Multifunctional tool for satellite AIT

Abstract

The invention discloses a multifunctional tool for satellite AIT, and relates to the technical field of satellite tools. The platform supporting columns comprise at least two fixed supporting columns and at least one rotating supporting column, the lower ends of the fixed supporting columns are fixedly connected with the base, and the lower ends of the rotating supporting columns are rotationally connected with the base; one end of the satellite mounting platform is rotationally connected with the upper end of each fixed supporting column, the other end of the satellite mounting platform is detachably connected with the upper end of the rotating supporting column, and the satellite mounting platform can turn over in a vertical plane around one end; the cabin plate supporting assembly is installed on the side face of the satellite installation platform and used for supporting a cabin plate when the satellite is opened; the hanging beam assembly is installed on the side face of the satellite installation platform and used for assisting the satellite installation platform in overturning manually or in cooperation with hoisting equipment. The tool integrates the functions of satellite attitude manual adjustment, hoisting equipment auxiliary attitude adjustment, satellite cabin opening supporting and the like, repeated equipment disassembly, assembly and debugging are not needed, procedures and used equipment are remarkably reduced, the operation efficiency is improved, and the equipment cost is reduced.

Description

Technical Field

[0001] The present application relates to the field of satellite tooling technology, and in particular to a multifunctional tooling for satellite AIT. Background Art

[0002] During the satellite's AIT (Assemble, Integrate, and Test) phase, the cabin needs to be opened multiple times or the movable panels need to be placed horizontally. The sailboard deployment test also requires adjusting the satellite's attitude. Currently, most domestic satellite manufacturers use a satellite parking vehicle to secure the entire satellite during this phase. A lifting vehicle or a traveling crane is used to suspend the cabin panels when opening the cabin, and a two-dimensional turntable is used to adjust the satellite's attitude during the sailboard deployment test. This operating mode requires repeated disassembly and assembly of satellite vehicles, lifting equipment, and turntables, among other specialized tooling. This not only leads to frequent equipment switching and a surge in assembly and debugging workload, but also increases the difficulty of product protection and quality risks due to repeated disassembly. Ultimately, this leads to systemic problems such as lengthy AIT process cycles, low operational efficiency, and rising overall costs. Summary of the Invention

[0003] In view of this, the purpose of this 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, comprising: a base; a platform pillar, installed on the top surface of the base, comprising at least two fixed pillars and at least one rotating pillar, the lower ends of the fixed pillars being fixedly connected to the base, and the lower ends of the rotating pillars being rotatably connected to the base; a satellite installation platform, one end of the satellite installation platform being rotatably connected to the upper ends of the fixed pillars, the other end of the satellite installation platform being detachably connected to the upper ends of the rotating pillars, and when the satellite installation platform is detached from the upper ends of the rotating pillars, the satellite installation platform can be flipped around one end in a vertical plane; a cabin support assembly, installed on the side of the satellite installation platform, for supporting the cabin when the satellite cabin is opened; and a lifting beam assembly, installed on the side of the satellite installation platform, for assisting the flipping of the satellite installation platform manually or in conjunction with lifting equipment.

[0005] In some optional embodiments, the satellite mounting platform includes a platform body, multiple cabin connecting plates, at least two second connecting seats, and at least one adapter seat. The platform body is a rectangular plate body, and the multiple cabin connecting plates are distributed and installed on the top surface of the platform body for connecting to the satellite cabin. At least two second connecting seats are installed at one end of the bottom surface of the platform body in the length direction. Each second connecting seat is rotatably connected to a seat bearing installed at the upper end of the fixed pillar through a rotating shaft. The adapter seat is installed at the other end of the bottom surface of the platform body in the length direction, and is detachably connected to the upper end of the rotating pillar through fasteners.

[0006] In some optional embodiments, the satellite installation platform further includes a platform handle, which is installed at one end of the platform body in the length direction and is used to operate the platform body to flip.

[0007] In some optional embodiments, at least one deck support assembly is provided on both long sides of the platform body, and each deck support assembly includes a tray, a first locking member, a deck support member, and a limit member. A slide groove extending vertically to the interior of the platform body is opened on the long side of the platform body, and the tray can be slidably installed in the slide groove along the extension direction of the slide groove. The first locking member is installed on the platform body and is used to lock the position of the tray in the slide groove. The deck support member is an elongated member, and one end of the deck support member is rotatably connected to the end of the pallet facing outside the slide groove. The deck support member can rotate around one end in a plane constructed by the vertical direction of the top surface of the platform body and the sliding direction of the pallet. The limit member is installed at the end of the pallet facing outside the slide groove, and is used to limit the rotation position of the deck support member and to cooperate with the fasteners to fix the deck support member when the deck support member rotates to the vertical direction of the top surface of the platform body.

[0008] In some optional embodiments, a first positioning hole is provided at the end of the tray facing the inside of the slide slot, and the first positioning hole is used to position and cooperate with the first locking piece when the tray slides into the slide slot. A second positioning hole is provided at the end of the tray facing outside the slide slot, and the second positioning hole is used to position and cooperate with the first locking piece when the tray extends out of the slide slot.

[0009] In some optional embodiments, at least one suspension beam assembly is provided on both long sides of the platform body, and each suspension beam assembly includes a suspension beam, a sling connector, and a second locking member. One end of the suspension beam is rotatably connected to the long side of the platform body, and the suspension beam can rotate around one end within the plane where the platform body is located. The sling connector is installed at the other end of the suspension beam and is used to connect the sling of the lifting equipment. The second locking member is used to lock the position of the suspension beam when the suspension beam is rotated to be perpendicular to the long side of the platform body.

[0010] In some optional embodiments, at least one clip is provided on each of the two long sides of the platform body, and the clip is used to clamp the hanging beam when the hanging beam is in contact with the long side.

[0011] In some optional embodiments, a positioning block is provided on a side of the fixing pillar, and the positioning block is used to cooperate with the fastener to fix the satellite mounting platform when the satellite mounting platform is flipped down to a vertical position.

[0012] In some optional embodiments, it further includes: a plurality of adjustable feet installed on the base, which are used to adjust the levelness of the multifunctional tooling for satellite AIT.

[0013] In some optional embodiments, it further includes: a plurality of casters installed on the bottom surface of the base for achieving the movement function.

[0014] Based on the above technical solution, the multifunctional tooling for satellite AIT provided by this application is capable of flipping the satellite installation platform in a vertical plane. The beam assembly can assist in flipping the satellite installation platform manually or in conjunction with lifting equipment. The cabin support assembly can support the cabin when the satellite cabin is opened. This multifunctional tooling for satellite AIT integrates multiple functions such as manual adjustment of satellite attitude, assisted attitude adjustment with lifting equipment, and satellite cabin opening support. There is no need to repeatedly disassemble and assemble equipment, which significantly reduces the process and equipment usage, improves work efficiency, and reduces equipment costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0016] Figure 1 This is a schematic structural diagram of a multifunctional tooling for satellite AIT provided in an embodiment of the present application.

[0017] Figure 2 This is a schematic structural diagram of the extended cabin panel support assembly in a multifunctional tooling for satellite AIT provided in an embodiment of the present application.

[0018] Figure 3 This is a structural schematic diagram of a multifunctional tooling for satellite AIT provided in an embodiment of the present application, in which a deck support member is rotated to a limit position.

[0019] Figure 4 This is a schematic structural diagram of a multifunctional tooling for satellite AIT provided in an embodiment of the present application after the suspension beam assembly and the rotating support are rotated.

[0020] Figure 5 This is a structural schematic diagram of a satellite installation platform in a multifunctional tooling for satellite AIT provided in an embodiment of the present application, which is flipped down to a vertical position.

[0021] Figure 6 This is a structural schematic diagram of a multifunctional tooling for satellite AIT used for satellite cabin opening support provided in an embodiment of the present application.

[0022] Figure 7 A schematic structural diagram of a multifunctional tooling for satellite AIT provided in an embodiment of the present application for a sailboard deployment test, wherein the sailboard is in a folded state.

[0023] Figure 8A schematic structural diagram of a multifunctional tooling for satellite AIT provided in an embodiment of the present application for a sailboard deployment test, wherein the sailboard is in a deployed state.

[0024] Reference numerals: 100, multifunctional tooling for satellite AIT; 10, base; 11, longitudinal beam; 12, transverse beam; 13, support plate; 20, platform pillar; 21, fixed pillar; 211, seat bearing; 212, positioning block; 213, connecting beam; 214, diagonal brace; 22, rotating pillar; 221, first connecting seat; 30, satellite mounting platform; 31, platform body; 32, cabin connecting plate; 33, second connecting seat; 34, adapter seat ; 35. Handle; 36. Buckle; 40. Cabin support assembly; 41. Tray; 42. First locking member; 43. Cabin support member; 44. Limiting member; 50. Lifting beam assembly; 51. Lifting beam; 52. Lifting device connector; 60. Caster; 70. Adjustable foot; 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 DESCRIPTION

[0025] Specific embodiments of the present application will be described in detail below with reference to the accompanying drawings. It is apparent that the described embodiments are only a portion of the embodiments of the present application, and not all of the embodiments. All other embodiments derived by persons of ordinary skill in the art based on the description of this application without inventive effort are intended to fall within the scope of protection of this application.

[0026] In the description of this application, unless otherwise specified or limited, the terms "connect," "dispose," and "install" should be understood broadly. For example, "connect" can mean 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 mean that two components are internally connected. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0027] The terms "upper", "lower", "left", "right", "front", "back", "center", "top", "bottom", "inside", "outside", "vertical", "horizontal", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, or the orientation or position relationship in which the product of the application is usually placed when used. They are only for the convenience of description and simplification of description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, they should not be understood as limiting the present application.

[0028] The terms "first," "second," "third," etc. are merely used to distinguish elements of similar nature, and do not indicate or imply relative importance or a particular order, unless expressly specified and limited otherwise.

[0029] The terms "comprises," "includes," "has," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not expressly listed or inherent to such process, method, article, or apparatus. In the absence of more limitations, an element defined by the phrase "comprising a ..." does not preclude the presence of additional identical elements in the process, method, article, or apparatus that includes the element.

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

[0031] The term "and / or" is a description of the association relationship of associated objects, indicating that three relationships can exist. For example, A and / or B can mean: A exists alone, A and B exist at the same time, and B exists alone.

[0032] The terms "one embodiment," "as an example," "in one implementation," and the like mean that the specific features, structures, materials, or characteristics described in conjunction with the embodiment or example may be included in at least one embodiment or example of the present application. The schematic representations of such terms do not necessarily refer to the same embodiment, nor are they mutually exclusive independent or alternative embodiments. The embodiments and features within the embodiments of the present application may be combined in appropriate ways unless there is a conflict.

[0033] Figure 1 A schematic structural diagram of a multifunctional tool 100 for satellite AIT provided in an embodiment of the present application is shown in FIG. Figure 1 As shown, the embodiment of the present application provides a multifunctional tool 100 for satellite AIT, comprising a base 10, platform pillars 20, a satellite mounting platform 30, a deck support assembly 40, a beam assembly 50, casters 60, and adjustable feet 70. Each component is described in detail below.

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

[0035] As an example, the base 10 includes two longitudinal beams 11, multiple transverse beams 12, and two support plates 13. The two longitudinal beams 11 and two transverse beams 12 are connected end-to-end to form a closed rectangular frame. The remaining transverse beams 12 are connected between the two longitudinal beams 11 and spaced apart along the length of the longitudinal beams 11, dividing the rectangular frame into multiple rectangular units. The two rectangular units at each end are embedded with matching support plates 13. The edges of the support plates 13 are connected to the surrounding longitudinal beams 11 and transverse beams 12. The support plates 13 serve as the mounting base for the platform pillars 20.

[0036] At least three platform struts 20 are mounted on the top surface of the base 10 and are used to mount and support the satellite mounting platform 30. Specifically, the platform struts 20 include at least two fixed struts 21 and at least one rotating strut 22. The lower ends of the fixed struts 21 are fixedly connected to the base 10, while the upper ends of the fixed struts 21 are rotatably connected to the satellite mounting platform 30. The lower ends of the rotating struts 22 are rotatably connected to the base 10, while the upper ends of the rotating struts 22 are detachably connected to the satellite mounting platform 30.

[0037] As an example, the platform support 20 includes two fixed supports 21 and one rotating support 22. The two fixed supports 21 are perpendicular to the base 10 and spaced apart along the length of the crossbeam 12. The lower ends of the two fixed supports 21 are fixed to a crossbeam 12 near one end of the longitudinal beam 11. The upper ends of the two fixed supports 21 are mounted with seat bearings 211. Each seat bearing 211 is rotatably connected to a second connecting seat 33 on the bottom surface of the satellite mounting platform 30 via a rotating shaft. The lower side portions of the two fixed supports 21 are mounted with positioning blocks 212. The positioning blocks 212 are used to cooperate with fasteners to secure the satellite mounting platform 30 when the satellite mounting platform 30 is tilted down to a vertical position. The length of the rotating support 22 is the same as that of the fixed support 21. The lower end of the rotating support 22 is rotatably connected to the support plate 13 near the other end of the longitudinal beam 11 through a pin and a first connecting seat 221, and is located on the vertical midline of the line connecting the lower ends of the two fixed supports 21. The upper end of the rotating support 22 is connected to the adapter seat 34 on the bottom surface of the satellite installation platform 30 (see Figure 4 ) detachable connection. When the upper end of the rotating support 22 is connected to the adapter 34 on the bottom surface of the satellite mounting platform 30, the rotating support 22 is perpendicular to the base 10, and the rotating support 22 and the two fixed supports 21 together support the satellite mounting platform 30. When the upper end of the rotating support 22 is detached from the adapter 34 on the bottom surface of the satellite mounting platform 30, the rotating support 22 can rotate about the lower end in a vertical plane.

[0038] Among them, the two fixed pillars 21 are the main supporting structures 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. The side of each fixed pillar 21 is also provided with a diagonal brace 214. The upper end of each diagonal brace 214 is connected to the side of the fixed pillar 21, and the lower end of the diagonal brace 214 is fixed on the base 10.

[0039] The satellite mounting platform 30 is used to mount the satellite capsule 1. One end of the satellite mounting platform 30 is pivotally connected to the upper end of the fixed support 21, and the other end of the satellite mounting platform 30 is detachably connected to the upper end of the rotating support 22. When the satellite mounting platform 30 is detached from the upper end of the rotating support 22, the satellite mounting platform 30 can be flipped about one end in a vertical plane to adjust the satellite's attitude.

[0040] As an example, the satellite installation 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, with a cabin connecting plate 32 installed at each of the four corners of the top surface of the platform body 31. Two second connecting seats 33 are installed at one end of the bottom surface of the platform body 31 in the longitudinal direction, and are rotatably connected to the seat bearings 211 at the upper ends of the two fixed pillars 21 through rotating shafts. The adapter seat 34 is installed at the other end of the bottom surface of the platform body 31 in the longitudinal direction, and is detachably connected to the upper ends of the rotating pillars 22 through fasteners. The handle 35 is installed at one end of the length direction of the platform body 31, and is mainly used to operate the platform body 31 to flip, and is also used to cooperate with the casters 60 to operate the movement of the entire tooling. Among them, when the adapter seat 34 is connected to 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 disassembled from the upper end of the rotating pillar 22, the platform body 31 can be flipped in a vertical plane around the axis of the second connecting seat 33.

[0041] The cabin support assembly 40 is installed on the side of the satellite installation platform 30 and is used to support the cabin 3 when the satellite cabin is opened.

[0042] As an example, there are two deck support assemblies 40, which are respectively installed on the two long sides (the sides where the long sides of the rectangle are located) of the platform body 31. Figure 2 and Figure 3As shown, each deck support assembly 40 includes a tray 41, a first locking member 42, a deck support member 43, and a stopper 44. Slideways extending perpendicularly into the interior of the platform body 31 are defined on both long sides of the platform body 31. The tray 41 is slidably mounted within the slideways along their extension direction. The tray 41 can be hidden within the slideways or extended from the slideways to support the deck 3. The first locking member 42 is a knob plunger mounted on the top surface of the platform body 31 and inserted into the slideways. A first locating hole (not shown) is defined on the end of the tray 41 facing the slideways. The first locating hole engages with the first locking member 42 when the tray 41 slides into the slideways, locking the tray 41 in place. A second locating hole (not shown) is defined on the end of the tray 41 facing the slideways. The second locating hole engages with the first locking member 42 when the tray 41 extends from the slideways, locking the tray 41 in place. The first locking member 42 can also be mounted on the bottom surface of the platform body 31. The deck support 43 is an elongated member, one end of which is rotatably connected to the end of the tray 41 facing outward from the chute via a rotating shaft. The deck support 43 can rotate about one end within a plane defined by the vertical direction of the top surface of the platform body 31 and the sliding direction of the tray 41. The tray 41 is provided with a long slot that can accommodate the deck support 43. When the deck support 43 rotates into the long slot, the deck support 43 can slide into the chute along with the tray 41 and hide. A limiter 44 is mounted on the end of the tray 41 facing outward from the chute to limit the rotational position of the deck support 43 and to cooperate with fasteners to secure the deck support 43 when the deck support 43 rotates to the vertical direction of the top surface of the platform body 31.

[0043] Among them, when the cabin support assembly 40 is not in use, Figure 1 As shown, the tray 41 and the deck support 43 are hidden in the slide slot together, and the first locking member 42 locks the position of the tray 41. When the deck support assembly 40 is in use, as shown in FIG. Figure 2 As shown, first rotate the first locking member 42 out to release the lock on the tray 41. After the tray 41 is pulled out of the chute and into position, the first locking member 42 is used to lock the position of the tray 41 again. 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 limiter 44, and then the cabin support 43 and the limiter 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 installation platform 30 and is used to assist the satellite installation platform 30 in turning over manually or in conjunction with lifting equipment.

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

[0046] When the hanging beam assembly 50 is not in use, Figure 1 As shown, the hanging beam 51 is fitted with the long side of the platform body 31 and is clamped by the buckle 36 provided on the long side. Figure 4 As shown, the hanging beam 51 is rotated to a position perpendicular to the long side of the platform body 31, and is connected to one end of the hanging beam 51 and the connecting hole on the platform body 31 through a second locking piece to fix the position of the hanging beam 51. At this time, the hanging beam 51 can be held by hand to assist in flipping the satellite installation platform 30. The sling connector 52 can be connected to the sling of lifting equipment such as a crane or a crane to assist in flipping the satellite installation platform 30.

[0047] A plurality of casters 60 are mounted on the base 10 to enable the entire tooling to move. The casters 60 may be fixed casters or movable casters.

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

[0049] There are multiple adjustable feet 70 installed on the base 10 for adjusting the levelness of the entire tooling.

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

[0051] The multifunctional tooling 100 for satellite AIT can be used for satellite cabin opening support, and can meet the needs of multiple cabin openings or placing the movable cabin panel 3 horizontally during the satellite AIT stage.

[0052] As an example, the structure of the satellite mounted on the tooling is as follows Figure 6 As shown, the satellite installation platform 30 is in a horizontal position supported by the fixed support 21 and the rotating support 22, and the satellite cabin 1 is connected to the cabin connecting plate 32 of the satellite installation platform 30 through the cabin adapter 2. Before the satellite cabin is opened, for each cabin support assembly 40, as shown in FIG. Figure 2 As shown, first release the lock of the first locking member 42 on the tray 41, pull the tray 41 out of the slide slot and into position, then lock the position of the tray 41 by the first locking member 42, and then, as shown in FIG. Figure 3 As shown, the panel support 43 is rotated perpendicular to the top surface of the platform body 31, so that the panel support 43 is restrained by the stopper 44. The panel support 43 and the stopper 44 are then connected with fasteners to fix the position of the panel support 43. The upper end of the panel support 43 can now be used to support the panel 3. For panels 3 that need to be opened, the screws connecting the panel 3 to the cabin body 1 are removed, and the hinge 4 is installed to allow the panel 3 to rotate via the hinge 4. When the satellite is opened, the panel 3 is rotated so that it is placed horizontally on the panel support 43. The panel support 43 provides the support function for opening the cabin, which can be used in scenarios such as single-unit installation, whole-satellite wiring, and open cabin testing.

[0053] The multifunctional tooling 100 for satellite AIT can be used for satellite attitude adjustment, meeting the satellite attitude adjustment requirements of windsurfing deployment tests. Satellite attitude adjustment includes manual satellite attitude adjustment, crane-assisted attitude adjustment, and precise satellite attitude adjustment.

[0054] As an example, the initial attitude of the satellite is Figure 6 As shown, the satellite installation platform 30 is in a horizontal position supported by the fixed support 21 and the rotating support 22. The satellite cabin 1 is connected to the cabin connecting plate 32 of the satellite installation platform 30 through the cabin adapter 2 and is in a horizontal posture. When the satellite needs to be adjusted from a horizontal posture to a vertical posture, as shown in FIG. Figure 4 As shown, first rotate the suspension beam 51 of each suspension beam assembly 50 to a position perpendicular to the long side of the platform body 31, and secure the suspension beam 51 in place using a second locking member. Next, remove the adapter 34 of the satellite mounting platform 30 from the upper end of the rotating support 22. The satellite's attitude can then be adjusted manually or with the use of a lifting device. For smaller satellites (e.g., less than 80 kg), manual adjustment of the satellite's attitude is possible. Specifically, two personnel stand on either side of the satellite mounting platform 30, each holding a suspension beam 51 and gently lowering it. Another personnel presses down on the handle 35 of the satellite mounting platform 30 and gently lifts it upward. Figure 5 As shown, when the satellite mounting platform 30 is tilted down to a vertical position, the satellite mounting platform 30 and the positioning block 212 are connected by fasteners to fix the position of the satellite mounting platform 30. For satellites that are difficult to adjust manually (for example, weighing 80kg-150kg), a crane or other lifting equipment is required. Specifically, the sling connectors 52 of the beam assembly 50 on both sides of the satellite mounting platform 30 are connected to the sling of the crane, and the satellite mounting platform 30 is slowly lowered by the crane. Figure 5 As shown, when the satellite mounting platform 30 is tilted down to a vertical position, the satellite mounting platform 30 and the positioning block 212 are connected by fasteners to fix the position of the satellite mounting platform 30. Afterwards, a level ruler is placed on the satellite reference surface (referring to the top surface of the cabin 1), and the satellite level is precisely adjusted by adjusting each adjustable foot 70 to ensure that the tooling reaches the sailboard installation posture. After the satellite posture is accurately adjusted, the sailboard 5 can be installed and the sailboard 5 deployment test can be carried out. Figure 7 and Figure 8 .

[0055] In summary, the multifunctional tooling for satellite AIT provided in the embodiment of the present application is capable of flipping the satellite installation platform in a vertical plane, the beam assembly can assist in flipping the satellite installation platform manually or in conjunction with lifting equipment, and the cabin support assembly can support the cabin when the satellite cabin is opened. The multifunctional tooling for satellite AIT integrates multiple functions such as manual adjustment of satellite attitude, lifting equipment-assisted attitude adjustment, satellite cabin opening support, and precise adjustment of satellite attitude. There is no need to repeatedly disassemble and assemble equipment, which significantly reduces the process and equipment usage, improves work efficiency, and reduces equipment costs.

[0056] The above is only a specific implementation method of the present application, but the scope of protection of the present application is not limited thereto. Any technician familiar with the field can easily think of various changes or replacements within the technical scope disclosed in the present application, which should all be included in the scope of protection of the present application.

Claims

1. A multifunctional tool for satellite AIT, characterized by: include: base; Platform pillars, mounted on the top surface of the base, including at least two fixed pillars and at least one rotating pillar, wherein the lower ends of the fixed pillars are fixedly connected to the base, and the lower ends of the rotating pillars are rotatably connected to the base; a satellite mounting platform, one end of the satellite mounting platform being rotatably connected to the upper end of each of the fixed pillars, the other end of the satellite mounting platform being detachably connected to the upper end of the rotating pillar, and the satellite mounting platform being capable of flipping about one end in a vertical plane when the satellite mounting platform is detached from the upper end of the rotating pillar; A cabin support assembly is installed on the side of the satellite installation platform and is used to support the cabin when the satellite cabin is opened; as well as The hanging beam assembly is installed on the side of the satellite installation platform and is used to assist the satellite installation platform to flip over manually or in conjunction with lifting equipment.

2. The multifunctional tool for satellite AIT according to claim 1, characterized in that: The satellite mounting platform includes a platform body, multiple cabin connecting plates, at least two second connecting seats, and at least one adapter seat. The platform body is a rectangular plate body. Multiple cabin connecting plates are distributed and installed on the top surface of the platform body for connecting to the satellite cabin. At least two second connecting seats are installed at one end of the bottom surface of the platform body in the length direction. Each second connecting seat is rotatably connected to a seat bearing installed at the upper end of the fixed pillar through a rotating shaft. The adapter seat is installed at the other end of the bottom surface of the platform body in the length direction and is detachably connected to the upper end of the rotating pillar through fasteners.

3. The multifunctional tool for satellite AIT according to claim 2, characterized in that: The satellite installation platform further includes a platform handle, which is installed at one end of the platform body in the length direction and is used to operate the platform body to flip.

4. The multifunctional tool for satellite AIT according to claim 2, characterized in that: and a plurality of locking members are installed on the platform body to lock the position of the tray in the slide groove.

5. The multifunctional tool for satellite AIT according to claim 4, characterized in that: A first positioning hole is provided at the end of the tray facing the inside of the slide slot, and the first positioning hole is used to position and cooperate with the first locking piece when the tray slides into the slide slot. A second positioning hole is provided at the end of the tray facing outside the slide slot, and the second positioning hole is used to position and cooperate with the first locking piece when the tray extends out of the slide slot.

6. The multifunctional tool for satellite AIT according to claim 2, characterized in that: At least one of the suspension beam assemblies is provided on each of the two long sides of the platform body, and each of the suspension beam assemblies includes a suspension beam, a sling connector, and a second locking member. One end of the suspension beam is rotatably connected to the long side of the platform body, and the suspension beam can rotate around one end within the plane where the platform body is located. The sling connector is installed at the other end of the suspension beam and is used to connect the sling of the lifting equipment. The second locking member is used to lock the position of the suspension beam when the suspension beam is rotated to be perpendicular to the long side of the platform body.

7. The multifunctional tool for satellite AIT according to claim 3, characterized in that: At least one clip is provided on each of the two long side surfaces of the platform body, and the clip is used to clamp the hanging beam when the hanging beam is in contact with the long side surfaces.

8. The multifunctional tool for satellite AIT according to claim 1, characterized in that: A positioning block is provided on the side of the fixing pillar, and the positioning block is used to cooperate with a fastener to fix the satellite installation platform when the satellite installation platform is turned down to a vertical position.

9. The multifunctional tool for satellite AIT according to claim 1, characterized in that: Also includes: A plurality of adjustable feet are installed on the base and are used to adjust the levelness of the multifunctional tooling for the satellite AIT.

10. The multifunctional tool for satellite AIT according to claim 1, characterized in that: Also includes: A plurality of casters are installed on the bottom surface of the base for realizing the movement function.

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