Multifunctional tool for satellite AIT

Abstract

A multifunctional tool for satellite AIT relates to the technical field of satellite tooling, comprising: a base; platform pillars, including at least two fixed pillars and at least one rotating pillar, the lower end of the fixed pillar is fixedly connected with the base, and the lower end of the rotating pillar is rotatably connected with the base; a satellite mounting platform, one end of which is rotatably connected with the upper end of each fixed pillar, and the other end is detachably connected with the upper end of the rotating pillar, and the satellite mounting platform can be turned over in a vertical plane; a cabin plate support assembly, installed on the side of the satellite mounting platform, used for supporting the cabin plate when the satellite is opened; and a hanging beam assembly, installed on the side of the satellite mounting platform, used for manually or cooperatively assisting the satellite mounting platform to turn over with the help of hoisting equipment. The tool integrates functions such as manual adjustment of satellite attitude, hoisting equipment assisted attitude adjustment, and support for opening the satellite cabin, and does not need to repeatedly disassemble and assemble the equipment and debug, thereby significantly reducing the process and the use of equipment, improving the operation efficiency, and reducing the equipment cost.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite tooling, in particular to a multifunctional tooling for satellite AIT. BACKGROUND

[0002] In the satellite AIT (Assemble, Integrate, and Test) stage, the satellite cabin needs to be opened multiple times or the movable cabin plate needs to be placed horizontally, and the sail plate unfolding test also needs to adjust the satellite attitude. At present, most domestic satellite manufacturing enterprises use satellite parking vehicles to fix the whole satellite in this stage, use lifting vehicles or cranes to suspend the cabin plate when opening the cabin, and use two-dimensional turntables to adjust the satellite attitude when the sail plate unfolding test is performed. This operation mode needs to repeatedly disassemble and assemble special toolings such as satellite vehicles, lifting equipment, and turntables, which not only leads to frequent switching of equipment, a sharp increase in assembly and debugging workload, but also increases the difficulty of product protection and quality risk due to multiple disassemblies, ultimately causing systematic problems such as long AIT process cycle, low operation efficiency, and rising comprehensive cost. SUMMARY

[0003] Therefore, the purpose of the present application is to provide a multifunctional tooling for satellite AIT to solve at least one of the above technical problems.

[0004] The present application provides a multifunctional tooling for satellite AIT, which comprises a base, a platform support installed on the top surface of the base, at least two fixed supports and at least one rotating support, the lower end of the fixed support is fixedly connected with the base, and the lower end of the rotating support is rotatably connected with the base, a satellite mounting platform, one end of the satellite mounting platform is rotatably connected with the upper end of each fixed support, the other end of the satellite mounting platform is detachably connected with the upper end of the rotating support, and when the satellite mounting platform is detached from the upper end of the rotating support, the satellite mounting platform can be flipped in a vertical plane, a cabin plate support assembly installed on the side surface of the satellite mounting platform for supporting the cabin plate when the satellite is opened, and a beam assembly installed on the side surface of the satellite mounting platform for manually or cooperatively assisting the satellite mounting platform to flip with the lifting equipment.

[0005] In some optional embodiments, the satellite mounting platform comprises a platform body, a plurality of cabin body connecting plates, at least two second connecting seats, and at least one adapter seat, the platform body is a rectangular plate body, the plurality of cabin body connecting plates are distributed and installed on the top surface of the platform body for connection with the cabin body of the satellite, the at least two second connecting seats are installed on one end of the length direction of the bottom surface of the platform body, each second connecting seat is rotatably connected with the bearing with seat installed on the upper end of the fixed support through a rotating shaft, and the adapter seat is installed on the other end of the length direction of the bottom surface of the platform body and is detachably connected with the upper end of the rotating support through a fastener.

[0006] In some alternative embodiments, the satellite mounting platform further comprises a platform handle mounted at one end of the length direction of the platform body, for operating the platform body to flip over.

[0007] In some alternative embodiments, at least one hatch support assembly is arranged on each of the two long sides of the platform body, each hatch support assembly comprising a tray, a first locking member, a hatch support member, and a limiting member, a sliding groove vertically extending into the platform body is formed on the long side of the platform body, the tray is slidably mounted in the sliding groove along the extending direction of the sliding groove, the first locking member is mounted on the platform body for locking the position of the tray in the sliding groove, the hatch support member is a long member, one end of the hatch support member is rotatably connected to the end of the tray facing away from the sliding groove, the hatch support member is rotatable about the one end in a plane formed by the vertical direction of the top surface of the platform body and the sliding direction of the tray, and the limiting member is mounted on the end of the tray facing away from the sliding groove for limiting the rotation position of the hatch support member and fixing the hatch support member with the fastener when the hatch support member is rotated to the vertical direction of the top surface of the platform body.

[0008] In some alternative embodiments, the end of the tray facing into the sliding groove is provided with a first positioning hole for positioning cooperation with the first locking member when the tray slides into the sliding groove, and the end of the tray facing away from the sliding groove is provided with a second positioning hole for positioning cooperation with the first locking member when the tray extends out of the sliding groove.

[0009] In some alternative embodiments, at least one hanging beam assembly is arranged on each of the two long sides of the platform body, each hanging beam assembly comprising a hanging beam, a sling connecting member, and a second locking member, one end of the hanging beam is rotatably connected to the long side of the platform body, the hanging beam is rotatable about the one end in the plane of the platform body, the sling connecting member is mounted on the other end of the hanging beam for connecting the sling of the hoisting equipment, and the second locking member is used for locking the position of the hanging beam when the hanging beam is rotated to be perpendicular to the long side of the platform body.

[0010] In some alternative embodiments, at least one buckle is arranged on each of the two long sides of the platform body, the buckle is used for clamping the hanging beam when the hanging beam is attached to the long side.

[0011] In some alternative embodiments, the side surface of the fixed support column is provided with a positioning block, the positioning block is used for fixing the satellite mounting platform with the fastener when the satellite mounting platform is flipped down to the vertical position.

[0012] In some alternative embodiments, further comprising: a plurality of adjustable foot screws mounted on the base for adjusting the levelness of the satellite AIT multifunctional tool.

[0013] In some alternative embodiments, further comprising: a plurality of casters mounted on the bottom surface of the base for realizing the moving function.

[0014] Based on the technical scheme, the multifunctional tool for satellite AIT provided by the application can overturn the satellite installation platform in the vertical plane, and the hoisting beam assembly can assist the satellite installation platform to overturn through manual operation or in cooperation with the hoisting equipment, and the cabin plate support assembly can support the cabin plate when the satellite is opened, so that the multifunctional tool for satellite AIT provided by the application integrates satellite attitude manual adjustment, hoisting equipment assisted attitude adjustment, satellite opening support and other functions, and does not need to be repeatedly disassembled and assembled, thereby significantly reducing the process and the use of equipment, improving the operation efficiency, and reducing the equipment cost. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical scheme of the embodiments of the application, the drawings needed to be used in the embodiments will be briefly introduced as follows, and it should be understood that the following drawings only show some embodiments of the application, and therefore should not be regarded as a limitation to the scope, and other related drawings can also be obtained by those skilled in the art without creative labor on the premise of the drawings.

[0016] Figure 1 A structural schematic diagram of a multifunctional tool for satellite AIT provided by an embodiment of the application.

[0017] Figure 2 A structural schematic diagram of a cabin plate support assembly of a multifunctional tool for satellite AIT provided by an embodiment of the application.

[0018] Figure 3 A structural schematic diagram of a cabin plate support assembly of a multifunctional tool for satellite AIT provided by an embodiment of the application.

[0019] Figure 4 A structural schematic diagram of a multifunctional tool for satellite AIT provided by an embodiment of the application.

[0020] Figure 5 A structural schematic diagram of a multifunctional tool for satellite AIT provided by an embodiment of the application.

[0021] Figure 6 A structural schematic diagram of a multifunctional tool for satellite AIT provided by an embodiment of the application.

[0022] Figure 7 A structural schematic diagram of a multifunctional tool for satellite AIT provided by an embodiment of the application.

[0023] Figure 8This is a schematic diagram of a multifunctional tooling for satellite AIT used in a solar panel deployment test, provided as an embodiment of this application, wherein the solar panel is in the deployed state.

[0024] Reference numerals: 100. Multifunctional tooling for satellite AIT; 10. Base; 11. Longitudinal beam; 12. Crossbeam; 13. Support plate; 20. Platform support column; 21. Fixed support column; 211. Bearing with seat; 212. Positioning block; 213. Connecting beam; 214. Diagonal brace; 22. Rotating support column; 221. First connecting seat; 30. Satellite installation platform; 31. Platform body; 32. Cabin connecting plate; 33. Second connecting seat; 34. Adapter seat 35. Handle; 36. Buckle; 40. Cabin support assembly; 41. Pallet; 42. First locking element; 43. Cabin support element; 44. Limiting element; 50. Lifting beam assembly; 51. Lifting beam; 52. Lifting tool connector; 60. Casters; 70. Adjustable feet; 71. Screw seat; 72. Screw; 73. Operating handle; 74. Locking nut; 75. Foot pad; 1. Cabin; 2. Cabin adapter; 3. Cabin; 4. Hinge; 5. Sailboard. Detailed Implementation

[0025] The specific embodiments of this application will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely a part of the embodiments of this application, and not all of them. Based on the description of this application, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this application.

[0026] In the description of this application, unless otherwise expressly specified and limited, the terms "connection," "setup," "installation," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0027] The terms “upper,” “lower,” “left,” “right,” “front,” “back,” “center,” “top,” “bottom,” “inner,” “outer,” “vertical,” “horizontal,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of description and simplification, 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 application.

[0028] The terms "first", "second", "third", and the like, are used merely to distinguish like elements and do not indicate or imply a relative importance or a specific order unless otherwise explicitly stated and limited.

[0029] The terms "comprises", "comprising", "includes", "including", "has", "having", "contains", "containing", or any other variant thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a", "has... a", "includes... a", or "contains... a", does not, without more constraints, preclude the existence of additional identical elements in the process, method, article, or apparatus that comprises, has, includes, or contains that element.

[0030] The term "a plurality" means two or more (including two).

[0031] The term "and / or", is a descriptive term that refers to an association relationship of associated objects, which means that there can be three relationships, for example, A and / or B, which can represent the three cases of A existing alone, A and B existing together, and B existing alone.

[0032] The terms "one embodiment", "as an example", "in an embodiment", and the like, describe a specific feature, structure, material, or characteristic that is included in at least one embodiment or example of the present application. The illustrative expressions of such terms do not necessarily refer to the same embodiment or independent or alternative embodiments that are not mutually exclusive. Embodiments and features in the present application can be combined in a suitable manner without conflict.

[0033] Figure 1 A structural schematic diagram of a multifunctional tool 100 for satellite AIT provided by the embodiments of the present application is shown in FIG. 1, which shows that the multifunctional tool 100 for satellite AIT provided by the embodiments of the present application comprises a base 10, a platform support 20, a satellite mounting platform 30, a hatchboard support assembly 40, a hoisting beam assembly 50, a castor 60, and an adjustable footing 70. The following will make specific description on each part. Figure 1 A structural schematic diagram of a multifunctional tool 100 for satellite AIT provided by the embodiments of the present application is shown in FIG. 1, which shows that the multifunctional tool 100 for satellite AIT provided by the embodiments of the present application comprises a base 10, a platform support 20, a satellite mounting platform 30, a hatchboard support assembly 40, a hoisting beam assembly 50, a castor 60, and an adjustable footing 70. The following will make specific description on each part.

[0034] The base 10 is a rectangular frame structure, which mainly provides a mounting base for the platform support 20.

[0035] As an example, the base 10 comprises two longitudinal beams 11, a plurality of cross beams 12, and two support plates 13. The two longitudinal beams 11 and the two cross beams 12 are connected end to end to form a closed rectangular frame, and the remaining cross beams 12 are connected between the two longitudinal beams 11 and are spaced along the length of the longitudinal beams 11 to divide the interior of the rectangular frame into a plurality of rectangular units. The two support plates 13 of matching size are embedded in the two rectangular units at the ends, the edges of the support plates 13 are connected with the surrounding longitudinal beams 11 and cross beams 12, and the support plates 13 serve as mounting bases for the platform pillars 20.

[0036] The platform pillars 20 are mounted on the top surface of the base 10, and the number is at least three, for mounting and supporting the satellite mounting platform 30. Specifically, the platform pillars 20 comprise at least two fixed pillars 21 and at least one rotating pillar 22. Among them, the lower end of the fixed pillar 21 is fixedly connected with the base 10, and the upper end of the fixed pillar 21 is rotatably connected with the satellite mounting platform 30. The lower end of the rotating pillar 22 is rotatably connected with the base 10, and the upper end of the rotating pillar 22 is detachably connected with the satellite mounting platform 30.

[0037] As an example, the platform pillars 20 comprise two fixed pillars 21 and one rotating pillar 22. The two fixed pillars 21 are both perpendicular to the base 10 and are spaced along the length of the cross beams 12, the lower end of each of the two fixed pillars 21 is fixed on one cross beam 12 close to one end of the longitudinal beam 11, and the upper end of each of the two fixed pillars 21 is mounted with a bearing 211, each bearing 211 is rotatably connected with one second connecting seat 33 on the bottom surface of the satellite mounting platform 30 through a rotating shaft, and the lower part of the side surface of each of the two fixed pillars 21 is mounted with a positioning block 212, which is used to fix the satellite mounting platform 30 with fasteners when the satellite mounting platform 30 is flipped to the vertical position. The length of the rotating pillar 22 is the same as that of the fixed pillar 21, the lower end of the rotating pillar 22 is rotatably connected with the support plate 13 close to the other end of the longitudinal beam 11 through a pin shaft and a first connecting seat 221, and is located on the vertical center line of the connecting line of the lower ends of the two fixed pillars 21, and the upper end of the rotating pillar 22 is detachably connected with an adapter seat 34 (see Figure 4 ) on the bottom surface of the satellite mounting platform 30 through fasteners. When the upper end of the rotating pillar 22 is connected with the adapter seat 34 on the bottom surface of the satellite mounting platform 30, the rotating pillar 22 is perpendicular to the base 10, and the rotating pillar 22 and the two fixed pillars 21 together support the satellite mounting platform 30; when the upper end of the rotating pillar 22 is detached from the adapter seat 34 on the bottom surface of the satellite mounting platform 30, the rotating pillar 22 can rotate in the vertical plane about the lower end.

[0038] The two fixed pillars 21 are the main support structure of the satellite mounting platform 30. In order to improve the structural stability of the two fixed pillars 21, a connecting beam 213 is connected between the two fixed pillars 21, and an inclined strut 214 is arranged on the side of each fixed pillar 21. The upper end of each inclined strut 214 is connected with the side of the fixed pillar 21, and the lower end of the inclined strut 214 is fixed on the base 10.

[0039] The satellite mounting platform 30 is used for mounting the cabin body 1 of the satellite. One end of the satellite mounting platform 30 is rotatably connected with the upper end of the fixed pillar 21, and the other end of the satellite mounting platform 30 is detachably connected with the upper end of the rotating pillar 22. When the satellite mounting platform 30 is detached from the upper end of the rotating pillar 22, the satellite mounting platform 30 can be flipped in a vertical plane about one end, which can be used for adjusting the attitude of the satellite.

[0040] As an example, the satellite mounting platform 30 includes a platform body 31, a plurality of cabin connecting plates 32, two second connecting seats 33, an adapter seat 34 (see Figure 4 ), and a platform handle 35. The platform body 31 is a rectangular plate body, and one cabin connecting plate 32 is mounted at each corner of the top surface of the platform body 31. The two second connecting seats 33 are mounted at one end of the length direction of the bottom surface of the platform body 31, and are rotatably connected with the bearing 211 of the upper end of the two fixed pillars 21 through the rotating shafts, respectively. The adapter seat 34 is mounted at the other end of the length direction of the bottom surface of the platform body 31, and is detachably connected with the upper end of the rotating pillar 22 through fasteners. The handle 35 is mounted at one end of the length direction of the platform body 31, and is mainly used for flipping the platform body 31, and is also used for cooperating with the casters 60 to operate the movement of the whole tooling. When the adapter seat 34 is connected with the upper end of the rotating pillar 22, the platform body 31 is supported by the rotating pillar 22 and the two fixed pillars, and is in a horizontal position. When the adapter seat 34 is detached from the upper end of the rotating pillar 22, the platform body 31 can be flipped in a vertical plane about the axis of the second connecting seat 33.

[0041] The cabin plate support assembly 40 is mounted on the side of the satellite mounting platform 30, and is used for supporting the cabin plate 3 when the satellite is opened.

[0042] As an example, the number of cabin plate support assemblies 40 is two, which are mounted on the two long sides (i.e. the sides where the long edges of the rectangle are located) of the platform body 31, respectively. As shown in Figure 2 and Figure 3As shown, each cabin support assembly 40 includes a tray 41, a first locking member 42, a cabin support member 43, and a limiting member 44. Each of the two long sides of the platform body 31 has a vertically extending groove into the interior of the platform body 31. The tray 41 is slidably installed in the groove along its extension direction. The tray 41 can slide into the groove and be hidden, or it can extend out of the groove to support the cabin 3. The first locking member 42 is a knob plunger, installed on the top surface of the platform body 31 and extending into the groove. The end of the tray 41 facing the groove has a first positioning hole (not shown in the figure). The first positioning hole is used to position and engage with the first locking member 42 when the tray 41 slides into the groove, locking the position of the tray 41. The end of the tray 41 facing out of the groove has a second positioning hole (not shown in the figure). The second positioning hole is used to position and engage with the first locking member 42 when the tray 41 extends out of the groove, locking the position of the tray 41. The first locking member 42 can also be installed on the bottom surface of the platform body 31. The cabin support member 43 is an elongated component. One end of the cabin support member 43 is rotatably connected to the end of the tray 41 facing outwards from the slide groove via a pivot. The cabin support member 43 can rotate around one end in a plane constructed by the vertical direction of the top surface of the platform body 31 and the sliding direction of the tray 41. The tray 41 has an elongated slot that can accommodate the cabin support member 43. When the cabin support member 43 rotates into the elongated slot, it can slide into the slide groove and be hidden along with the tray 41. A limiting member 44 is installed at the end of the tray 41 facing outwards from the slide groove to limit the rotational position of the cabin support member 43 and to fix the cabin support member 43 with fasteners when it rotates to the vertical direction of the top surface of the platform body 31.

[0043] Among them, when the panel support assembly 40 is not in use, such as Figure 1 As shown, the tray 41 and the deck support 43 are concealed together within the slide groove, and the first locking member 42 locks the position of the tray 41. When in use, the deck support assembly 40, as... Figure 2 As shown, first unscrew the first locking member 42 to release the lock on the tray 41. After pulling the tray 41 out of the groove into place, lock the position of the tray 41 again using the first locking member 42. Then, as shown... Figure 3 As shown, the cabin support 43 is rotated to the vertical direction of the top surface of the platform body 31, so that the cabin support 43 is limited by the limiting member 44. Then, the cabin support 43 and the limiting member 44 are connected by fasteners to fix the position of the cabin support 43. At this time, the cabin support 43 can be used to support the cabin 3.

[0044] The lifting beam assembly 50 is installed on the side of the satellite mounting platform 30 for manually or in conjunction with lifting equipment to assist in the tilting of the satellite mounting platform 30.

[0045] As an example, the number of the beam assemblies 50 is two, which are installed on the two long sides of the platform body 31 respectively. As shown in Figure 4 each beam assembly 50 includes a beam 51, a sling connector 52, and a second locking member (not shown in the figure). One end of the beam 51 is rotatably connected to the long side of the platform body 31 through a rotating shaft, and the beam 51 can rotate around the one end in the plane of the platform body 31. The sling connector 52 is installed on the other end of the beam 51 and is used to connect the sling of the hoisting equipment. The second locking member is a screw pin, which is used to lock the position of the beam 51 when the beam 51 is rotated to be perpendicular to the long side of the platform body 31. The one end of the beam 51 and the platform body 31 are correspondingly provided with connecting holes for connecting with the second locking member.

[0046] When the beam assembly 50 is not used, as shown in Figure 1 the beam 51 is attached to the long side of the platform body 31 and is clamped by the buckle 36 provided on the long side. When the beam assembly 50 is used, as shown in Figure 4 the beam 51 is rotated to the position perpendicular to the long side of the platform body 31, and the position of the beam 51 is fixed by connecting the second locking member with the connecting holes on the one end of the beam 51 and the platform body 31. At this time, the beam 51 can be held by hand to assist the satellite installation platform 30 to be turned over, and the sling connector 52 can be connected with the sling of the hoisting equipment such as a trolley or a crane to assist the satellite installation platform 30 to be turned over.

[0047] The casters 60 are installed on the base 10 and are used to realize the moving function of the whole tooling. The casters 60 can be fixed casters or movable casters.

[0048] As an example, the casters 60 are movable casters, and the number is four. The four casters 60 are installed at the four corners of the bottom surface of the base 10 respectively.

[0049] The adjustable feet 70 are installed on the base 10 and are used to adjust the levelness of the whole tooling.

[0050] As an example, the adjustable feet 70 are fine adjustment feet with micron-level adjustment accuracy, and the number is four. Two adjustable feet 70 are installed on each of the two longitudinal beams 11 of the base 10. As shown in Figure 2As shown, each adjustable footing 70 includes a screw rod base 71 mounted on the side of the longitudinal beam 11, a screw rod 72 threadedly connected to the screw rod base 71 and arranged in a vertical direction, an operating handle 73 mounted on the upper end of the screw rod 72, a locking nut 74 mounted on the screw rod 72, and a foot pad 75 mounted on the lower end of the screw rod 72. In use, the locking nut 74 is loosened, the screw rod 72 is rotated by operating the handle 73, and the position of the base 10 in the vertical direction is adjusted. When the adjustment is completed, the locking nut 74 is tightened.

[0051] The multifunctional tool 100 for satellite AIT can be used for satellite cabin opening support, and can meet the requirement of placing the movable cabin plate 3 horizontally in the satellite AIT stage.

[0052] As an example, the structure of the satellite installed on the tool is as shown in Figure 6 As shown, the satellite mounting platform 30 is in a horizontal position under the support of the fixed support column 21 and the rotating support column 22, and the cabin body 1 of the satellite is connected to the cabin connecting plate 32 of the satellite mounting platform 30 through the cabin adapter 2. Before opening the cabin of the satellite, for each cabin plate support assembly 40, as shown in Figure 2 As shown, the first locking member 42 is first unlocked to release the locking of the tray 41, the tray 41 is pulled out to the position from the sliding groove, and then the position of the tray 41 is locked by the first locking member 42. Then, as shown in Figure 3 As shown, the cabin plate support member 43 is rotated to be perpendicular to the top surface of the platform body 31, the cabin plate support member 43 is limited by the limiting member 44, and then the cabin plate support member 43 and the limiting member 44 are connected by the fastening member to fix the position of the cabin plate support member 43. At this time, the upper end of the cabin plate support member 43 can be used to support the cabin plate 3. For the cabin plate 3 that needs to be opened, the screw connecting the cabin plate 3 and the cabin body 1 is removed, the hinge 4 is installed, and the cabin plate 3 is rotatable through the hinge 4. When the satellite is opened, the cabin plate 3 is rotated to be horizontally placed on the cabin plate support member 43, and the cabin plate support member 43 realizes the opening support function and can be applied to single machine installation, whole satellite wiring, cabin opening test, etc.

[0053] The multifunctional tool 100 for satellite AIT can be used for satellite attitude adjustment, and can meet the requirement of satellite attitude adjustment for sail plate unfolding test. The satellite attitude adjustment includes satellite attitude manual adjustment, hoisting equipment assisted attitude adjustment, and satellite attitude precise adjustment.

[0054] As an example, the initial attitude of the satellite is as shown in Figure 6 As shown, the satellite mounting platform 30 is in a horizontal position under the support of the fixed support column 21 and the rotating support column 22, and the cabin body 1 of the satellite is connected to the cabin connecting plate 32 of the satellite mounting platform 30 through the cabin adapter 2, in a horizontal attitude. When it is required to adjust the satellite from the horizontal attitude to the vertical attitude, as shown inFigure 4 As shown, first, the hanger beam 51 of each hanger beam assembly 50 is rotated to a position perpendicular to the long side of the platform body 31, and the position of the hanger beam 51 is fixed by the second locking member, then, the adapter 34 of the satellite mounting platform 30 is detached from the upper end of the rotating column 22, and then, the satellite attitude can be adjusted by manual or hoisting equipment. For a satellite with a small mass (for example, less than 80 kg), the satellite attitude can be adjusted manually, specifically, two workers stand on both sides of the satellite mounting platform 30, hold one hanger beam 51 respectively, and gently put it down, and another worker presses the handle 35 of the satellite mounting platform 30 downward and gently lifts it upward, as shown in FIG. 6. Figure 5 As shown, when the satellite mounting platform 30 is turned down to the vertical position, the satellite mounting platform 30 and the positioning block 212 are connected by the fastener to fix the position of the satellite mounting platform 30. For a satellite with a mass that is difficult to adjust manually (for example, 80-150 kg), a crane or other hoisting equipment is needed, specifically, the hanger connector 52 of the hanger beam assembly 50 on both sides of the satellite mounting platform 30 is connected to the hanger of the crane, and the satellite mounting platform 30 is slowly lowered by the crane, as shown in FIG. 7. Figure 5 As shown, when the satellite mounting platform 30 is turned down to the vertical position, the satellite mounting platform 30 and the positioning block 212 are connected by the fastener to fix the position of the satellite mounting platform 30. Then, a level is placed on the satellite reference surface (the top surface of the cabin body 1), and the satellite levelness is accurately adjusted by adjusting each adjustable foot 70, to ensure that the tooling reaches the sailboard installation attitude. After the satellite attitude is accurately adjusted, the sailboard 5 can be installed and sailboard 5 deployment test can be performed, as shown in FIG. 8. Figure 7 and Figure 8 .

[0055] In summary, the multifunctional tooling for satellite AIT provided by the embodiments of the present application can be turned over in the vertical plane, the hanger beam assembly can assist the satellite mounting platform to turn over by manual or hoisting equipment, and the cabin plate support assembly can support the cabin plate when the satellite is opened. The multifunctional tooling for satellite AIT provided by the embodiments of the present application integrates satellite attitude manual adjustment, hoisting equipment assisted attitude adjustment, satellite opening support, satellite attitude accurate adjustment and other functions, does not need to be repeatedly disassembled and assembled, significantly reduces the process and equipment, improves the operation efficiency, and reduces the equipment cost.

[0056] The above merely provides specific embodiments of the present application, but the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of various changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A multifunctional tooling for satellite AIT, characterized in that, The utility model relates to a satellite installation platform, comprising: a base; a platform support installed on the top surface of the base, comprising at least two fixed supports and at least one rotating support, the lower end of the fixed support being fixedly connected to the base, and the lower end of the rotating support being rotatably connected to the base; a satellite installation platform, one end of the satellite installation platform being rotatably connected to the upper end of each fixed support, the other end of the satellite installation platform being detachably connected to the upper end of the rotating support, and the satellite installation platform being able to be flipped in a vertical plane when the satellite installation platform is detached from the upper end of the rotating support; a hatch support assembly installed on the side of the satellite installation platform for supporting the hatch when the satellite is opened; and a hoisting beam assembly installed on the side of the satellite installation platform for assisting the satellite installation platform in flipping manually or in cooperation with hoisting equipment; wherein the satellite installation platform comprises a platform body, the platform body being a rectangular plate body and at least one hatch support assembly being arranged on each long side of the platform body, each hatch support assembly comprising a tray, a first locking member, a hatch support member, and a limiting member, a sliding groove extending vertically into the platform body being formed on the long side of the platform body, the tray being slidably installed in the sliding groove, the first locking member being installed on the platform body for locking the position of the tray in the sliding groove, the hatch support member being a long member, one end of the hatch support member being rotatably connected to the end of the tray facing away from the sliding groove, the hatch support member being able to rotate in a plane formed by the vertical direction of the top surface of the platform body and the sliding direction of the tray, and the limiting member being installed on the end of the tray facing away from the sliding groove for limiting the rotation position of the hatch support member and fixing the hatch support member with a fastener when the hatch support member is rotated to the vertical direction of the top surface of the platform body.

2. The multifunctional tooling for satellite AIT according to claim 1, wherein, The satellite installation platform further comprises a plurality of hatch body connecting plates, at least two second connecting seats, and at least one adapter seat, the plurality of hatch body connecting plates being distributed and installed on the top surface of the platform body for connecting with the hatch body of a satellite, at least two second connecting seats being installed at one end of the length direction of the bottom surface of the platform body, each second connecting seat being rotatably connected to a bearing with a shaft installed on the upper end of the fixed support, and the adapter seat being installed at the other end of the length direction of the bottom surface of the platform body and being detachably connected to the upper end of the rotating support with a fastener.

3. The multifunctional tooling for satellite AIT according to claim 1, wherein, The satellite installation platform further comprises a platform handle installed at one end of the length direction of the platform body for operating the flipping of the platform body.

4. The multifunctional tooling for satellite AIT according to claim 1, wherein, The end of the tray facing into the sliding groove is provided with a first positioning hole for positioning and cooperating with the first locking member when the tray slides into the sliding groove, and the end of the tray facing away from the sliding groove is provided with a second positioning hole for positioning and cooperating with the first locking member when the tray extends out of the sliding groove.

5. The multifunctional tooling for satellite AIT according to claim 1, wherein, At least one of the beam assemblies is provided on each of the two long sides of the platform body, each of the beam assemblies comprising a beam, a hoist connector and a second locking member, one end of the beam being rotatably connected to the long side of the platform body, the beam being rotatable about the one end in the plane of the platform body, the hoist connector being mounted on the other end of the beam for connecting a hoist of a hoisting device, and the second locking member being used to lock the position of the beam when the beam is rotated to be perpendicular to the long side of the platform body.

6. The multifunctional tooling for satellite AIT according to claim 5, wherein, At least one buckle is provided on each of the two long sides of the platform body, the buckle being used to hold the beam when the beam is attached to the long side.

7. The multifunctional tooling for satellite AIT according to claim 1, wherein, A positioning block is provided on the side of the fixed support column, the positioning block being used to fix the satellite installation platform with fasteners when the satellite installation platform is folded down to the vertical position.

8. The multifunctional tooling for satellite AIT according to claim 1, wherein, Further comprising: A plurality of adjustable foot screws are mounted on the base for adjusting the levelness of the multifunctional tooling for satellite AIT.

9. The multifunctional tooling for satellite AIT according to claim 1, wherein, Further comprising: A plurality of casters are mounted on the bottom surface of the base for realizing the moving function.

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