Satellite fairing assembly system

Abstract

The embodiment of the present application provides a satellite fairing assembly system. The satellite fairing assembly system includes a first assembly component and a second assembly component, and the first assembly component and the second assembly component are respectively connected to a fairing body; at least one of the first assembly component and the second assembly component includes: a mounting frame, which is used to connect with the fairing body; an adjustment device, which is connected to the mounting frame, and is used to drive the mounting frame to move in at least one direction of a first direction parallel to the horizontal plane, a second direction parallel to the horizontal plane, and a vertical direction, so as to adjust the position of the fairing body, so that each fairing body is docked to form a fairing; wherein the first direction and the second direction intersect. The embodiment of the present application realizes that a variety of working conditions can be completed in the fairing assembly process using a set of tooling, which reduces the types of equipment in the rocket assembly process, simplifies the operation process, and is more convenient to use.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace equipment, and in particular, to a satellite fairing assembly system. Background Art

[0002] Satellite fairings are used to protect satellites and other payloads to prevent satellites from being affected by harmful environments such as aerodynamic forces, aerodynamic heating, and acoustic vibrations. They are an important component of transport rockets.

[0003] At present, most of the fairing assembly tools use an integral structure to complete the assembly of the fairing half-shells. First, the assembly tools are assembled with the fairing half-shells respectively, and then the assembly tools are pushed to align the fairings, and then the special lifting and flipping tools are used to realize the vertical lifting and flipping of the fairings. In the rocket assembly process, there are many types of equipment used to assemble the fairings, and the management and operation are cumbersome. Summary of the invention

[0004] In view of the shortcomings of the existing methods, the present application proposes a satellite fairing assembly system to solve the technical problems existing in the prior art of a large number of types of equipment for assembling fairings and complicated management and operation.

[0005] In a first aspect, an embodiment of the present application provides a satellite fairing assembly system, comprising a first assembly component and a second assembly component, wherein the first assembly component and the second assembly component are respectively connected to a fairing body;

[0006] At least one of the first assembly component and the second assembly component comprises:

[0007] A mounting frame, used for connecting with the fairing body;

[0008] An adjusting device connected to the installation frame, used to drive the installation frame to move in at least one of a first direction parallel to the horizontal plane, a second direction parallel to the horizontal plane and a vertical direction, so as to adjust the position of the fairing body so that the fairing bodies are butted together to form a fairing;

[0009] The first direction and the second direction intersect.

[0010] Optionally, the satellite fairing assembly system further includes a support platform disposed between the first assembly component and the second assembly component;

[0011] The support platform includes a support platform body and a turntable arranged on the support platform body. The turntable is used to connect with the satellite bracket connection structure. The turntable is rotatably arranged around the axis of the fairing relative to the support platform body to adjust the position of the satellite bracket connection structure so that the satellite bracket connection structure can be docked with the fairing.

[0012] Optionally, the adjustment device includes a first moving mechanism, and the first moving mechanism is connected to the fairing body and the supporting platform body respectively;

[0013] The first moving mechanism is movably arranged relative to the supporting platform body along a first direction so as to make the fairing bodies approach or move away from each other.

[0014] Optionally, the first moving mechanism includes:

[0015] A base, with the mounting frame mounted on top of the base;

[0016] A roller is mounted on the bottom of the base and is rotatably arranged relative to the base;

[0017] The adjusting device also includes a guide rail bracket and a first guide rail installed on the guide rail bracket. The guide rail bracket is connected to the supporting platform body. The first guide rail extends along a first direction. The roller is slidably matched with the first guide rail.

[0018] 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 to the fairing body through the second moving mechanism;

[0019] At least a part of the structure of the second moving mechanism is movably arranged along the second direction relative to the first moving mechanism to adjust the position of the fairing body in the second direction.

[0020] Optionally, the second moving mechanism includes:

[0021] A first screw elevator is mounted on the base of the first moving mechanism, and a lead screw of the first screw elevator is movably arranged relative to the base along a second direction;

[0022] The sliding seat is connected to the mounting frame and the lead screw respectively. Driven by the lead screw, the sliding seat and the mounting frame move along the second direction.

[0023] The adjusting device also includes a second guide rail installed on the base, the second guide rail extends along the second direction, and the sliding seat and the second guide rail are slidably matched.

[0024] 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 to the fairing body through the third moving mechanism;

[0025] At least a part of the structure of the third moving mechanism is movably arranged in the vertical direction relative to the second moving mechanism to adjust the position of the fairing body in the vertical direction.

[0026] Optionally, the installation frame includes:

[0027] A first ring frame, used to be connected to the fairing body, and the first ring frame has a first arc-shaped groove for accommodating the fairing body;

[0028] A second ring frame is used to connect with the fairing body, the second ring frame has a second arc 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, and at least one of the first ring frame and the second ring frame is provided with a lifting lug, which is used to connect with the lifting equipment;

[0029] The support frame is connected to the first ring frame and the second ring frame respectively, and the support frame is installed on the adjusting device.

[0030] Optionally, the support platform further comprises:

[0031] Leveling legs, mounted on the supporting platform body, for leveling the turntable so that the top surface of the turntable is parallel to the horizontal plane;

[0032] The caster is installed at the bottom of the supporting platform body and is rotatably arranged relative to the supporting platform body. Under the action of external force, the caster rotates to drive the supporting platform body to move.

[0033] Optionally, the support platform further comprises:

[0034] A slewing support structure is mounted on the supporting platform body, and the turntable is rotatably connected to the supporting platform body through the slewing support structure;

[0035] The rotary drive mechanism is installed on the supporting platform body and connected to the turntable. The turntable rotates under the drive of the rotary drive mechanism.

[0036] The rotary locking mechanism is installed on the supporting platform body and is used to cooperate with the turntable to lock the position of the turntable.

[0037] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include:

[0038] In the embodiment of the present application, the first assembly component and the second assembly component are respectively connected to a fairing body, and the first assembly component and the second assembly component are respectively used to adjust the position of the connected fairing bodies so that the fairing bodies can be close to each other to form a fairing with the joint cover.

[0039] The adjusting device, the mounting frame and the fairing body are connected in sequence, and the mounting frame supports the fairing body. The adjusting device can drive the mounting frame to move in a first direction and a second direction in a horizontal plane and in a vertical direction in a vertical plane, thereby realizing multi-degree-of-freedom movement of the fairing body in two directions (i.e., the first direction and the second direction) in a horizontal plane and in an up-and-down direction (i.e., the vertical direction) in a vertical plane, thereby adjusting the position of the fairing body so that the fairing bodies can approach and align with each other, realizing the docking function and completing the assembly process of the fairing.

[0040] The satellite fairing assembly system of the embodiment of the present application, driven by the adjustment device, has the function of moving in two directions in the horizontal plane to achieve horizontal lifting, and moving in the vertical plane in the up and down directions to achieve vertical lifting, which meets the needs of the satellite fairing to dock with the rocket compartment in both horizontal and vertical ways, and can complete the horizontal lifting, vertical lifting, vertical docking of the fairing half-cover during the rocket fairing assembly process, and achieve the docking of the two fairing half-covers in a vertical state to form a satellite fairing. In the process of hoisting and docking the fairing half-cover, there is no need to replace different tooling, and a set of tooling can be used to complete various working conditions in the fairing assembly process, reducing the types of equipment in the rocket assembly process, simplifying the operation process, and making it more convenient to use.

[0041] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0043] Figure 1 A schematic structural diagram of a satellite fairing assembly system provided in an embodiment of the present application;

[0044] Figure 2 A schematic diagram of the structure of a support platform of a satellite fairing assembly system provided in an embodiment of the present application;

[0045] Figure 3 A schematic diagram of the structure of a ground rail and a support platform of a satellite fairing assembly system provided in an embodiment of the present application;

[0046] Figure 4 A schematic diagram of the structure of an adjustment device and a support platform of a satellite fairing assembly system provided in an embodiment of the present application;

[0047] Figure 5 A schematic structural diagram of an installation frame and a fairing body of a satellite fairing assembly system provided in an embodiment of the present application (wherein the fairing body is in a horizontal state);

[0048] Figure 6 A schematic structural diagram of an installation frame, a fairing body, and a hoisting device of a satellite fairing assembly system provided in an embodiment of the present application (wherein the fairing body is in a vertical state);

[0049] Figure 7 A schematic structural diagram of a mobile docking vehicle for a satellite fairing assembly system provided in an embodiment of the present application;

[0050] Figure 8 A schematic diagram of a satellite fairing assembly system and a fairing assembly structure provided in an embodiment of the present application;

[0051] Fig. 9 A schematic diagram of the hoisting structure of the fairing provided in an embodiment of the present application.

[0052] Reference numerals:

[0053] 100-satellite fairing assembly system; 10-first assembly component; 20-second assembly component; 30-installation frame; 31-first ring frame; 32-second ring frame; 33-lifting ear; 34-support frame; 35-ground support leg; 40-adjustment device; 41-first moving mechanism; 411-base; 412-roller; 413-first scale; 414-first pointer; 42-ground rail; 421-guide rail bracket; 422-first guide rail; 423-second guide rail; 424-ground rail limit seat; 425-first positioning hole; 426-ground rail connector; 427-first limit baffle; 428-third guide rail; 429-second limit baffle; 43-second moving mechanism; 431-first spiral elevator; 432 - sliding seat; 44- third moving mechanism; 441- second spiral elevator; 442- support plate; 443- guide hole; 444- second scale; 445- second pointer; 45- mobile docking vehicle; 50- support platform; 51- support platform body; 511- positioning seat; 52- turntable; 53- leveling legs; 54- casters; 55- slewing support structure; 56- slewing drive mechanism; 561- linear drive structure; 562- connecting rod structure; 57- slewing locking mechanism; 58- turntable limiting structure; 581- arc limiting hole; 582- limiting rod; 60- fairing; 61- fairing body; 62- satellite bracket connecting structure; 63- first mounting hole; 64- second mounting hole; 70- hoisting equipment. DETAILED DESCRIPTION

[0054] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0055] Those skilled in the art will appreciate that, unless expressly stated otherwise, the singular forms "a", "an", "said" and "the" used herein may also include plural forms. It should be further understood that the term "comprising" used in the specification of the present application refers to the presence of the features, integers, steps, operations, elements and / or components, but does not exclude the implementation of other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0056] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0057] At present, most of the fairing assembly tooling adopts an integral structural form to complete the assembly of the fairing half-shades. First, the assembly tooling is assembled with the fairing half-shades respectively, and then the assembly tooling is pushed to mate the fairing, and then the vertical lifting and flipping of the fairing is realized by using special lifting and flipping tooling. During assembly, the fairing assembly tooling only realizes the assembly function. To realize the lifting and flipping functions of the star-shade assembly, it is necessary to design a lifting and flipping tooling separately. There are many types of equipment used to assemble the fairing, resulting in too many types of equipment in the rocket assembly process, and cumbersome management and operation. At the same time, because the assembly tooling is not compatible with the lifting and flipping functions of the star-shade assembly, it is necessary to design more mechanical interfaces for the fairing, which will increase the weight of the fairing and lead to a corresponding reduction in carrying capacity.

[0058] In addition, some fairing assembly tools use unguided universal wheels to move during the docking process. Since there is no guidance during the docking process, there is a risk of collision with the satellite. Some solutions use guide rails for guided docking, but the support platform of the satellite cover assembly and the guide rail are an integrated structure. The overall structure has a large tool size, poor adjustment ability, difficulty in transportation, and high transportation cost.

[0059] The satellite fairing assembly system provided in the present application is intended to solve at least one of the above technical problems in the prior art.

[0060] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0061] The present application embodiment provides a satellite fairing assembly system. The structural schematic diagram of the satellite fairing assembly system 100 is as follows: Figure 1As shown, it includes a first assembly component 10 and a second assembly component 20 ( Figure 1 The dotted line frame is used to distinguish the first assembly component 10 and the second assembly component 20. The first assembly component 10 is located on one side of the dotted line frame, and the second assembly component 20 is located on the other side of the dotted line frame. The first assembly component 10 and the second assembly component 20 are respectively connected to a fairing body 61 (such as Figure 5 , Figure 6 , Figure 8 and Fig. 9 The first assembly component 10 and the second assembly component 20 both include a mounting frame 30 and an adjusting device 40. The mounting frame 30 is used to be connected to the fairing body 61. The adjusting device 40 is connected to the mounting frame 30 and is used to drive the mounting frame 30 to move along a first direction parallel to the horizontal plane, a second direction parallel to the horizontal plane, and a vertical direction to adjust the position of the fairing body 61 so that each fairing body 61 is connected to form the fairing 60. The first direction and the second direction intersect.

[0062] In the embodiment of the present application, the first assembly component 10 and the second assembly component 20 are respectively connected to a fairing body 61, and the first assembly component 10 and the second assembly component 20 are respectively used to adjust the position of the connected fairing bodies 61 so that each fairing body 61 can be close to each other to form a fairing 60 (or the fairing 60 can be called a star cover assembly) by combining the covers.

[0063] The adjusting device 40, the mounting frame 30 and the fairing body 61 are connected in sequence, and the mounting frame 30 supports the fairing body 61. The adjusting device 40 can drive the mounting frame 30 to move in the first direction and the second direction in the horizontal plane and in the vertical direction in the vertical plane, thereby realizing multi-degree-of-freedom movement of the fairing body 61 in two directions (i.e., the first direction and the second direction) in the horizontal plane and in the up and down directions (i.e., the vertical direction) in the vertical plane, thereby adjusting the position of the fairing body 61 so that the fairing bodies 61 can approach and align with each other, realizing the docking function and completing the assembly process of the fairing 60.

[0064] It should be noted that in the related art, the fairing 60 includes two fairing half-covers that are separately arranged, and the two fairing half-covers can be connected to the joint cover to form the fairing 60. In the embodiment of the present application, the fairing body 61 is the fairing half-cover, and the first assembly component 10 and the second assembly component 20 are respectively connected to a fairing body 61, which is used to adjust the position of the fairing body 61 so that the two fairing bodies 61 form the fairing 60 to the joint cover. Of course, when the fairing 60 includes three or more fairing sub-covers that are separately arranged, the present application can adaptively adjust the number of the first assembly component 10 and / or the second assembly component 20, so that several first assembly components 10 and several second assembly components 20 are respectively connected to one fairing sub-cover, and the position of the fairing sub-cover is adjusted so that three or more fairing sub-covers can be close to each other to form the fairing 60 to the joint cover.

[0065] The satellite fairing assembly system of the embodiment of the present application, driven by the adjustment device 40, has the function of moving in two directions in the horizontal plane to achieve horizontal lifting, and moving in the vertical plane in the up and down directions to achieve vertical lifting, which meets the needs of the satellite fairing to dock with the rocket compartment in both horizontal and vertical ways, and can complete the horizontal lifting, vertical lifting, vertical docking of the fairing half-cover during the rocket fairing assembly process, and achieve the docking of the two fairing half-covers in a vertical state to form a satellite fairing. In the process of hoisting and docking the fairing half-cover, there is no need to replace different tooling, and a set of tooling can be used to complete various working conditions in the fairing assembly process, reducing the types of equipment in the rocket assembly process, simplifying the operation process, and making it more convenient to use.

[0066] Of course, in some optional embodiments of the present application, the adjustment device 40 can also be used to drive the mounting frame 30 to move along the first direction, or along the second direction, or along the vertical direction, or along the first direction and the second direction, or along the first direction and the vertical direction, or along the second direction and in the vertical direction, according to actual needs.

[0067] Of course, in some optional embodiments of the present application, according to actual needs, only the first assembly component 10 includes the mounting frame 30 and the adjusting device 40, so that the position of the connected fairing body 61 can be adjusted, and the second assembly component 20 is used to support the fairing body 61, and the position of the fairing body 61 connected to the second assembly component 20 is fixed; or only the second assembly component 20 includes the mounting frame 30 and the adjusting device 40, so that the position of the connected fairing body 61 can be adjusted, and the first assembly component 10 is used to support the fairing body 61, and the position of the fairing body 61 connected to the first assembly component 10 is fixed.

[0068] Optionally, the first direction and the second direction are perpendicular.

[0069] Alternatively, if Figures 1 to 4 As shown, in the embodiment of the present application, the satellite fairing assembly system 100 further includes a support platform 50 disposed between the first assembly component 10 and the second assembly component 20; the support platform 50 includes a support platform body 51 and a turntable 52 disposed on the support platform body 51, and the turntable 52 is used to connect with the satellite bracket connection structure 62 (such as Figure 8 and Fig. 9 The turntable 52 is connected with the support platform body 51 around the fairing 60 (as shown in FIG. Figure 8 and Fig. 9 The axis of the satellite support connecting structure 62 is rotatably arranged to adjust the position of the satellite support connecting structure 62 so that the satellite support connecting structure 62 can dock with the fairing 60.

[0070] In the embodiment of the present application, the support platform body 51 supports the turntable 52. The turntable 52 rotates around the axis of the fairing 60, driving the satellite bracket connecting structure 62 to rotate together, thereby adjusting the position and angle of the satellite bracket connecting structure 62 in the horizontal plane, aligning the satellite bracket connecting structure 62 with the fairing 60 to complete the docking, thereby facilitating the connection of the satellite bracket connecting structure 62 and the fairing 60 to form a satellite fairing.

[0071] The support platform 50 serves as the bearing body of the satellite bracket connection structure 62, and is arranged in the center of the satellite fairing assembly system 100 as a whole. The support platform 50 also serves as the supporting body of the star cover assembly after the satellite fairing is closed. The satellite fairing assembly system 100 of the embodiment of the present application has four degrees of freedom adjustment for the fairing body 61 and the fairing 60, including movement in two directions in the horizontal plane, namely horizontal movement in the first direction and horizontal movement in the second direction, up and down movement in the vertical direction, and rotational movement around the axis of the fairing. It can realize the functions of horizontal lifting, vertical lifting, and rotational docking of the star cover assembly with the satellite bracket connection structure, and meet the needs of horizontal and vertical docking of the star cover assembly with the rocket compartment. In the process of hoisting and closing the fairing half-cover, hoisting the star cover assembly, and rotating and docking with the satellite bracket connection structure, there is no need to replace different tooling, which simplifies the operation process.

[0072] Alternatively, if Figure 8 As shown, a first mounting hole 63 is provided on the fairing 60, and a second mounting hole 64 is provided on the satellite bracket connecting structure 62. By rotating the turntable 52, the satellite bracket connecting structure 62 is driven to rotate so that 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 pass through the first mounting hole 63 and the second mounting hole 64 to connect the satellite bracket connecting structure 62 and the fairing 60.

[0073] Alternatively, if Figure 5 and Figure 6As shown, in the embodiment of the present application, the mounting frame 30 includes a first ring frame 31, a second ring frame 32 and a support frame 34, the first ring frame 31 is used to connect with the fairing body 61, and the first ring frame 31 has a first arc-shaped groove for accommodating the fairing body 61; the second ring frame 32 is used to connect with the fairing body 61, and the second ring frame 32 has a second arc-shaped groove for accommodating the fairing body 61, the first ring frame 31 and the second ring frame 32 are arranged at intervals along the axial direction of the fairing, and optionally, the first arc-shaped groove is attached to the outer wall of the connection part of the fairing body 61 and the first ring frame 31, and the second arc-shaped groove is attached to the outer wall of the connection part of the fairing body 61 and the second ring frame 32, so as to better accommodate, install and support the fairing body 61. Optionally, the first arc-shaped groove and the second arc-shaped groove have 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 for connecting to the lifting device 70 ; the support frame 34 is respectively connected to the first ring frame 31 and the second ring frame 32 , and the support frame 34 is installed on the adjustment device 40 .

[0074] In the embodiment of the present application, the first ring frame 31 and the second ring frame 32 are respectively connected to different positions of the same fairing half-cover, and then the support frame 34 is respectively connected to the first ring frame 31 and the second ring frame 32 to form a combination of the installation frame 30 and the fairing half-cover, and the two half-cover assemblies are vertically connected to the fairing to form a star cover assembly. At least one of the first ring frame 31 and the second ring frame 32 is provided with a lifting ear 33, and the lifting ear 33 is used as an interface for the lifting and flipping of the star cover assembly. By connecting the lifting device 70 with the lifting ear 33, the flipping of the star cover assembly is completed. The installation frame 30 integrates the function of the star cover assembly flipping tooling. On the premise of meeting the requirements of the fairing half-cover combination, it has the function of realizing the flipping of the star cover assembly. During the flipping and hoisting process of the star cover assembly, the contact area between the installation frame 30 and the fairing 60 is large, and the tooling rigidity is high. After being connected to the fairing, the fairing half-cover and the star cover assembly can protect the fairing during the flipping process, while reducing the strength of the fairing hoisting and flipping structure, and improving the carrying capacity of the rocket.

[0075] Alternatively, if Figure 5 and Figure 6 As shown, in the embodiment of the present application, the support frame 34 is provided with a ground-supporting leg 35 on one side facing the adjustment device 40, and the support frame 34 is connected to the adjustment device 40 through the ground-supporting leg 35. The support frame 34 provides the ground-supporting leg 35 vertically parked on the adjustment device 40 to assist in completing the cover closing.

[0076] Optionally, the ground-supporting legs 35 and the adjusting devices 40 are arranged in a one-to-one correspondence. Figure 1 , Figures 3 to 6As shown, in the embodiment of the present application, three groups of adjustment devices 40 and three ground-supporting legs 35 are respectively arranged on both sides of the support platform 50 along the first direction, and one ground-supporting leg 35 is connected to one adjustment device 40, and each adjustment device 40 is respectively 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. The adjustment devices 40 on each side are respectively used to carry the mounting frame 30 connected to the fairing half-cover, realize the support of the ground-supporting legs 35 on each side, so as to support the support frame 34 on that side and drive the mounting frame 30 to move.

[0077] Alternatively, if Figure 7 As shown, in the embodiment of the present application, the adjustment device 40 includes a first moving mechanism 41, which is connected to the fairing body 61 and the supporting platform body 51 respectively; the first moving mechanism 41 is movably arranged relative to the supporting platform body 51 along a first direction, and the first moving mechanism 41 drives the fairing body 61 to move along the first direction, so that each fairing body 61 is close to or away from each other. When each fairing body 61 is close to each other, the joining process can be completed.

[0078] Alternatively, if Figure 7 As shown, 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, and the base 411 supports the mounting frame 30; the roller 412 is mounted on the bottom of the base 411 and is rotatably arranged relative to the base 411. The rotation of the roller 412 drives the base 411 to move, thereby driving the mounting frame 30 and the fairing body 61 to move; the adjustment device 40 also includes a guide rail bracket 421 and a first guide rail 422 (such as Figure 3 and Figure 4 As shown), the guide rail bracket 421 supports the first guide rail 422, and the guide rail bracket 421 is connected to the support platform body 51, so that the relative positions of the guide rail bracket 421 and the support platform body 51 are fixed, and the first guide rail 422 extends along the first direction, and the roller 412 slides with the first guide rail 422, and the first guide rail 422 has a guiding effect on the roller 412. The roller 412 slides along the first guide rail 422, and the base 411 can be moved along the first direction, so that the installation frame 30 and the fairing body 61 move along the first direction, and then the fairing bodies 61 can be close to or away from each other, and the fairing bodies 61 can approach each other to reach the docking position.

[0079] Alternatively, if Figure 3 and Figure 4 As shown, in the embodiment of the present application, the first guide rail 422 is connected to the guide rail bracket 421 to form the ground rail 42. Optionally, as Figure 3 and Figure 4As shown, in the embodiment of the present application, the guide rail bracket 421 is detachably connected to the support platform body 51. When in use, the guide rail bracket 421 and the support platform body 51 can be assembled together. When idle or transported, the guide rail bracket 421 and the support platform body 51 can be disassembled to facilitate storage and transportation.

[0080] Optionally, a ground rail stopper 424 (such as Figure 3 As shown), a positioning seat 511 is provided on the supporting platform body 51 (as shown Figure 2 The ground rail limit seat 424 is provided with a first positioning hole 425 (as shown in Figure 3 As shown), a second positioning hole is provided on the positioning seat 511, and a locking member (such as a bolt, etc.) is used to pass through the first positioning hole 425 and the second positioning hole to detachably fix the guide rail bracket 421 to the support platform body 51, thereby realizing the installation guidance and limitation of the ground rail, which is convenient for assembly and disassembly.

[0081] Optionally, the guide rail bracket 421 is a frame structure formed by splicing a plurality of rod structures. Optionally, the rod structure is an aluminum profile, which is light in weight and helps to achieve lightweight.

[0082] like Figure 3 and Figure 4 As shown, in the embodiment of the present application, three sets of adjustment devices 40 are respectively arranged on both sides of the support platform 50 along the first direction, and the three sets of adjustment devices 40 include three ground rails 42. The guide rail brackets 421 are connected by ground rail connectors 426 to realize the connection between the ground rails and form a combination. Optionally, the ground rail connector 426 is an aluminum profile.

[0083] Alternatively, if Figure 7 As shown, in the embodiment of the present application, two rows of rollers 412 are arranged at the bottom of the base 411, and each row of rollers 412 is arranged along a first direction, and the two rows of rollers 412 are arranged at intervals in a direction perpendicular to the first direction. Two rows of first guide rails 422 corresponding to the two rows of rollers 412 are installed on the guide rail bracket 421, and each row of rollers 412 slides with the corresponding first guide rails 422; a first limit baffle 427 is also provided at the bottom of the base 411, and the first limit baffle 427 is arranged on the inner side of the roller 412. Along the radial direction of the roller 412, the size of the first limit baffle 427 is larger than the size of the roller 412. When the roller 412 slides along the first guide rail 422, the first limit baffle 427 can limit the deviation of the roller 412 to prevent the roller 412 from disengaging from the first guide rail 422, thereby ensuring that the roller 412 slides along the first guide rail 422.

[0084] Alternatively, if Figure 7As shown, in the embodiment of the present application, the adjusting device 40 also includes a second moving mechanism 43, and the second moving mechanism 43 is arranged on the first moving mechanism 41. The first moving mechanism 41 is connected to the mounting frame 30 through the second moving mechanism 43, and 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 the first direction, driving the second moving mechanism 43, the mounting frame 30 and the fairing body 61 to move along the first direction, so that each fairing body 61 is close to docking; at least part of the structure of the second moving mechanism 43 is movably arranged along the second direction relative to the first moving mechanism 41, driving the mounting frame 30 and the fairing body 61 to move along the second direction to adjust the position of the fairing body 61 in the second direction, so that each fairing body 61 is aligned to facilitate docking with the fairing.

[0085] Alternatively, if Figure 7 As shown, in the embodiment of the present application, the second moving mechanism 43 includes a first spiral elevator 431 and a sliding seat 432. The first spiral elevator 431 is installed on the base 411 of the first moving mechanism 41. The base 411 has a supporting effect on the first spiral elevator 431. The lead screw of the first spiral elevator 431 is movably arranged relative to the base 411 along the second direction; the sliding seat 432 is respectively connected to the mounting frame 30 and the lead screw. Under the action of external force, the lead screw of the first spiral elevator 431 moves relative to the base 411 along the second direction. Driven by the lead screw, the sliding seat 432 and the mounting frame 30 move along the second direction, thereby driving the fairing body 61 to move along the second direction to adjust the horizontal position of the fairing body 61; the adjusting device 40 also includes a second guide rail 423 installed 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 slidably matched. The second guide rail 423 guides the sliding seat 432 . The sliding seat 432 slides along the second guide rail 423 , so that the sliding seat 432 drives the installation frame 30 and the fairing body 61 to move along the second direction.

[0086] In the embodiment of the present application, the first screw elevator 431 includes components such as a worm gear, a bearing, and a lead screw. The worm is driven by a motor or manually to rotate, and the worm drives the turbine to rotate. The internal thread of the turbine cavity cooperates with the external thread of the lead screw to drive the lead screw to move; thereby, the sliding seat 432 is driven to move by the lead screw.

[0087] Of course, in some optional embodiments of the present application, the second moving mechanism 43 can also include a ball screw to replace the first screw elevator 431 according to actual needs. The ball screw includes 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 along the axial direction of the screw; thereby, the sliding seat 432 is driven to move through the nut.

[0088] Alternatively, if Figure 7As shown, in the embodiment of the present application, a first scale 413 is further provided on the base 411, and a first pointer 414 is provided on the sliding seat 432. The first pointer 414 points to the scale on the first scale 413 to display the position of the sliding seat 432. The first pointer 414 moves with the sliding seat 432 relative to the base 411. The first pointer 414 points to different scales of the first scale 413 to display the movement spacing of the sliding seat 432.

[0089] Alternatively, if Figure 7 As shown, in the embodiment of the present application, the adjusting device 40 also includes a third moving mechanism 44, and the third moving mechanism 44 is arranged on the second moving mechanism 43. The second moving mechanism 43 is connected to the mounting frame 30 through the third moving mechanism 44, and 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, driving 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 arranged in 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 in the vertical direction to adjust the position of the fairing body 61 in the vertical direction.

[0090] Alternatively, if Figure 7 As shown, in the embodiment of the present application, the third moving mechanism 44 includes a second spiral elevator 441 and a support plate 442. The second spiral elevator 441 is installed on a sliding seat 432. The sliding seat 432 supports the second spiral elevator 441. The lead screw of the second spiral elevator 441 is movably arranged in a vertical direction relative to the sliding seat 432. The support plate 442 is respectively connected to the mounting frame 30 and the lead screw. Under the action of external force, the lead screw of the second spiral elevator 441 moves in a vertical direction relative to the sliding seat 432. Driven by the lead screw, the support plate 442 and the mounting frame 30 move in a vertical direction, thereby driving the fairing body 61 to move in a vertical direction, and adjusting the height position of the fairing body 61.

[0091] Alternatively, if Figure 7 As shown, in the embodiment of the present application, the adjusting device 40 also includes a third guide rail 428 installed on the sliding seat 432, the third guide rail 428 extends in the vertical direction, a guide hole 443 is provided on the support plate 442, the third guide rail 428 is passed through the guide hole 443, so that the support plate 442 slides along the third guide rail 428, and the third guide rail 428 guides the support plate 442.

[0092] Alternatively, if Figure 7As shown, in the embodiment of the present application, a second limit baffle 429 is also provided at one end of the third guide rail 428 away from the sliding seat 432. Along the direction perpendicular to the axis of the third guide rail 428, the size of the second limit baffle 429 is larger than the size of the guide hole 443. The second limit baffle 429 is used to stop the support plate 442 from sliding along the third guide rail 428 to prevent the support plate 442 from falling off the third guide rail 428.

[0093] Alternatively, if Figure 7 As shown, in the embodiment of the present application, a second scale 444 is further provided on the sliding seat 432, and a second pointer 445 is provided on the support plate 442. The second pointer 445 points to the scale on the second scale 444 to display the position of the support plate 442. The second pointer 445 moves with the support plate 442 relative to the sliding seat 432, and the second pointer 445 points to different scales of the second scale 444 to display the movement spacing of the support plate 442.

[0094] Optionally, in the embodiment of the present application, the support plate 442 is used to be detachably fixedly connected to the ground-supporting legs 35 of the installation frame 30 .

[0095] It should be noted that in the embodiment of the present application, the structure and working principle of the second spiral elevator 441 may be similar to or the same as the structure and working principle of the first spiral elevator 431, and will not be repeated here.

[0096] Of course, in some optional embodiments of the present application, the third moving mechanism 44 can also include a ball screw to replace the second screw elevator 441 according to actual needs, so as to realize the function of driving the support plate 442 to move in the vertical direction.

[0097] Alternatively, if Figure 7 As shown, in the embodiment of the present application, the first moving mechanism 41, the second moving mechanism 43 and the third moving mechanism 44 are connected in sequence to form a mobile docking vehicle 45.

[0098] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the support platform 50 further includes a leveling leg 53 , which is mounted on the support platform body 51 and is used to level the turntable 52 so that the top surface of the turntable 52 is parallel to the horizontal plane.

[0099] The leveling legs 53 adjust the height of the supporting platform body 51 in the vertical direction. There are multiple leveling legs 53, and the multiple leveling legs 53 are arranged at intervals on the supporting platform body 51. Optionally, the multiple leveling legs 53 are evenly spaced. The multiple leveling legs 53 respectively adjust the height of different positions of the supporting platform body 51 so that the top surface of the turntable 52 is parallel to the horizontal plane.

[0100] Optionally, the leveling legs 53 may be a linear drive mechanism, such as a motor, a cylinder or a hydraulic drive.

[0101] Optionally, a level meter or an inclinometer is provided on the top surface of the turntable 52 to detect the levelness of the top surface of the turntable 52 .

[0102] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the support platform 50 also includes casters 54, which are installed at the bottom of the support platform body 51 and are rotatably arranged relative to the support platform body 51. Under the action of external force, the casters 54 rotate to drive the support platform body 51 to move, so as to facilitate the adjustment of the position of the support platform 50.

[0103] Optionally, there are multiple casters 54, and the multiple casters 54 are arranged at intervals. Optionally, the multiple casters 54 are evenly spaced.

[0104] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the support platform 50 further includes a swivel support structure 55 , which is mounted on the support platform body 51 , and the turntable 52 is rotatably connected to the support platform body 51 via the swivel support structure 55 .

[0105] Optionally, the slewing support structure 55 is a bearing. The axis of the bearing mounted on the supporting platform body 51 coincides with the axis of the fairing 60 after the fairing is closed.

[0106] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the support platform 50 also includes a rotary drive mechanism 56, which is installed on the support platform body 51. The support platform body 51 supports the rotary drive mechanism 56. The rotary drive mechanism 56 is connected to the turntable 52, and the turntable 52 rotates under the drive of the rotary drive mechanism 56.

[0107] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the rotary drive mechanism 56 includes a linear drive structure 561 and a connecting rod structure 562, one end of the connecting rod structure 562 is pivotally connected to the output end of the linear drive structure 561, and the other end of the connecting rod structure 562 is pivotally connected to the turntable 52. Driven by the output end of the linear drive structure 561, the connecting rod structure 562 transmits power to the turntable 52, causing the turntable 52 to rotate.

[0108] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the support platform 50 further includes a rotary locking mechanism 57 , which is mounted on the support platform body 51 and is used to cooperate with the turntable 52 to lock the position of the turntable 52 .

[0109] Optionally, the rotary locking mechanism 57 includes an adjusting member and a brake pad. The adjusting member is arranged on the supporting platform body 51 and is located on the outer periphery of the turntable 52. The adjusting member is movably arranged along the radial direction of the turntable 52 relative to the supporting platform body 51. The brake pad is installed on the adjusting pad and is located on the side of the adjusting pad facing the turntable 52. By adjusting the position of the adjusting member, the brake pad can be brought into contact with the turntable 52, thereby relying on the friction between the brake pad and the turntable 52 to brake the turntable 52, thereby locking the position of the turntable 52. The brake pad can also be released from the contact with the turntable 52, so that the turntable 52 is not affected by the friction from the brake pad and can be rotated relative to the supporting platform body 51, thereby adjusting the position of the turntable 52.

[0110] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the support platform 50 further includes a turntable limiting structure 58, and the turntable limiting structure 58 is used to limit the extreme position of the turntable 52. Specifically, as Figure 2 As shown, the turntable limiting structure 58 includes an arc-shaped limiting hole 581 arranged on the supporting platform body 51 and a limiting rod 582 installed on the turntable 52. The end of the limiting rod 582 away from the turntable 52 is inserted into the arc-shaped limiting hole 581. The arc-shaped limiting hole 581 is an arc-shaped hole extending around the axis of the rotating support structure 55. The limiting rod 582 rotates with the turntable 52 around the axis of the rotating support structure 55. The limiting rod 582 moves along the arc-shaped limiting hole 581 in the arc-shaped limiting hole 581. The limiting rod 582 can respectively abut against the inner wall surfaces at both ends of the arc-shaped limiting hole 581 along the arc, thereby limiting the limit position of the limiting rod 582 moving in the arc-shaped limiting hole 581, thereby achieving the purpose of limiting the limit position of the rotation of the turntable 52.

[0111] The workflow of the satellite fairing assembly system in this application is as follows:

[0112] 1. If Figure 2 As shown, the support platform 50 is placed on the ground, and the upper surface of the turntable 52 of the support platform 50 is leveled using the leveling legs 53;

[0113] 2. Connect the guide rail bracket 421 and the first guide rail 422 in advance, and connect them through the ground rail limit seat 424 (such as Figure 3 ) and the positioning seat 511 (as shown in Figure 2 4) and then connect the middle ground rail and the side ground rail using the ground rail connector 426 to form a frame structure (as shown in FIG. Figure 3 and Figure 4 shown);

[0114] 3. Place the mobile docking vehicle 45 with adjustment capability on the ground rail 42;

[0115] 4. Connect and fix the first ring frame 31 and the second ring frame 32 to a fairing half cover respectively;

[0116] 5. Connect and fix the support frame 34 to the first ring frame 31 and the second ring frame 32 respectively;

[0117] 6. Use a lifting device 70 (such as a lifting device) to lift the fairing half cover from a horizontal state (such as Figure 5 as shown) to a vertical position (as shown) Figure 6 shown);

[0118] 7. Hoist the vertical fairing half-cover onto the three sets of mobile docking vehicles 45 on one side. After it falls into place, fix the ground-supporting legs 35 of the mounting frame 30 and the support plate 442 on the mobile docking vehicle 45 with fasteners;

[0119] 8. In the same manner as above, connect another set of fairing half covers with the mounting frame 30 to form a combination, and hoist the combination above the three sets of mobile docking vehicles 45 on the other side, and fix the ground support legs 35 and the support plate 442 with fasteners;

[0120] 9. Push the two sets of fairing half covers separately, and move the mobile docking vehicle 45 toward the support platform 50 to complete the vertical docking of the fairing half covers, and install the fairing longitudinal connectors to combine the two fairing half covers to form a fairing 60 (such as Figure 8 As shown), during the docking process, the two fairing half covers can be aligned by adjusting the first spiral elevator 431 of the mobile docking vehicle 45 to facilitate docking;

[0121] 10. After the fairing half-covers are docked, adjust the second screw elevator 441 of the mobile docking vehicle 45 to move the fairing half-cover assembly downward and quickly fall onto the satellite bracket connecting structure 62, and install the fairing axial connecting bolts;

[0122] 11. According to the alignment of the first mounting hole 63 on the fairing 60 and the second mounting hole 64 on the satellite bracket connecting structure 62, unlock the rotary locking mechanism 57 on the support platform 50, and manually crank the screw elevator of the rotary drive mechanism 56 to make the turntable 52 drive the satellite bracket connecting structure 62 to rotate around the central axis of the rotary support structure 55 to ensure that the first mounting hole 63 and the second mounting hole 64 are aligned (such as Figure 8 As shown), the fairing 60 and the satellite bracket connecting structure 62 are installed and fixed together through the fairing axial connecting bolts;

[0123] 12. Remove the fasteners connecting the support frame 34 and the first ring frame 31, and the fasteners connecting the support frame 34 and the second ring frame 32, disassemble the support frame 34 and the first ring frame 31, and disassemble the support frame 34 and the second ring frame 32;

[0124] 13. If Fig. 9As shown, the two sets of first ring frames 31 are fastened by bolts through the light holes on the flange surface to form an integral structure, and then the lifting ears 33 on the two sets of first ring frames 31 are respectively connected to the lifting equipment 70;

[0125] 14. Flip the star cover assembly into a horizontal state so that it can be horizontally docked with the entire arrow.

[0126] 15. Remove the fasteners used to connect the first ring frame 31 and the fairing half cover, the second ring frame 32 and the fairing half cover, and then remove the first ring frame 31 and the second ring frame 32 by the lifting equipment 70, thus completing the assembly process of the satellite fairing.

[0127] The satellite fairing assembly system of the present application is composed of multiple modules such as a support platform 50, a ground rail 42, a mobile docking vehicle 45, and an installation frame 30. The envelope size is relatively large. The support platform 50, the ground rail 42, the mobile docking vehicle 45, and the installation frame 30 are assembled. Each module is independent of each other and is assembled when used, which reduces the accuracy requirements for tooling installation, reduces the difficulty of tooling transportation, and reduces transportation costs. At the same time, some modules can be compatible with fairings of other sizes.

[0128] The satellite fairing assembly system of the present application can be used as a docking and lifting tooling equipment for a rocket-satellite fairing assembly.

[0129] By applying the embodiments of the present application, at least the following beneficial effects can be achieved:

[0130] In the embodiment of the present application, the first assembly component and the second assembly component are respectively connected to a fairing body, and the first assembly component and the second assembly component are respectively used to adjust the position of the connected fairing bodies so that the fairing bodies can be close to each other to form a fairing with the joint cover.

[0131] The adjusting device, the mounting frame and the fairing body are connected in sequence, and the mounting frame supports the fairing body. The adjusting device can drive the mounting frame to move in a first direction and a second direction in a horizontal plane and in a vertical direction in a vertical plane, thereby realizing a multi-degree-of-freedom movement of the fairing body in two directions in a horizontal plane and in an up-and-down direction in a vertical plane, thereby adjusting the position of the fairing body so that the fairing bodies can approach and align with each other, realizing the function of docking and joining the fairing, and completing the assembly process of the fairing.

[0132] The satellite fairing assembly system of the embodiment of the present application, driven by the adjustment device, has the function of moving in two directions in the horizontal plane to achieve horizontal lifting, and moving in the vertical plane in the up and down directions to achieve vertical lifting, which meets the needs of the satellite fairing to dock with the rocket compartment in both horizontal and vertical ways, and can complete the horizontal lifting, vertical lifting, vertical docking of the fairing half-cover during the rocket fairing assembly process, and achieve the docking of the two fairing half-covers in a vertical state to form a satellite fairing. In the process of hoisting and docking the fairing half-cover, there is no need to replace different tooling, and a set of tooling can be used to complete various working conditions in the fairing assembly process, reducing the types of equipment in the rocket assembly process, simplifying the operation process, and making it more convenient to use.

[0133] The support platform serves as the bearing body of the satellite bracket connection structure, and is arranged in the center of the satellite fairing assembly system as a whole. The support platform also serves as the supporting body of the star cover assembly after the satellite fairing is closed. The satellite fairing assembly system of the embodiment of the present application has four degrees of freedom adjustment for the fairing body and the fairing, including movement in two directions in the horizontal plane, namely horizontal movement in the first direction and horizontal movement in the second direction, up and down movement in the vertical direction, and rotational movement around the axis of the fairing. It can realize the functions of horizontal lifting, vertical lifting, and rotational docking of the star cover assembly with the satellite bracket connection structure, and meet the needs of horizontal and vertical docking of the star cover assembly with the rocket compartment. In the process of hoisting and closing the fairing half-cover, hoisting the star cover assembly, and rotational docking with the satellite bracket connection structure, there is no need to replace different tooling, which simplifies the operation process.

[0134] In the embodiment of the present application, the first ring frame and the second ring frame are respectively connected to different positions of the same fairing half-cover, and then the support frame is respectively connected to the first ring frame and the second ring frame to form a combination of the installation frame and the fairing half-cover, and the two half-cover assemblies are vertically connected to the fairing to form a star cover assembly. At least one of the first ring frame and the second ring frame is provided with a lifting lug, which serves as an interface for the lifting and flipping of the star cover assembly. The star cover assembly is flipped by connecting the lifting equipment to the lifting lug. The installation frame integrates the function of the star cover assembly flipping tooling. On the premise of meeting the requirements of the fairing half-cover combination, it has the function of realizing the flipping of the star cover assembly. During the flipping and hoisting process of the star cover assembly, the installation frame has a large contact area with the fairing, and the tooling has high rigidity. After being connected to the fairing, the fairing half-cover and the star cover assembly can protect the fairing during the flipping process, while reducing the strength of the fairing hoisting and flipping structure, and improving the carrying capacity of the rocket.

[0135] Those skilled in the art will appreciate that the various operations, methods, steps, measures, and schemes in the processes discussed in this application may be alternated, altered, combined, or deleted. Further, other steps, measures, and schemes in the various operations, methods, and processes discussed in this application may also be alternated, altered, rearranged, decomposed, combined, or deleted. Further, the steps, measures, and schemes in the prior art that are similar to those disclosed in this application may also be alternated, altered, rearranged, decomposed, combined, or deleted.

[0136] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0137] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0138] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0139] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0140] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A satellite fairing assembly system, characterized in that: It comprises a first assembly component and a second assembly component, wherein the first assembly component and the second assembly component are respectively connected to a fairing body; At least one of the first assembly component and the second assembly component comprises: A mounting frame, used to be connected to the fairing body; An adjusting device connected to the installation frame, used to drive the installation frame to move in 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 body so that the fairing bodies are butted together to form a fairing; wherein the first direction and the second direction intersect; The satellite fairing assembly system also includes a support platform disposed between the first assembly component and the second assembly component; The support platform includes a support platform body and a turntable disposed on the support platform body, the turntable is used to be connected to the satellite bracket connection structure, and the turntable is rotatably disposed relative to the support platform body around the axis of the fairing to adjust the position of the satellite bracket connection structure so that the satellite bracket connection structure is docked with the fairing; The installation frame includes: A first ring frame, used to be connected to the fairing body, the first ring frame having a first arc-shaped groove for accommodating the fairing body; a second ring frame, used to be connected to the fairing body, the second ring frame having a second arc-shaped groove for accommodating the fairing body, the first ring frame and the second ring frame being spaced apart along the axial direction of the fairing, and at least one of the first ring frame and the second ring frame being provided with a lifting lug, the lifting lug being used to be connected to a lifting device; A support frame is connected to 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 according to claim 1, characterized in that: The adjusting device comprises a first moving mechanism, and the first moving mechanism is respectively connected to the fairing body and the supporting platform body; The first moving mechanism is movably arranged relative to the supporting platform body along the first direction so as to make the fairing bodies approach or move away from each other.

3. The satellite fairing assembly system according to claim 2, characterized in that: The first moving mechanism comprises: A base, the mounting frame being mounted on the top of the base; A roller, mounted on the bottom of the base and rotatably arranged relative to the base; The adjusting device also includes a guide rail bracket and a first guide rail mounted on the guide rail bracket, the guide rail bracket is connected to the supporting platform body, the first guide rail extends along the first direction, and the roller is slidably matched with the first guide rail.

4. The satellite fairing assembly system according to claim 2 or 3, characterized in that: 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 to the fairing body through the second moving mechanism; At least a part of the structure of the second moving mechanism is movably arranged along the second direction relative to the first moving mechanism to adjust the position of the fairing body in the second direction.

5. The satellite fairing assembly system according to claim 4, characterized in that: The second moving mechanism comprises: A first screw elevator is mounted on a base of the first moving mechanism, wherein a lead screw of the first screw elevator is movably arranged relative to the base along a second direction; A sliding seat, connected to the installation frame and the lead screw respectively, driven by the lead screw, the sliding seat and the installation frame move along the second direction; The adjusting device further comprises a second guide rail mounted on the base, the second guide rail extends along the second direction, and the sliding seat and the second guide rail are slidably matched.

6. The satellite fairing assembly system according to claim 4, characterized in that: 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 to the fairing body through the third moving mechanism; At least a part of the structure of the third moving mechanism is movably arranged in the vertical direction relative to the second moving mechanism to adjust the position of the fairing body in the vertical direction.

7. The satellite fairing assembly system according to claim 1, characterized in that: The support platform also includes: A leveling leg, mounted on the supporting platform body, for leveling the turntable so that the top surface of the turntable is parallel to the horizontal plane; The caster is installed at the bottom of the supporting platform body and is rotatably arranged relative to the supporting platform body. Under the action of external force, the caster rotates to drive the supporting platform body to move.

8. The satellite fairing assembly system according to claim 7, characterized in that: The support platform also includes: A slewing support structure is mounted on the supporting platform body, and the turntable is rotatably connected to the supporting platform body through the slewing support structure; A rotary drive mechanism is installed on the supporting platform body and connected to the turntable, and the turntable rotates under the drive of the rotary drive mechanism; The rotary locking mechanism is installed on the supporting platform body and is used to cooperate with the turntable to lock the position of the turntable.

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