Cable connection system for satellite

Abstract

The utility model relates to a cable connecting system for a satellite. The cable connecting system comprises a control unit, a cabin plate and a switching device. The control unit is configured to be in communication connection with a plurality of single-machine devices through cables; the cabin plate comprises a main cabin plate and a plurality of auxiliary cabin plates, and the control unit is arranged on the main cabin plate; the plurality of auxiliary cabin plates and the main cabin plate are jointly enclosed to form a cabin; at least one stand-alone device is arranged on at least one auxiliary deck; the switching device is arranged on the main cabin plate; the switching device comprises a shell, the shell is provided with an input port and an output port, and a circuit board used for connecting the input port and the output port is arranged in the shell. Wherein the control unit is configured to be connected to the input port through a first cable; the stand-alone device on the secondary deck is configured to be connected to the output port through a second cable. According to the invention, a many-to-many complex connection form is converted into a one-to-many connection form, so that the difficulty of cable laying is reduced, and the laying efficiency and feasibility of the cable are improved.

Description

Technical Field

[0001] This disclosure relates to the field of spaceborne electronic equipment technology, and specifically to a satellite cable connection system. Background Technology

[0002] Satellite cabling is a crucial component of a satellite's overall circuitry, responsible for transmitting satellite power and signals. The reliability of the cabling directly impacts the reliability of the electrical system. Given the large number of devices on a satellite—including those for energy, orbit control, communication, monitoring, thermal control, and structure—the interconnected cabling network spans the entire satellite, making the production, installation, and protection of satellite cables challenging aspects of quality control. Simplifying the cabling network from the outset is of great significance for shortening satellite development cycles and improving quality control.

[0003] To address the optimization of cable networks, researchers have proposed cableless solutions, such as developing wireless networking protocols using TDMA and FDMA technologies to enable wireless communication between devices. Other researchers have proposed reducing the workload of cable network design and implementation through cable path optimization or automated cable network laying algorithms. However, these technologies have not been widely adopted. Cableless design still urgently needs to address the stability and reliability of signal transmission, especially in the complex space environment where interference resistance in wireless transmission is a major technical challenge. Furthermore, the research, development, manufacturing, and maintenance costs of cableless technology are high, and for some low-Earth orbit, short-life satellites, frequent replacements are necessary, resulting in low economic efficiency for cableless design. In addition, for different satellite models, cable networks are affected by factors such as unit layout, payload type, and connector type, leading to poor universality and replaceability. Existing automated cable laying algorithms struggle to account for various onboard conditions, and improving algorithms for a single specific case is too costly. Ultimately, a significant investment of manpower is still needed to perfect automated cable network laying systems.

[0004] Against this backdrop, current mainstream cable network design is still primarily driven by the designer's experience. The cable routing is designed based on the connection relationships between various units on the satellite. During the process, attention must also be paid to the independent routing of power and signal cables, cable penetration through compartments and supports, as well as various details such as interference with thermal control components and individual units, resulting in increasingly complex cable network design.

[0005] Satellites contain numerous individual units, each with multiple electrical connectors. These connectors interconnect to form a "spider web" of cables. This "many-to-many" interface connection, as the number of satellite units increases, will make the overall satellite cable network increasingly complex. On the one hand, this will increase the workload of cable network design; on the other hand, to ensure the effectiveness of cable installation, the inspection process will become extremely cumbersome. Furthermore, the operability of this "many-to-many" integrated cable during installation is limited, greatly reducing the cable laying efficiency of the personnel. In addition, the complex cable structure also poses risks such as equipment or structural interference. Utility Model Content

[0006] This disclosure provides a satellite cable connection system to address the problems existing in the prior art.

[0007] According to a first aspect of this disclosure, a satellite cable connection system is provided, comprising:

[0008] A control unit configured to communicate with multiple standalone devices via cables;

[0009] A compartment panel, comprising a main compartment panel and multiple sub-compartments, wherein the control unit is disposed on the main compartment panel; the multiple sub-compartments are configured to enclose a compartment together with the main compartment panel; and at least one single-unit device is disposed on at least one sub-compartment panel.

[0010] A transfer device is mounted on the main cabin panel; the transfer device includes a housing, an input port and an output port are provided on the housing, and a circuit board for connecting the input port and the output port is provided inside the housing;

[0011] The control unit is configured to be connected to the input port via a first cable; the stand-alone device on the sub-cabin board is configured to be connected to the output port via a second cable.

[0012] In one embodiment of this disclosure, at least one stand-alone device is provided on the main deck; the stand-alone device on the main deck is configured to be directly connected to the control unit via a third cable.

[0013] In one embodiment of this disclosure, the stand-alone device on the main deck includes a dual-wire stand-alone unit, and the third cable for connecting the dual-wire stand-alone unit to the control unit is configured as a double-bundle cable.

[0014] In one embodiment of this disclosure, different compartments are provided with stand-alone devices of the same type, and cables for connecting the stand-alone devices of the same type are configured to connect to the same output port.

[0015] In one embodiment of this disclosure, at least one of the similar stand-alone devices is disposed on the main deck and configured to be connected to the output port via a fourth cable.

[0016] In one embodiment of this disclosure, at least two stand-alone devices are provided on the same sub-cabin plate, and a docking device is also provided. The docking device is configured to be connected to the at least two stand-alone devices via a fifth cable; the output port is configured to be connected to the docking device via a second cable.

[0017] In one embodiment of this disclosure, the second cable is configured as a single-strand cable.

[0018] In one embodiment of this disclosure, the housing is provided with a plurality of input ports and a plurality of output ports, wherein the number of output ports is greater than or equal to the number of input ports.

[0019] In one embodiment of this disclosure, the bottom end of the housing is configured to extend to both sides to form mounting portions, and the adapter is configured to connect to the main compartment plate via the mounting portions.

[0020] In one embodiment of this disclosure, the housing is provided with a plurality of ports, at least some of which are selectively configured as input ports or output ports.

[0021] One beneficial effect of this disclosure is that by setting up a switching device, the control unit and the individual units on the auxiliary compartment plate do not need to be directly connected. This allows for the replanning of the cables connecting the control unit to multiple individual units, transforming the complex "many-to-many" connection into a "one-to-many" connection. This enables single-plate cable laying, allowing cable implementation on each compartment plate to proceed in parallel, thereby reducing the difficulty of cable laying and improving its efficiency and feasibility. Specifically, before merging compartments, the cables on each compartment plate can be laid separately. Then, during merging, only the second cable needs to be connected to achieve the wiring connection between compartments, greatly reducing the difficulty and time of final assembly. Statistical data from actual applications show that the satellite cable connection system of this disclosure can increase the laying efficiency to approximately three times the original level.

[0022] Other features and advantages of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0023] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments of the present disclosure and, together with their description, serve to explain the principles of the present disclosure.

[0024] Figure 1This is a diagram of a satellite cable connection system in existing technology;

[0025] Figure 2 This is a schematic diagram of a cable connection provided in an embodiment of this disclosure;

[0026] Figure 3 This is another cable connection diagram provided in one embodiment of the present disclosure;

[0027] Figure 4 This is a schematic diagram of the structure of an adapter provided in an embodiment of the present disclosure;

[0028] Figure 5 This is a rear view of an adapter provided in an embodiment of this disclosure;

[0029] Figure 6 This is a cross-sectional view of an adapter provided in an embodiment of this disclosure.

[0030] Figures 1 to 6 The one-to-one correspondence between the component names and the reference numerals in the figures is as follows:

[0031] 1. Control unit; 21. Main compartment panel; 22. Sub-compartment panel; 3. Adapter device; 31. Housing; 32. Port; 321. Input port; 322. Output port; 33. Circuit board; 34. Mounting part; 35. Through hole; 41. First cable; 42. Second cable; 43. Third cable; 44. Fourth cable; 45. Fifth cable; 51. Star sensor; 511. First star sensor; 512. Second star sensor; 521. First flywheel; 522. Second flywheel; 523. Third flywheel; 524. Fourth flywheel; 531. First magnetometer; 532. Second magnetometer; 541. First gyroscope; 542. Second gyroscope; 6. Docking device. Detailed Implementation

[0032] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the present disclosure.

[0033] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this disclosure or its application or use.

[0034] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0035] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0036] In this article, terms such as "up," "down," "front," "back," "left," and "right" are used only to indicate the relative positional relationship between related parts, rather than to define the absolute position of these related parts.

[0037] In this article, "first," "second," etc., are used only to distinguish one another, and not to indicate degree of importance, order, or prerequisite for each other.

[0038] In this document, terms such as “equal” and “same” are not strict mathematical and / or geometric limitations, but also include errors that are understandable to those skilled in the art and permissible in manufacturing or use.

[0039] refer to Figure 1 The existing satellite cable connection system includes a control unit 1 and multiple stand-alone devices. The control unit 1 is configured to communicate with the multiple stand-alone devices via cables. The stand-alone devices may include: a star sensor 51, a first flywheel 521, a second flywheel 522, a third flywheel 523, a fourth flywheel 524, a first magnetometer 531, a second magnetometer 532, a first gyroscope 541, and a second gyroscope 542. Of course, the stand-alone devices may also include other types of satellite stand-alone devices known to those skilled in the art. This disclosure does not limit the specific type of stand-alone devices.

[0040] like Figure 1 As shown, each individual unit is directly connected to the control unit 1 via cables, which makes the cables in the compartment easily intertwine, forming a very complex "spider web" type of cable. This makes installation difficult, and the messy and complex cable network can easily cause wiring errors, requiring a high level of experience from the operators. Figure 1 The cables connecting the various individual devices shown share a common connector, for example, for Figure 1 The cable bundle on the right, with the ends of Star Sensor 51, Second Gyroscope 542, First Flywheel 521, Second Flywheel 522, Third Flywheel 523, Fourth Flywheel 524, and First Gyroscope 541 sharing the same connector, is connected to Control Unit 1. This structure results in multiple cables being connected end to end, forming a complex mesh cable bundle.

[0041] Furthermore, each individual unit is actually installed on a different panel. This coupling means that only a small portion of the cable can be laid on one panel, and the remaining portion can only be completed during the final assembly stage. The laying work is carried out serially, resulting in low efficiency.

[0042] Additionally, it should be noted that Figure 1The cables shown are looped, such as the second gyroscope 542 connected to the control unit by a double-bundle cable, resulting in a loop. If new structures need to be added after the cabin is closed, the looped cables must first be cut, the loop removed, the new structures installed in the cabin, and then the cables re-welded into a loop, causing a significant amount of extra work. Therefore, when designing individual unit layouts, it is crucial to consider the feasibility of the final assembly stage, fully considering the installation sequence of structures, individual units, and cables to prevent repeated cable cutting and uncutting due to looped cables or cabin opening / closing requirements.

[0043] To solve the above problems, refer to Figure 2 and Figure 3 This disclosure provides a satellite cable connection system, which includes: a control unit 1, a panel, and an adapter 3. The control unit 1 is configured to communicate with multiple individual devices via cables. The control unit can be an SMU (System-Mounted Unit), capable of distributing power and transmitting control signals to each individual device separately.

[0044] The compartment includes a main compartment 21 and multiple sub-compartments 22. A control unit 1 is mounted on the main compartment 21, and the sub-compartments 22 are configured to enclose a compartment together with the main compartment 21. It is understood that the main compartment 21 and the sub-compartments 22 can be identical compartments. In this disclosure, the compartment on which the control unit 1 is installed is referred to as the main compartment 21, and the other compartments are referred to as sub-compartments 22. (Reference) Figure 2 and Figure 3 In one specific embodiment, the -Z panel is the main compartment panel 21, and the +X and -X panels are auxiliary compartment panels 22. It is understood that the panels are used to enclose and form compartments. In the most common box-type satellites of the prior art, there are at least six panels, which can be used to form a hexahedral (such as a cuboid or cube) compartment. In this case, one main compartment panel 21 and five auxiliary compartment panels 22 can be provided. It should be noted that, for ease of explanation, this embodiment only shows the -Z, +X, and -X panels in the figures.

[0045] refer to Figures 2 to 6 The adapter 3 is mounted on the main deck 21. The adapter 3 includes a housing 31, on which an input port 321 and an output port 322 are provided. Inside the housing 31 is a circuit board 33 for connecting the input port 321 and the output port 322. Figure 4 and Figure 5 As shown, the adapter 3 can be a cuboid structure, and its housing 31 can be made of aluminum alloy, with its surface subjected to conductive oxidation treatment. In a specific embodiment of this disclosure, the total mass of the adapter 3 is 6.2 kg. It is understood that the total mass of the adapter 3 should not be too large, thereby avoiding excessive satellite weight.

[0046] In one embodiment of this disclosure, a plurality of ports 32 may be provided on the housing 31, and at least some of the ports 32 may be selectively configured as input ports 321 or output ports 322. Before laying the wiring, the connection path can be designed according to the location of each individual device, thereby activating at least some of the ports 32 on the adapter 3. Through program settings, the multiple activated ports 32 can be respectively set as input ports 321 or output ports 322, and the input ports 321 and output ports 322 can be matched with each other.

[0047] like Figure 6 As shown, the housing 31 encloses an inner cavity, within which a circuit board 33 is disposed. Multiple circuit boards 33 can be disposed, and multiple connectors extend from the circuit boards 33 to facilitate connection with external cables. Integrated circuits are disposed on the circuit boards 33, interconnecting multiple ports 32. When any number of ports 32 are used as input ports 321 or output ports 322, the circuit board 33 can connect the input ports 321 to the corresponding output ports 322. Some cables in the satellite cable connection system are replaced by the circuit board 33. Compared to cables, the circuit board 33 has better modularity; cables that are prone to tangling can be connected to the input ports 321 before tangling occurs, and signals are transmitted to the output ports 322 closer to the corresponding individual devices via the circuit board 33, thus avoiding complex "spider web" cable patterns and greatly reducing the design difficulty of cables. Furthermore, the circuit board 33 has high integration, thereby saving some cables, improving the utilization of internal space, and providing greater space margin for satellite configuration and layout.

[0048] In one embodiment of this disclosure, reference is made to Figure 4 and Figure 5 The bottom end of the shell 31 is configured to extend to both sides to form mounting portions 34, and the adapter 3 is configured to connect to the main compartment plate 21 through the mounting portions 34. Multiple through holes 35 are provided on the mounting portions 34; for example, four through holes 35 can be spaced apart on one side of the mounting portion 34, so that the adapter 3 can be fixedly mounted to the main compartment plate 21 with screws. The two mounting portions 34 are symmetrically arranged on both sides of the bottom end of the shell 31, thereby ensuring the balance and stability of the installation.

[0049] In one embodiment of this disclosure, the input port 321 and the output port 322 are located on a side of the housing 31 that is different from the side where the mounting portion 34 is located. (See reference...) Figure 4 and Figure 5The ports 32 on the housing 31 can be located on the top and back surfaces, while the left and right sides where the mounting portion 34 is located are constructed to be covered by the housing 31. This avoids interference between the plug-in input port 321 and the output port 322 and the mounting portion 34, so that the mounting position of the adapter 3 on the main compartment plate 21 can still be easily adjusted even when the cables are plugged in.

[0050] refer to Figure 2 and Figure 3 At least one stand-alone device is provided on at least one sub-cabin plate 22. The control unit 1 is configured to be connected to an input port 321 via a first cable 41, and the stand-alone device on the sub-cabin plate 22 is configured to be connected to an output port 322 via a second cable 42. For example: Reference Figure 2 and Figure 3 At points ① and ④, two stand-alone devices, a first star sensor 511 and a second star sensor 512, are installed on the auxiliary compartment plate 22 (+X plate). The control unit 1 installed on the main compartment plate 21 (-Z plate) is connected to the input port 321 (IN-1 and / or IN-2) via the first cable 41. The signal is transmitted to the output port 322 (OUT-2) through the circuit board 33 inside the adapter device 3. The output port 322 is connected to the first star sensor 511 and the second star sensor 512 across the compartment plate via the second cable 42.

[0051] Before merging the compartments, the first star sensor 511 and the second star sensor 512 can be pre-installed on the auxiliary compartment plate 22 (+X plate), and the wiring between them, as well as the wiring between them and other single-unit devices (not shown in the figure) installed on the auxiliary compartment plate 22 (+X plate), can all be laid in advance. During merging, it is only necessary to connect the output port 322 to the first star sensor 511 and the second star sensor 512 respectively through the second cable 42 to easily realize the wiring connection between the main compartment plate 21 (-Z plate) and the auxiliary compartment plate 22 (+X plate).

[0052] In one specific embodiment of this disclosure, the second cable 42 is constructed as a single-bundle cable. This ensures that the connecting cables between the compartments are single-bundle cables, thereby preventing cable loops between the compartments. This avoids the problem of repeated cable cutting and untying caused by cable loops between compartments or the need to open and close compartments. If new structures need to be added after the compartments are closed, operators do not need to cut cables but can directly install the new structures into the compartment. Therefore, this disclosure achieves a loop-free design for the cable network between compartments.

[0053] In one embodiment of this disclosure, the housing 31 is provided with a plurality of input ports 321 and a plurality of output ports 322, wherein the number of output ports 322 is greater than or equal to the number of input ports 321. Thus, a first cable 41 containing multiple signals from individual devices can be connected to a corresponding input port 321. The multiple signals can be redistributed in the circuit board 33 to assign a single signal destined for a single device to a single output port 322. The adapter 3 can map a smaller number of input ports 321 to a larger number of output ports 322, thereby splitting the multiple signals contained in each first cable 41, thus ensuring that the signal output to the second cable 42 is a single signal destined for a specific individual device. The multiple output ports 322 can each be connected to their respective individual devices via a single bundle of second cables 42, thereby facilitating a "one-to-one" cross-panel connection during the compartment closing process, i.e., each second cable 42 corresponds to a single individual device. The individual units on the auxiliary compartment 22 and the transfer unit 3 basically only need to be connected in a "one-to-one" manner, which reduces the difficulty and time of final assembly.

[0054] This disclosure, by setting up a switching device 3, eliminates the need for direct connection between the control unit 1 and individual devices on the auxiliary compartment panel 22. This allows for the redesign of cables connecting the control unit 1 to multiple individual devices, transforming the complex "many-to-many" connection into a "one-to-many" connection. This enables single-panel cable laying, allowing parallel cable installation across different compartments, thereby reducing the difficulty of cable laying and improving its efficiency and feasibility. Specifically, before merging compartments, cables on each compartment can be laid separately. Then, during merging, only the second cable 42 needs to be connected to achieve the wiring connection between compartments, significantly reducing the difficulty and time required for final assembly. Statistical data from practical applications show that the satellite cable connection system of this disclosure can increase laying efficiency to approximately three times the original level.

[0055] In one embodiment of this disclosure, reference is made to Figure 2 and Figure 3 At least one stand-alone device is provided on the main deck 21, and the stand-alone device on the main deck 21 is configured to be directly connected to the control unit 1 via a third cable 43. For example, a first magnetometer 531 and a second magnetometer 532 are provided on the main deck 21 (-Z plate), and the control unit 1 provided on the main deck 21 (-Z plate) is located close to the first magnetometer 531 and the second magnetometer 532. Thus, the control unit 1 is configured to be directly connected to the first magnetometer 531 and the second magnetometer 532 via the third cable 43.

[0056] Understandably, during the single-panel installation before merging, all individual units on the main panel 21 are already connected to the control unit 1. This allows for cross-panel wiring connections during the merging process. The adapter 3 is primarily used for cross-panel wiring connections. Cable connections on the same panel are relatively simple and easy to implement. Therefore, individual units located on the same panel and close to the control unit 1 can be directly connected to the control unit 1 without going through the adapter 3.

[0057] Furthermore, the single-unit device on the main deck 21 includes a dual-wire single unit, and the third cable 43 used to connect the dual-wire single unit to the control unit 1 is constructed as a double-bundle cable. For example, a dual-wire single unit is provided on the main deck 21 (-Z plate): a first gyroscope 541 and a second gyroscope 542. The control unit 1, provided on the main deck 21 (-Z plate), is directly connected to the first gyroscope 541 and the second gyroscope 542 via the double-bundle third cable 43. The dual-wire connection structure will cause the third cable 43 to form a loop. However, since the first gyroscope 541, the second gyroscope 542 are close to the control unit 1, and the loop of the single board will not have much impact on other spaces in the cabin, this connection method can still maintain good feasibility and can basically avoid the problem of repeated cable cutting and untying caused by the loop of cables between the decks or the need to open and close the cabin.

[0058] It should be noted that, for example, dual-line single units such as the first gyroscope 541 and the second gyroscope 542, the problem of cable looping will inevitably be encountered when connecting cables. Therefore, it is necessary to arrange the dual-line single units on the main compartment plate 21 as much as possible, thereby ensuring that the looping only occurs on the main compartment plate 21 and avoiding the problem of cable looping between compartments. This ensures the feasibility of the satellite cable connection system.

[0059] In one embodiment of this disclosure, identical single-unit devices are installed on different compartments, and the cables for connecting the identical single-unit devices are configured to connect to the same output port 322. Thus, instead of opening multiple output ports 322 due to multiple identical single-unit devices being installed on different compartments, only a single output port 322 needs to be opened, and each output port 322 is connected to the respective identical single-unit devices via cables. This facilitates unified power distribution and signal output for the identical single-unit devices.

[0060] Furthermore, at least one of the similar stand-alone devices is mounted on the main deck panel 21 and configured to be connected to the output port 322 via a fourth cable 44. For example: Reference Figure 2 , Figure 3At points ② and ③, a first flywheel 521 and a fourth flywheel 524 are installed on the main compartment plate 21 (-Z plate), and a second flywheel 522 and a third flywheel 523 are installed on the auxiliary compartment plate 22 (-X plate). Since the four flywheels are of the same type and are single-unit devices, they need to be connected to the same output port 322 (OUT-1). This output port 322 (OUT-1) is connected to the first flywheel 521 and the fourth flywheel 524 on the same compartment plate via a fourth cable 44, and is connected to the second flywheel 522 and the third flywheel 523 across compartment plates via a second cable 42. It should be noted that the first flywheel 521 and the fourth flywheel 524 are located on the main compartment plate 21 (-Z plate) at a relatively far distance from the control unit 1, making direct connection to the control unit 1 inconvenient. Connecting them via the adapter device 3 is more advantageous for the wiring design.

[0061] In one embodiment of this disclosure, at least two stand-alone devices are provided on the same auxiliary compartment plate 22, and a docking device 6 is also provided; the docking device 6 is configured to connect to the at least two stand-alone devices via a fifth cable 45, and an output port 322 is configured to connect to the docking device 6 via a second cable 42, wherein the docking device 6 may specifically be an adapter. For example: Reference Figure 2 , Figure 3 At points ② and ⑤, two single-unit devices, a second flywheel 522 and a third flywheel 523, are installed on the auxiliary compartment plate 22 (-X plate), and a docking device 6 is installed on the auxiliary compartment plate 22 (-X plate) near the main compartment plate 21 (-Z plate). Before the compartments are closed, the second flywheel 522 and the third flywheel 523 are connected to the docking device 6 through the fifth cable 45, thereby completing the single-plate laying of the auxiliary compartment plate 22 (-X plate). Then, during the compartment closure process, the output port 322 (OUT-1) is connected to the docking device 6 across the compartment plate through the second cable 42.

[0062] As can be seen, by setting up the docking device 6, it is convenient to lay the single panels in advance before the module merging, thus making the subsequent module merging work simpler. The laying of each single panel can be carried out simultaneously, thereby improving the laying efficiency. During module merging, the staff only needs to connect the second cable 42 from the output port 322 to the docking device 6 on each sub-module panel 22, which further simplifies the module merging steps, greatly speeds up the laying progress of the entire satellite cable system, reduces the time ratio of cable implementation during AIT assembly, and shortens the overall project duration of the assembly process.

[0063] The various embodiments of this disclosure have been described above. These descriptions are exemplary and not exhaustive, and are not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein. The scope of this disclosure is defined by the appended claims.

Claims

1. A satellite cable connection system, characterized in that, include: Control unit (1), the control unit (1) is configured to communicate with multiple stand-alone devices via cables; The compartment includes a main compartment (21) and multiple sub-compartments (22), and the control unit (1) is disposed on the main compartment (21); The multiple sub-cabin panels (22) are configured to enclose a compartment together with the main cabin panel (21); At least one single-unit device is provided on at least one auxiliary compartment plate (22); A transfer device (3) is provided on the main cabin plate (21); The adapter (3) includes a housing (31), on which an input port (321) and an output port (322) are provided, and a circuit board (33) for connecting the input port (321) and the output port (322) is provided inside the housing (31). The control unit (1) is configured to be connected to the input port (321) via a first cable (41); the stand-alone device on the sub-cabin plate (22) is configured to be connected to the output port (322) via a second cable (42).

2. The satellite cable connection system according to claim 1, characterized in that, At least one stand-alone device is provided on the main deck panel (21); the stand-alone device on the main deck panel (21) is configured to be directly connected to the control unit (1) via a third cable (43).

3. The satellite cable connection system according to claim 2, characterized in that, The stand-alone device on the main cabin panel (21) includes a dual-line stand-alone unit, and the third cable (43) for connecting the dual-line stand-alone unit to the control unit (1) is configured as a double-bundle cable.

4. The satellite cable connection system according to claim 1, characterized in that, Different compartments are equipped with the same type of stand-alone devices, and the cables for connecting the same type of stand-alone devices are configured to connect to the same output port (322).

5. The satellite cable connection system according to claim 4, characterized in that, At least one of the single-unit devices of the same type is disposed on the main compartment plate (21) and is configured to be connected to the output port (322) via a fourth cable (44).

6. The satellite cable connection system according to claim 1, characterized in that, At least two stand-alone devices are provided on the same sub-cabin plate (22), and a docking device (6) is also provided, the docking device (6) being configured to be connected to the at least two stand-alone devices via a fifth cable (45); the output port (322) is configured to be connected to the docking device (6) via a second cable (42).

7. The satellite cable connection system according to any one of claims 1 to 6, characterized in that, The second cable (42) is constructed as a single-strand cable.

8. The satellite cable connection system according to claim 1, characterized in that, The housing (31) is provided with a plurality of input ports (321) and a plurality of output ports (322), wherein the number of output ports (322) is greater than or equal to the number of input ports (321).

9. The satellite cable connection system according to claim 1, characterized in that, The bottom end of the shell (31) is configured to extend to both sides to form a mounting portion (34), and the adapter (3) is configured to be connected to the main compartment plate (21) through the mounting portion (34).

10. The satellite cable connection system according to claim 1, characterized in that, The housing is provided with a plurality of ports (32), at least some of which are optionally configured as input ports (321) or output ports (322).

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