General design method and general structure of closed flat panel satellite

Abstract

The application relates to a general design method and general structure of a closed flat satellite, and belongs to the field of satellite main structures, satellite load layout design and cable networks, in particular to integrated design of cable networks, satellite load layout and satellite main structures; the application solves the problems of the existing closed flat satellite, i.e. limited cabin space, difficult cable layout design, complex cable layout, low space utilization rate, weight increase and influence on the performance of the whole satellite; the general structure comprises a satellite main structure, various single-machine loads and a cable network; the various single-machine loads and the cable network adopt integrated structure design; the general design method and general structure of the closed flat satellite are suitable for providing a closed flat satellite with high space utilization rate, light weight and being suitable for batch production.

Description

Technical Field

[0001] This invention relates to the fields of satellite main structure, on-board payload layout design and cable network, and particularly to the integrated design of cable network, on-board payload layout and satellite main structure. Background Technology

[0002] Flat-panel satellites have become a major trend in satellite design due to their structural suitability for large-scale low-Earth orbit constellation deployments and ability to reduce launch costs.

[0003] For enclosed flat-panel satellites, the limited space within the satellite cabin due to altitude restrictions makes cable routing design particularly challenging. Such satellite structures often face the problem of interconnecting upper and lower individual payloads, leading to complex wiring and numerous upper and lower transition cables during the cabin assembly phase. This not only increases cable weight but may also result in insufficient cable bending radii or interference with other onboard payloads, ultimately affecting the overall installation efficiency and system reliability. As a crucial component of the satellite, the cable network connects different individual devices and plays a critical role in power supply, signal transmission, and control signal transmission. However, cable network design faces challenges in terms of weight, volume, and reliability. Traditional cable networks typically design the cable layout separately from the overall satellite structure, leading to complex cable layouts, low space utilization, and increased weight, impacting overall satellite performance requirements.

[0004] In the overall design of large flat-panel satellites, the number of onboard payloads increases significantly, and the space used for cables also increases considerably. Under the current limitations of rocket fairing size, the increased satellite height due to the space used for internal cables will affect the number of flat-panel satellites that can be launched in a single launch. Summary of the Invention

[0005] This invention proposes an overall design method and structure for enclosed flat-panel satellites, which solves the problems of limited internal space in existing enclosed flat-panel satellites, making cable routing layout design difficult, resulting in complex cable layout, low space utilization, increased weight, and thus affecting the overall satellite performance.

[0006] The overall design method for a closed flat-panel satellite according to the present invention includes the following steps:

[0007] Overall structural design steps: The overall structure of a closed flat-panel satellite includes the main satellite structure, various individual payloads, and the cable network;

[0008] Main structure design steps: The main structure of the satellite includes honeycomb structure panel I, honeycomb structure panel II, and main structural frame;

[0009] The main connection design steps are as follows: the honeycomb structure panel I and the honeycomb structure panel II are arranged vertically and connected by the main structural frame; the honeycomb structure panel I, the honeycomb structure panel II, and the main structural frame are connected and fixed by fastening standard parts; various single-unit loads and cable networks are fixedly installed on the honeycomb structure panel I and the honeycomb structure panel II.

[0010] Functional area design steps: The main structure of the satellite is divided into multiple functional areas according to the overall design requirements of the satellite; the honeycomb structure panel I and the honeycomb structure panel II are divided into platform equipment area and functional payload area, so that the highly related single payloads are placed on the same honeycomb structure panel, and then according to the functions of various single payloads, the single payloads that achieve the same function are placed in the same functional area.

[0011] Integrated design steps: The various single-unit loads and cable network adopt an integrated structural design: The cable network includes flexible plate cables, rigid plate cables, and electrical connectors; The flexible plate cables adopt a modular design, consisting of multiple flexible plate cable modules; The honeycomb structure plate I and honeycomb structure plate II respectively leave height space between them and the main structural frame for the flexible plate cable modules to pass through; The multiple flexible plate cable modules pass through various functional areas to connect the various single-unit loads to each other; The multiple flexible plate cable modules are interconnected at the locations of the rigid plate cables using electrical connectors to form a complete cable network.

[0012] Furthermore, a preferred embodiment is provided, wherein the plurality of functional areas include a data management subsystem, a power supply subsystem, an attitude and orbit control subsystem, a communication and data transmission subsystem, a thermal control subsystem, and a functional payload system.

[0013] Furthermore, a preferred embodiment is provided, wherein placing single-unit loads that perform the same function within the same functional area according to the functions of various single-unit loads includes:

[0014] By analyzing the interconnection relationships and transmitted data of various individual loads, as well as the operating power of each individual load, the signal transmission paths and power supply paths between various individual loads are determined.

[0015] Optimize the layout of individual loads from a global perspective by placing loads with the same function in the same functional area to reduce the area spanned and total length of interconnecting cables.

[0016] Furthermore, a preferred embodiment is provided, wherein the honeycomb structure panel I and the honeycomb structure panel II are respectively provided with a height space between them and the main structural frame for the flexible board cable module to pass through, including:

[0017] The honeycomb structure panel I and the honeycomb structure panel II are respectively provided with main structural frame spacers between them and the main structural frame.

[0018] Furthermore, in a preferred embodiment, the padding height of the main structural frame pad is 4mm.

[0019] Furthermore, a preferred embodiment is provided in which the rigid plate cable position bracket is installed above the honeycomb structure plate I and the honeycomb structure plate II.

[0020] Furthermore, a preferred embodiment is provided in which the bottom of the electrical connector protrudes from the rigid plate cable; a mounting pad is used for compensation so that the rigid plate cable is mounted higher than the honeycomb structure plate I and honeycomb structure plate II.

[0021] Furthermore, a preferred embodiment is provided, wherein rigid plate cables are fixedly installed on the honeycomb structure plate I and the honeycomb structure plate II respectively, and electrical connectors are fixedly installed on the rigid plate cables;

[0022] The electrical connectors of the rigid plate cables on the honeycomb structure panel I and honeycomb structure panel II are connected to each other via adapter cables.

[0023] Furthermore, a preferred embodiment is provided in which the flexible plate cable module is integrally flat and vulcanized.

[0024] The present invention also provides an overall structure of a closed flat-panel satellite, wherein the overall structure is designed using any of the above-described overall design methods for closed flat-panel satellites.

[0025] The present invention has the following beneficial effects:

[0026] 1. The overall design method of the enclosed flat-panel satellite described in this invention adopts an integral flat vulcanization molding scheme for the flexible plate cable, which has advantages such as light weight, small size, and strong adaptability to satellite structure compared with ordinary cables. In combination with the existing process technology, the design work is carried out in an integrated manner with the single-unit payload structure. During the overall satellite design process, while meeting the reasonable layout of the flexible plate cable, the space inside and outside the satellite cabin required for cable connection can be saved, thereby improving the occupancy rate of the satellite cabin space, further reducing the overall volume of the satellite, effectively reducing the overall height of the satellite, further increasing the number of stacked flat-panel satellites launched at one time, and improving the launch efficiency of network satellites.

[0027] 2. The overall design method of the enclosed flat-panel satellite described in this invention divides the main structure of the satellite (i.e., the space of the honeycomb structure panel) into different functional areas, and places single-unit payloads with the same function in the same area or adjacent areas, thereby improving the flexibility of on-board missions.

[0028] 3. The overall design method of the enclosed flat-panel satellite described in this invention places interconnected single-unit payloads in the same or adjacent areas, which can reduce cable length, improve signal processing capabilities, and reduce cable design difficulty.

[0029] 4. The overall design method of the enclosed flat-panel satellite described in this invention uses flexible plate cables, which can reduce the weight of the (on-board) cable network and the wiring space; compared with ordinary cables, the weight reduction of flexible plate cables can reach more than 50%, further reducing the cost of rocket launch.

[0030] 5. The overall design method of the enclosed flat-panel satellite described in this invention adopts a modularly designed flexible plate cable. The installation efficiency of the flexible plate cable is significantly improved compared with that of ordinary cables. According to existing manufacturing processes, the reliability of the flexible plate cable is higher after mass production, thereby increasing the overall reliability of the satellite system. It is suitable for the mass production of networking satellites, and can also effectively reduce the production cost of cable networks and improve efficiency in subsequent mass production.

[0031] The overall design method and structure of the enclosed flat-panel satellite described in this invention are applicable to providing an enclosed flat-panel satellite with high space utilization, light weight, and suitability for mass production. Attached Figure Description

[0032] To more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0033] Figure 1 This is a schematic diagram of an overall structure consisting of a honeycomb structure panel I, a main structural frame, a flexible cable, and a single-unit load, according to one embodiment of the present invention.

[0034] Figure 2 In one embodiment of the present invention, a schematic diagram of the overall composition of the cable network is shown, where the black area represents rigid plate cables and the rest represents flexible plate cables and electrical connectors.

[0035] Figure 3 This is a schematic diagram of a modular design for a flexible board cable in one embodiment of the present invention;

[0036] Figure 4 This is a schematic diagram of the installation method of the flexible plate cable and the honeycomb structure plate I in one embodiment of the present invention;

[0037] Figure 5 This is a schematic diagram of the pads on the honeycomb structure plate I during the installation of a flexible plate cable, according to one embodiment of the present invention.

[0038] Figure 6 This is a schematic diagram of the structure of the mounting pad in one embodiment of the present invention;

[0039] Figure 7 This is a schematic diagram of the main structural frame and its gaskets in one embodiment of the present invention;

[0040] Figure 8 This is a schematic diagram of the interface of an electrical connector in one embodiment of the present invention;

[0041] Figure 9 This is a schematic diagram illustrating the signal connection between honeycomb structure panel I and honeycomb structure panel II via an adapter cable and an electrical connector, as shown in one embodiment of the present invention.

[0042] Figure label:

[0043] 1. Single unit load; 2. Honeycomb structure panel I; 3. Main structural frame; 3-1. Main structural frame gasket; 3-2. Main structural frame beam unit; 4. Flexible plate cable; 4-1. Flexible plate cable module I; 4-2. Flexible plate cable module II; 4-3. Flexible plate cable module III; 4-4. Electrical connector; 4-5. Mounting pad; 4-6. Fastening standard parts; 4-7. Flexible plate cable module IV; 4-8. Rigid plate cable; 5. Honeycomb structure panel II; 6. Transfer cable; 7. The portion of the flexible plate cable crossing the main structural frame. Detailed Implementation

[0044] To make the technical solutions and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail and completely below with reference to the accompanying drawings. The various embodiments described below are only some preferred embodiments of the present invention, and not all of them; the various embodiments described below are intended to explain the present invention and should not be construed as limiting the present invention; reasonable combinations of the technical features defined in the various embodiments of the present invention, as well as all other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort, are all within the scope of protection of the present invention.

[0045] In one embodiment, a general design method for a closed flat-panel satellite is provided, the method comprising the following steps:

[0046] Overall structural design steps: The overall structure of a closed flat-panel satellite includes the main satellite structure, various individual payloads, and the cable network;

[0047] Main structure design steps: The main structure of the satellite includes honeycomb structure panel I, honeycomb structure panel II, and main structural frame;

[0048] The main connection design steps are as follows: the honeycomb structure panel I and the honeycomb structure panel II are arranged vertically and connected by the main structural frame; the honeycomb structure panel I, the honeycomb structure panel II, and the main structural frame are connected and fixed by fastening standard parts; various single-unit loads and cable networks are fixedly installed on the honeycomb structure panel I and the honeycomb structure panel II.

[0049] Functional area design steps: The main structure of the satellite is divided into multiple functional areas according to the overall design requirements of the satellite; the honeycomb structure panel I and the honeycomb structure panel II are divided into platform equipment area and functional payload area, so that the highly related single payloads are placed on the same honeycomb structure panel, and then according to the functions of various single payloads, the single payloads that achieve the same function are placed in the same functional area.

[0050] Integrated Design Steps: The various individual loads and cable network adopt an integrated structural design: the cable network includes flexible plate cables, rigid plate cables, and electrical connectors; the flexible plate cables adopt a modular design, consisting of multiple flexible plate cable modules; the honeycomb structure plate I and honeycomb structure plate II respectively leave height space between themselves and the main structural frame for the flexible plate cable modules to pass through; the multiple flexible plate cable modules pass through various functional areas to connect the various individual loads to each other; the multiple flexible plate cable modules are interconnected at the locations of the rigid plate cables using electrical connectors to form a complete cable network.

[0051] In this embodiment, the layout of the single-unit payload can be selected and adjusted according to the overall satellite design requirements.

[0052] In this embodiment, the modular design of the flexible plate cable can be adjusted according to the overall design requirements.

[0053] In this embodiment, the installation and fixing of the flexible plate cable can be adjusted according to the specific form of the flexible plate cable.

[0054] In this embodiment, such as Figure 1 and Figure 2 As shown, in the overall structure of the enclosed flat-panel satellite, the single-unit payload and the cable network adopt an integrated structural design.

[0055] In this embodiment, such as Figure 3 and Figure 4 As shown, the cable network includes flexible plate cables, rigid plate cables, and electrical connectors. The flexible plate cables adopt a modular design. Different flexible plate cable modules are connected to different single-unit loads; multiple flexible plate cable modules are connected through electrical connectors 4-4, realizing the interconnection between different single-unit loads.

[0056] exist Figure 3The flexible plate cable includes flexible plate cable module I 4-1, flexible plate cable module II 4-2, and flexible plate cable module III 4-3.

[0057] exist Figure 4 The flexible plate cable also includes a flexible plate cable module IV4-7.

[0058] In this embodiment, the single-unit load is mounted on the honeycomb structure plate I using standard fasteners; the single-unit load is provided with an associated connector interface, and the flexible plate cable is provided with a connector; the connector on the flexible plate cable and the associated connector interface on the single-unit load are plugged into each other to realize the connection between the flexible plate cable and the single-unit load.

[0059] Use standard fasteners to install the flexible board cable onto the honeycomb structure panel I.

[0060] In another embodiment, the plurality of functional areas includes a data management subsystem, a power supply subsystem, an attitude and orbit control subsystem, a communication and data transmission subsystem, a thermal control subsystem, and a functional payload system.

[0061] In this implementation, the satellite can be divided into several other functional areas according to the overall design requirements of the satellite.

[0062] In this embodiment, the thermal control subsystem refers to the temperature control system of the satellite platform.

[0063] In this embodiment, the functional payload system refers to the main mission equipment of the satellite, generally called the payload unit.

[0064] In another embodiment, the thickness of the portion 7 of the flexible cable that crosses the main structural frame is designed to be less than 2 mm.

[0065] In another embodiment, placing single-machine loads that perform the same function within the same functional area according to the functions of various single-machine loads includes:

[0066] By analyzing the interconnection relationships and transmitted data of various individual loads, as well as the operating power of each individual load, the signal transmission paths and power supply paths between various individual loads are determined.

[0067] Optimize the layout of individual loads from a global perspective by placing loads with the same function in the same functional area to reduce the area spanned and total length of interconnecting cables.

[0068] In this embodiment, the interconnection structure composed of the flexible plate cable and various single-unit loads realizes the integrated design of the platform computer and data management subsystem, power supply subsystem, attitude and orbit control subsystem, communication and data transmission subsystem, thermal control subsystem, and functional load system with the satellite main structure. This can significantly reduce the complex design requirement that the satellite can only connect cables when the satellite is in the same compartment, and achieve lighter interconnection of cables.

[0069] In another embodiment, a height space is left between the honeycomb structure panel I and the honeycomb structure panel II and the main structural frame for the flexible board cable module to pass through, including:

[0070] The honeycomb structure panel I and the honeycomb structure panel II are respectively provided with main structural frame spacers between them and the main structural frame.

[0071] In this embodiment, the layout spacing and size parameters of the main structural frame gaskets can be adjusted according to design requirements.

[0072] In this embodiment, such as Figure 7 As shown, a main structural frame gasket 3-1 is provided at the fixed connection between the honeycomb structural panel I or honeycomb structural panel II and the main structural frame, and the connection is fixed by fastening standard parts.

[0073] The main structural frame spacer 3-1 is used to leave a height space between the honeycomb structural panel I or honeycomb structural panel II and the main structural frame for the flexible board cable module to pass through, so that the flexible board cable module can pass through different functional areas.

[0074] In this embodiment, the height of the main structural frame pad 3-1 is 4mm.

[0075] In another embodiment, the rigid plate cable position frame is installed above the honeycomb structure plate I and the honeycomb structure plate II.

[0076] In this embodiment, the flexible plate cable module is generally attached to the surfaces of honeycomb structure plate I and honeycomb structure plate II and fixedly installed using fastening standard parts.

[0077] In another embodiment, the bottom of the electrical connector protrudes from the steel plate cable; a mounting pad is used for compensation so that the position of the steel plate cable is higher than that of the honeycomb structure plate I and the honeycomb structure plate II during installation.

[0078] In this embodiment, such as Figure 5 and Figure 6 As shown, after the electrical connector 4-4 is fixed on the steel plate cable, the bottom of the electrical connector (i.e., the pin position) will protrude from the steel plate cable, making it impossible for the steel plate cable to be installed on the honeycomb structure board. Therefore, mounting pads are used to raise the steel plate cable above the honeycomb structure board to compensate for the protrusion of the bottom of the electrical connector.

[0079] In this embodiment, the height of the mounting pad is determined based on the actual height of the bottom of the electrical connector (i.e., the pin position) protruding from the steel plate cable.

[0080] In another embodiment, the height of the mounting pad is 6mm.

[0081] In another embodiment, rigid plate cables are fixedly installed on the honeycomb structure plate I and the honeycomb structure plate II, and electrical connectors are fixedly installed on the rigid plate cables.

[0082] The electrical connectors of the rigid plate cables on the honeycomb structure panel I and honeycomb structure panel II are connected to each other via adapter cables.

[0083] In this embodiment, such as Figure 8 and Figure 9 As shown:

[0084] First, install and fix the honeycomb structure panel II5 to the main structural frame using standard fasteners;

[0085] Rigid plate cables are fixedly installed on the honeycomb structure plate I2 and honeycomb structure plate I5 respectively, realizing the centralized design of signal conversion interface;

[0086] Electrical connectors 4-4, which meet the requirements of upper and lower power signals, are fixedly installed on the rigid plate cable;

[0087] Use adapter cable 6 to complete the insertion of the electrical connectors of the upper and lower honeycomb structure panels;

[0088] After the insertion is completed, the honeycomb structure panel I2 is installed and fixed to the main structural frame 3 using fastening standard parts, thus completing the connection and assembly of the cables and single-unit loads inside the enclosed flat-panel satellite cabin.

[0089] In another embodiment, the flexible cable module is integrally flat and vulcanized.

[0090] In another embodiment, a closed flat-panel satellite overall structure is provided, which is designed using any of the above-described closed flat-panel satellite overall design methods;

[0091] The overall structure includes the satellite's main structure, various individual payloads, and the cable network;

[0092] The main structure of the satellite includes honeycomb structure panel I, honeycomb structure panel II, and main structural frame;

[0093] The honeycomb structure panel I and honeycomb structure panel II are arranged vertically and connected by the main structural frame; the honeycomb structure panel I, honeycomb structure panel II and the main structural frame are connected and fixed by fastening standard parts; various single-machine loads and cable networks are fixedly installed on the honeycomb structure panel I and honeycomb structure panel II.

[0094] The main structure of the satellite is divided into multiple functional areas according to the overall design requirements of the satellite. The honeycomb structure panel I and the honeycomb structure panel II are divided into platform equipment area and functional payload area, so that highly related single payloads are placed on the same honeycomb structure panel. Then, according to the functions of various single payloads, single payloads that achieve the same function are placed in the same functional area to increase design coupling.

[0095] The various individual loads and cable networks are designed as an integrated structure.

[0096] The cable network includes flexible plate cables, rigid plate cables, and electrical connectors.

[0097] The flexible plate cable adopts a modular design and is composed of multiple flexible plate cable modules. The honeycomb structure plate I and the honeycomb structure plate II are respectively provided with height space between them and the main structural frame for the flexible plate cable modules to pass through. The multiple flexible plate cable modules pass through various functional areas to connect various single-machine loads to each other. The multiple flexible plate cable modules are interconnected by electrical connectors at the location of the rigid plate cable to form a complete cable network.

[0098] The above description of several specific embodiments further details the technical solution provided by the present invention in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the above-described specific embodiments are not intended to limit the present invention. Any reasonable modifications and improvements to the present invention, reasonable combinations of embodiments, and equivalent substitutions based on the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A general design method for a closed flat-panel satellite, characterized in that, The method includes the following steps: Overall structural design steps: The overall structure of a closed flat-panel satellite includes the main satellite structure, various individual payloads, and the cable network; Main structure design steps: The main structure of the satellite includes honeycomb structure panel I, honeycomb structure panel II, and main structural frame; The main connection design steps are as follows: the honeycomb structure panel I and the honeycomb structure panel II are arranged vertically and connected by the main structural frame; the honeycomb structure panel I, the honeycomb structure panel II, and the main structural frame are connected and fixed by fastening standard parts; various single-unit loads and cable networks are fixedly installed on the honeycomb structure panel I and the honeycomb structure panel II. Functional area design steps: The main structure of the satellite is divided into multiple functional areas according to the overall design requirements of the satellite; the honeycomb structure panel I and the honeycomb structure panel II are divided into platform equipment area and functional payload area, so that the highly related single payloads are placed on the same honeycomb structure panel, and then according to the functions of various single payloads, the single payloads that achieve the same function are placed in the same functional area. Integrated design steps: The various single-unit loads and cable network adopt an integrated structural design: The cable network includes flexible plate cables, rigid plate cables, and electrical connectors; The flexible plate cables adopt a modular design, consisting of multiple flexible plate cable modules; The honeycomb structure plate I and honeycomb structure plate II respectively leave height space between them and the main structural frame for the flexible plate cable modules to pass through; The multiple flexible plate cable modules pass through various functional areas to connect the various single-unit loads to each other; The multiple flexible plate cable modules are interconnected at the locations of the rigid plate cables using electrical connectors to form a complete cable network.

2. The overall design method for a closed flat-panel satellite according to claim 1, characterized in that, The multiple functional areas include a data management subsystem, a power supply subsystem, an attitude and orbit control subsystem, a communication and data transmission subsystem, a thermal control subsystem, and a functional payload system.

3. The overall design method for a closed flat-panel satellite according to claim 1, characterized in that, The method of placing single-machine loads that perform the same function within the same functional area based on the functions of various single-machine loads includes: By analyzing the interconnection relationships and transmitted data of various individual loads, as well as the operating power of each individual load, the signal transmission paths and power supply paths between various individual loads are determined. Optimize the layout of individual loads from a global perspective by placing loads with the same function in the same functional area to reduce the area spanned and total length of interconnecting cables.

4. The overall design method for a closed flat-panel satellite according to claim 1, characterized in that, The honeycomb structure panel I and honeycomb structure panel II are respectively provided with height space between themselves and the main structural frame for the flexible board cable module to pass through, including: The honeycomb structure panel I and the honeycomb structure panel II are respectively provided with main structural frame spacers between them and the main structural frame.

5. The overall design method for a closed flat-panel satellite according to claim 4, characterized in that, The height of the padding for the main structural frame is 4mm.

6. The overall design method for a closed flat-panel satellite according to claim 1, characterized in that, The rigid plate cable position frame is installed above the honeycomb structure plate I and honeycomb structure plate II.

7. The overall design method for a closed flat-panel satellite according to claim 6, characterized in that, The bottom of the electrical connector protrudes from the steel plate cable; a mounting pad is used for compensation so that the position of the steel plate cable is higher than that of the honeycomb structure plate I and honeycomb structure plate II during installation.

8. The overall design method for a closed flat-panel satellite according to claim 1, characterized in that, Rigid plate cables are fixedly installed on the honeycomb structure plate I and honeycomb structure plate II respectively, and electrical connectors are fixedly installed on the rigid plate cables; The electrical connectors of the rigid plate cables on the honeycomb structure panel I and honeycomb structure panel II are connected to each other via adapter cables.

9. The overall design method for a closed flat-panel satellite according to claim 1, characterized in that, The flexible cable module is integrally flat and vulcanized.

10. The overall structure of a closed flat-panel satellite, characterized in that, The overall structure is designed using the overall design method for the closed flat-panel satellite described in any one of claims 1 to 9.

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