CN118342261B - Satellite fairing assembly system - Google Patents

Abstract

The embodiment of the application provides a satellite fairing assembly system. The satellite fairing assembly system comprises a first assembly component and a second assembly component, wherein the first assembly component and the second assembly component are respectively connected with one fairing body, at least one of the first assembly component and the second assembly component comprises a mounting frame and an adjusting device, the mounting frame is used for being connected with the fairing body, the adjusting device is connected with the mounting frame and used for driving the mounting frame to move along at least one of a first direction parallel to a horizontal plane, a second direction parallel to the horizontal plane and a vertical direction so as to adjust the positions of the fairing bodies, and the fairings are butted to form the fairing, wherein the first direction and the second direction are intersected. The embodiment of the application realizes the requirements of various working conditions in the radome closing process by adopting one set of tool, reduces the equipment types in the rocket assembly process, simplifies the operation flow and is more convenient to use.

Description

Satellite fairing assembly system

Technical Field

The application relates to the technical field of aerospace equipment, in particular to a satellite fairing assembly system.

Background

The satellite fairing is used for protecting satellites and other payloads so as to prevent the satellites from being influenced by harmful environments such as aerodynamic force, pneumatic heating, sound vibration and the like, and is an important component of a rocket for transportation.

At present, most of the cowling closing tools adopt an integral structural form to complete the cowling half-cover closing, firstly, the cowling closing tools are assembled with the cowling half-cover respectively, then the cowling is jointed by pushing the tools, and then the vertical lifting and overturning of the cowling are realized by utilizing special lifting and overturning tools. In the rocket assembly process, equipment for assembling the fairing is more in variety and is complex in management and operation.

Disclosure of Invention

Aiming at the defects of the prior art, the application provides a satellite fairing assembly system which is used for solving the technical problems of more equipment types for assembling fairings and complicated management and operation in the prior art.

In a first aspect, an embodiment of the present application provides a satellite fairing assembly system, including a first assembly component and a second assembly component, where the first assembly component and the second assembly component are respectively connected to a fairing body;

at least one of the first fitting component and the second fitting component comprises:

The mounting frame is used for being connected with the fairing body;

The adjusting device is connected with the mounting frame and is used for driving the mounting frame to move along at least one of a first direction parallel to a horizontal plane, a second direction parallel to the horizontal plane and a vertical direction so as to adjust the positions of the fairing bodies, so that the fairing bodies are butted to form a fairing;

Wherein the first direction and the second direction intersect.

Optionally, the satellite fairing assembly system further comprises a support platform disposed between the first assembly component and the second assembly component;

the supporting platform comprises a supporting platform body and a rotary table arranged on the supporting platform body, the rotary table is used for being connected with the satellite support connecting structure, and the rotary table is rotatably arranged around the axis of the fairing relative to the supporting platform body so as to adjust the position of the satellite support connecting structure, so that the satellite support connecting structure is in butt joint with the fairing.

Optionally, the adjusting device comprises a first moving mechanism, and the first moving mechanism is respectively connected with the fairing body and the supporting platform body;

The first moving mechanism is movably arranged along a first direction relative to the supporting platform body so as to enable the fairing bodies to be close to or far away from each other.

Optionally, the first moving mechanism includes:

the mounting frame is arranged at the top of the base;

the roller is arranged at the bottom of the base and is rotatably arranged relative to the base;

The adjusting device further comprises a guide rail bracket and a first guide rail arranged on the guide rail bracket, the guide rail bracket is connected with the supporting platform body, the first guide rail extends along a first direction, and the idler wheels are in sliding fit with the first guide rail.

Optionally, the adjusting device further comprises a second moving mechanism, the second moving mechanism is arranged on the first moving mechanism, and the first moving mechanism is connected with the fairing body through the second moving mechanism;

At least part of the structure of the second moving mechanism is movably arranged along the second direction relative to the first moving mechanism so as to adjust the position of the fairing body in the second direction.

Optionally, the second moving mechanism includes:

the first spiral lifter is arranged on the base of the first moving mechanism, and a screw rod of the first spiral lifter is movably arranged along a second direction relative to the base;

the sliding seat is respectively connected with the mounting frame and the screw rod, and the sliding seat and the mounting frame move along the second direction under the drive of the screw rod;

The adjusting device further comprises a second guide rail arranged on the base, the second guide rail extends along a second direction, and the sliding seat is in sliding fit with the second guide rail.

Optionally, the adjusting device further comprises a third moving mechanism, the third moving mechanism is arranged on the second moving mechanism, and the second moving mechanism is connected with the fairing body through the third moving mechanism;

At least part of the structure of the third moving mechanism is arranged movably along the vertical direction relative to the second moving mechanism so as to adjust the position of the fairing body in the vertical direction.

Optionally, the mounting frame includes:

the first ring frame is used for being connected with the fairing body and provided with a first arc-shaped groove for accommodating the fairing body;

The second ring frame is used for being connected with the fairing body, the second ring frame is provided with a second arc-shaped groove for accommodating the fairing body, the first ring frame and the second ring frame are arranged at intervals along the axial direction of the fairing, at least one of the first ring frame and the second ring frame is provided with a lifting lug, and the lifting lug is used for being connected with hoisting equipment;

And the supporting frame is respectively connected with the first ring frame and the second ring frame and is arranged on the adjusting device.

Optionally, the support platform further comprises:

the leveling support legs are arranged on the supporting platform body and used for leveling the turntable so that the top surface of the turntable is parallel to the horizontal plane;

The truckle is installed in the bottom of supporting platform body, and rotationally sets up for the supporting platform body, under the exogenic action, the truckle rotates and drives the supporting platform body and remove.

Optionally, the support platform further comprises:

The rotary support structure is arranged on the support platform body, and the turntable is rotatably connected with the support platform body through the rotary support structure;

The rotary driving mechanism is arranged on the supporting platform body, is connected with the turntable and is driven by the rotary driving mechanism to rotate;

the rotary locking mechanism is arranged on the supporting platform body and is used for being matched with the turntable so as to lock the position of the turntable.

The technical scheme provided by the embodiment of the application has the beneficial technical effects that:

In the embodiment of the application, the first assembly component and the second assembly component are respectively connected with one fairing body, and the first assembly component and the second assembly component are respectively used for adjusting the positions of the connected fairing bodies so that the fairing bodies can be mutually close to each other to form the fairing for the joint cover.

The adjusting device, the mounting frame and the fairing body are connected in sequence, the mounting frame has a supporting effect on the fairing body, the mounting frame can be driven to move in the horizontal plane along the first direction and the second direction and move in the vertical plane along the vertical direction through the adjusting device, so that the fairing body can move in the horizontal plane along the two directions (namely the first direction and the second direction) and move in the vertical plane along the up-down direction (namely the vertical direction) along multiple degrees of freedom, the position of the fairing body is adjusted, the fairing bodies are convenient to be close to and aligned with each other, the joint fairing function is realized, and the assembly process of the fairing is completed.

According to the satellite fairing assembly system provided by the embodiment of the application, the mounting frame is driven by the adjusting device to move in two directions in the horizontal plane to realize horizontal lifting and move in the vertical plane to realize vertical lifting, so that the requirements of butting the satellite fairing in two modes of horizontal and vertical with a rocket cabin section are met, the working conditions of horizontal lifting, vertical butt joint of the fairing halves and the like in the rocket fairing closing process can be completed, the butting of the two fairing halves in the vertical state is realized, and the satellite fairing is formed. In the processes of hoisting and jointing the radome half-covers, the radome half-covers do not need to be replaced by different tools, and the requirements of various working conditions in the radome jointing process can be met by adopting one set of tools, so that the types of equipment in the rocket assembly process are reduced, the operation flow is simplified, and the use is more convenient.

Additional aspects and advantages of the application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application.

Drawings

The foregoing and/or additional aspects and advantages of the application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings, in which:

Fig. 1 is a schematic structural diagram of a satellite fairing assembly system according to an embodiment of the application;

Fig. 2 is a schematic structural diagram of a support platform of a satellite fairing assembly system according to an embodiment of the application;

FIG. 3 is a schematic view of a ground rail and a support platform of a satellite fairing assembly system according to an embodiment of the present application;

fig. 4 is a schematic structural view of an adjusting device and a supporting platform of a satellite fairing assembly system according to an embodiment of the present application;

Fig. 5 is a schematic structural diagram of a mounting frame and a fairing body of a satellite fairing assembly system according to an embodiment of the application (where the fairing body is in a horizontal state);

Fig. 6 is a schematic structural diagram of a mounting frame, a fairing body and a hoisting device of a satellite fairing assembly system according to an embodiment of the application (in which the fairing body is in a vertical state);

fig. 7 is a schematic structural diagram of a mobile docking vehicle of a satellite fairing assembly system according to an embodiment of the present application;

FIG. 8 is a schematic diagram of an assembly structure of a satellite fairing assembly system and a fairing according to an embodiment of the application;

fig. 9 is a schematic view of a hoisting structure of a fairing according to an embodiment of the application.

Reference numerals:

100-satellite fairing assembly; 10-a first assembly component; 20-a second fitting component; 30-mounting a frame; 31-a first ring frame; 32-a second ring frame; 33-lifting lugs; 34-supporting frames; 35-supporting the ground support leg; 40-adjusting means; 41-a first movement mechanism; 411-base; 412-a roller; 413-a first scale; 414-a first pointer; 42-ground rail; 421-a rail bracket; 422-first rail; 423-a second rail; 424-ground rail limit seat; 425-first positioning holes; 426-ground rail connection; 427-first limit baffle; 428-a third rail; 429-a second limit baffle; 43-a second movement mechanism; 431-first screw lift; 432-sliding seat; 44-a third movement mechanism; 441-a second screw lift; 442-a support plate; 443-guiding holes; 444-second scale; 445-second pointer; 45-moving the docking vehicle; 50-supporting a platform; 51-supporting a platform body; 511-a positioning seat; 52-a turntable; 53-leveling the legs; 54-casters; 55-slewing bearing; 56-a slewing drive mechanism; 561-linear drive structure; 562-a linkage structure; 57-a swivel locking mechanism; 58-a turntable limiting structure; 581-arc-shaped limiting holes; 582-stop lever; 60-fairing; 61-fairing body; 62-satellite stand connection structure; 63-a first mounting hole; 64-a second mounting hole; 70-hoisting equipment.

Detailed Description

Embodiments of the present application are described below with reference to the drawings in the present application. It should be understood that the embodiments described below with reference to the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application, and the technical solutions of the embodiments of the present application are not limited.

As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless expressly stated otherwise, as understood by those skilled in the art. It should be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of other features, information, data, steps, operations, elements, components, and/or groups thereof, all of which may be included in the present application. The term "and/or" as used herein refers to at least one of the items defined by the term, e.g., "a and/or B" may be implemented as "a", or as "B", or as "a and B".

For the purpose of making the objects, technical solutions and advantages of the present application more apparent, the embodiments of the present application will be described in further detail with reference to the accompanying drawings.

At present, most of the cowling closing tools adopt an integral structural form to complete the cowling half-cover closing, firstly, the cowling closing tools are assembled with the cowling half-cover respectively, then the cowling is jointed by pushing the tools, and then the vertical lifting and overturning of the cowling are realized by utilizing special lifting and overturning tools. During assembly, the fairing closing tool only realizes the closing function, and the lifting and overturning functions of the star cover assembly are realized by additionally designing the lifting and overturning tool, so that more equipment types are used for assembling the fairing, and the equipment types are excessive in the rocket assembly process, and the management and operation are complex. Meanwhile, the cover closing tool is not compatible with the lifting and overturning functions of the star cover assembly, so that more mechanical interfaces are required to be designed for the fairing, the weight of the fairing can be increased, and the carrying capacity is correspondingly reduced.

In addition, the part of the fairing-covering tool adopts unguided universal wheel movement in the process of covering the joint, and the risk of collision with satellites exists because of unguided in the process of butting. In other schemes, although guide rails are adopted for guide butt joint, the star cover assembly supporting platform and the guide rails are of an integrated structure, the whole structure is adopted, the tool size is large, the adjusting capacity is poor, the transportation is difficult, and the transportation cost is high.

The application provides a satellite fairing assembly system, which aims to solve at least one technical problem in the prior art.

The following describes the technical scheme of the present application and how the technical scheme of the present application solves the above technical problems in detail with specific embodiments. It should be noted that the following embodiments may be referred to, or combined with each other, and the description will not be repeated for the same terms, similar features, similar implementation steps, and the like in different embodiments.

An embodiment of the present application provides a satellite fairing assembly system, where a schematic structural diagram of the satellite fairing assembly system 100 is shown in fig. 1, and the satellite fairing assembly system includes a first assembly 10 and a second assembly 20 (dashed boxes in fig. 1 are used to distinguish the first assembly 10 and the second assembly 20, the first assembly 10 is located on one side of the dashed boxes, and the second assembly 20 is located on the other side of the dashed boxes), and the first assembly 10 and the second assembly 20 are respectively connected to a fairing body 61 (as shown in fig. 5, 6, 8, and 9). The first assembly component 10 and the second assembly component 20 comprise a mounting frame 30 and an adjusting device 40, the mounting frame 30 is used for being connected with a fairing body 61, the adjusting device 40 is connected with the mounting frame 30 and used for driving the mounting frame 30 to move along a first direction parallel to a horizontal plane, a second direction parallel to the horizontal plane and a vertical direction so as to adjust the position of the fairing body 61, and the fairing bodies 61 are abutted to form the fairing 60, wherein the first direction and the second direction are intersected.

In the embodiment of the present application, the first assembly 10 and the second assembly 20 are respectively connected to one fairing body 61, and the first assembly 10 and the second assembly 20 are respectively used for adjusting the positions of the connected fairing bodies 61, so that the fairing bodies 61 can be close to each other to form the fairing 60 (or the fairing 60 is a star-shaped assembly) for the joint cover.

The adjusting device 40, the mounting frame 30 and the fairing body 61 are sequentially connected, the mounting frame 30 has a supporting effect on the fairing body 61, the mounting frame 30 can be driven to move in the first direction and the second direction in the horizontal plane and move in the vertical direction in the vertical plane through the adjusting device 40, so that the fairing body 61 can move in the two directions (namely the first direction and the second direction) in the horizontal plane and move in the vertical plane along the multiple degrees of freedom (namely the vertical direction), the position of the fairing body 61 is adjusted, the fairing bodies 61 are conveniently close to each other and aligned, the joint fairing function is realized, and the assembly process of the fairing 60 is completed.

In the related art, the fairing 60 includes two fairing halves that are separately provided, and the two fairing halves are joined to each other to form the fairing 60. In the embodiment of the present application, the fairing body 61 is a fairing half, and the first assembly component 10 and the second assembly component 20 are respectively connected to one fairing body 61 for adjusting the position of the fairing body 61, so that the two fairing bodies 61 form the fairing 60 for the joint cover. Of course, when the fairing 60 includes three or more fairing sections that are separately provided, the present application may adaptively adjust the number of the first assembly components 10 and/or the second assembly components 20 such that the number of the first assembly components 10 and the number of the second assembly components 20 are respectively connected to one fairing section, and adjust the positions of the fairing sections such that the three or more fairing sections may be adjacent to each other to form the fairing 60 for the joint cover.

According to the satellite fairing assembly system provided by the embodiment of the application, under the drive of the regulating device 40, the mounting frame 30 is provided with the functions of horizontally lifting in two directions in a horizontal plane and vertically lifting in an up-down direction in a vertical plane, so that the requirements of butting the satellite fairing in two modes of horizontally and vertically with a rocket cabin section are met, the working conditions of horizontally lifting, vertically lifting and vertically butting the fairing halves in the vertical state in the rocket fairing-closing process can be completed, and the purpose of butting the two fairing halves in the vertical state is achieved. In the processes of hoisting and jointing the radome half-covers, the radome half-covers do not need to be replaced by different tools, and the requirements of various working conditions in the radome jointing process can be met by adopting one set of tools, so that the types of equipment in the rocket assembly process are reduced, the operation flow is simplified, and the use is more convenient.

Of course, in some alternative embodiments of the present application, the adjusting device 40 may be further configured to move the mounting frame 30 in a first direction, a second direction, a vertical direction, a first direction and a second direction, a first direction and a vertical direction, or a second direction and a vertical direction, as required.

Of course, in some alternative embodiments of the present application, only the first assembly 10 may include the mounting frame 30 and the adjusting device 40, the position of the connected fairing 61 may be adjusted, the second assembly 20 may be used to support the fairing 61, the position of the fairing 61 connected to the second assembly 20 may be fixed, or only the second assembly 20 may include the mounting frame 30 and the adjusting device 40, the position of the connected fairing 61 may be adjusted, the first assembly 10 may be used to support the fairing 61, and the position of the fairing 61 connected to the first assembly 10 may be fixed.

Optionally, the first direction and the second direction are perpendicular.

Optionally, as shown in fig. 1 to 4, the satellite fairing assembly system 100 further includes a support platform 50 disposed between the first assembly 10 and the second assembly 20, the support platform 50 including a support platform body 51 and a turntable 52 disposed on the support platform body 51, the turntable 52 being configured to be coupled to a satellite support connection structure 62 (shown in fig. 8 and 9), the turntable 52 being rotatably disposed relative to the support platform body 51 about an axis of the fairing 60 (shown in fig. 8 and 9) to adjust a position of the satellite support connection structure 62 to interface the satellite support connection structure 62 with the fairing 60.

In the embodiment of the present application, the supporting platform body 51 has a supporting function on the turntable 52, and the turntable 52 rotates around the axis of the fairing 60 to drive the satellite support connecting structure 62 to rotate together, so as to adjust the position and angle of the satellite support connecting structure 62 in the horizontal plane, and align the satellite support connecting structure 62 with the fairing 60, so as to complete the butt joint, and facilitate the connection between the satellite support connecting structure 62 and the fairing 60, thereby forming the satellite fairing.

The support platform 50 serves as a carrier body for the satellite support connection structure 62, is centrally disposed throughout the satellite fairing assembly system 100, and the support platform 50 also serves as a satellite fairing assembly support body after the satellite fairing is covered. The satellite fairing assembly system 100 of the present embodiment provides 4 degree of freedom adjustment of the fairing body 61 and fairing 60 in which movement in two directions in a horizontal plane, i.e., horizontal movement in a first direction and horizontal movement in a second direction, up and down movement in a vertical direction, rotational movement about the fairing axis. The device can realize the functions of horizontal lifting, vertical lifting and rotation butt joint of the satellite support connecting structure of the satellite cover assembly, and meet the requirements of the horizontal and vertical modes of the satellite cover assembly for butt joint with rocket cabin sections. In the processes of lifting the fairing and closing the fairing, lifting the star cover assembly and rotating and butting the star cover assembly and the satellite support connecting structure, different tools are not required to be replaced, and the operation flow is simplified.

Alternatively, as shown in fig. 8, a first mounting hole 63 is formed on the fairing 60, a second mounting hole 64 is formed on the satellite support connecting structure 62, the satellite support connecting structure 62 is rotated by rotating the turntable 52, the second mounting hole 64 is aligned with the first mounting hole 63, and then a locking member (such as a bolt) is used to connect the satellite support connecting structure 62 and the fairing 60 through the first mounting hole 63 and the second mounting hole 64.

Optionally, as shown in fig. 5 and 6, in the embodiment of the present application, the mounting frame 30 includes a first ring frame 31, a second ring frame 32 and a supporting frame 34, where the first ring frame 31 is used to connect with the fairing body 61, the first ring frame 31 has a first arc-shaped slot for accommodating the fairing body 61, the second ring frame 32 is used to connect with the fairing body 61, the second ring frame 32 has a second arc-shaped slot for accommodating the fairing body 61, and the first ring frame 31 and the second ring frame 32 are arranged at intervals along the axial direction of the fairing, optionally, the first arc-shaped slot is attached to the outer wall of the connection portion between the fairing body 61 and the first ring frame 31, and the second arc-shaped slot is attached to the outer wall of the connection portion between the fairing body 61 and the second ring frame 32, so as to better accommodate, mount and support the fairing body 61. Optionally, the first arcuate slot and the second arcuate slot are the same shape and inner diameter. At least one of the first ring frame 31 and the second ring frame 32 is provided with a lifting lug 33, the lifting lug 33 is used for being connected with a lifting device 70, a supporting frame 34 is respectively connected with the first ring frame 31 and the second ring frame 32, and the supporting frame 34 is arranged on the adjusting device 40.

In the embodiment of the application, the first ring frame 31 and the second ring frame 32 are respectively connected with different positions of the same fairing half cover, then the supporting frame 34 is respectively connected with the first ring frame 31 and the second ring frame 32 to form a combined body of the mounting frame 30 and the fairing half cover, and the two half cover combined bodies are vertically jointed with each other to form the star cover combined body. At least one of the first ring frame 31 and the second ring frame 32 is provided with a lifting lug 33, the lifting lug 33 is used as an interface for lifting and overturning the radome assembly, the lifting device 70 is connected with the lifting lug 33 to finish overturning of the radome assembly, the mounting frame 30 integrates the function of the radome assembly overturning tool, the radome assembly overturning function is realized on the premise of meeting the requirements of covering the radome half-shells, the contact area of the mounting frame 30 and the radome 60 is large, the tool rigidity is high, after the connection with the radome, the radome half-shells and the radome assembly overturning process can play a protective role on the radome, the radome hoisting and overturning structural strength is reduced, and the carrying capacity of a rocket is improved.

Alternatively, as shown in fig. 5 and 6, in the embodiment of the present application, a side of the support frame 34 facing the adjusting device 40 is provided with a support leg 35, and the support frame 34 is connected to the adjusting device 40 through the support leg 35. The support bracket 34 provides a ground support leg 35 that rests vertically onto the adjustment device 40 to assist in completing the closure.

Optionally, the ground supporting legs 35 are arranged in a one-to-one correspondence with the adjusting devices 40. As shown in fig. 1, 3 to 6, in the embodiment of the present application, three sets of adjustment devices 40 and three ground supporting legs 35 are respectively disposed on two sides of the support platform 50 along the first direction, one ground supporting leg 35 is connected to one adjustment device 40, each adjustment device 40 is connected to the support frame 34 through the corresponding ground supporting leg 35, and the three adjustment devices 40 simultaneously adjust the position of the support frame 34. Each side adjusting device 40 is used for bearing the mounting frame 30 connected with the fairing half cover, so as to support each side supporting leg 35, support the side supporting frame 34 and drive the mounting frame 30 to move.

Alternatively, as shown in fig. 7, in the embodiment of the present application, the adjusting device 40 includes a first moving mechanism 41, where the first moving mechanism 41 is connected to the fairing body 61 and the supporting platform body 51, respectively, and the first moving mechanism 41 is movably disposed along a first direction relative to the supporting platform body 51, and the first moving mechanism 41 drives the fairing bodies 61 to move along the first direction so as to make the fairing bodies 61 approach to or separate from each other. The hood bodies 61 are brought close to each other to complete the hood joining process.

Optionally, as shown in fig. 7, in the embodiment of the present application, the first moving mechanism 41 includes a base 411 and a roller 412, the mounting frame 30 is mounted on the top of the base 411, the base 411 supports the mounting frame 30, the roller 412 is mounted on the bottom of the base 411 and is rotatably disposed relative to the base 411, the roller 412 rotates to drive the base 411 to move, thereby driving the mounting frame 30 and the fairing 61 to move, the adjusting device 40 further includes a rail bracket 421 and a first rail 422 (as shown in fig. 3 and 4) mounted on the rail bracket 421, the rail bracket 421 supports the first rail 422, the rail bracket 421 is connected to the supporting platform body 51, such that the relative positions of the rail bracket 421 and the supporting platform body 51 are fixed, the first rail 422 extends along a first direction, the roller 412 is slidably engaged with the first rail 422, the roller 412 has a guiding effect on the roller 412 slides along the first rail 422, and the base 411 can move along the first direction, thereby driving the mounting frame 30 and the fairing 61 to move along the first direction, and further driving each fairing 61 to approach or separate from each other, and the fairing 61 approaches each other.

Alternatively, as shown in fig. 3 and 4, in the embodiment of the present application, the first rail 422 is connected to the rail bracket 421 to form the ground rail 42. Optionally, as shown in fig. 3 and 4, in the embodiment of the present application, the rail bracket 421 is detachably connected to the supporting platform body 51, and in use, the rail bracket 421 and the supporting platform body 51 may be assembled together, and in idle or carrying, the rail bracket 421 and the supporting platform body 51 may be detached for storage and transportation.

Optionally, the rail bracket 421 is provided with a ground rail limiting seat 424 (as shown in fig. 3), the supporting platform body 51 is provided with a positioning seat 511 (as shown in fig. 2), the ground rail limiting seat 424 is provided with a first positioning hole 425 (as shown in fig. 3), the positioning seat 511 is provided with a second positioning hole, and a locking member (such as a bolt or the like) passes through the first positioning hole 425 and the second positioning hole to detachably and fixedly connect the rail bracket 421 with the supporting platform body 51, so that the installation guiding and limiting of the ground rail are realized, and the assembly and the disassembly are convenient.

Optionally, the rail bracket 421 is a frame structure formed by splicing a plurality of rod structures. Optionally, the rod structure is an aluminum profile, is light, and contributes to achieving light weight.

As shown in fig. 3 and 4, in the embodiment of the present application, three groups of adjustment devices 40 are respectively disposed on two sides of the support platform 50 along the first direction, the three groups of adjustment devices 40 include three ground rails 42, and the rail brackets 421 are connected by a ground rail connecting member 426, so as to achieve connection between the ground rails, thereby forming a combination. Optionally, the ground rail connection 426 is an aluminum profile.

Optionally, as shown in fig. 7, in the embodiment of the present application, two rows of rollers 412 are disposed at the bottom of the base 411, each row of rollers 412 is arranged along a first direction, the two rows of rollers 412 are arranged at intervals along a direction perpendicular to the first direction, two rows of first rails 422 corresponding to the two rows of rollers 412 one by one are mounted on the rail bracket 421, each row of rollers 412 is slidably matched with the corresponding first rail 422, a first limit baffle 427 is further disposed at the bottom of the base 411, the first limit baffle 427 is disposed at the inner side of the rollers 412, the size of the first limit baffle 427 is larger than the size of the rollers 412 along the radial direction of the rollers 412, and when the rollers 412 slide along the first rails 422, the first limit baffle 427 can limit the deflection of the rollers 412, prevent the rollers 412 from being separated from the first rails 422, and ensure that the rollers 412 slide along the first rails 422.

Optionally, as shown in fig. 7, in the embodiment of the present application, the adjusting device 40 further includes a second moving mechanism 43, where the second moving mechanism 43 is disposed on the first moving mechanism 41, the first moving mechanism 41 is connected to the mounting frame 30 through the second moving mechanism 43, the first moving mechanism 41 has a supporting effect on the second moving mechanism 43 and the mounting frame 30, the first moving mechanism 41 moves along a first direction to drive the second moving mechanism 43, the mounting frame 30 and the fairing bodies 61 to move along the first direction so as to make each fairing body 61 approach to butt joint, and at least part of structures of the second moving mechanism 43 are movably disposed along a second direction relative to the first moving mechanism 41 to drive the mounting frame 30 and the fairing bodies 61 to move along the second direction so as to adjust positions of the fairing bodies 61 in the second direction, so as to align each fairing body 61 for facilitating butt joint.

Alternatively, as shown in fig. 7, in the embodiment of the present application, the second moving mechanism 43 includes a first spiral lifter 431 and a sliding seat 432, the first spiral lifter 431 is mounted on the base 411 of the first moving mechanism 41, the base 411 has a supporting function on the first spiral lifter 431, a screw rod of the first spiral lifter 431 is movably disposed along a second direction relative to the base 411, the sliding seat 432 is respectively connected with the mounting frame 30 and the screw rod, the screw rod of the first spiral lifter 431 moves along the second direction relative to the base 411 under the action of external force, the sliding seat 432 and the mounting frame 30 move along the second direction under the action of the screw rod, so as to drive the fairing body 61 to move along the second direction, and the adjusting device 40 further includes a second guide rail 423 mounted on the base 411, the second guide rail 423 extends along the second direction, and the sliding seat 432 and the second guide rail 423 are slidingly matched. The second guide rail 423 has a guiding function on the sliding seat 432, and the sliding seat 432 slides along the second guide rail 423, so that the sliding seat 432 drives the mounting frame 30 and the fairing 61 to move along the second direction.

In the embodiment of the present application, the first screw lifter 431 includes parts such as a worm gear, a bearing, a screw, and the like. The worm is driven by a motor or manually to rotate, the worm drives the turbine to rotate, the internal thread machined in the inner cavity of the turbine is matched with the external thread of the screw rod, and the screw rod is driven to move, so that the sliding seat 432 is driven to move through the screw rod.

Of course, in some alternative embodiments of the present application, the second moving mechanism 43 may also include a ball screw instead of the first screw lifter 431, the ball screw may include a screw, a nut, etc., and the screw is driven by a motor or manually to rotate, and the screw drives the nut to move axially along the screw, so that the sliding seat 432 is driven by the nut to move.

Optionally, as shown in fig. 7, in the embodiment of the present application, a first scale 413 is further disposed on the base 411, a first pointer 414 is disposed on the sliding base 432, the first pointer 414 points to a scale on the first scale 413 to display a position of the sliding base 432, the first pointer 414 moves with the sliding base 432 relative to the base 411, and the first pointer 414 points to a different scale on the first scale 413 to display a moving distance of the sliding base 432.

Optionally, as shown in fig. 7, in the embodiment of the present application, the adjusting device 40 further includes a third moving mechanism 44, where the third moving mechanism 44 is disposed on the second moving mechanism 43, the second moving mechanism 43 is connected to the mounting frame 30 through the third moving mechanism 44, the second moving mechanism 43 has a supporting effect on the third moving mechanism 44, the second moving mechanism 43 moves along the second direction to drive the third moving mechanism 44, the mounting frame 30 and the fairing body 61 to move along the second direction, at least part of the structure of the third moving mechanism 44 is movably disposed along the vertical direction relative to the second moving mechanism 43, and the third moving mechanism 44 drives the mounting frame 30 and the fairing body 61 to move along the vertical direction to adjust the position of the fairing body 61 in the vertical direction.

Alternatively, as shown in fig. 7, in the embodiment of the present application, the third moving mechanism 44 includes a second spiral lifter 441 and a supporting disc 442, the second spiral lifter 441 is mounted on the sliding seat 432, the sliding seat 432 has a supporting function on the second spiral lifter 441, a screw rod of the second spiral lifter 441 is movably arranged along a vertical direction relative to the sliding seat 432, the supporting disc 442 is respectively connected with the mounting frame 30 and the screw rod, the screw rod of the second spiral lifter 441 moves along the vertical direction relative to the sliding seat 432 under the action of external force, and the supporting disc 442 and the mounting frame 30 move along the vertical direction under the action of the screw rod, so as to drive the fairing body 61 to move along the vertical direction, and adjust the height position of the fairing body 61.

Optionally, as shown in fig. 7, in the embodiment of the present application, the adjusting device 40 further includes a third guide rail 428 mounted on the sliding seat 432, the third guide rail 428 extends in a vertical direction, a guide hole 443 is provided on the support disc 442, and the third guide rail 428 is penetrated in the guide hole 443, so that the support disc 442 slides along the third guide rail 428, and the third guide rail 428 guides the support disc 442.

Optionally, as shown in fig. 7, in the embodiment of the present application, a second limit stop 429 is further disposed at an end of the third rail 428, which is far away from the sliding seat 432, and the second limit stop 429 has a size greater than that of the guide hole 443 in a direction perpendicular to the axis of the third rail 428, and the second limit stop 429 is used for stopping the sliding of the support disc 442 along the third rail 428, so as to prevent the support disc 442 from being removed from the third rail 428.

Optionally, as shown in fig. 7, in the embodiment of the present application, a second scale 444 is further disposed on the sliding seat 432, a second pointer 445 is disposed on the supporting disc 442, the second pointer 445 points to a scale on the second scale 444 to display a position of the supporting disc 442, the second pointer 445 moves with the supporting disc 442 relative to the sliding seat 432, and the second pointer 445 points to a different scale of the second scale 444 to display a moving distance of the supporting disc 442.

Alternatively, in an embodiment of the present application, the support plate 442 is configured to be detachably and fixedly coupled to the ground supporting leg 35 of the mounting frame 30.

It should be noted that, in the embodiment of the present application, the structure and the working principle of the second screw lifter 441 may be similar to or the same as those of the first screw lifter 431, and are not described herein.

Of course, in some alternative embodiments of the present application, the third moving mechanism 44 may also include a ball screw instead of the second screw lifter 441 according to actual needs, so as to implement a function of driving the supporting disk 442 to move in the vertical direction.

Alternatively, as shown in fig. 7, in the embodiment of the present application, the first moving mechanism 41, the second moving mechanism 43, and the third moving mechanism 44 are sequentially connected to form a moving docking vehicle 45.

Optionally, as shown in fig. 2, in the embodiment of the present application, the supporting platform 50 further includes leveling legs 53, and the leveling legs 53 are mounted on the supporting platform body 51 for leveling the turntable 52 such that the top surface of the turntable 52 is parallel to the horizontal plane.

The leveling support legs 53 adjust the height of the supporting platform body 51 along the vertical direction, the number of the leveling support legs 53 is multiple, the leveling support legs 53 are arranged on the supporting platform body 51 at intervals, and optionally, the leveling support legs 53 are uniformly arranged at intervals. The plurality of leveling legs 53 respectively adjust the heights of the support platform body 51 at different positions such that the top surface of the turntable 52 is parallel to the horizontal plane.

Alternatively, the leveling legs 53 may be linear drive mechanisms, such as motors, air cylinders, hydraulic drives, or the like.

Optionally, the top surface of the turntable 52 is provided with a level or angle gauge for detecting the levelness of the top surface of the turntable 52.

Optionally, as shown in fig. 2, in the embodiment of the present application, the supporting platform 50 further includes casters 54, where the casters 54 are installed at the bottom of the supporting platform body 51 and rotatably disposed relative to the supporting platform body 51, and the casters 54 rotate to drive the supporting platform body 51 to move under the action of external force, so as to adjust the position of the supporting platform 50.

Alternatively, the number of casters 54 is plural, and the casters 54 are arranged at intervals. Optionally, a plurality of casters 54 are evenly spaced.

Optionally, as shown in fig. 2, in the embodiment of the present application, the support platform 50 further includes a rotary support structure 55, where the rotary support structure 55 is mounted on the support platform body 51, and the turntable 52 is rotatably connected to the support platform body 51 through the rotary support structure 55.

Optionally, the slewing bearing 55 is a bearing. The axis of the bearing mounted on the support platform body 51 coincides with the axis of the cowling 60 after the cowling is closed.

Optionally, as shown in fig. 2, in the embodiment of the present application, the supporting platform 50 further includes a rotation driving mechanism 56, the rotation driving mechanism 56 is installed on the supporting platform body 51, the supporting platform body 51 has a supporting function on the rotation driving mechanism 56, the rotation driving mechanism 56 is connected with the turntable 52, and the turntable 52 is driven by the rotation driving mechanism 56 to rotate.

Alternatively, as shown in fig. 2, in the embodiment of the present application, the swing driving mechanism 56 includes a linear driving structure 561 and a link structure 562, one end of the link structure 562 is pivotally connected to an output end of the linear driving structure 561, the other end of the link structure 562 is pivotally connected to the turntable 52, and the link structure 562 transmits power to the turntable 52 under the driving of the output end of the linear driving structure 561, so that the turntable 52 rotates.

Optionally, as shown in fig. 2, in the embodiment of the present application, the supporting platform 50 further includes a rotation locking mechanism 57, and the rotation locking mechanism 57 is mounted on the supporting platform body 51 and is used for cooperating with the turntable 52 to lock the position of the turntable 52.

Optionally, the rotation locking mechanism 57 includes an adjusting member disposed on the supporting platform body 51 and located at an outer periphery of the turntable 52, the adjusting member being movably disposed with respect to the supporting platform body 51 in a radial direction of the turntable 52, and a brake plate mounted on the adjusting plate and located at a side of the adjusting plate facing the turntable 52, the position of the adjusting member being adjusted to bring the brake plate into abutment with the turntable 52 to thereby lock the position of the turntable 52 by means of friction between the brake plate and the turntable 52, and also to release the abutment of the brake plate with the turntable 52 so that the turntable 52 is not subjected to friction from the brake plate and is rotatable with respect to the supporting platform body 51 to thereby adjust the position of the turntable 52.

Optionally, as shown in fig. 2, in the embodiment of the present application, the supporting platform 50 further includes a turntable limiting structure 58, and the turntable limiting structure 58 is used to limit the rotation limit position of the turntable 52. Specifically, as shown in fig. 2, the turntable limiting structure 58 includes an arc-shaped limiting hole 581 disposed on the supporting platform body 51 and a limiting rod 582 mounted on the turntable 52, one end of the limiting rod 582, far away from the turntable 52, is penetrated in the arc-shaped limiting hole 581, the arc-shaped limiting hole 581 is an arc-shaped hole extending around the axis of the rotating supporting structure 55, the limiting rod 582 rotates around the axis of the rotating supporting structure 55 along with the turntable 52, the limiting rod 582 moves along the arc-shaped limiting hole 581 in the arc-shaped limiting hole 581, and the limiting rod 582 can respectively abut against inner wall surfaces of two ends of the arc-shaped limiting hole 581, so that the limiting position of the limiting rod 582 moving in the arc-shaped limiting hole 581 is limited, and the purpose of limiting the rotation of the turntable 52 is achieved.

The working flow of the satellite fairing assembly system is as follows:

1. As shown in fig. 2, the supporting platform 50 is placed on the ground, and the upper surface of the turntable 52 of the supporting platform 50 is leveled by using leveling legs 53;

2. The guide rail bracket 421 and the first guide rail 422 are connected in advance, the guide rail bracket is connected with the positioning seat 511 (shown in fig. 2) of the supporting platform 50 through the ground rail limiting seat 424 (shown in fig. 3), and the ground rail connecting piece 426 is used for connecting the middle ground rail with the side ground rail to form a frame structure (shown in fig. 3 and 4);

3. Placing a mobile docking car 45 with adjustment capability on the ground rail 42;

4. The first ring frame 31 and the second ring frame 32 are respectively connected and fixed with a fairing half-cover;

5. the support frame 34 is respectively connected and fixed with the first ring frame 31 and the second ring frame 32;

6. overturning the fairing half-cover from a horizontal state (as shown in fig. 5) to a vertical state (as shown in fig. 6) by lifting devices 70 (such as lifting devices) through lifting lugs 33 of the mounting frame 30;

7. Hoisting the fairing half cover in a vertical state above three groups of movable docking vehicles 45 on one side, and fixing the ground supporting legs 35 of the mounting frame 30 and the supporting discs 442 on the movable docking vehicles 45 by using fasteners after the fairing half cover falls in place;

8. in the same manner as described above, the other group of fairing halves and the mounting frame 30 are connected to form a combined body, and the combined body is hoisted to the upper part of the three groups of movable docking vehicles 45 on the other side, and the ground supporting support legs 35 and the supporting plate 442 are fixed by fasteners;

9. Respectively pushing the two groups of fairing halves to approach the support platform 50 along with the movable docking vehicle 45, completing vertical docking of the fairing halves, installing a fairing longitudinal connector to cover the two fairing halves to form a fairing 60 (shown in fig. 8), and aligning the two fairing halves during docking by adjusting the first screw lift 431 of the movable docking vehicle 45 so as to facilitate docking;

10. After the half cowling is docked, the second screw lift 441 of the mobile docking vehicle 45 is adjusted to enable the half cowling assembly to move downwards and fall onto the satellite support connecting structure 62 quickly, and a half cowling axial connecting bolt is installed;

11. Unlocking the rotation locking mechanism 57 on the support platform 50 according to the alignment of the first mounting hole 63 on the fairing 60 and the second mounting hole 64 on the satellite support connecting structure 62, and manually rotating the spiral lifter of the driving mechanism 56 to drive the turntable 52 to rotate the satellite support connecting structure 62 around the central axis of the rotation support structure 55, so as to ensure the alignment of the first mounting hole 63 and the second mounting hole 64 (as shown in fig. 8), so as to fix the fairing 60 and the satellite support connecting structure 62 together through the fairing axial connecting bolt;

12. Removing fasteners of the connecting support frame 34 and the first ring frame 31 and the connecting support frame 34 and the second ring frame 32, and detaching the support frame 34 and the first ring frame 31 and detaching the support frame 34 and the second ring frame 32;

13. As shown in fig. 9, two groups of first ring frames 31 are fastened by using unthreaded holes on the flange surface to form an integral structure, and lifting lugs 33 on the two groups of first ring frames 31 are respectively connected to lifting equipment 70;

14. the star cover assembly is turned to be in a horizontal state, and the condition of horizontally butting with a whole rocket is provided.

15. The fastening members for connecting the first ring frame 31 and the fairing half-cover, and the second ring frame 32 and the fairing half-cover are removed, and then the first ring frame 31 and the second ring frame 32 are removed through the hoisting device 70, so that the satellite fairing assembly process is completed.

The satellite fairing assembly system consists of a plurality of modules such as the supporting platform 50, the ground rail 42, the movable docking vehicle 45 and the mounting frame 30, has larger envelope size, adopts the supporting platform 50, the ground rail 42, the movable docking vehicle 45 and the mounting frame 30 to be assembled in a plurality of modules, and the modules are mutually independent, so that the assembly is realized during use, the requirement on the installation precision of a tool is reduced, the transportation difficulty of the tool is reduced, the transportation cost is reduced, and meanwhile, part of the modules can be compatible with the use of fairings with other sizes.

The satellite fairing assembly system can be used as a rocket fairing assembly butt-joint hoisting tool device.

By applying the embodiment of the application, at least the following beneficial effects can be realized:

In the embodiment of the application, the first assembly component and the second assembly component are respectively connected with one fairing body, and the first assembly component and the second assembly component are respectively used for adjusting the positions of the connected fairing bodies so that the fairing bodies can be mutually close to each other to form the fairing for the joint cover.

The adjusting device, the mounting frame and the fairing body are connected in sequence, the mounting frame has a supporting effect on the fairing body, the mounting frame can be driven to move in the horizontal plane along the first direction and the second direction and move in the vertical plane along the vertical direction through the adjusting device, so that the fairing body can move in the horizontal plane along the two directions and move in the vertical plane along the multiple degrees of freedom of the vertical direction, the position of the fairing body is adjusted, the fairing bodies are convenient to be mutually close to and aligned, the joint cover function is realized, and the assembly process of the fairing is completed.

According to the satellite fairing assembly system provided by the embodiment of the application, the mounting frame is driven by the adjusting device to move in two directions in the horizontal plane to realize horizontal lifting and move in the vertical plane to realize vertical lifting, so that the requirements of butting the satellite fairing in two modes of horizontal and vertical with a rocket cabin section are met, the working conditions of horizontal lifting, vertical butt joint of the fairing halves and the like in the rocket fairing closing process can be completed, the butting of the two fairing halves in the vertical state is realized, and the satellite fairing is formed. In the processes of hoisting and jointing the radome half-covers, the radome half-covers do not need to be replaced by different tools, and the requirements of various working conditions in the radome jointing process can be met by adopting one set of tools, so that the types of equipment in the rocket assembly process are reduced, the operation flow is simplified, and the use is more convenient.

The supporting platform is used as a bearing main body of the satellite support connecting structure and is arranged in the middle of the whole satellite fairing assembly system, and the supporting platform is also used as a satellite fairing assembly supporting main body after the satellite fairings are covered. The satellite fairing assembly system provided by the embodiment of the application has 4 degrees of freedom adjustment for the fairing body and the fairing, wherein the movement in the horizontal plane along two directions, namely the horizontal movement along the first direction and the horizontal movement along the second direction, the up-and-down movement along the vertical direction and the rotation movement around the fairing axis can realize the functions of horizontal lifting, vertical lifting and rotation docking of the satellite fairing assembly with a satellite support connection structure, and the requirements of the satellite fairing assembly on docking with a rocket cabin in two modes of horizontal and vertical are met. In the processes of lifting the fairing and closing the fairing, lifting the star cover assembly and rotating and butting the star cover assembly and the satellite support connecting structure, different tools are not required to be replaced, and the operation flow is simplified.

In the embodiment of the application, the first ring frame and the second ring frame are respectively connected with different positions of the same fairing half cover, the support frame is respectively connected with the first ring frame and the second ring frame to form a combined body of the mounting frame and the fairing half cover, and the two half cover combined bodies are vertically jointed with the fairing half cover to form the star cover combined body. The lifting lug is arranged on at least one of the first ring frame and the second ring frame and serves as an interface for lifting and overturning the star cover assembly, the lifting lug is connected with lifting lug through lifting equipment, the star cover assembly is overturned, the mounting frame integrates the function of the star cover assembly overturning tool, the star cover assembly overturning function is realized on the premise that the requirements of the fairing half cover closing cover are met, the star cover assembly overturning and lifting process is realized, the contact area of the mounting frame and the fairing is large, the tool rigidity is high, after the mounting frame is connected with the fairing, the fairing half cover and the star cover assembly overturning process can play a protective role on the fairing, meanwhile, the lifting and overturning structural strength of the fairing is reduced, and the carrying capacity of a rocket is improved.

Those of skill in the art will appreciate that the various operations, methods, steps in the flow, acts, schemes, and alternatives discussed in the present application may be alternated, altered, combined, or eliminated. Further, other steps, means, or steps in a process having various operations, methods, or procedures discussed herein may be alternated, altered, rearranged, disassembled, combined, or eliminated. Further, steps, measures, schemes in the prior art with various operations, methods, flows disclosed in the present application may also be alternated, altered, rearranged, decomposed, combined, or deleted.

In the description of the present application, directions or positional relationships indicated by words such as "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., are based on exemplary directions or positional relationships shown in the drawings, are for convenience of description or simplification of describing embodiments of the present application, and do not indicate or imply that the devices or components referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.

The terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more.

In the description of the present application, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, directly connected, or indirectly connected through an intermediary, or may be in communication with the interior of two elements. The specific meaning of the above terms in the present application will be understood in specific cases by those of ordinary skill in the art.

In the description of the present specification, a particular feature, structure, material, or characteristic may be combined in any suitable manner in one or more embodiments or examples.

The foregoing is only a part of the embodiments of the present application, and it should be noted that, for those skilled in the art, other similar implementation means based on the technical idea of the present application may be adopted without departing from the technical idea of the solution of the present application, which is also within the protection scope of the embodiments of the present application.

Claims (8)

1. A satellite fairing assembly system comprising a first assembly and a second assembly, the first assembly and the second assembly each being coupled to a fairing;

at least one of the first fitting component and the second fitting component comprises:

the mounting frame is used for being connected with the fairing body;

The adjusting device is connected with the mounting frame and is used for driving the mounting frame to move along at least one of a first direction parallel to a horizontal plane, a second direction parallel to the horizontal plane and a vertical direction so as to adjust the position of the fairing bodies, so that the fairing bodies are butted to form a fairing;

wherein the first direction and the second direction intersect;

the satellite fairing assembly system further includes a support platform disposed between the first assembly and the second assembly;

the supporting platform comprises a supporting platform body and a rotary table arranged on the supporting platform body, the rotary table is used for being connected with a satellite support connecting structure, and the rotary table is rotatably arranged around the axis of the fairing relative to the supporting platform body so as to adjust the position of the satellite support connecting structure and enable the satellite support connecting structure to be in butt joint with the fairing;

the mounting frame includes:

the first ring frame is used for being connected with the fairing body and provided with a first arc-shaped groove for accommodating the fairing body;

The second ring frame is used for being connected with the fairing body, the second ring frame is provided with a second arc-shaped groove for accommodating the fairing body, the first ring frame and the second ring frame are arranged at intervals along the axial direction of the fairing, at least one of the first ring frame and the second ring frame is provided with a lifting lug, and the lifting lug is used for being connected with lifting equipment;

the support frame is connected with the first ring frame and the second ring frame respectively, and the support frame is installed on the adjusting device.

2. The satellite fairing assembly system of claim 1, wherein said adjustment apparatus includes a first movement mechanism coupled to said fairing body and said support platform body, respectively;

The first moving mechanism is movably arranged along the first direction relative to the supporting platform body so as to enable the fairing bodies to be close to or far away from each other.

3. The satellite fairing assembly system of claim 2, wherein said first movement mechanism comprises:

the mounting frame is mounted on the top of the base;

the roller is arranged at the bottom of the base and is rotatably arranged relative to the base;

The adjusting device further comprises a guide rail bracket and a first guide rail arranged on the guide rail bracket, the guide rail bracket is connected with the supporting platform body, the first guide rail extends along the first direction, and the roller is in sliding fit with the first guide rail.

4. A satellite fairing assembly system as recited in claim 2 or 3, wherein said adjustment means further comprises a second movement mechanism disposed on said first movement mechanism, said first movement mechanism being coupled to said fairing body by said second movement mechanism;

at least part of the structure of the second moving mechanism is movably arranged along the second direction relative to the first moving mechanism so as to adjust the position of the fairing body in the second direction.

5. The satellite fairing assembly system of claim 4, wherein said second movement mechanism comprises:

A first screw lifter mounted on a base of the first moving mechanism, a screw of the first screw lifter being movably disposed in a second direction with respect to the base;

The sliding seat is respectively connected with the mounting frame and the screw rod, and the sliding seat and the mounting frame move along the second direction under the drive of the screw rod;

The adjusting device further comprises a second guide rail arranged on the base, the second guide rail extends along the second direction, and the sliding seat is in sliding fit with the second guide rail.

6. The satellite fairing assembly system of claim 4, wherein said adjustment apparatus further comprises a third movement mechanism disposed on said second movement mechanism, said second movement mechanism coupled to said fairing body via said third movement mechanism;

at least part of the structure of the third moving mechanism is movably arranged along the vertical direction relative to the second moving mechanism so as to adjust the position of the fairing body along the vertical direction.

7. The satellite fairing assembly system of claim 1, wherein said support platform further comprises:

The leveling support legs are arranged on the supporting platform body and used for leveling the turntable so that the top surface of the turntable is parallel to the horizontal plane;

The truckle is installed the bottom of supporting platform body, and for supporting platform body rotationally sets up, under the exogenic action, the truckle rotates and drives supporting platform body removes.

8. The satellite fairing assembly system of claim 7, wherein said support platform further comprises:

the rotary support structure is arranged on the support platform body, and the turntable is rotatably connected with the support platform body through the rotary support structure;

the rotary driving mechanism is arranged on the supporting platform body, is connected with the turntable and is driven by the rotary driving mechanism to rotate;

the rotary locking mechanism is arranged on the supporting platform body and is used for being matched with the rotary table so as to lock the position of the rotary table.