Spaceflight satellite modular structure assembly capable of being rapidly assembled

Abstract

The utility model relates to the field of spaceflight satellite modules, in particular to a spaceflight satellite modular structure assembly capable of being quickly assembled, which comprises a cubesat shell, a connecting plate is arranged on the outer side of the cubesat shell, and a solar panel body is fixedly connected to the outer side of the connecting plate. A connecting mechanism and a mounting mechanism are arranged between the connecting plate and the cubesat shell, the connecting mechanism comprises a first inserting block fixedly connected to one side of the connecting plate, a first inserting groove is formed in one side of the cubesat shell, and a clamping groove is formed in the cubesat shell; according to the device, through the insertion design of a first insertion block and a first insertion groove in the connecting mechanism, the solar panel can be rapidly and conveniently installed on the cubesat shell, the stability after insertion is ensured through the cooperation of a clamping block and a clamping groove, an automatic locking function is provided through the arrangement of a first spring, the installation operation is simplified, and the installation efficiency is improved. And the efficiency of mutually assembling the cubesat shell and the connecting plate is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aerospace satellite modules, and particularly relates to a modular structure component of an aerospace satellite that can be quickly assembled. Background Art

[0002] The modular structure components of an aerospace satellite refer to dividing the satellite into multiple functionally independent modules through standardization and modular design. Each module performs a specific task or function. Generally, aerospace satellite modules are divided into structural modules, power modules, communication modules, etc. In a cube satellite, the solar panels in the solar module are generally connected to the structural module to ensure the normal use of the solar panels. Generally, the structural module refers to the outer shell and framework of the satellite, which connects and supports other modules.

[0003] After retrieval, in the prior art, Chinese Patent Publication No.: CN221114374U, Authorization Date: June 11, 2024, discloses a satellite solar panel deployment mechanism. The articulated deployment mechanism further includes an annular guide sleeve threadedly connected to the guide screw. Four active rods are equidistantly arranged along the circumferential direction of the outer surface of the guide sleeve. One end of each active rod away from the guide sleeve is hinged between two solar panels, and one end of the active rod away from the guide sleeve is located between two driven rods; the reason for setting a plurality of power conversion mechanisms arranged in an annular array is to maximize the number of solar panels arranged according to the characteristics of this folding mechanism. After the articulated deployment mechanism is set, the stored solar panels are very regular, and after its deployment, it can give sufficient tensile and compressive forces to ensure that it will not be caused by centrifugal force during deployment. Most importantly, this mechanism can provide more installation quantities in the same design space.

[0004] However, this device still has the following defects: Although the connection between the guide sleeve and the guide screw can be used to realize the deployment and retraction of the solar panels when the guide sleeve moves, when the staff installs the solar panels, multiple hinge shaft parts need to be used and matched with the guide sleeve, which is not only troublesome and inconvenient during installation, but also greatly reduces the installation efficiency. Summary of the Utility Model

[0005] In view of the above problems, the utility model provides a modular structure component of an aerospace satellite that can be quickly assembled, including a cube satellite housing. A connecting plate is arranged on the outer side of the cube satellite housing. A solar panel body is fixedly connected to the outer side of the connecting plate. A connecting mechanism and an installation mechanism are arranged between the connecting plate and the cube satellite housing;

[0006] The connecting mechanism includes a first plug fixedly connected to one side of the connecting plate. A first slot is provided on one side of the cube satellite housing. A card slot is provided inside the cube satellite housing, and the first slot communicates with the card slot. The first plug is movably inserted inside the first slot. An installation slot is provided on one side of the first plug. A first spring is provided inside the installation slot, and one end of the first spring is fixedly connected to the first plug. The other end of the first spring is fixedly connected to a clamping block, and the clamping block is movably clamped inside the card slot.

[0007] Furthermore, the installation mechanism includes a second plug fixedly connected to one side of the connecting plate. A second slot is provided on one side of the cube satellite housing. The second plug is movably inserted inside the second slot. A second spring is provided inside the second slot. One end of the second spring is fixedly connected to the cube satellite housing, and the other end of the second spring is fixedly connected to a limiting block, and the limiting block is movably inserted inside the second plug.

[0008] Furthermore, a sliding groove is provided inside the first plug, and the sliding groove communicates with the installation slot. A sliding block is fixedly connected to one side of the clamping block, and the sliding block is slidably connected inside the sliding groove.

[0009] Furthermore, a resilient rubber is fixedly connected inside the first plug, and the resilient rubber is provided inside the installation slot. One end of the resilient rubber is fixedly connected to the clamping block, and the resilient rubber is provided inside the first spring.

[0010] Furthermore, a limiting rod is provided inside the first slot. One end of the limiting rod is fixedly connected to the cube satellite housing. A limiting groove is provided on one side of the first plug, and the limiting rod is movably inserted inside the limiting groove.

[0011] Furthermore, a connecting groove is provided on one side of the cube satellite housing. A plug rod is fixedly connected to one side of the connecting plate, and the plug rod is movably inserted inside the connecting groove.

[0012] Furthermore, threaded holes are provided on one side of both the connecting plate and the cube satellite housing. A connecting block is provided outside the connecting plate. A bolt is threadedly connected inside the connecting block, and the bolt is provided inside the threaded hole.

[0013] Furthermore, a first filling block is provided inside the first slot, a second filling block is provided inside the second slot, and both the first filling block and the second filling block are connected to the cube satellite housing.

[0014] The beneficial effects of the present utility model are:

[0015] 1. In this device, through the insertion design of the first insertion block and the first slot in the connection mechanism, the solar panel can be quickly and conveniently installed on the cube satellite housing. The cooperation of the clamping block and the clamping groove ensures the stability after insertion, and the setting of the first spring provides an automatic locking function, simplifies the installation operation, and improves the efficiency when the cube satellite housing and the connecting plate are assembled with each other.

[0016] 2. When the clamping block moves in this device, it will drive the slider to move together, and through the connection relationship between the sliding groove and the slider, it plays a restrictive role on the clamping block, making the movement of the clamping block stable enough and not prone to deviation.

[0017] Other features and advantages of the present utility model will be described in the subsequent description, and, partly, will be obvious from the description, or will be understood by implementing the present utility model. The objectives and other advantages of the present utility model can be achieved and obtained through the structures pointed out in the description, the claims, and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following-described drawings are some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0019] Figure 1 Shows the structural main diagram according to the embodiment of the present utility model;

[0020] Figure 2 Shows the cross-sectional structural schematic diagram according to the embodiment of the present utility model;

[0021] Figure 3 Shows the structural schematic diagram of the first slot and the connection slot according to the embodiment of the present utility model;

[0022] Figure 4 Shows the structural schematic diagram of the second insertion block and the insertion rod according to the embodiment of the present utility model;

[0023] Figure 5 Shows the structural schematic diagram of the connection block according to the embodiment of the present utility model;

[0024] Figure 6 Shows according to the present utility model Figure 2 The enlarged structural schematic diagram at A;

[0025] Figure 7 Shows according to the present utility model Figure 2 The enlarged structural schematic diagram at B.

[0026] In the figure: 1. Cube satellite housing; 2. Connection plate; 3. Solar panel body; 4. Connection mechanism; 41. First plug; 42. First slot; 43. Card slot; 44. Installation groove; 45. First spring; 46. Clamping block; 5. Installation mechanism; 51. Second plug; 52. Second slot; 53. Second spring; 54. Limit block; 6. Rebound rubber; 71. Slide groove; 72. Slide block; 81. Limit groove; 82. Limit rod; 91. First filling block; 92. Second filling block; 101. Connection block; 102. Threaded hole; 103. Bolt; 111. Plug rod; 112. Connection groove. Specific implementation mode

[0027] In order to make the purposes, technical solutions and advantages of the embodiments of the present utility model clearer, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are some, but not all, of the embodiments of the present utility model. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0028] The embodiments of the present utility model provide a modular structure component of a space satellite that can be quickly assembled, including a cube satellite housing 1. Exemplarily, as Figures 1-7 shown.

[0029] A connection plate 2 is arranged on the outer side of the cube satellite housing 1, a solar panel body 3 is fixedly connected to the outer side of the connection plate 2, and a connection mechanism 4 and an installation mechanism 5 are arranged between the connection plate 2 and the cube satellite housing 1.

[0030] The connection mechanism 4 includes a first plug 41 fixedly connected to one side of the connection plate 2. A first slot 42 is opened on one side of the cube satellite housing 1. A card slot 43 is opened inside the cube satellite housing 1, and the first slot 42 is communicated with the card slot 43. The first plug 41 is movably inserted inside the first slot 42. An installation groove 44 is opened on one side of the first plug 41. A first spring 45 is arranged inside the installation groove 44, and one end of the first spring 45 is fixedly connected to the first plug 41. The other end of the first spring 45 is fixedly connected to a clamping block 46, and the clamping block 46 is movably clamped inside the card slot 43.

[0031] The installation mechanism 5 includes a second insertion block 51 fixedly connected to one side of the connecting plate 2. A second insertion slot 52 is formed on one side of the cube satellite housing 1. The second insertion block 51 is movably inserted into the inner side of the second insertion slot 52. A second spring 53 is arranged inside the second insertion slot 52. One end of the second spring 53 is fixedly connected to the cube satellite housing 1, and the other end of the second spring 53 is fixedly connected to a limiting block 54. The limiting block 54 is movably inserted into the inner side of the second insertion block 51.

[0032] Specifically, through the insertion design of the first insertion block 41 and the first insertion slot 42 in the connection mechanism 4, the solar panel can be quickly and conveniently installed on the cube satellite housing 1. The cooperation between the clamping block 46 and the clamping slot 43 ensures the stability after insertion. Moreover, the arrangement of the first spring 45 provides an automatic locking function, simplifies the installation operation, enables the staff to quickly disassemble or replace the solar panel body 3 before launch or during maintenance, and improves the efficiency when the cube satellite housing 1 and the connecting plate 2 are assembled with each other.

[0033] In addition, the clamping block 46 and the limiting block 54 cooperate with the clamping slot 43 and the second insertion block 51 respectively through springs, realizing a double fixing structure, thereby providing a strong locking effect and effectively reducing the loosening of the connecting plate 2 due to vibration when the cube satellite housing 1 is in use.

[0034] A sliding groove 71 is formed inside the first insertion block 41, and the sliding groove 71 communicates with the installation groove 44, as Figures 1-7 shown.

[0035] One side of the clamping block 46 is fixedly connected with a sliding block 72, and the sliding block 72 is slidably connected to the inner side of the sliding groove 71.

[0036] A resilient rubber 6 is fixedly connected to the inner side of the first insertion block 41. The resilient rubber 6 is arranged inside the installation groove 44. One end of the resilient rubber 6 is fixedly connected to the clamping block 46, and the resilient rubber 6 is arranged inside the first spring 45.

[0037] A limiting rod 82 is arranged inside the first insertion slot 42. One end of the limiting rod 82 is fixedly connected to the cube satellite housing 1. A limiting groove 81 is formed on one side of the first insertion block 41, and the limiting rod 82 is movably inserted into the inner side of the limiting groove 81.

[0038] Specifically, when the clamping block 46 moves, it will drive the sliding block 72 to move together. And due to the connection relationship between the sliding groove 71 and the sliding block 72, it plays a limiting role on the clamping block 46, making the movement of the clamping block 46 stable enough and not prone to deviation.

[0039] In addition, the resilient rubber 6 can limit the expansion and contraction of the first spring 45, making it difficult for the first spring 45 to bend or shift during elastic expansion and contraction. Moreover, the resilient rubber 6 can also increase the elastic thrust on the latch 46 during reset through its own elasticity.

[0040] In addition, after the first insert block 41 is inserted into the inner side of the first slot 42, the limiting rod 82 will also be inserted into the inner side of the limiting slot 81, thereby increasing the stability of the first insert block 41 during use and reducing the large-amplitude shaking of the connecting plate 2 during use due to the unstable connection between the first insert block 41 and the first slot 42.

[0041] A connecting groove 112 is formed on one side of the cube satellite housing 1, and a plug rod 111 is fixedly connected to one side of the connecting plate 2. The plug rod 111 is movably inserted into the inner side of the connecting groove 112, as Figures 1-7 shown.

[0042] Threaded holes 102 are formed on one side of both the connecting plate 2 and the cube satellite housing 1. A connecting block 101 is arranged on the outer side of the connecting plate 2. A bolt 103 is threadedly connected to the inner side of the connecting block 101, and the bolt 103 is arranged in the threaded hole 102.

[0043] A first filling block 91 is arranged on the inner side of the first slot 42, and a second filling block 92 is arranged on the inner side of the second slot 52. Both the first filling block 91 and the second filling block 92 are connected to the cube satellite housing 1.

[0044] Specifically, when the connecting plate 2 is connected to one side of the cube satellite housing 1, the plug rod 111 will be inserted into the inner side of the connecting groove 112, thereby further increasing the stability of the connecting plate 2 during use. The bolt 103 can connect the connecting block 101 to the outer side of the connecting plate 2 through the threaded hole 102, and effectively increase the connection firmness between the connecting plate 2 and the cube satellite housing 1, thereby enhancing the stability of the connecting plate 2 during use.

[0045] In addition, the arrangement of the first filling block 91 and the second filling block 92 makes it difficult for the first insert block 41 and the second insert block 51 to shake in the gap between them and the cube satellite housing 1 after being inserted into the inner side of the cube satellite housing 1, greatly increasing the stability of the first insert block 41 and the second insert block 51 during use.

[0046] Using the modular structure component of the space satellite that can be quickly assembled proposed by the embodiment of the present utility model, its working principle is as follows: When this device is in use, the staff can connect the connecting plate 2 to one side of the cube satellite housing 1 to install the solar panel body 3. During the installation, the staff can push the connecting plate 2 towards one side of the cube satellite housing 1 and align the insertion rod 111 with the connecting groove 112. Then, the insertion rod 111 will first insert into the inner side of the connecting groove 112, playing a limiting role in the subsequent movement of the connecting plate 2. At the same time, the first insertion block 41 will insert into the inner side of the first insertion slot 42, and the second insertion block 51 will insert into the inner side of the second insertion slot 52.

[0047] When the first insertion block 41 inserts into the inner side of the first insertion slot 42, the clamping block 46 will come into contact with the connecting plate 2 and move towards the inner side of the installation groove 44 due to the extrusion force. At the same time, the first spring 45 will be compressed during the movement. Then, after the first insertion block 41 is completely inserted into the inner side of the first insertion slot 42, the clamping block 46 will be reset by the elasticity of the first spring 45 and be clamped into the inner side of the clamping groove 43.

[0048] At the same time, when the second insertion block 51 inserts into the inner side of the second insertion slot 52, the limiting block 54 will also be extruded. Then, the limiting block 54 will be reset by its own elasticity and insert into the inner side of the second insertion block 51 to achieve the limitation of the second insertion block 51. At this time, the assembly of the connecting plate 2 and the cube satellite housing 1 can be completed. After that, only need to connect the connecting block 101 to the outside of the connecting plate 2 through the bolt 103 to further increase the stability between the connecting plate 2 and the cube satellite housing 1.

[0049] Although the present utility model has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: They can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present utility model.

Claims

1. A rapidly assembled modular structural assembly for a space satellite, comprising a cube satellite shell (1), characterized in that: A connecting plate (2) is provided on the outer side of the cube satellite shell (1), a solar panel body (3) is fixedly connected to the outer side of the connecting plate (2), and a connecting mechanism (4) and a mounting mechanism (5) are provided between the connecting plate (2) and the cube satellite shell (1); The connection mechanism (4) comprises a first plug block (41) fixedly connected to one side of the connection plate (2); a first slot (42) is provided on one side of the cube satellite shell (1); a clamping slot (43) is provided inside the cube satellite shell (1), and the first slot (42) is communicated with the clamping slot (43); the first plug block (41) is movably plugged into the inner side of the first slot (42); a mounting slot (44) is provided on one side of the first plug block (41); a first spring (45) is provided inside the mounting slot (44); one end of the first spring (45) is fixedly connected to the first plug block (41); the other end of the first spring (45) is fixedly connected to a clamping block (46); the clamping block (46) is movably clamped into the inner side of the clamping slot (43).

2. The rapidly assembled modular structural assembly for a space satellite according to claim 1, characterized in that: The mounting mechanism (5) comprises a second plug-in block (51) fixedly connected to one side of the connecting plate (2); a second slot (52) is provided on one side of the cube satellite shell (1); the second plug-in block (51) is movably plugged into the inner side of the second slot (52); a second spring (53) is provided on the inner side of the second slot (52); one end of the second spring (53) is fixedly connected to the cube satellite shell (1); the other end of the second spring (53) is fixedly connected to a limit block (54); and the limit block (54) is movably plugged into the inner side of the second plug-in block (51).

3. The rapidly assembled modular structural assembly for a space satellite according to claim 2, characterized in that: A slide groove (71) is provided on the inner side of the first plug block (41), and the slide groove (71) is communicated with the mounting groove (44). A slider (72) is fixedly connected to one side of the clamping block (46), and the slider (72) is slidably connected to the inner side of the slide groove (71).

4. The rapidly assembled modular structural assembly for a space satellite according to claim 3, characterized in that: A resilient rubber (6) is fixedly connected to the inner side of the first plug block (41), the resilient rubber (6) is arranged on the inner side of the mounting groove (44), one end of the resilient rubber (6) is fixedly connected to the clamping block (46), and the resilient rubber (6) is arranged on the inner side of the first spring (45).

5. The modular structural assembly of a space satellite capable of rapid assembly according to claim 4, characterized in that: A limiting rod (82) is arranged on the inner side of the first slot (42), one end of the limiting rod (82) is fixedly connected to the cube satellite shell (1), one side of the first plug block (41) is provided with a limiting slot (81), and the limiting rod (82) is movably inserted into the inner side of the limiting slot (81).

6. The rapidly assembled modular structural assembly for a space satellite according to claim 3, characterized in that: A connection groove (112) is provided on one side of the cube satellite shell (1), and an insertion rod (111) is fixedly connected to one side of the connection plate (2), and the insertion rod (111) is movably inserted into the inner side of the connection groove (112).

7. The rapidly assembled modular structural assembly for a space satellite according to claim 5, characterized in that: A threaded hole (102) is provided on one side of the connection plate (2) and the cube satellite shell (1); a connection block (101) is provided on the outside of the connection plate (2); a bolt (103) is threadedly connected to the inside of the connection block (101); and the bolt (103) is provided on the inside of the threaded hole (102).

8. The rapidly assembled modular structural assembly for a space satellite according to claim 6, characterized in that: A first filling block (91) is arranged on the inner side of the first slot (42), a second filling block (92) is arranged on the inner side of the second slot (52), and both the first filling block (91) and the second filling block (92) are connected to the cube satellite shell (1).

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