themselves are heavy and valuable. During manual handling, flipping and positioning, there is a risk of bumping and damaging the hatch panels or the precision equipment inside the cabin, and there is also a safety threat to the operators.

[0005] Therefore, there is an urgent need in this field for a special auxiliary tooling that can enable rapid, accurate, and safe temporary positioning and engagement of the panel, and support testing and troubleshooting in an informal installation state. Summary of the Invention

[0006] In order to solve one or more technical problems existing in the prior art, the present invention provides a multifunctional auxiliary tooling for satellite panels and a method for testing satellite panels.

[0007] The technical solution of this invention to solve the above-mentioned technical problems is as follows: This invention provides a multi-functional auxiliary tooling for satellite cabin panels, including a base platform, a lifting mechanism, a flipping drive mechanism, a cross slide, a bottom support, and a contouring support frame. The lifting mechanism is mounted on the base platform and can move left and right via a translation mechanism. The bottom support is hinged to the top lifting end of the lifting mechanism via a first hinge shaft. The bottom of the cross slide is mounted on the bottom support. The contouring support frame is fixed to the top of the cross slide and can move back and forth and left and right under the drive of the cross slide. The first hinge shaft extends along the front-back direction. The two ends of the flipping drive mechanism are respectively hinged to the bottom of the cross slide and the top lifting end of the lifting mechanism. The flipping drive mechanism is used to drive the bottom support, the cross slide, and the contouring support frame to flip or reset around the first hinge shaft toward one side of the lifting mechanism.

[0008] The beneficial effects of this invention are: the multi-functional auxiliary tooling for satellite modules of this invention integrates the functions of movement, lifting, three-dimensional precision adjustment and controllable flipping, which can realize the rapid docking and separation of satellite modules, effectively avoid repeated disassembly and assembly, thereby improving the overall assembly efficiency, ensuring operational safety and eliminating potential quality hazards.

[0009] Based on the above technical solution, the present invention can be further improved as follows.

[0010] Furthermore, the contour support frame has multiple flange plates on its peripheral edge for connecting satellite cabin panels, the contour support frame has positioning pins or positioning holes, and the flange plates have bolt holes.

[0011] The beneficial effect of adopting the above-mentioned further solution is that by setting positioning pins or positioning holes, precise docking and assembly between the contour support frame and the satellite module can be achieved.

[0012] Furthermore, the tilting drive mechanism includes multiple hydraulic cylinders. The cylinder body of the hydraulic cylinder is hinged to the top lifting end of the lifting mechanism via a second hinge shaft, and the driving end of the hydraulic cylinder is hinged to the bottom of the cross slide via a third hinge shaft. Both the second and third hinge shafts are arranged parallel to the first hinge shaft.

[0013] Furthermore, the top lifting end of the lifting mechanism is provided with a receiving groove for accommodating the tilting drive mechanism, and the top and one side of the receiving groove are open structures.

[0014] The beneficial effect of adopting the above-mentioned further solution is that by setting a receiving groove at the top lifting end of the lifting mechanism, the assembly and installation of the hydraulic cylinder is facilitated.

[0015] Furthermore, a limiting arm is fixed at the bottom of the contour support frame. When the flipping drive mechanism drives the contour support frame to flip to one side to a set angle, the limiting arm abuts against one side wall of the top lifting end of the lifting mechanism.

[0016] The beneficial effect of adopting the above-mentioned further solution is that, by setting a limiting arm, when the contour support frame is flipped to a set angle, it can be supported against the left side wall of the top lifting end of the lifting mechanism through the limiting arm.

[0017] Furthermore, wheels are installed at the bottom of the base platform, and a spiral support leg is threadedly connected to the base platform. The spiral support leg passes through the base platform and is threadedly connected to the base platform.

[0018] The beneficial effect of adopting the above-mentioned further solution is that by setting the spiral support legs, the spiral support legs can be twisted downwards to support the ground during use, thus preventing the base platform from moving.

[0019] Furthermore, the base platform includes a first connecting arm and a second connecting arm extending left and right. A first guide rail extending left and right is fixed on the first connecting arm, and a second guide rail extending left and right is fixed on the second connecting arm. The bottom of the lifting mechanism is slidably mounted on the first and second guide rails. The translation mechanism adopts a screw and nut drive mechanism and is used to drive the lifting mechanism to move left and right along the first and second guide rails.

[0020] Furthermore, the cross slide includes two vertically mounted lead screw and nut drive mechanisms.

[0021] The beneficial effect of adopting the above-mentioned further solution is that by using a lead screw and nut drive mechanism as a cross slide, the contour support frame can be moved stably and accurately in the front, back, left and right directions.

[0022] Furthermore, the contour-following support frame is a polygonal frame structure.

[0023] This invention also provides a satellite panel testing method, which is implemented using the multifunctional auxiliary tooling for satellite panels as described above, and includes the following steps: S1, move the multi-functional auxiliary tooling for the satellite module to a predetermined work position near the satellite module and position it there; S2, fix the satellite module to the side of the contour support frame away from the cross slide; S3, using a lifting mechanism, raises the satellite module to a preset height above the target docking surface on the satellite body; S4, start the flipping drive mechanism to flip the satellite panel to an angle parallel to the docking interface on the satellite body. By operating the translation mechanism, cross slide and lifting mechanism, the contour support frame and the satellite panel on it are precisely positioned to the target docking position. S5. Adjust the lifting mechanism so that the satellite panel is aligned with the interface of the satellite body. At this point, electrical performance testing and troubleshooting testing can be performed. S6. After the test is completed, the contour support frame and the satellite panel on it are raised using the lifting mechanism, and the satellite panel is flipped back to the horizontal state by operating the flipping drive mechanism, so that the multi-functional auxiliary tooling of the satellite panel can be removed.

[0024] The beneficial effects of this invention are: the satellite panel testing method of this invention greatly improves installation efficiency and accuracy, eliminates potential quality problems, and ensures operational safety. Attached Figure Description

[0025] Figure 1 This is a side view of the multi-functional auxiliary tooling for the satellite module of the present invention. Figure 2 This is a top view of the multi-functional auxiliary tooling for the satellite module of the present invention. Figure 3 This is a three-dimensional structural schematic diagram of the multifunctional auxiliary tooling for the satellite compartment panel of the present invention; Figure 4 This is a side view of the multi-functional auxiliary tooling for the satellite module of the present invention in use. Figure 5 for Figure 4 Enlarged structural diagram of section A in the middle; Figure 6 This is a three-dimensional structural diagram of the multi-functional auxiliary tooling for the satellite module of the present invention in use. Figure 7 This is a top view of the multi-functional auxiliary tooling for the satellite module of the present invention in use.

[0026] The attached diagram lists the components represented by each number as follows: 1. Base platform; 11. Wheel body; 12. Spiral support leg; 13. First guide rail; 14. Second guide rail; 15. First connecting arm; 16. Second connecting arm; 2. Lifting mechanism; 21. Receiving slot; 22. First hinge shaft; 23. Second hinge shaft; 24. Third hinge shaft; 3. Bottom support; 31. Cross slide table; 32. First lead screw and nut drive mechanism; 33. Second lead screw and nut drive mechanism; 34. First slide rail; 35. Second slide rail; 4. Contouring support frame; 41. Limiting arm; 42. Flange plate; 43. Connecting bolts; 5. Hydraulic cylinder; 6. Satellite body; 61. Satellite panel; 62. Interlocking interface; 63. First electrical component; 64. Second electrical component; 65. Cable. Detailed Implementation

[0027] The principles and features of the present invention are described below. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0028] Example 1 like Figures 1-7 As shown, a multi-functional auxiliary tooling for satellite cabin panels in this embodiment includes a base platform 1, a lifting mechanism 2, a flipping drive mechanism, a cross slide 31, a bottom support 3, and a contour support frame 4. The lifting mechanism 2 is mounted on the base platform 1 and can move left and right via a translation mechanism. The bottom support 3 is hinged to the top lifting end of the lifting mechanism 2 via a first hinge shaft 22. The bottom of the cross slide 31 is mounted on the bottom support 3. The contour support frame 4 is fixed to the top of the cross slide 31 and can move back and forth and left and right under the drive of the cross slide 31. The first hinge shaft 22 extends in the front-back direction. The two ends of the flipping drive mechanism are respectively hinged to the bottom of the cross slide 31 and the top lifting end of the lifting mechanism 2. The flipping drive mechanism is used to drive the bottom support 3, the cross slide 31, and the contour support frame 4 to flip or reset around the first hinge shaft 22 toward the lifting mechanism 2.

[0029] like Figures 1-4 and Figure 6 As shown, in a preferred embodiment, wheels 11 are mounted on the bottom of the base platform 1, and spiral support legs 12 are threadedly connected to the base platform 1. The spiral support legs 12 pass through the base platform 1 and are threadedly connected to it. The base platform 1 has a rectangular structure, and a wheel 11 can be installed at each of the four corners of the base platform 1, and a spiral support leg 12 can be installed at each of the four corners. By setting the spiral support legs, during use, the spiral support legs can be screwed downwards to support the platform on the ground, preventing the base platform from moving.

[0030] Specifically, the cross slide 31 in this embodiment includes two vertically mounted lead screw and nut drive mechanisms. Using lead screw and nut drive mechanisms as the cross slide enables stable and precise forward, backward, left, and right movement of the contour support frame. The two lead screw and nut drive mechanisms of the cross slide 31 are a first lead screw and nut drive mechanism 32 and a second lead screw and nut drive mechanism 33. Both the first lead screw and nut drive mechanism 32 and the second lead screw and nut drive mechanism 33 can use common lead screw and nut drive mechanisms; their specific structures will not be described in detail. The lead screw and the first slide rail 34 of the first lead screw and nut drive mechanism 32 extend in the forward and backward direction, while the lead screw and the second slide rail 35 of the second lead screw and nut drive mechanism 33 extend in the left and right direction. The first lead screw and nut drive mechanism 32 can drive the second lead screw and nut drive mechanism 33 to move forward and backward, and the second lead screw and nut drive mechanism 33 can drive the contour support frame 4 to move in the left and right direction.

[0031] Specifically, such as Figure 6 As shown, the contour support frame 4 in this embodiment is a polygonal frame structure, preferably a rectangular frame structure.

[0032] The lifting mechanism 2 in this embodiment can be a hydraulic lifting mechanism or any other mechanism capable of lifting.

[0033] The multi-functional auxiliary tooling for satellite modules in this embodiment integrates movement, lifting, three-dimensional precision adjustment, and controllable flipping functions. It enables rapid docking and separation of satellite modules, effectively avoiding repeated disassembly and assembly, thereby improving assembly efficiency, ensuring operational safety, and eliminating potential quality risks.

[0034] Example 2 Based on Embodiment 1, this embodiment provides a preferred assembly scheme for the contour-following support frame 4 and the satellite module 61. For example... Figures 1-7 As shown, in this embodiment, the contour support frame 4 has multiple flange plates 42 on its peripheral edge for connecting the satellite module 61. The contour support frame 4 has positioning pins or positioning holes, and the flange plates 42 have bolt holes. The flange plates 42 are detachably connected to the satellite module 61 by connecting bolts 43. By setting positioning pins or positioning holes, precise docking and assembly between the contour support frame and the satellite module can be achieved. If positioning pins are set on the contour support frame 4, positioning holes are set on the satellite module 61; conversely, if positioning pins are set on the satellite module 61, positioning holes are set on the contour support frame 4.

[0035] Example 3 Based on Embodiment 1 or Embodiment 2, this embodiment provides a preferred solution for a flipping drive mechanism. For example... Figure 6 and Figure 7As shown, the tilting drive mechanism of this embodiment includes a plurality of hydraulic cylinders 5. The cylinder body of the hydraulic cylinder 5 is hinged to the top lifting end of the lifting mechanism 2 via a second hinge shaft 23. The driving end of the hydraulic cylinder 5 is hinged to the bottom of the cross slide 31 via a third hinge shaft 24. The second hinge shaft 23 and the third hinge shaft 24 are both arranged parallel to the first hinge shaft 22.

[0036] Preferred, such as Figure 6 and Figure 7 As shown, in this embodiment, two hydraulic cylinders 5 are preferably used.

[0037] Example 4 Based on any of the above embodiments, this embodiment provides a preferred assembly scheme for the lifting mechanism and the tilting drive mechanism. For example... Figure 6 As shown, the top lifting end of the lifting mechanism 2 in this embodiment has a receiving groove 21 for accommodating the tilting drive mechanism. The top and one side (shown as the right side in the figure) of the receiving groove 21 are open structures. By providing a receiving groove at the top lifting end of the lifting mechanism, the assembly and installation of the hydraulic cylinder is facilitated.

[0038] In this embodiment, the right side opening of the receiving groove 21 is used to install the first hinge shaft 22 on the left side of the top lifting end of the lifting mechanism 2. When the hydraulic cylinder 5 lifts the cross slide and other components upward, the contour support frame 4 can be flipped to the left side of the top lifting end of the lifting mechanism 2. Generally, when the contour support frame 4 is flipped to a vertical state, the bottom left side of the contour support frame 4 can be placed against the left side wall of the top lifting end of the lifting mechanism 2.

[0039] Example 5 Based on any of the above embodiments, this embodiment provides a preferred structure for the contour-following support frame 4. For example... Figure 1 and Figure 4 As shown, in this embodiment, the bottom of the contouring support frame 4 is fixed with a limiting arm 41. When the flipping drive mechanism drives the contouring support frame 4 to flip to one side (left side in the figure) to a set angle (maximum flipping angle), the limiting arm 41 abuts against one side wall (left side wall in the figure) of the top lifting end of the lifting mechanism. By setting the limiting arm, when the contouring support frame flips to the set angle, it can be supported against the left side wall of the top lifting end of the lifting mechanism through the limiting arm.

[0040] Example 6 Based on any of the above embodiments, this embodiment provides a preferred structure for the base platform 1. For example... Figure 2As shown, the base platform 1 in this embodiment includes a first connecting arm 15 and a second connecting arm 16 extending left and right. A first guide rail 13 extending left and right is fixed on the first connecting arm 15, and a second guide rail 14 extending left and right is fixed on the second connecting arm 16. The bottom of the lifting mechanism 2 is slidably mounted on the first guide rail 13 and the second guide rail 14. The translation mechanism is driven by a screw and nut and is used to drive the lifting mechanism 2 to move left and right along the first guide rail 13 and the second guide rail 14. The translation mechanism in this embodiment can be a hydraulic cylinder, a pneumatic cylinder, etc., but a screw and nut drive mechanism is preferred for precise driving of the lifting mechanism.

[0041] Example 7 This embodiment provides a satellite module testing method, implemented using the multi-functional auxiliary tooling for satellite modules as described in any of the above embodiments, including the following steps: S1, move the satellite panel multi-functional auxiliary tooling to a predetermined work position near the satellite panel 61 and position it (specifically by twisting the spiral support leg 12 downwards so that the spiral support leg 12 is supported on the ground for positioning). S2, fix the satellite panel 61 to the side of the contour support frame 4 away from the cross slide 31, that is, the top surface of the contour support frame 4 when it is not flipped. S3, the satellite panel 61 is raised to a preset height above the target docking surface on the satellite body 6 by the lifting mechanism 2; S4, start the flipping drive mechanism to flip the satellite panel to an angle parallel to the docking interface 62 on the satellite body 6. By operating the translation mechanism, the cross slide 31 and the lifting mechanism 2, the contour support frame 4 and the satellite panel 61 on it are precisely positioned to the target docking position. The second electrical component 64 on the satellite panel 61 is connected to the first electrical component 63 on the satellite body 6 through the cable 65.

[0042] S5, adjust the lifting mechanism 2 so that the satellite panel 61 is aligned with the interface 62 of the satellite body 6. At this time, electrical performance testing and troubleshooting testing can be carried out. S6. After the test is completed, use the lifting mechanism 2 to lift the contour support frame 4 and the satellite compartment 61 on it, and use the flipping drive mechanism to flip the satellite compartment 61 back to the horizontal state. Then the satellite compartment multi-functional auxiliary tooling can be removed (the spiral support leg 12 can be loosened away from the ground first so that the wheel can move on the ground, and then the auxiliary tooling can be removed).

[0043] The satellite panel testing method in this embodiment greatly improves installation efficiency and accuracy, eliminates potential quality problems, and ensures operational safety.

[0044] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0045] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0046] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0047] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0048] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0049] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A multifunctional auxiliary tool for satellite cabin panel, characterized in that, The multifunctional auxiliary tool for satellite cabin plate includes a base platform, a lifting mechanism, a turnover driving mechanism, a cross slide, a bottom support and a profiling support frame, the lifting mechanism is installed on the base platform and can move left and right through a translation mechanism, the bottom support is hinged to the top lifting end of the lifting mechanism through a first hinge shaft, the bottom of the cross slide is installed on the bottom support, the profiling support frame is fixed to the top of the cross slide and can move forward, backward, left and right under the drive of the cross slide, and the first hinge shaft extends in the front-back direction.

2. The multifunctional auxiliary tooling for satellite cabin panel according to claim 1, characterized in that, A plurality of flange plates for connecting the satellite cabin plate are arranged on the circumferential edge of the profiling support frame, positioning pins or positioning holes are arranged on the profiling support frame, and bolt holes are arranged on the flange plates.

3. The multifunctional auxiliary tooling for satellite cabin panel according to claim 1, characterized in that, The turnover driving mechanism includes a plurality of hydraulic cylinders, the cylinder bodies of the hydraulic cylinders are hinged to the top lifting end of the lifting mechanism through a second hinge shaft, and the driving ends of the hydraulic cylinders are hinged to the bottom of the cross slide through a third hinge shaft.

4. The multifunctional auxiliary tooling for satellite cabin panel according to claim 1, characterized in that, The top lifting end of the lifting mechanism is provided with a receiving groove for accommodating the turnover driving mechanism, and the top and one side of the receiving groove are open structures.

5. The multifunctional auxiliary tooling for satellite cabin panels of claim 1, wherein, When the profiling support frame is turned to a set angle under the drive of the turnover driving mechanism, a limiting arm fixed to the bottom of the profiling support frame abuts against the side wall of the top lifting end of the lifting mechanism.

6. The multifunctional auxiliary tooling for satellite cabin panels of claim 1, wherein, A wheel body is installed at the bottom of the base platform, and a spiral supporting leg is threadedly connected to the base platform, penetrates the base platform and is threadedly connected with the base platform.

7. The multifunctional auxiliary tooling for satellite cabin panels of claim 1, wherein, The base platform includes a first connecting arm and a second connecting arm extending left and right, a first guide rail extending left and right is fixed to the first connecting arm, a second guide rail extending left and right is fixed to the second connecting arm, the bottom of the lifting mechanism is slidingly installed on the first guide rail and the second guide rail, and the translation mechanism adopts a lead screw nut driving mechanism and is used to drive the lifting mechanism to move left and right along the first guide rail and the second guide rail.

8. The multifunctional auxiliary tooling for satellite cabin panels of claim 1, wherein, The cross slide includes two vertically assembled lead screw nut driving mechanisms.

9. The multifunctional auxiliary tooling for satellite cabin panels of claim 1, wherein, The profiling support frame is a polygonal frame structure.

10. A satellite deck plate testing method, characterized by, The multifunctional auxiliary tool for satellite cabin plate is implemented by adopting any one of the satellite cabin plate multifunctional auxiliary tools according to claims 1 to 9, and the following steps are included: S1, moving the multifunctional auxiliary tool for satellite cabin plate to a predetermined work station near the satellite cabin plate and positioning it; S2, fixing the satellite cabin plate to the side of the profiling support frame away from the cross slide; S3, lifting the satellite cabin plate to a predetermined height above the target docking surface on the satellite body through the lifting mechanism; S4, the satellite cabin plate is flipped to a parallel angle with the docking interface on the satellite body by starting the flipping driving mechanism, and the profiled support frame and the satellite cabin plate thereon are precisely positioned to the target docking position by operating the translation mechanism, the cross slide and the lifting mechanism; S5, the satellite cabin plate is adjusted to be close to the docking interface on the satellite body by adjusting the lifting mechanism, and the electrical performance test and the troubleshooting test can be performed at this time; S6, after the test is completed, the profiled support frame and the satellite cabin plate thereon are lifted by the lifting mechanism, and the satellite cabin plate is flipped to the horizontal state by operating the flipping driving mechanism, so that the satellite cabin plate multifunctional auxiliary tooling can be removed.

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