Satellite assembling method

Abstract

The invention provides a satellite assembly method. A satellite comprises but is not limited to an image acquisition part, a power supply part, a power part, a data processing part, an attitude processing part and a main bearing plate. The main force bearing plate comprises a first force bearing part and a second force bearing part, and the first force bearing part and the second force bearing part are symmetrical about the center of the main force bearing plate; the method comprises the following steps: S1, positioning an image acquisition part through a first bracket, and fixedly connecting the image acquisition part to a first bearing part; s2, arranging a power supply part on the second force bearing part and adjacent to the image acquisition part; s3, a power part is fixedly connected to the position adjacent to the output end of the image acquisition part; s4, after the power part is installed on the main force bearing plate, a data processing part is arranged adjacent to the power part; and S5, arranging the attitude processing part on the first force bearing part adjacent to the data processing part. All functional parts of the satellite are integrally arranged, so that the structure of the satellite is more compact, the overall size and weight are reduced, and the assembling efficiency of the satellite is improved.

Description

Technical Field

[0001] The present application belongs to the field of aerospace satellite technology, and specifically relates to a satellite assembly method. Background Art

[0002] Existing satellite assembly methods often adopt more traditional process flows and lack standardized and modular design concepts. This results in the assembly process, the connection between the various components is not tight enough, and the assembly steps are cumbersome and error-prone. Due to the lack of efficient assembly tools and equipment, the assembly cycle is long, making it difficult to meet the needs of rapid response and low cost. Traditional satellite assembly methods usually install various functional components in a dispersed manner, resulting in a complex overall structure of the satellite, which is difficult to maintain and upgrade. At the same time, due to the complex connection relationship between the various components, assembly errors and loose connections are prone to occur during the assembly process, affecting the stability and reliability of the satellite. In addition, traditional satellite assembly methods often require customized design and production according to specific mission requirements, resulting in high production costs and difficulty in quickly responding to market demand. At the same time, due to the high degree of customization, the satellite also faces great difficulties in subsequent maintenance and upgrades. Summary of the invention

[0003] Therefore, the technical problem to be solved by the present application is to provide a satellite assembly method, which can make the satellite structure more compact, reduce the overall volume and weight of the satellite, improve the satellite launch efficiency and reduce the launch cost by integrating the various functional components of the satellite.

[0004] In order to solve the above problems, the present application provides a satellite assembly method, wherein the satellite includes but is not limited to an image acquisition component, a power supply component, a power component, a data processing component, and an attitude processing component; the satellite also includes a main bearing plate, the main bearing plate includes a first bearing part and a second bearing part, and the first bearing part and the second bearing part are symmetrical about the center of the main bearing plate;

[0005] The method comprises: S1, positioning the image acquisition component by a first bracket and fixing the image acquisition component to the first load-bearing part;

[0006] S2, connecting the power supply component to the second force-bearing part and adjacent to the image acquisition component;

[0007] S3, fixedly connecting the power component adjacent to the output end of the image acquisition component;

[0008] S4, after the power component is installed on the main bearing plate, the data processing component is arranged on a second bearing portion adjacent to the power component;

[0009] S5. Dispose the posture processing component on the first load-bearing part adjacent to the data processing component.

[0010] Furthermore, the satellite further comprises: a communication component;

[0011] The method further includes: S6, arranging the communication component on the second load-bearing portion and adjacent to the power supply component.

[0012] Furthermore, in S1, the image acquisition component is fixedly connected in front of the first load-bearing part, and a heat insulation pad is provided on the first load-bearing part to protect the image acquisition component.

[0013] Furthermore, the power supply component includes a battery, a battery board, and a battery card;

[0014] In step S2, before the power supply component is connected to the second load-bearing part, silicone rubber is applied between batteries, between batteries and battery panels, between batteries and battery clamps, and at battery lead wires.

[0015] Furthermore, the posture processing component includes a star sensor, and the star sensor is connected to the second load-bearing part;

[0016] The attitude processing component also includes a flywheel, the flywheel integrates at least two mass blocks for balancing the satellite, and the flywheel is fixedly connected to the star sensor.

[0017] Furthermore, the method also includes: S7, installing a side panel skin of the satellite, wherein the side panel skin includes but is not limited to a first side surface, and a through hole for accommodating the image acquisition component is provided on the first side surface.

[0018] Furthermore, the satellite further includes a navigation component and a second side surface, and the second side surface is arranged opposite to the first side surface;

[0019] The method further includes: S8, installing a navigation component, wherein the navigation component is disposed on the first side surface and adjacent to the through hole.

[0020] Furthermore, the method further comprises: S01, positioning the image acquisition component by a first bracket and fixing the image acquisition component in front of the first force-bearing part, and installing a second micro-touch switch on the first force-bearing part;

[0021] The second micro-touch switch is arranged between the image acquisition component and the communication component.

[0022] Furthermore, the method further comprises: S9, installing a separation switch pressure plate on the first side surface;

[0023] The separation switch pressing plate is cooperatively connected with the second micro-touch switch.

[0024] Furthermore, the satellite further comprises: a secondary bearing plate, wherein the secondary bearing plate is arranged in parallel with the main bearing plate, and the secondary bearing plate is fixedly connected to the main bearing plate via at least two vertically arranged connecting components.

[0025] Beneficial Effects

[0026] The satellite assembly method provided in the embodiment of the present invention integrates the various functional parts of the satellite to make the structure of the satellite more compact, reduce the overall volume and weight of the satellite, thereby improving the launch efficiency of the satellite and reducing the launch cost. The present invention provides a detailed assembly method and process flow chart, clarifies key information such as required materials and tightening torque, makes the assembly process more standardized and simplified, and reduces the difficulty and error rate of assembly.

[0027] In addition, the present application effectively improves the stability and attitude control capability of the satellite during in-orbit operation by precisely installing components such as flywheels and mass blocks, ensuring that the satellite can accurately complete the intended mission. The present invention ensures that the connection between the various components of the satellite is firm and reliable by using high-quality materials and strict assembly processes, improves the reliability and durability of the satellite, and extends the service life of the satellite. The assembly method is suitable for different types of micro-satellites, has high flexibility and adaptability, and can be customized and optimized according to specific mission requirements.

[0028] Since the satellite of the present application adopts a standardized and modular assembly method, the satellite is more convenient and quick to maintain, which reduces the maintenance cost and time. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 A flowchart of a method for assembling a satellite according to an embodiment of the present application;

[0030] Figure 2 A schematic diagram of the three-dimensional structure of a satellite structure according to an embodiment of the present application;

[0031] Figure 3 This is another schematic diagram of the satellite structure of an embodiment of the present application;

[0032] Figure 4 This is another schematic diagram of the satellite structure of an embodiment of the present application;

[0033] Figure 5 This is a schematic structural diagram of the side panel skin of the satellite structure of an embodiment of the present application.

[0034] The reference numerals are as follows: 1. image acquisition component, 11. first bracket, 12. second bracket, 2. power supply component, 3. power component, 4. data processing component, 5. attitude processing component, 51. star sensor, 512. mounting plate, 52. flywheel, 521. mass block, 53. separation switch assembly, 531. first micro-touch switch, 6. main load-bearing plate, 61. first load-bearing part, 611. second micro-touch switch, 62. second load-bearing part, 7. communication component, 8. navigation component, 9. side panel skin, 91. first side surface, 911. through hole, 912. separation switch pressure plate, 913. X-band conical spiral antenna, 92. second side surface; 10. secondary load-bearing plate. DETAILED DESCRIPTION

[0035] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0036] In addition, 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. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0037] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like 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 mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0038] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0039] See also Figures 1 to 5As shown, according to an embodiment of the present application, a satellite assembly method is provided, wherein the satellite includes but is not limited to an image acquisition component 1, a power supply component 2, a power component 3, a data processing component 4, and an attitude processing component 5; the satellite also includes a main load-bearing plate 6, wherein the main load-bearing plate 6 includes a first load-bearing part 61 and a second load-bearing part 62, wherein the first load-bearing part 61 and the second load-bearing part 62 are symmetrical about the center of the main load-bearing plate, and specifically, the first load-bearing part 61 and the second load-bearing part 62 are symmetrically distributed with the transverse center axis of the main load-bearing plate as the symmetry axis.

[0040] In a feasible embodiment, the method includes: S1, providing a heat insulation pad on the first load-bearing part 61 to protect the image acquisition component 1, positioning the image acquisition component 1 through the first bracket 11 and fixing the image acquisition component 1 to the first load-bearing part 61. Specifically, the first bracket 11 is vertically fixedly connected to the main load-bearing plate 6 using a 0.7Nm tightening torque and a M2.5*8 specification plum pan head screw, the image acquisition component 1 includes a camera, and the inner side of the main load-bearing plate 6 uses a 2.2Nm tightening torque and a M4*14*5 plum pan head screw to achieve a fixed connection between the camera and the first load-bearing part 61, and the outer side of the main load-bearing plate 6 uses a 2.2Nm tightening torque and a plum countersunk screw M4*14*2 to achieve a fixed connection between the camera and the first load-bearing part 61.

[0041] S2, connecting the power supply component 2 to the second force-bearing portion 62 and adjacent to the image acquisition component 1;

[0042] S3, at a position adjacent to the output end of the image acquisition component 1, the power component 3 is fixedly connected to the first load-bearing part 61 by a M4*10 plum countersunk screw with a tightening torque of 2.2 Nm;

[0043] S4, after the power component 3 is installed on the first load-bearing part 61, the second load-bearing part 62 adjacent to the power component 3 is provided with the data processing component 4 for receiving and processing the data from the image acquisition component 1 and other sensors. Specifically, the data processing component 4 is fixedly connected to the first load-bearing part 61 using M3*12 plum countersunk screws with a tightening torque of 1Nm;

[0044] S5. Dispose the posture processing component 5 on the first load-bearing part 61 adjacent to the data processing component 4.

[0045] In the present embodiment, the data processing component 4 integrates an onboard computer (OBC), which has a fine and stable structure. Specifically, the onboard computer is mainly composed of an OBC mounting box. To ensure a close fit between the components, M2.5×6 plum countersunk screws are used inside the OBC mounting box to fix the IOBC final version to the IOBC skin. Subsequently, M3×8 plum countersunk screws are used to fix the OBC mounting box to its cover with a tightening torque of 1Nm, further enhancing the stability and reliability of the structure. In addition, in order to optimize thermal management, a thermal pad is provided at the contact interface between the bottom of the OBC mounting box and the second load-bearing part 62. This design of the present application not only promotes the effective conduction of heat, but also improves the thermal efficiency and operating stability of the entire system, ensuring the efficient and continuous operation of the onboard computer in a complex space environment.

[0046] In this embodiment, the satellite further includes: a communication component 7 , and the method further includes: S6 , arranging the communication component 7 on the second load-bearing portion 62 and adjacent to the power supply component 2 .

[0047] In this embodiment, the power supply component 2 is a multi-layer structure, including: a battery panel 22, a battery clamp 23; in step S2, the connection of the power supply component 2 also includes applying silicone rubber between batteries, between batteries and battery panels, between batteries and battery clamps, and at the battery lead-out wires before the second load-bearing part 62. Among them, the connection method of the power supply component 2 specifically includes: S1, by using plum countersunk screws M3*8 to connect the double-pass stud structure of model M3 with each layer of battery panel 22, the tightening torque is 1N. Multiple batteries 21 are arranged in parallel on each layer of battery panel 22, S2, after each battery 21 is connected to each layer of battery panel 22, a balance board is placed on the double-pass stud respectively to observe whether there is a gap between the main control board and the balance board. S3. If there is a gap between the main control board and the balance board, it is necessary to install an M3 flat washer between the battery panel 22 and the balance board, and use M3*8 countersunk screws to secure them. The tightening torque is 1Nm. The specific number of flat washers needs to be selected according to the gap between the double-pass studs and the battery cover. To avoid the risk of short circuit, do not let them fall onto the circuit board. S4. Side panels are set vertically around the battery panel to fix the batteries, battery panels and other parts inside the enclosed area. In the present application, after the power supply component 2 is integrated into a module, the connection points and wiring complexity between the power supply component 2 and other components can be greatly reduced during the satellite assembly process, thereby simplifying the assembly process and improving assembly efficiency.

[0048] In a feasible embodiment, the posture processing component 5 includes a precise star sensor 51 and an efficient flywheel 52. The star sensor 51 is fixedly connected to the first load-bearing part 61 by using a M2.5*8 plum countersunk screw with a tightening torque of 0.7Nm, and the separation switch assembly 53 is firmly connected to the mounting plate 512 of the star sensor 51 by using a sturdy plum countersunk screw M28. Furthermore, in order to ensure the reliability of the connection, a tightening torque of 0.7Nm is used to tightly fix the star sensor 51 to the mounting plate of the star sensor 51 by using a plum pan head screw M2.56. Such a design not only enhances the stability of the structure, but also improves the working accuracy of the sensor. In this application, the flywheel 52 is used as a key element for posture adjustment. A plum countersunk screw with a model of M3*10 is used with a tightening torque of 1Nm to fix the flywheel to the first load-bearing part 61. Specifically, at least two, in this embodiment, four mass blocks 521 are integrated inside the flywheel 52. These mass blocks are evenly distributed on each surface of the flywheel housing composed of four hexagonal surfaces, with the center of the flywheel housing as a symmetrical point. Each mass block is a cylinder of the same volume and weight. Such a layout not only helps to achieve the dynamic balance of the satellite, but also can accurately control the attitude of the satellite by adjusting the motion state of the mass block when necessary, thereby improving the stability and pointing accuracy of the satellite.

[0049] In the present application, the design of integrating the flywheel housing with the mass block not only simplifies the structure of the satellite's attitude control system, reduces the assembly errors between components, but also improves the overall rigidity and stability of the system. In addition, by effectively connecting the separation switch assembly 53 with the star sensor 51, not only the rapid response capability of the satellite under specific tasks is ensured, but also the data transmission path between the sensor and the control system is optimized, signal interference is reduced, and the accuracy and efficiency of attitude control are improved.

[0050] In this embodiment, the disconnect switch assembly 53 is composed of a plurality of precision parts, specifically including: a disconnect switch cap, a spring with a specification of 0.3320, a mounting frame, a disconnect switch pin shaft rod, an M1.6*4 countersunk screw, a nut and a flat washer of corresponding specifications, a travel switch adapter plate, and a first micro-touch switch 531. The detailed assembly steps of the disconnect switch assembly include: S1, preliminary assembly of the pin shaft and the spring: First, pass one end of the disconnect switch pin shaft rod through the preset through hole on the mounting frame, and connect a spring with a specification of 0.3320 in series at this end. This step ensures that the spring can correctly act on the pin shaft and provide the necessary elastic force for the subsequent switch action. S2, install the disconnect switch cap: Then, insert the disconnect switch cap on the end of the pin shaft rod that has passed the spring. To ensure the compactness and stability of the assembly, the length of this end of the disconnect switch pin shaft rod is designed to be no longer than the length of the disconnect switch cap. S3, fix the travel switch adapter plate: Use an M1.6*4 countersunk screw, a matching nut and a flat washer to firmly install the travel switch adapter plate on the mounting frame. During this installation process, preferably, adjust the position of the contact piece of the micro-touch switch so that it is precisely aligned with the separation switch pin to ensure the accuracy of the switch action. S4. Connect the first micro-touch switch 531: Then, fix the micro-touch switch to the travel switch adapter plate through appropriate screws and nuts to complete the electrical connection part and ensure the reliable transmission of the switch signal. S5. Finally, in order to enhance the stability of the component, evenly apply 704 silicone rubber on the surface of the installed pan head nut and nut. This step not only improves the durability of the component, but also provides a guarantee for its stable operation in harsh environments.

[0051] In a feasible implementation, the satellite further includes: a communication component 7; the communication component is arranged on the second load-bearing part 62, and is adjacent to the image acquisition component 1 and the power supply component 2 respectively; the communication component 7 includes a measurement and control digital transmission component, and the detailed assembly steps of the measurement and control digital transmission component include: S1. In an optimized implementation, the communication component 7 of the satellite is cleverly arranged on the second load-bearing part 62, and is adjacent to the image acquisition component 1 and the power supply component 2, which not only optimizes the space utilization, but also promotes the coordinated work between the components. The detailed assembly steps include: S1. Preliminary fixation of the measurement and control digital transmission component: First, at the bottom of the measurement and control digital transmission, a plum pan head screw M3*6 is used for preliminary fixation. In this step, the screwing in of the screw does not require the application of glue, nor does it require the setting of a specific tightening torque, in order to achieve the preliminary positioning and stability of the component. S2. Install the stud and apply thread glue: Install the stud for the measurement and control digital transmission component. In this process, apply a proper amount of thread glue on the threaded part of the stud to enhance the firmness and sealing of the connection. At the same time, monitor the amount of glue used to avoid excessive overflow. The installation of the studs must be based on the principle that they cannot be turned manually to ensure the stability of the connection. S3. Install aluminum alloy columns: To further enhance the structural stability and heat dissipation performance of the measurement and control digital transmission components, 10mm aluminum alloy columns are installed on the two corners of the first side. At the same time, 6mm aluminum alloy columns are installed at the opposite diagonal positions to achieve structural balance and stability. S4. Add flat washers to enhance the connection: To further optimize the contact and stability between the measurement and control digital transmission components and the mounting structure, 2 0.5mm thick flat washers are placed on the 10mm aluminum alloy columns, and 1 0.5mm thick flat washers are placed on the 6mm aluminum alloy columns. The flat washers not only enhance the contact area between components, but also reduce friction and wear during assembly, thereby extending the service life of the components. S5. Install the M3*14 copper column, apply thread locking glue on the top of the M3*85 stud, and use tools to tighten it here; S6. Install the magnetic bar lift, install a magnetic bar on the upper and lower sides of the magnetic bar mounting plate, and use the hexagon socket head screw M2.5*8 with nuts to fix it, tightening torque; 0.7Nm; place the magnetic bar mounting plate on the M3*14 copper column, and install the M3*18 double-pass structure on the top; S7. Remove the 4 plum blossom pan head screws M3*6 installed in S1.

[0052] In this embodiment, the method further includes: S7, installing the side panel skin 9 and the navigation component 8 of the satellite. Specifically, a tightening torque of 0.7 Nm is used at the first screw hole of the side panel skin 9, and a M2.5*5 type plum pan head screw is used to fix it to other side panel skins, and a tightening torque of 0.7 Nm is used at the screw holes of the remaining parts to fix it to other side panel skins. The side panel skin 9 includes but is not limited to a first side surface 91, and a through hole 911 for accommodating the image acquisition component 1 is provided on the first side surface 91. The navigation component is arranged inside the first side surface 91. Furthermore, the navigation component 9 includes a GPS Taimin, and the detailed assembly steps include: S1, installing the Xunlian GPS, using a plum pan head screw M3*8 to fix it, with a tightening torque of 1Nm, to fix the Xunlian GPS to the first side of the second bracket 12; S2, installing the X-band oscillator antenna, using a plum pan head screw M2.5*5 to fix it, with a tightening torque of 0.7Nm, to fix the Xunlian GPS to the second side of the second bracket; S3, installing the Taimin, using a plum pan head screw M2.5*6 to fix it, with a tightening torque of 0.7Nm.

[0053] In a feasible implementation manner, the satellite further includes a navigation component 8 and a second side surface 92 . The navigation component 8 is disposed on the first side surface 91 and is adjacent to the through hole 911 . The second side surface 92 is disposed opposite to the first side surface 91 .

[0054] In a feasible embodiment, the method also includes: S01, positioning the image acquisition component 1 through the first bracket 11 and fixing the image acquisition component 1 in front of the first force-bearing part 61, and installing a micro-touch switch 611 on the first force-bearing part 61; the micro-touch switch 611 is arranged between the image acquisition component 1 and the communication component 7.

[0055] In this embodiment, the method further includes: installing a separation switch pressing plate 912 on the first side surface 91 ; and the separation switch pressing plate 912 is cooperatively connected with the second micro-touch switch 611 .

[0056] In this embodiment, the satellite further includes: a secondary bearing plate 10, wherein the secondary bearing plate 10 is arranged parallel to the main bearing plate 6, and the secondary bearing plate 10 is fixedly connected to the main bearing plate 6 by at least two vertically arranged connecting components.

[0057] In a feasible embodiment, the satellite also includes an X-band conical spiral antenna 913 for data transmission and communication, which is arranged on the first side 91.

[0058] It is easy for those skilled in the art to understand that, under the premise of no conflict, the above-mentioned advantageous methods can be freely combined and superimposed.

[0059] The above are only preferred embodiments of the present application and are not intended to limit the present application. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present application shall be included in the protection scope of the present application. The above are only preferred implementations of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and variations can be made without departing from the technical principles of the present application, and these improvements and variations should also be regarded as the protection scope of the present application.

Claims

1. A satellite assembly method, characterized in that: The satellite includes, but is not limited to, an image acquisition component (1), a power supply component (2), a power component (3), a data processing component (4), and an attitude processing component (5); the satellite also includes a main load-bearing plate (6), the main load-bearing plate (6) includes a first load-bearing portion (61) and a second load-bearing portion (62), the first load-bearing portion (61) and the second load-bearing portion (62) are symmetrical about the center of the main load-bearing plate; The method comprises: S1, positioning the image acquisition component (1) by means of a first bracket (11) and fixing the image acquisition component (1) to the first load-bearing part (61); S2, connecting the power supply component (2) to the second force-bearing portion (62) and adjacent to the image acquisition component (1); S3, fixedly connecting the power component (3) adjacent to the output end of the image acquisition component (1); S4, after the power component (3) is installed on the main bearing plate (6), the data processing component (4) is arranged on a second bearing portion (62) adjacent to the power component (3); S5. Dispose the posture processing component (5) on the first load-bearing part (61) adjacent to the data processing component (4).

2. A satellite assembly method according to claim 1, characterized in that: The satellite further comprises: a communication component (7); The method further comprises: S6, arranging the communication component (7) on the second load-bearing portion (62) and adjacent to the power supply component (2).

3. A satellite assembly method according to claim 2, characterized in that: In S1, the image acquisition component (1) is fixedly connected in front of the first force-bearing part (61), and a heat insulation pad is provided on the first force-bearing part (61) to protect the image acquisition component (1).

4. A satellite assembly method according to claim 3, characterized in that: The power supply component (2) comprises a battery, a battery board, and a battery card; In step S2, before the power supply component is connected to the second load-bearing part (62), silicone rubber is also applied between batteries, between batteries and battery panels, between batteries and battery clamps, and between batteries and lead wires.

5. A satellite assembly method according to claim 1, characterized in that: The posture processing component (5) comprises a star sensor (51), and the star sensor (51) is connected to the second load-bearing part (62); The attitude processing component (5) further comprises a flywheel (52), wherein the flywheel (52) integrates at least two mass blocks (521) for balancing the satellite, and the flywheel (52) is fixedly connected to the star sensor (51).

6. A satellite assembly method according to claim 1, characterized in that: The method further comprises: S7, installing a side panel skin (9) of the satellite, wherein the side panel skin (9) includes but is not limited to a first side surface (91), and a through hole (911) for accommodating the image acquisition component (1) is provided on the first side surface (91).

7. A satellite assembly method according to claim 6, characterized in that: The satellite further comprises a navigation component (8) and a second side surface (92), wherein the second side surface (92) is arranged opposite to the first side surface (91); The method further comprises: S8, installing a navigation component (8), wherein the navigation component (8) is arranged on the first side surface (91) and is adjacent to the through hole (911).

8. A satellite assembly method according to claim 7, characterized in that: The method further comprises: S01, positioning the image acquisition component (1) by means of a first bracket (11) and fixing the image acquisition component (1) in front of the first force-bearing part (61), and installing a second micro-touch switch (611) on the first force-bearing part (61); The second micro-touch switch (611) is arranged between the image acquisition component (1) and the communication component (7).

9. A satellite assembly method according to claim 8, characterized in that: The method further comprises: S9, installing a separation switch pressure plate (912) on the first side surface (91); The separation switch pressing plate (912) is cooperatively connected with the second micro-touch switch (611).

10. A satellite assembly method according to any one of claims 1 to 9, characterized in that: The satellite further comprises: a secondary bearing plate (10), wherein the secondary bearing plate (10) is arranged in parallel with the main bearing plate (6), and the secondary bearing plate (10) is fixedly connected to the main bearing plate (6) via at least two vertically arranged connecting components.

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