A microsatellite configuration and assembly method suitable for mass production

Abstract

This invention discloses a microsatellite configuration and assembly method suitable for mass production, belonging to the field of spacecraft technology. The microsatellite configuration includes: a satellite body; a satellite base plate module mounted on the bottom of the satellite body; a satellite electronics module mounted and connected to the rear of the satellite body; satellite Y-plates mounted on both sides of the satellite body, with the Y-plates fixedly connected to the sides of the satellite electronics module; a satellite X-plate mounted and connected to the front of the satellite body; and solar panels connected to both sides of the Y-plates. This invention adopts a modular design, dividing the satellite into two parts: an electronics module and a base plate module. This allows for parallel satellite assembly, reducing overall operation time, improving satellite maintainability, and simplifying operation.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, and in particular to a microsatellite configuration and assembly method suitable for mass production. Background Technology

[0002] Currently, most microsatellite designs require a strict assembly sequence for each component, resulting in a long assembly chain and extended assembly time. Furthermore, repairs require disassembling the components in reverse order, leading to lengthy and complex repair processes. Additionally, manual assembly during module docking reduces assembly safety. Therefore, a new microsatellite configuration that enables rapid assembly while maintaining high safety standards is needed. Summary of the Invention

[0003] The purpose of this invention is to solve the technical problems existing in the prior art by providing a novel microsatellite configuration and assembly method that is suitable for rapid mass production and high safety requirements.

[0004] To achieve the above objectives, the present invention first provides a microsatellite configuration suitable for mass production, the specific technical solution of which is as follows:

[0005] A microsatellite configuration suitable for mass production includes:

[0006] The satellite body has a satellite base plate module installed at its bottom, a satellite electronics module installed and connected to the rear side of the satellite body, satellite Y-plates installed on both sides of the satellite body, and the satellite Y-plates are respectively connected and fixed to the sides of the satellite electronics module; a satellite X-plate is installed and connected to the front side of the satellite body.

[0007] Solar panels are connected to both sides of the satellite's Y-plate.

[0008] In addition, the present invention provides an assembly method for a microsatellite configuration suitable for mass production. This assembly method employs a gantry-type assembly fixture, which includes a satellite base plate module fixture and a satellite electronics module fixture. The satellite base plate module fixture includes a crossbeam, rollers, a pair of handwheel adjustment assemblies, and a pair of support columns. The two ends of the crossbeam are fixedly connected to the support columns to form a U-shaped fixture frame. The pair of handwheel adjustment assemblies are arranged opposite to each other and connected to the support columns for adjusting and fixing the position of the satellite base plate module. Rollers are installed below each support column. The satellite electronics module fixture has the same structure as the satellite base plate module fixture and is used to adjust and fix the position of the satellite electronics module.

[0009] Each of the handwheel adjustment components includes: a bearing housing, a bearing, a crossbar, a handwheel, a nut, and a U-shaped connecting frame. The bearing housing is fixedly connected to the support column and has a bearing inside. The crossbar passes through the bearing and cooperates with it. Each end of the crossbar has a threaded section. The outer side of the crossbar is threadedly connected to the handwheel, and the inner side of the crossbar is threadedly connected to the U-shaped connecting frame and fixed in position by the nut.

[0010] The U-shaped connecting frame has multiple mounting holes for fixed connection with the satellite base plate module; the assembly method is as follows:

[0011] Step 1: Using satellite baseplate module tooling and satellite electronics module tooling, perform the individual assembly work on the satellite body, satellite baseplate module, and satellite electronics module. After the assembly work is completed, pre-install the satellite body and satellite baseplate module.

[0012] Step 2: Adjust the U-shaped connecting frame in the satellite base plate module tooling to a horizontal state, then place the satellite body and the satellite base plate module after installation on the U-shaped connecting frame, and fix the satellite base plate module on the U-shaped connecting frame through the mounting holes and screws;

[0013] Step 3: Adjust the U-shaped connecting bracket in the satellite electronics module fixture to a vertical position, and fix it to the side of the satellite electronics module through the mounting holes and screws;

[0014] Step 4: Push the satellite baseboard module fixture or satellite electronics module fixture closer together and adjust their relative positions to meet the final assembly requirements. Connect the satellite electronics module and the satellite baseboard module.

[0015] Step 5: Disassemble the connection between the satellite electronics module tooling and the electronics module, and complete the assembly of the satellite Y-board, satellite X-board and solar array.

[0016] Furthermore, the inner side of the handwheel contacts the bearing seat and generates friction, which is used to lock the rotation angle of the crossbar.

[0017] Beneficial effects of the present invention

[0018] Compared with existing technologies, this invention firstly adopts a modular design, dividing the satellite into two parts: an electronics module and a base plate module. This allows the satellite assembly chain to proceed in parallel, reducing overall operation time, improving satellite maintainability, and simplifying operation.

[0019] Secondly, the use of gantry-type assembly fixtures provides excellent openness, which facilitates assembly operations. The flip-over function allows for operation on all sides of the satellite, and the movable function makes site utilization more convenient. The docking of modules after flipping makes the satellite assembly work efficient and safe. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the microsatellite configuration provided by the present invention;

[0021] Figure 2 Exploded view of the microsatellite configuration provided for this invention;

[0022] Figure 3 This is a schematic diagram of the satellite base plate module tooling structure provided by the present invention;

[0023] Figure 4 A schematic diagram illustrating the preparation for satellite module docking provided by this invention;

[0024] Figure 5 This invention provides a schematic diagram of the satellite module docking process.

[0025] Figure 6 A diagram showing the completed docking of the satellite module provided by this invention;

[0026] Figure 7 A schematic diagram of the handwheel adjustment assembly provided by the present invention;

[0027] Figure 8 Detailed diagram of the connection between the satellite base plate module tooling and the U-shaped connecting frame provided for this invention;

[0028] Figure 9 Detailed diagram of the connection between the satellite electronics module tooling and the U-shaped connector provided for this invention.

[0029] In the picture,

[0030] 1. Satellite body; 2. Satellite base plate module; 3. Satellite electronics module; 4. Satellite module docking preparation; 5. Satellite Y-plate; 6. Solar array; 7. Satellite base plate module tooling; 8. Satellite electronics module tooling;

[0031] 71. Crossbeam; 72. Support column; 73. Roller; 74. Handwheel adjustment assembly;

[0032] 741. Bearing housing; 742. Bearing; 743. Crossbar; 744. Handwheel; 745. Nut; 746. U-shaped connecting bracket. Detailed Implementation

[0033] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings.

[0034] It should be noted that the terms "front side", "rear side", etc. used herein indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the purpose of describing the invention and simplifying the description. Similar expressions are only for illustrative purposes and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the invention.

[0035] See Figure 1-9 ;

[0036] First, the present invention provides a microsatellite configuration suitable for mass production, the microsatellite configuration comprising:

[0037] The satellite body 1 has a satellite base plate module 2 installed at its bottom, a satellite electronics module 3 installed and connected to the rear side of the satellite body 1, and satellite Y-plates 5 installed on both sides of the satellite body 1, which are respectively connected and fixed to the sides of the satellite electronics module 3; a satellite X-plate 4 is installed and connected to the front side of the satellite body 1.

[0038] The satellite Y-plate 5 has solar panels 6 connected to both sides.

[0039] In addition, the present invention also provides an assembly method for a microsatellite configuration suitable for mass production. This assembly method adopts a gantry-type assembly fixture, which includes a satellite base plate module fixture 7 and a satellite electronics module fixture 8. The satellite base plate module fixture 7 includes a crossbeam 71, rollers 73, a pair of handwheel adjustment components 74, and a pair of support columns 72. The two ends of the crossbeam 71 are fixedly connected to the support columns 72 to form a U-shaped fixture frame. The pair of handwheel adjustment components 74 are arranged opposite to each other and connected to the support columns 72, and are used to adjust and fix the position of the satellite base plate module 2. Rollers 73 are installed under each support column 72. The satellite electronics module fixture 8 has the same structure as the satellite base plate module fixture 7 and is used to adjust and fix the position of the satellite electronics module 3. The crossbeams 71 in the satellite base plate module fixture 7 and the satellite electronics module fixture 8 can be selected with different lengths to avoid collision and interference between the rollers 73 below them.

[0040] Each handwheel adjustment assembly 74 includes: a bearing seat 741, a bearing 742, a crossbar 743, a handwheel 744, a nut 745, and a U-shaped connecting bracket 746. The bearing seat 741 is fixedly connected to the support column 72 and has a bearing 742 inside. The crossbar 743 passes through the bearing 742 and works with it. Each end of the crossbar 743 has a thread. The outer side of the crossbar 743 is threaded to the handwheel 744, and the inner side of the crossbar 743 is threaded to the U-shaped connecting bracket 746 and fixed in position by the nut 745. Furthermore, the inner side of the handwheel 744 contacts the bearing seat 741 and generates friction to lock the rotation angle of the crossbar 743.

[0041] The U-shaped connecting bracket 746 has multiple mounting holes for fixed connection with the satellite base plate module 2; the assembly method is as follows:

[0042] Step 1: Using satellite base plate module fixture 7 and satellite electronics module fixture 8, perform the assembly work on the satellite body 1, satellite base plate module 2, and satellite electronics module 3 respectively. After the assembly work is completed, pre-install the satellite body 1 and satellite base plate module 2.

[0043] Step 2: Adjust the U-shaped connecting frame 746 in the satellite base plate module tooling 7 to a horizontal state, then place the satellite body 1 and the satellite base plate module 2 after installation on the U-shaped connecting frame 746, and fix the satellite base plate module 2 on the U-shaped connecting frame 746 through the mounting holes and screws;

[0044] Step 3: Adjust the U-shaped connecting bracket 746 in the satellite electronics module fixture 8 to a vertical position, and fix it to the side of the satellite electronics module 3 through the mounting holes and screws;

[0045] Step 4: Push the satellite base plate module fixture 7 or the satellite electronics module fixture 8 closer together and adjust their relative positions so that the relative positions of the satellite electronics module 3 and the satellite base plate module 2 meet the assembly requirements, and connect the satellite electronics module 3 and the satellite base plate module 2.

[0046] Step 5: Disassemble the connection between the satellite electronics module tooling 8 and the electronics module 3, and complete the assembly of the satellite Y-board 5, satellite X-board 4 and solar array 6.

[0047] In this invention, the horizontal direction can be finely adjusted on the crossbar 743 via the U-shaped connecting bracket 746, thereby adjusting the position of the aforementioned satellite components.

Claims

1. A method of assembling a microsatellite configuration suitable for batch production, characterized in that, The microsatellite configuration includes: The satellite body (1) has a satellite base plate module (2) installed at the bottom of the satellite body (1), a satellite electronics module (3) installed and connected to the rear side of the satellite body (1), and satellite Y-plates (5) installed on both sides of the satellite body (1). The satellite Y-plates (5) are connected and fixed to both sides of the satellite electronics module (3). A satellite X-plate (4) is installed and connected to the front side of the satellite body (1). The satellite Y-plate (5) is connected to solar panels (6) on both sides respectively; The assembly method adopts a gantry-type assembly fixture, which includes a satellite base plate module fixture (7) and a satellite electronics module fixture (8). The satellite base plate module fixture (7) includes a crossbeam (71), rollers (73), a pair of handwheel adjustment components (74), and a pair of support columns (72). The two ends of the crossbeam (71) are fixedly connected to the support columns (72) to form a U-shaped fixture frame. The pair of handwheel adjustment components (74) are arranged opposite to each other and connected to the support columns (72) to adjust and fix the position of the satellite base plate module (2). Rollers (73) are installed under each support column (72). The satellite electronics module fixture (8) has the same structure as the satellite base plate module fixture (7) and is used to adjust and fix the position of the satellite electronics module (3). Each of the handwheel adjustment components (74) includes: a bearing seat (741), a bearing (742), a crossbar (743), a handwheel (744), a nut (745), and a U-shaped connecting frame (746). The bearing seat (741) is fixedly connected to the support column (72) and has a bearing (742) inside. The crossbar (743) passes through the bearing (742) and works with it. Both ends of the crossbar (743) are provided with a thread. The outer side of the crossbar (743) is threaded to the handwheel (744), and the inner side of the crossbar (743) is threaded to the U-shaped connecting frame (746) and fixed in position by the nut (745). The U-shaped connecting frame (746) has multiple mounting holes for fixed connection with the satellite base plate module (2); the assembly method is as follows: Step 1: Using the satellite base plate module fixture (7) and the satellite electronics module fixture (8), perform the assembly work on the satellite body (1), the satellite base plate module (2), and the satellite electronics module (3). After the assembly work is completed, pre-install the satellite body (1) and the satellite base plate module (2). Step 2: Adjust the U-shaped connecting frame (746) in the satellite base plate module tooling (7) to a horizontal state, and then place the satellite body (1) and satellite base plate module (2) after installation on the U-shaped connecting frame (746), and fix the satellite base plate module (2) on the U-shaped connecting frame (746) through the mounting holes and screws; Step 3: Adjust the U-shaped connecting bracket (746) in the satellite electronics module fixture (8) to a vertical position, and fix it to the side of the satellite electronics module (3) through the mounting holes and screws; Step 4: Push the satellite base plate module fixture (7) or the satellite electronics module fixture (8) closer together and adjust their relative positions so that the relative positions of the satellite electronics module (3) and the satellite base plate module (2) meet the assembly requirements, and connect the satellite electronics module (3) and the satellite base plate module (2). Step 5: Disassemble the connection between the satellite electronics module tooling (8) and the electronics module (3) to complete the assembly of the satellite Y board (5), satellite X board (4) and solar array (6).

2. The assembly method for a microsatellite configuration suitable for mass production according to claim 1, characterized in that, The inner side of the handwheel (744) contacts the bearing seat (741) and generates friction, which is used to lock the rotation angle of the crossbar (743).

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