Satellite cable-laying operations platform

Abstract

A satellite cable laying operation platform relates to the technical field of satellite manufacturing, comprising: a platform body, including a bottom plate, two first side plates, two second side plates, a plurality of partition plates, a plurality of quick-release positioning blocks, and a middle beam, the bottom plate is rectangular, the two first side plates can rotate around the two short sides of the bottom plate respectively, the two second side plates can rotate around the two long sides of the bottom plate respectively, the plurality of partition plates are installed on the top of the bottom plate, the quick-release positioning block is used to position the first side plate and the bottom plate when the first side plate is perpendicular to the bottom plate, and the middle beam is used to be arranged on the first side plate and the partition plate; a plurality of electrical interface analogs are installed on the platform body and are used for laying cables. By simulating the satellite cabin environment and performing cable laying work, the wiring work in the satellite AIT link can be moved forward, the reliability of the whole satellite cable network space layout can be verified in advance, the laid cable network can be directly used in the satellite AIT link in the form of components, the satellite production efficiency is improved, and the satellite manufacturing period is shortened.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite manufacturing, in particular to a satellite cable laying operation platform. BACKGROUND

[0002] Satellites face technical challenges in the assembly process due to the compact internal space and dense equipment. The complex structural layout puts higher requirements on cable path planning. Limited by the narrow wiring space, the cable needs to meet the electrical connection requirements of multiple devices while avoiding physical interference with precision instruments and structural components, which forms a double constraint on the optimization design and dynamic avoidance capability of the cable layout in three-dimensional space.

[0003] In the traditional manufacturing process, mechanical installation and electrical connection procedures are highly coupled, and the two need to be alternately implemented in the AIT (Assemble, Integrate, and Test) stage. Although most of the cables are in the form of finished wire harnesses, some cables still need to be welded or crimped on site, resulting in a scattered, discontinuous, and non-standardized process. Moreover, multiple workers need to frequently switch between different work modes to meet the requirements of different procedures, which not only increases the complexity of on-site management, but also requires a lot of process layout and procedure arrangement work. These factors will prolong the satellite manufacturing cycle and restrict the mass production of satellites. SUMMARY

[0004] Therefore, the purpose of the present application is to provide a satellite cable laying operation platform to solve at least one of the above technical problems.

[0005] The present application provides a satellite cable laying operation platform, comprising: a platform main body, including a bottom plate, two first side plates, two second side plates, a plurality of partition plates, a plurality of quick-release positioning blocks, and a middle beam, the bottom plate is rectangular, the two first side plates are respectively arranged on the two short sides of the bottom plate and are rotatably connected with the bottom plate, and can rotate around the corresponding short side of the bottom plate, the two second side plates are respectively arranged on the two long sides of the bottom plate and are rotatably connected with the bottom plate, and can rotate around the corresponding long side of the bottom plate, the plurality of partition plates are installed on the upper surface of the bottom plate in the long side extension direction of the bottom plate, the quick-release positioning block is used to position the first side plate and the bottom plate when the first side plate is perpendicular to the bottom plate, and the middle beam is used to span the first side plate and the partition plate and limit the deformation of the first side plate and the partition plate; a plurality of electrical interface simulators are installed on the bottom plate, the two first side plates, the two second side plates, the plurality of partition plates, and the middle beam, and are used to simulate the electrical interface of the satellite equipment to lay the satellite cable; wherein, when the two first side plates and the two second side plates are enclosed, the platform main body forms a satellite simulation cabin.

[0006] In some optional embodiments, the first side plate is isosceles trapezoidal, the second side plate is rectangular, and the long side of the rectangle is equal in length to the long side of the base plate, and the short side is equal in length to the leg of the first side plate.

[0007] In some optional embodiments, the short bottom edge of each first side plate is rotatably connected to the corresponding short side of the base plate via a rotating shaft, and the short bottom edge is provided with a quick-release opening for mounting a quick-release positioning block, and the base plate is correspondingly provided with a positioning hole for inserting the quick-release positioning block.

[0008] In some optional embodiments, the quick-release opening penetrates the first side plate, and the cross section of the quick-release opening is T-shaped with the lower end of the T-shape opening onto the short bottom edge of the first side plate; the cross section of the quick-release positioning block is H-shaped, and the quick-release positioning block is inserted into the corresponding T-shaped horizontal section of the quick-release opening, slides downward along the corresponding T-shaped vertical section of the quick-release opening, and then is inserted into the positioning hole to position the first side plate and the base plate.

[0009] In some optional embodiments, each second side plate is provided with a movable hinge on each of the two short sides, and the base plate is provided with a fixed hinge on each of the two short sides, and each movable hinge is rotatably connected to the corresponding fixed hinge via a hinge shaft.

[0010] In some optional embodiments, each partition plate is vertically arranged above the base plate and parallel to the short side of the base plate, and the bottom of the partition plate is detachably connected to the base plate.

[0011] In some optional embodiments, the partition plate is isosceles trapezoidal, and the short bottom edge of each partition plate is inserted into a slot formed on the base plate.

[0012] In some optional embodiments, the platform body further comprises a plurality of positioning assemblies for positioning the partition plate and the base plate, and each partition plate is provided with a positioning opening near the bottom edge for mounting the positioning assembly; the positioning assembly comprises a positioning buckle and a positioning block, the cross section of the positioning buckle is U-shaped, the positioning buckle is inserted into the positioning opening in the horizontal direction so that the two parts at the ends of the corresponding U-shape clamp the two side surfaces of the partition plate, and the positioning block is inserted into the positioning opening and abuts against the positioning buckle to prevent the positioning buckle from coming out of the positioning opening.

[0013] In some optional embodiments, the electrical interface simulation component comprises at least one of the following: an integrated electronic interface simulation component, a PCDU interface simulation component, a battery interface simulation component, a satellite-ground interface simulation component, a payload antenna interface simulation component, a star table interface simulation component, an S flywheel interface simulation component, an X flywheel interface simulation component, an SADA interface simulation component, an inter-satellite communication interface simulation component, a platform communication interface simulation component, a PPCU interface simulation component, a magnetometer interface simulation component, a thermal control interface simulation component, and a switching interface simulation component.

[0014] In some optional embodiments, further comprising: a plurality of wire harness management members installed on the bottom plate, the second side plate and the partition plate, for supporting and constraining the satellite cable.

[0015] Based on the above technical solution, the satellite cable laying operation platform provided by the application adopts the cable network modular manufacturing concept, simulates the satellite cabin environment to construct the satellite cable laying operation platform, so as to perform the cable laying work, facilitate the early verification of the reliability of the whole-satellite cable network space layout, thereby the wiring work in the satellite AIT link can be moved forward, the wiring and satellite manufacturing can be implemented in parallel, and the original wiring required in the satellite AIT link is reduced, the serial and detection work of multiple batches and multiple types, the laid cable network can be directly used in the satellite AIT link in the form of an assembly, the satellite production efficiency is improved, and the satellite manufacturing cycle is shortened. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the application, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0017] Figure 1 A structural schematic diagram of a satellite cable laying operation platform provided by an embodiment of the application.

[0018] Figure 2 A structural schematic diagram of a platform body provided by an embodiment of the application.

[0019] Figure 3 An exploded structural schematic diagram of a platform body provided by an embodiment of the application.

[0020] Figure 4 A bottom structural schematic diagram of a platform body provided by an embodiment of the application.

[0021] Figure 5 A structural schematic diagram of a satellite cable laying operation platform provided by an embodiment of the application from another angle.

[0022] Figure 6 A structural schematic diagram of a satellite cable laying operation platform provided by an embodiment of the application in an unfolded and flattened state.

[0023] Figure 7 A corresponding cable network laying schematic diagram. Figure 1 A corresponding cable network laying schematic diagram.

[0024] Figure 8 A structural schematic diagram of a satellite cable laying operation platform provided by an embodiment of the application in a cabin closing state.

[0025] Label: 1, cable network; 100, satellite cable laying operation platform; 10, platform main body; 11, bottom plate; 111, positioning hole; 112, fixed hinge; 113, slot; 12, first side plate; 121, quick release opening; 13, second side plate; 131, movable hinge; 14, partition plate; 141, positioning opening; 15, quick release positioning block; 16, middle beam; 161, clamping groove; 17, positioning assembly; 171, positioning buckle; 172, positioning block; 18, leveling pad; 20, electrical interface analog; 21, integrated electronic interface analog; 22, PCDU interface analog; 23, battery interface analog; 24, satellite-ground interface analog; 25, load antenna interface analog; 26, star table interface analog; 27, S flywheel interface analog; 28, X flywheel interface analog; 29, SADA interface analog; 210, inter-satellite communication interface analog; 211, platform communication interface analog; 212, PPCU interface analog; 213, magnetometer interface analog; 214, thermal control interface analog; 215, switching interface analog; 30, wire harness management; 31, wire harness arrangement support; 32, wire harness arrangement tube. DETAILED DESCRIPTION

[0026] The specific embodiments of the present application will be described in detail in the following with reference to the drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the description of the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the scope of protection of the present application.

[0027] In the description of the present application, unless otherwise explicitly specified and limited, the terms "connection", "arrangement", "installation" and the like should be understood broadly, for example, "connection" can be fixed connection, can also be detachable connection, or integrally connected; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through intermediate medium; can be internal communication of two elements. For those of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0028] The orientation or positional relationship indicated by the terms "upper", "lower", "left", "right", "front", "back", "center", "top", "bottom", "inner", "outer", "vertical", "horizontal", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship commonly placed when the product of the application is used, and is only for the convenience of description and simplification of description, and does not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0029] The terms "first", "second", "third", etc. are merely intended to distinguish similar elements, and are not intended to indicate or imply relative importance or specific order, unless otherwise explicitly specified and limited.

[0030] The terms "comprise", "contain", "have" or any other variant thereof are intended to cover non-exclusive inclusions, so that processes, methods, articles or devices that include a series of elements not only include those elements, but also include other elements not explicitly listed, or further include elements inherent in such processes, methods, articles or devices. Without more limitations, the element defined by the statement "comprising a" does not exclude the presence of other identical elements in the process, method, article or device comprising the element.

[0031] The term "a plurality of" means two or more (including two).

[0032] The term "and / or", which is a description of the association relationship of the associated objects, means that there can be three relationships, for example, A and / or B, which can represent the three cases of A alone, A and B together, and B alone.

[0033] The terms "one embodiment", "as an example", "in an embodiment", etc. mean that the specific features, structures, materials or characteristics described in connection with the embodiment or example can be included in at least one embodiment or example of the present application. The illustrative representation of such terms does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment to other embodiments. In the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined in a suitable manner.

[0034] Figure 1 A structural schematic diagram of a satellite cable laying operation platform 100 provided by an embodiment of the present application is shown in Figure 1 The present application provides a satellite cable laying operation platform 100, which comprises a platform main body 10 and a plurality of electrical interface simulation pieces 20 arranged on the platform main body 10. The specific description of each part is as follows.

[0035] As shown in Figure 2 and Figure 3 The platform main body 10 comprises a bottom plate 11, two first side plates 12, two second side plates 13, a plurality of partition plates 14, a plurality of quick-release positioning blocks 15, and a middle beam 16.

[0036] The bottom plate 11 is rectangular and horizontally arranged as a reference plate. Two first side plates 12 are arranged on the two short sides of the bottom plate 11 respectively, each of which is rotatably connected with the bottom plate 11 and can rotate around the corresponding short side of the bottom plate 11. Two second side plates 13 are arranged on the two long sides of the bottom plate 11 respectively, each of which is rotatably connected with the bottom plate 11 and can rotate around the corresponding long side of the bottom plate 11. A plurality of partition plates 14 are distributed along the long side extension direction of the bottom plate 11, each of which is vertically arranged on the bottom plate 11 and parallel to the short side of the bottom plate 11, and the bottom of the partition plate 14 is detachably connected with the bottom plate 11. Quick-release positioning blocks 15 are used to position the first side plates 12 with the bottom plate 11 when the first side plates 12 are perpendicular to the bottom plate 11. A middle beam 16 is arranged on the upper surface of the first side plates 12 and the partition plates 14 in a direction parallel to the long side of the bottom plate 11, which limits the deformation of the first side plates 12 and the partition plates 14 in the extension direction of the middle beam 16. Among them, the two first side plates 12 and the two second side plates 13 can be unfolded to a horizontal state (see Figure 6 ) to lay cables, and the two first side plates 12 and the two second side plates 13 can also be enclosed (see Figure 8 ), so that the platform body 10 forms a satellite simulation cabin.

[0037] Regarding the first side plate 12 and the quick-release positioning block 15, as an example, the first side plate 12 is isosceles trapezoidal, and the short bottom edge of each first side plate 12 is rotatably connected with the corresponding short side of the bottom plate 11 through a rotating shaft, and the short bottom edge is provided with a quick-release opening 121 for installing the quick-release positioning block 15, and the bottom plate 11 is correspondingly provided with a positioning hole 111 for inserting the quick-release positioning block 15. Among them, the quick-release opening 121 penetrates the first side plate 12, the cross section of the quick-release opening 121 is T-shaped and the lower end of the T-shaped part reaches the short bottom edge of the first side plate 12, and the cross section of the quick-release positioning block 15 is H-shaped. Each first side plate 12 can rotate within a range of 0°-90°, when the first side plate 12 is rotated to a position perpendicular to the bottom plate 11, the quick-release positioning block 15 can be horizontally inserted into the corresponding T-shaped horizontal section of the quick-release opening 121, then the corresponding H-shaped middle section of the quick-release positioning block 15 is slid downward along the corresponding T-shaped vertical section of the quick-release opening 121, and finally the corresponding H-shaped one end of the quick-release positioning block 15 is inserted into the positioning hole 111 on the bottom plate 11 to position the first side plate 12 with the bottom plate 11.

[0038] As an example, the second side plate 13 is rectangular, and the length of the long side is equal to the length of the long side of the bottom plate 11, and the length of the short side is equal to the length of the waist of the first side plate 12. The two short sides of the second side plate 13 are each provided with a movable hinge 131, and the two short sides of the bottom plate 11 are each provided with a fixed hinge 112. Each movable hinge 131 is rotatably connected to the corresponding fixed hinge 112 through a hinge shaft, so that the second side plate 13 can rotate around the corresponding long side of the bottom plate 11. Further, each second side plate 13 can rotate within a range of 0°-65°.

[0039] As an example, the partition plate 14 is isosceles trapezoidal and has a size comparable to that of the first side plate 12. The short bottom edge of each partition plate 14 is inserted into the long strip-shaped slot 113 formed on the bottom plate 11. In order to ensure the stability of the position of the partition plate 14 and prevent the partition plate 14 from falling, the platform body 10 further comprises a plurality of positioning assemblies 17. Each partition plate 14 is provided with a positioning opening 141 near the short bottom for mounting the positioning assembly 17. The positioning assembly 17 comprises a positioning buckle 171 and a positioning block 172. The positioning buckle 171 is U-shaped in cross section and is inserted into the positioning opening 141 in the horizontal direction, so that the two parts at the two ends of the corresponding U-shaped part clamp the two side plate surfaces of the partition plate 14, respectively. The positioning block 172 is inserted into the positioning opening 141 and abuts against the positioning buckle 171, preventing the positioning buckle 171 from coming out of the positioning opening 141, thereby positioning the partition plate 14 and the bottom plate 11.

[0040] As an example, the bottom surface of the middle beam 16 has a plurality of clamping grooves 161 for clamping the long bottom edge of the first side plate 12 and the long bottom edge of the partition plate 14. Figure 3 As shown, the number of partition plates 14 is two, the two first side plates 12 are perpendicular to the bottom plate 11, the middle beam 16 is arranged across one first side plate 12 and two partition plates 14 in a direction parallel to the long side of the bottom plate 11, and clamps the long bottom edge of the first side plate 12 and the long bottom edge of the two partition plates 14 through the clamping grooves 161.

[0041] The platform body 10 can further comprise a plurality of leveling pads 18. As an example, the bottom surface of the bottom plate 11 is provided with a plurality of leveling pads 18 to provide support for the bottom plate 11; the opposite surfaces of the two side plates are each provided with a leveling pad 18 to provide support for the first side plate 12 when the first side plate 12 is rotated to a horizontal position; and the material of the leveling pad 18 can be bakelite, which has high mechanical strength, good insulation, heat resistance, and corrosion resistance.

[0042] The electrical interface analogues 20 are sheet metal analogues for simulating the electrical interfaces of various devices in the satellite (e.g. a direct satellite mobile phone), which can be formed by welding aluminum plates, with low material cost and easy processing. The electrical interface analogues 20 are installed on the bottom plate 11, the first side plate 12, the second side plate 13, the partition plate 14, and the middle beam 16 of the platform main body 10.

[0043] As an example, as shown in Figure 1 and Figure 5 , the electrical interface analogues 20 include an integrated electronic interface analogue 21, a PCDU (Power Conditioning and Distribution Unit) interface analogue 22, a battery interface analogue 23, a satellite-ground interface analogue 24, a payload antenna interface analogue 25, a star table interface analogue 26, an S flywheel interface analogue 27, an X flywheel interface analogue 28, an SADA (Solar Array Drive Assembly) interface analogue 29, an inter-satellite communication interface analogue 210, a platform communication interface analogue 211, a PPCU (Power Processing and Control Unit) interface analogue 212, a magnetometer interface analogue 213, a thermal control interface analogue 214, and a switching interface analogue 215.

[0044] The integrated electronic interface analogue 21 is arranged on one second side plate 13, for simulating the electrical interface of an integrated electronic module, which is responsible for intelligent fusion processing of satellite platform data, multi-system collaborative scheduling and on-orbit autonomous decision-making, overall planning of payload data distribution, platform device health management, and encrypted communication of satellite-ground link.

[0045] The battery interface analogue 23 is arranged on the bottom plate 11, for simulating the electrical interface of a battery, which is used for storing electrical energy.

[0046] The PCDU interface analogue 22 is arranged on one first side plate 12, for simulating the electrical interface of a PCDU, which is responsible for voltage regulation, power distribution and protection of the satellite power system, and management of the energy of the solar cell array and the battery.

[0047] The satellite-ground interface analogue 24 is arranged on another second side plate 13, for simulating the electrical interface of a satellite-ground module, which is responsible for communication and data exchange between the satellite and the ground system.

[0048] The payload antenna interface analog 25 is arranged on the partition plate 14 and is used for simulating the electrical interface of a payload antenna, which is an electromagnetic wave radiation / receiving device serving a specific mission target. The star table interface analog 26 simulates the electrical interface of a star table module, which is responsible for the storage management of satellite full-life cycle parameters, on-orbit state monitoring, cross-system instruction routing and security encryption.

[0049] The S flywheel interface analog 27 and the X flywheel interface analog 28 are both arranged on the partition plate 14 and are respectively used for simulating the electrical interfaces of an S flywheel and an X flywheel, which are used for momentum management and torque adjustment in a satellite attitude control system to adjust the satellite attitude.

[0050] The SADA interface analog 29 is in a number of two and is arranged on the two second side plates 13 respectively and is used for simulating the electrical interface of an SADA, which is responsible for driving the solar panel to rotate to ensure that the solar panel always faces the sun.

[0051] The inter-satellite communication interface analog 210 is arranged on the other second side plate 13 and is used for simulating the electrical interface of an inter-satellite communication module, which is responsible for ultra-high-speed data relay between satellite constellations, cooperative mission scheduling of star clusters and anti-interference encrypted transmission, and supports inter-satellite networking and deep space link extension.

[0052] The platform communication interface analog 211 is in a number of multiple and is arranged on the other second side plate 13 and the middle beam 16 and is used for simulating the electrical interface of a platform communication module, which is responsible for real-time data routing, health state aggregation and fault-tolerant reconstruction control between satellite subsystems, and guarantees the millisecond-level cooperative operation of attitude and orbit control, energy, payload, thermal control and other subsystems.

[0053] The PPCU interface analog 212 is arranged on the other first side plate 12 and is used for simulating the electrical interface of a PPCU, which is a core component in a satellite electric propulsion system and is mainly responsible for providing the required high-voltage power supply and accurate control signals for an electric thruster.

[0054] The magnetometer interface analog 213 is arranged on the bottom plate 11 and is used for simulating the electrical interface of a magnetometer module, which is responsible for satellite space magnetic field vector measurement, residual magnetism compensation and attitude determination assistance, and provides a high-precision control reference for a magnetic torque device.

[0055] The thermal control interface analog 214 is in a number of multiple and can be arranged on the bottom plate 11, the two first side plates 12, the two second side plates 13 and the middle beam 16 and is used for simulating the electrical interface of a thermal control module, which is responsible for the thermal management of the whole platform of the satellite.

[0056] The switching interface analog 215 is in a number of multiple and is arranged on the partition plate 14 and is used for simulating the electrical interface of a switching module.

[0057] The satellite cable laying operation platform 100 can further comprise a plurality of wire harness management members 30. As an example, as shown in Figure 1 and Figure 5 , the wire harness management member 30 comprises a plurality of wire harness arrangement supports 31 arranged on the bottom plate 11 and the second side plate 13, and a plurality of wire harness arrangement tubes 32 arranged on the bottom plate 11 and the partition plate 14.

[0058] The use process of the satellite cable laying operation platform 100: as shown in Figure 6 , first remove the middle beam 16, rotate the two first side plates 12 and the two second side plates 13 to the horizontal state, and then start the cable laying from the integrated electronic interface simulation 21 or the PCDU interface simulation 22. During the cable laying process, the cable needs to be tied, welded and compressed. When the cable laying of the electrical interface simulation 20 on the two first side plates 12 and the middle beam 16 is performed, the two first side plates 12 are respectively rotated to be perpendicular to the bottom plate 11, and the two first side plates 12 are positioned with the bottom plate 11 by using the quick-release positioning block 15, the middle beam 16 is installed, and then the cable laying of the electrical interface simulation 20 on the two first side plates 12 and the middle beam 16 is performed. The finally laid cable net 1 is shown in Figure 7 . Then, as shown in Figure 8 , rotate the two second side plates 13 to the position enclosed by the two first side plates 12, simulate the satellite cabin combination, and perform the cable net 1 inspection, mainly check the cable stress state, cable position, etc., and then adjust the cable to ensure the reliability of the cable arrangement. After the adjustment is completed, the cable net 1 is removed as a whole in the form of an assembly, and the cable net 1 can be directly used in the satellite AIT link.

[0059] In summary, the satellite cable laying operation platform provided by the embodiment of the present application adopts the cable net modular manufacturing concept, simulates the satellite cabin environment to build the satellite cable laying operation platform, performs the cable laying work, facilitates the early verification of the reliability of the whole satellite cable net spatial layout, so that the wiring work in the satellite AIT link can be pre-processed, the wiring and satellite manufacturing can be implemented in parallel, and the original wiring required in the satellite AIT link is reduced. The serial and detection work of multiple batches and multiple types, the laid cable net can be directly used in the satellite AIT link in the form of an assembly, the satellite production efficiency is improved, and the satellite manufacturing cycle is shortened.

[0060] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art can easily think of various changes or replacements within the technical range disclosed in the present application, which should be covered within the protection scope of the present application.

Claims

1. A satellite cable-laying operations platform, characterized by, The platform body comprises a bottom plate, two first side plates, two second side plates, a plurality of partitions, a plurality of quick-release positioning blocks, and a middle beam. The bottom plate is rectangular. The two first side plates are arranged on the two short sides of the bottom plate and are rotationally connected with the bottom plate, and can rotate around the corresponding short side of the bottom plate. The two second side plates are arranged on the two long sides of the bottom plate and are rotationally connected with the bottom plate, and can rotate around the corresponding long side of the bottom plate. The plurality of partitions are distributed and installed on the top surface of the bottom plate along the long side extension direction of the bottom plate. The quick-release positioning block is used to position the first side plate and the bottom plate when the first side plate is perpendicular to the bottom plate. The middle beam is used to be arranged across the first side plate and the partition to limit the deformation of the first side plate and the partition. A plurality of electrical interface analogs are installed on the bottom plate, the two first side plates, the two second side plates, the plurality of partitions, and the middle beam, and are used to simulate the electrical interface of a satellite device to lay satellite cables. When the two first side plates and the two second side plates are enclosed, the platform body forms a satellite simulation cabin. The platform body further comprises a plurality of positioning assemblies. The positioning assembly is used to position the partition and the bottom plate. The bottom edge of each partition is inserted into a slot formed on the bottom plate. The partition near the bottom edge is provided with a positioning opening for installing the positioning assembly. The positioning assembly comprises a positioning buckle and a positioning block. The cross section of the positioning buckle is U-shaped. The positioning buckle is inserted into the positioning opening along the horizontal direction, so that the two parts at the two ends of the U-shaped part clamp the two side plate surfaces of the partition, respectively. The positioning block is inserted into the positioning opening and abuts against the positioning buckle to prevent the positioning buckle from coming out of the positioning opening. The first side plate is isosceles trapezoidal, the second side plate is rectangular, the long side of the rectangle is equal in length to the long side of the bottom plate, and the short side is equal in length to the waist of the first side plate.

2. The satellite cable-laying operations platform of claim 1, wherein, The short bottom edge of each first side plate is rotationally connected with the corresponding short side of the bottom plate through a rotating shaft, and the short bottom edge is provided with a quick-release opening for installing the quick-release positioning block. The bottom plate is correspondingly provided with a positioning hole for inserting the quick-release positioning block.

3. The satellite cable-laying operations platform of claim 2, wherein, The quick-release opening penetrates the first side plate, and the cross section of the quick-release opening is T-shaped and the lower end of the T-shaped part is connected to the short bottom edge of the first side plate. The cross section of the quick-release positioning block is H-shaped. The quick-release positioning block is inserted into the corresponding T-shaped horizontal part of the quick-release opening, slides downward along the corresponding T-shaped vertical part of the quick-release opening, and is then inserted into the positioning hole to position the first side plate and the bottom plate.

4. The satellite cable-laying operations platform of claim 3, wherein, Each second side plate is provided with a movable hinge on the two short sides, and the bottom plate is provided with a fixed hinge on the two short sides. Each movable hinge is rotationally connected with the corresponding fixed hinge through a hinge shaft.

5. The satellite cable-laying operations platform of claim 2, wherein, Each partition is arranged vertically on the top surface of the bottom plate and is parallel to the short side of the bottom plate. The bottom of the partition is detachably connected with the bottom plate.

6. The satellite cable-laying operations platform of claim 1, wherein, ​ 7. The satellite cable-laying operations platform of claim 6, wherein, The partition is isosceles trapezoid, and the short bottom edge of each partition is inserted into the slot on the bottom plate.

8. The satellite cable-laying operations platform of claim 1, wherein, The electrical interface analogues include at least one of the following: integrated electronic interface analogue, PCDU interface analogue, battery interface analogue, satellite-ground interface analogue, load antenna interface analogue, star table interface analogue, S flywheel interface analogue, X flywheel interface analogue, SADA interface analogue, inter-satellite communication interface analogue, platform communication interface analogue, PPCU interface analogue, magnetometer interface analogue, thermal control interface analogue, switching interface analogue.

9. The satellite cable-laying operations platform of claim 1, wherein, Further comprising: A plurality of wire harness management pieces are installed on the bottom plate, the second side plate and the partition plate for supporting and restraining satellite cables.

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