A satellite structure based on structural reuse

Abstract

This invention discloses a satellite structure based on structural reuse, belonging to the field of spacecraft structural design technology. It includes a rectangular cylindrical structure composed of an antenna mounting plate, a first outer side plate, a second outer side plate, and a base plate. A first main partition and a second main partition are installed at one end of the rectangular cylindrical structure to form a first mounting cavity; a third main partition and a fourth main partition are installed at the other end of the rectangular cylindrical structure to form a second mounting cavity; a third mounting cavity is formed between the second and third main partitions; electronic equipment boxes are provided in the first and second mounting cavities; the third mounting cavity is used to install non-plug-in equipment; the outer surface of the antenna mounting plate is used to install SAR antenna elements, and the inner surface is used to install antenna waveguides, TR components, power supplies, and other equipment; the outer surfaces of the first and second outer side plates provide mounting interfaces for satellite surface equipment. This satellite structure reduces the satellite's volume and improves the utilization rate of the satellite's overall payload envelope.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft structure technology, specifically relating to a satellite structure based on structural reuse. Background Technology

[0002] As satellite mission requirements become increasingly complex, the demand for integrated engineering system design is rising. In traditional satellite development, the platform and payload, as well as the platform structure and individual electronic devices, are independent units in terms of configuration and structural design. The design of each subsystem unit and the satellite structure is based on interface interfaces, which are clear and unambiguous. This results in shortcomings in the installation structure of the platform, payload, and individual electronic devices, such as long force transmission paths, numerous connection structures, low efficiency, and functional redundancy, in order to achieve functions such as structural load-bearing and maintaining configuration. Consequently, the overall satellite launch mass is heavy, the satellite envelope size is large, and the development cost is also high.

[0003] Constrained by launch vehicle weight and the available fairing envelope, traditional interface-based design methods for satellite structures and payloads, as well as structural and electronic components, have led to an increase in overall satellite and payload size and hampered performance improvements. Furthermore, the shallow coupling between mechanical, electrical, and thermal engineering disciplines results in numerous performance deficiencies, such as poor launch phase mechanical resistance and an overall bulkiness that fails to meet the demands of agile satellite maneuverability for compact structures and low inertia. For microsatellites, traditional development models are even less suited to the engineering design requirements of rapid spacecraft design, low cost, compact structure, high rigidity, and low inertia.

[0004] Currently, the integrated design of satellite platforms and payloads in my country mainly focuses on interface-based integration. In contrast, advanced satellites abroad, such as the Hubble Space Telescope (HST) and the James Webb Space Telescope (JWST), have achieved integrated functional and performance design. China's integrated design level lags significantly behind advanced international levels. For example, Chinese invention patent CN108860659A discloses an integrated satellite based on a deployable planar phased array antenna. This invention directly utilizes a hollow triangular prism formed by the three-part planar phased array antenna as the platform structure. Its overall satellite size and internal volume are small, making the layout of all satellite equipment difficult. The hinged connection of the three planar phased array antennas limits its load-bearing capacity. Another example is Chinese invention patent CN105235916A, which discloses a compact integrated satellite configuration, proposing a payload-centric integrated satellite configuration to achieve a layout around the payload. However, all equipment is still arranged on the structural plate using traditional fixed installation methods, failing to achieve reuse of the main structure.

[0005] Therefore, it is evident that carrying out integrated design of satellite platform structure and payload, as well as integrated design among various systems of the satellite platform, has become one of the key technologies for improving satellite performance and cost-effectiveness. Summary of the Invention

[0006] In view of this, the present invention provides a satellite structure based on structural reuse, which integrates the antenna mounting plate with the satellite structure (i.e., the main structure of the satellite) and the electronic equipment box with the satellite structure, solving the space size problem of small-volume satellites carrying large-size, high-performance payloads, realizing the performance requirements of compact satellite structure, high rigidity, and low inertia, and improving the level of satellite integration and lightweighting.

[0007] The present invention adopts the following technical solution:

[0008] A satellite structure based on structural reuse includes a rectangular cylindrical structure composed of an antenna mounting plate, a first outer side plate, a second outer side plate, and a base plate, as well as a first main partition, a second main partition, a third main partition, and a fourth main partition.

[0009] The first main partition and the second main partition are fixedly installed in parallel at one end of the rectangular cylindrical structure chamber as the first set of partitions to form the first installation cavity.

[0010] The third and fourth main partitions are arranged in parallel at the other end of the rectangular cylindrical structure chamber as the second set of partitions to form the second mounting cavity.

[0011] A third mounting cavity is formed between the second main partition and the third main partition;

[0012] Electronic device boxes are installed in the first and second mounting cavities, forming a plug-in type single-unit mounting structure.

[0013] The third mounting cavity is used to install non-plug-in equipment, including battery packs for power supply and distribution systems, sensors, actuators, tanks, and pipelines for control and propulsion systems.

[0014] The outer side of the antenna mounting plate is used to install SAR antenna elements, and the inner side is used to install equipment including antenna waveguides, TR components, and power supplies.

[0015] The outer surfaces of the first and second outer plates are used to provide mounting interfaces for star table equipment, including solar panels.

[0016] In the cylindrical structure, the first outer side plate and the second outer side plate are adjacent to each other, and star-rocket docking joints are provided at the junctions of the antenna mounting plate, the bottom plate, and the main partition plate, as well as at the junctions of the first outer side plate, the bottom plate, and the main partition plate.

[0017] Furthermore, the rectangular cylindrical structure extends out from two opposite sides of the antenna mounting plate, and the extended portion is supported by the antenna support structure.

[0018] Furthermore, the antenna mounting plate is the same length as the rectangular cylindrical structure, and a fixed antenna array is mounted on the antenna mounting plate. Deployable antenna arrays that protrude from the rectangular cylindrical structure are mounted on the two opposite sides of the fixed antenna array in the longitudinal direction.

[0019] Furthermore, the electronic device housing has a "C"-shaped structure;

[0020] The "C"-shaped structure is detachably connected to the partitions in the first and second mounting cavities.

[0021] Furthermore, the electronic device enclosure includes an enclosure base plate and two guide rails disposed opposite to each other on the longitudinal sides of the enclosure base plate;

[0022] The guide rail plate is equipped with mounting interfaces including electronic device inserts, locking strips, and sealing strips.

[0023] Furthermore, the bottom plate of the insertion box has an aluminum honeycomb sandwich structure.

[0024] Furthermore, the antenna mounting plate is a carbon fiber panel aluminum honeycomb sandwich structure with embedded aluminum heat pipes;

[0025] The carbon fiber panel in the aluminum honeycomb sandwich structure is composed of polyacrylonitrile-based carbon fiber woven fabric, polyacrylonitrile-based carbon fiber unidirectional prepreg, and pitch-based high thermal conductivity carbon fiber unidirectional prepreg mixed and layered in a centrally symmetrical manner.

[0026] The aluminum heat pipe is embedded in the aluminum honeycomb core sandwich structure of the carbon fiber panel aluminum honeycomb sandwich structure, and the length direction of the aluminum heat pipe is orthogonal to the layup direction of the asphalt-based high thermal conductivity carbon fiber unidirectional prepreg.

[0027] The polyacrylonitrile-based carbon fiber woven fabric is located on the outermost layer of the carbon fiber panel;

[0028] The polyacrylonitrile-based carbon fiber unidirectional prepreg is located in the middle layer of the carbon fiber panel;

[0029] The pitch-based high thermal conductivity carbon fiber unidirectional prepreg is located between the polyacrylonitrile-based carbon fiber woven fabric and the polyacrylonitrile-based carbon fiber unidirectional prepreg.

[0030] The high thermal conductivity refers to a thermal conductivity of 600 W / (m·K) or higher.

[0031] Furthermore, the polyacrylonitrile-based carbon fiber woven fabric is an M40J woven fabric;

[0032] The polyacrylonitrile-based carbon fiber unidirectional prepreg is carbon fiber M40J non-woven fabric;

[0033] The asphalt-based high thermal conductivity carbon fiber unidirectional prepreg is a high thermal conductivity carbon fiber nonwoven fabric.

[0034] And the ply angle is [±45] M40 / 90 D / 0 M40 / 0 M40 / 90 D / [±45] M40 .

[0035] Furthermore, the carbon fiber panel is provided with a plurality of arrayed waveguide insertion holes, and a reinforcing beam is provided in the aluminum honeycomb core sandwich layer at the position corresponding to the waveguide insertion holes.

[0036] Furthermore, the reinforcing beam is a C-shaped beam made of carbon fiber woven fabric, and a segmented metal support structure is provided inside the C-shaped beam.

[0037] Beneficial effects:

[0038] 1. The present invention provides a rectangular cylindrical box-type structure composed of an antenna mounting plate, a first outer side plate, a second outer side plate, and a base plate in a satellite structure based on structural reuse. A first main partition and a second main partition are arranged parallel to each other at one end of the rectangular cylindrical structure chamber, forming a first mounting cavity between them. A third main partition and a fourth main partition are arranged parallel to each other at the other end of the rectangular cylindrical structure chamber, forming a second mounting cavity between them. A third mounting cavity is formed between the second and third main partitions. Electronic device inserts are disposed within the first and second mounting cavities, constituting an insert-type structure. The single-unit installation structure includes a third mounting cavity for installing non-plug-in equipment, including battery packs for the power supply and distribution system, sensors, actuators, tanks, and pipelines for the control and propulsion system; the outer side of the antenna mounting plate is used to install SAR antenna units, and the inner side is used to install equipment including antenna waveguides, TR components, and power supplies; the outer surfaces of the first and second outer plates provide mounting interfaces for satellite array equipment, including solar panels; in the rectangular cylindrical box-plate structure, the first and second outer plates are adjacent, and satellite-rocket docking joints are provided at the junctions of the antenna mounting plate, the base plate, and the main partition, as well as at the junctions of the first outer plate, the base plate, and the main partition.

[0039] Thus, compared with traditional satellite structures, this invention adopts an integrated configuration of antenna mounting plate and satellite structure. The ground-facing module of the main satellite structure directly serves as the antenna mounting plate. The antenna unit, waveguide, TR component, power supply equipment, etc. of the SAR antenna are integrated and installed on the ground-facing (i.e., inner side) of the satellite structure using the antenna mounting plate. This greatly reduces the number of connecting structural components between the payload SAR antenna and the main satellite structure in the prior art, thereby reducing the satellite volume. This can improve the utilization rate of the satellite's overall payload envelope, giving the satellite structure a larger payload installation area and internal space, enabling the satellite to increase the antenna payload capacity and install more payloads and individual units.

[0040] In addition, the present invention installs the electronic equipment box between the two main bulkheads of the satellite structure. The main bulkheads are not only the core load-bearing components of the entire satellite structure, but also together with the electronic equipment box form the installation and packaging structure of the electronic equipment unit, realizing the integration of the electronic equipment box and the satellite structure, which can greatly improve the integration level of the entire satellite. Moreover, the location of the satellite-rocket docking joint meets the requirements of local high strength and high rigidity, and can transfer the load to the launch vehicle.

[0041] The satellite structure based on structural reuse provided by this invention achieves integration in two dimensions: the integration of the antenna mounting plate with the satellite structure and the integration of the electronic equipment enclosure with the satellite structure. This highly integrated design significantly reduces satellite mass and size, resulting in a compact overall structure. Simultaneously, it meets the performance requirements of highly maneuverable, low-cost satellites for high rigidity and low inertia. Compared to traditional satellite structures, it eliminates the need for compartmentalized design to accommodate large-area antenna payloads, significantly reducing satellite integration cycle and development costs, making it particularly suitable for microsatellites.

[0042] 2. The portion of the antenna mounting plate that protrudes from the rectangular cylindrical structure is supported by the antenna support structure, which improves the rigidity of the antenna mounting interface and enhances the antenna's installation dynamics.

[0043] 3. The antenna mounting plate is the same length as the rectangular cylindrical structure, and a fixed antenna array is mounted on the antenna mounting plate. Deployable antenna arrays that protrude from the rectangular cylindrical structure are mounted on the two opposite sides of the fixed antenna array in the longitudinal direction.

[0044] In this way, several antenna clamping seats are used to press the two sets of deployable antenna arrays onto the two opposite sides of the longitudinal direction of the satellite structure. At this time, the two main bulkheads located on the outer side of the satellite structure can also serve as the outer surface of the satellite to provide the installation interface for satellite surface equipment and the heat dissipation surface of the satellite.

[0045] 4. The “C”-shaped electronic device box is detachably connected to the partitions in the first and second mounting cavities, allowing for repeated disassembly and reassembly of the electronic device box and the satellite structure. This satisfies both the integrated design requirements and the requirements for disassembly and maintenance during the integration testing phase, making the integration of the electronic unit board and the electronic device box more flexible.

[0046] 5. The carbon fiber panel aluminum honeycomb sandwich panel is provided with multiple arrayed waveguide insertion holes, and a reinforcing beam is provided at the position of the waveguide insertion hole in the aluminum honeycomb core sandwich panel.

[0047] Therefore, because the waveguide components of the antenna have extremely high requirements for the positional and dimensional accuracy of the waveguide insertion holes, and the array-type opening method will also lead to a loss of strength and stiffness of the antenna mounting plate, reinforcing beams are set at the positions of the waveguide insertion holes in the aluminum honeycomb core sandwich to thicken the local honeycomb panel of the waveguide insertion holes to meet the depth requirements of the waveguide insertion holes, and effectively compensate for the loss of structural strength and stiffness caused by the array of waveguide insertion holes. At the same time, the reinforcing beams can provide sufficient support stiffness for the carbon fiber panel to avoid the problem of poor processing technology due to insufficient local structural stiffness during the processing of waveguide insertion holes after the structural plate is composite molded, which would affect the positional and dimensional accuracy of the waveguide insertion holes.

[0048] 6. The carbon fiber C-beam is equipped with a segmented metal support structure. This not only makes full use of the metal support structure to support the internal filling of the reinforcing beam and improve the normal stiffness of the structure, but also reduces the thermal mismatch between the metal support structure and the carbon fiber reinforcing beam in the length direction of the reinforcing beam. In addition, the excellent machinability of the metal better ensures the fitting accuracy between the metal support structure and the C-beam and constrains the carbon fiber panel material, avoiding the problem of carbon fiber panel delamination and burrs affecting the positional and dimensional accuracy of the waveguide insertion holes during machining. Attached Figure Description

[0049] Figure 1 This is a schematic diagram of a satellite structure based on structural reuse provided in Embodiment 1 of the present invention;

[0050] Figure 2 for Figure 1 A structural diagram excluding the antenna mounting plate;

[0051] Figure 3 for Figure 1 A structural diagram excluding the first and second outermost plates;

[0052] Figure 4 for Figure 1A schematic diagram of the integrated structure of the electronic equipment box and the satellite structure (only the electronic equipment box and the main bulkhead are shown in the figure), where (a) shows the installation of one electronic equipment box and (b) shows the installation of two electronic equipment boxes;

[0053] Figure 5 for Figure 4 Schematic diagram of the structure of the electronic equipment box in the middle;

[0054] Figure 6 This is a schematic diagram of a satellite structure based on structural reuse, including a deployable antenna, provided in Embodiment 2 of the present invention.

[0055] Figure 7 for Figure 6 The diagram shows the satellite structure unfolding in orbit.

[0056] Figure 8 for Figure 7 A schematic diagram of a deployable antenna array with one outer panel removed.

[0057] Figure 9 This is a schematic diagram of the structure of a circuit board for an electronic device.

[0058] Figure 10 A schematic diagram of the structure of an antenna mounting plate provided in Embodiment 3 of the present invention;

[0059] Figure 11 for Figure 10 A schematic diagram of the structure of the antenna mounting plate after removing a carbon fiber panel (aluminum honeycomb is not shown in the figure);

[0060] Figure 12 for Figure 10 Assembly diagram of the reinforcing beam and metal support structure in the central antenna mounting plate;

[0061] Figure 13 for Figure 12 Schematic diagram of the structure of the medium-strength beam blank;

[0062] Figure 14 for Figure 12 A schematic diagram of the metal support structure in the middle;

[0063] Figure 15 for Figure 12 Schematic diagram of the structure of the intermediate-strength beam;

[0064] Among them, 1-base plate, 1001-satellite docking interface, 2-antenna mounting plate, 201-ground surface, 202-sky surface, 3-main partition, 4-electronic equipment box, 401-guide rail plate, 402-box bottom plate, 403-connecting corner strip, 404-connecting corner box, 405-first side, 406-second side, 5-outer side plate, 6-antenna support structure, 7-clamping seat, 8-deployable antenna array, 9-waveguide insertion hole, 10-satellite docking connector embedded part, 11-aluminum heat pipe, 12-reinforcing beam. Detailed Implementation

[0065] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0066] Example 1:

[0067] Reference Figures 1-6 A satellite structure based on structural reuse includes a rectangular cylindrical structure (a cylindrical structure with a rectangular cross-section and open at both ends) consisting of an antenna mounting plate 2, two outer side plates 5 (referred to as the first outer side plate and the second outer side plate, respectively) connected by a base plate 1, and four main partitions 3 (referred to as the first main partition, the second main partition, the third main partition, and the fourth main partition, respectively), wherein:

[0068] The length of antenna mounting plate 2 is greater than the length of outer side plate 5 and bottom plate 1, causing rectangular cylindrical structures to protrude from opposite sides of antenna mounting plate 2. The first and second main partitions are arranged parallel to each other at one end of the rectangular cylindrical structure chamber as the first set of main partitions, forming a first mounting cavity between the first and second main partitions; the third and fourth main partitions are arranged parallel to each other at the other end of the rectangular cylindrical structure chamber as the second set of main partitions, forming a second mounting cavity between the third and fourth main partitions; a third mounting cavity is formed between the second and third main partitions; the volume of the third mounting cavity is greater than the volumes of the first and second mounting cavities; electronic equipment slots 4 are installed in the first and second mounting cavities, forming slots. The structure is a single-unit installation structure; the third mounting cavity is used to install non-plug-in equipment, including battery packs of the power supply and distribution system, sensors of the control and propulsion system, actuators, tanks, pipelines, etc.; the outer surfaces of the first and second outer plates are used to provide mounting interfaces for satellite table equipment, including solar panels; in the cylindrical structure, the first and second outer plates are adjacent, and the junctions of the antenna mounting plate 2, the base plate 1, and the main partition 3, as well as the junctions of the first outer plate, the base plate 1, and the main partition 3, are all provided with satellite-rocket docking joints as satellite-rocket docking interfaces 1001, and these junctions also serve as interfaces for parking the entire satellite.

[0069] Specifically, the external dimensions of the antenna mounting plate 2 are determined by the area required for antenna load installation and the overall satellite envelope size. In this embodiment, the antenna mounting plate 2 is a carbon fiber panel aluminum honeycomb sandwich structure plate. Its ground side 201 (i.e., the outer side) is used to install SAR antenna units, and its other side facing the sky side 202 (i.e., the inner side) is used to install SAR antenna waveguides, TR components, power supplies and other equipment.

[0070] In addition, such as Figures 1-3 As shown, the satellite structure based on structural reuse also includes antenna support structures 6 symmetrically arranged on both sides of the rectangular cylindrical structure. The antenna support structures 6 support the portion of the antenna mounting plate 2 that protrudes from the rectangular cylindrical structure, thereby improving the rigidity of the antenna mounting interface and enhancing the antenna's installation dynamics. The outer boundary of the antenna support structures 6 does not exceed the usable envelope of the entire satellite. In this embodiment, the structural plates in the antenna support structures 6 are all in the form of honeycomb sandwich structures, with three plates in each antenna support structure 6 directly connected to the antenna mounting plate 2. The shape of the antenna support structures 6 can be a right triangle, rectangle, or trapezoid, or it can be a rod structure or a support structure, depending on the overall satellite configuration requirements. The specific shape can be flexibly determined according to the overall satellite configuration.

[0071] In this embodiment, the antenna mounting plate 2 is rectangular, with its two longitudinal sides connected to the second outer side plate and the bottom plate respectively, and the other two sides connected to the antenna support structure 6. It is also internally connected to the main partition plate 3 to ensure that the satellite structure has sufficient rigidity and to provide a reasonable load environment for the antenna mounting interface.

[0072] More specifically, the aforementioned main partition 3 serves as both the main load-bearing structural plate, connected to the base plate 1, antenna mounting plate 2, and outer side plate 5 to bear the load of the transmitting section, and also provides an installation interface for the electronic equipment box 4, together forming the installation and packaging structure of the electronic equipment unit. For example... Figure 3 As shown, the electronic equipment box 4 is installed between the two main partitions 3 inside the satellite structure. The electronic equipment box 4 and the main partitions 3 together constitute the electronic equipment box mounting structure.

[0073] In this embodiment, as Figure 4 and Figure 5 As shown, each electronic device housing 4 adopts a "C"-shaped structure, including a housing base plate 402 and two guide rail plates 401 arranged opposite each other on the longitudinal sides of the housing base plate 402. The guide rail plates 401 and the housing base plate 402 are connected as a whole. During installation, the guide rail plates 401 are connected to the satellite structure via connecting corner strips 403, and the housing base plate 402 is connected to the satellite structure via connecting corner boxes 404. The integrated connection of the guide rail plates 401 and the housing base plate 402 in the electronic device housing 4 allows for complete disassembly from the satellite structure, meeting the requirements of detachability and maintainability.

[0074] More specifically, the guide rail plate 401 of the electronic equipment box 4 is a machined metal part, providing installation interfaces for single-unit boards, locking strips, sealing strips, etc. The second side 406 of the guide rail plate 401 is connected to the box base plate 402, and the first side 405 of the guide rail plate 401 is connected to the main partition plate 3 through the connecting corner strip 403 (the electronic equipment box 4 can also be directly connected to the main partition plate 3). The height of the guide rail plate 401 is determined by the installation requirements of the single-unit boards, and sufficient clearance is left between the guide rail plate 401, the box base plate 402 and the two main partition plates 3 of the satellite structure for repeated assembly and disassembly. It is worth noting that the number of electronic equipment boxes 4 in the first and second mounting cavities can be adjusted according to requirements. Moreover, a certain gap is left between the box base plate 402 in the electronic equipment box 4 and the inner side of the antenna mounting plate 2 to meet the requirements for installing SAR antenna waveguides, TR components, power supplies, and other equipment on the inner side of the antenna mounting plate 2.

[0075] like Figure 5 As shown, the base plate 402 of the electronic device box 4 can be made of machined metal or a honeycomb sandwich panel, providing a mounting interface for the electronic unit's PCB base plate. The shape of the base plate 402 of the electronic device box 4 meets the mounting requirements of the PCB base plate and the guide rail plate 401 of the electronic device box 4. In particular, referring to... Figure 9 In this embodiment, after the electronic device insert is installed into the first mounting cavity and the second mounting cavity, a closed body with one end open is formed, and the electronic device insert is encapsulated. Specifically, three sides of the electronic device insert are inside the mounting cavity, and one side is flush with the open end of the mounting cavity.

[0076] It should be noted that, to meet the temperature control requirements of the SAR antenna, a heat insulation pad is added between the antenna mounting plate 2 and other structural plates when they are connected. Where loads need to be transferred between the base plate 1, main partition plate 3, electronic equipment box 4, outer side plate 5, and antenna support structure 6, depending on the overlapping relationship of the structural components and boundary constraints, direct connection can be achieved using embedded parts between the honeycomb panels, or indirect connection can be achieved using metal connectors.

[0077] Example 2:

[0078] Unlike Embodiment 1, in order to further reduce the envelope of the entire satellite in its collapsed state and increase the SAR antenna payload capacity, in this embodiment, the antenna mounting plate 2 is the same length as the rectangular cylindrical structure, the antenna mounting plate 2 does not protrude from the rectangular cylindrical structure, and a fixed antenna array is mounted on the antenna mounting plate 2. Deployable antenna arrays 8 protruding from the rectangular cylindrical structure are mounted on the two opposite sides of the fixed antenna array in the longitudinal direction. Antenna clamping seats 7 are provided on the two opposite sides of the satellite structure in the longitudinal direction for clamping the deployable antenna arrays 8 in the collapsed state. That is, the entire satellite configuration adopts a planar SAR antenna payload consisting of a fixed antenna array (fixed on the antenna mounting plate 2) and two sets of deployable antenna arrays 8.

[0079] like Figure 7 As shown, after the satellite is launched into orbit, the deployable antenna array 8 is deployed using the antenna deployment mechanism. The two sets of deployable antenna arrays 8 and the fixed antenna array form a large antenna array.

[0080] like Figures 6-8 As shown, compared to Embodiment 1, the satellite structure is composed of several antenna clamping seats 7 to press two sets of deployable antenna arrays 8 onto the two sides of the satellite structure. In this case, the two main bulkheads 3 located on the outer side of the satellite structure can also serve as interfaces for installing satellite surface equipment and heat dissipation surfaces for the satellite.

[0081] Example 3:

[0082] Based on the above embodiment one or embodiment two, this embodiment provides a specific antenna mounting plate 2 structure.

[0083] like Figure 10-15 As shown, the antenna mounting plate 2 includes a carbon fiber panel aluminum honeycomb sandwich structure and an aluminum heat pipe 11. The carbon fiber panel in the carbon fiber panel aluminum honeycomb sandwich structure is composed of polyacrylonitrile-based carbon fiber woven fabric, polyacrylonitrile-based carbon fiber unidirectional prepreg, and pitch-based high thermal conductivity carbon fiber unidirectional prepreg, layered in a centrally symmetrical manner. The aluminum heat pipe 11 is embedded within the aluminum honeycomb core sandwich structure, and the length direction of the aluminum heat pipe 11 is orthogonal to the layup direction of the pitch-based high thermal conductivity carbon fiber unidirectional prepreg. Here, "high thermal conductivity" refers to a thermal conductivity of 600 W / mK or higher.

[0084] In contrast to traditional designs where the antenna, structural plate, and thermal management are separate development subsystems, and to integrated mechanical and thermal designs like the aluminum panel honeycomb sandwich structure with thermal management, this invention uses a carbon fiber panel aluminum honeycomb sandwich structure. The carbon fiber panel is composed of polyacrylonitrile-based carbon fiber woven fabric, polyacrylonitrile-based carbon fiber unidirectional prepreg, and pitch-based high thermal conductivity carbon fiber unidirectional prepreg, layered in a centrally symmetrical manner. Furthermore, the length direction of the embedded aluminum heat pipe 11 is orthogonal to the layup direction of the high thermal conductivity carbon fiber unidirectional prepreg. This allows the antenna mounting plate to possess high strength, high rigidity, high thermal conductivity, and low coefficient of thermal expansion. This enables it to meet the extremely high requirements of SAR antennas for lightweight design, high thermal conductivity, and high dimensional stability. While achieving high-precision SAR antenna installation, it also serves as the main load-bearing structure and incorporates thermal management functions. Therefore, the antenna mounting plate of this invention simultaneously possesses the functions of antenna integration installation, main structural support, efficient thermal management, and thermal dimensional stability, greatly improving the overall lightweight design of the satellite.

[0085] In this embodiment, placing the polyacrylonitrile-based carbon fiber woven fabric on the outermost layer of the carbon fiber panel effectively avoids delamination and burr problems in the carbon fiber panel during high-precision machining. The pitch-based high thermal conductivity carbon fiber unidirectional prepreg improves the thermal conductivity of the carbon fiber panel in the direction perpendicular to the aluminum heat pipe 11, while the polyacrylonitrile-based carbon fiber unidirectional prepreg improves the stiffness and strength of the carbon fiber panel along the heat pipe direction. Specifically, in this scheme, the three carbon fiber materials are mixed and layered in a centrally symmetrical manner: the middle layer of the carbon fiber panel is a polyacrylonitrile-based carbon fiber unidirectional prepreg layer; the upper and lower layers of the polyacrylonitrile-based carbon fiber unidirectional prepreg are both pitch-based high thermal conductivity carbon fiber unidirectional prepreg layers; and the outer layer of the pitch-based high thermal conductivity carbon fiber unidirectional prepreg layer is a polyacrylonitrile-based carbon fiber woven fabric layer.

[0086] It should be noted that the polyacrylonitrile-based carbon fiber woven fabric, polyacrylonitrile-based carbon fiber unidirectional prepreg, and pitch-based high thermal conductivity carbon fiber unidirectional prepreg each contain a variety of carbon fiber types to choose from. For example, the polyacrylonitrile-based carbon fiber woven fabric can use T-series or M-series carbon fiber woven fabric prepreg, and the polyacrylonitrile-based carbon fiber unidirectional prepreg can use M-series carbon fiber unidirectional prepreg. Specifically, in this embodiment, the polyacrylonitrile-based carbon fiber woven fabric is M40J woven fabric, the polyacrylonitrile-based carbon fiber unidirectional prepreg is M40J carbon fiber non-woven fabric, and the pitch-based high thermal conductivity carbon fiber unidirectional prepreg is high thermal conductivity carbon fiber non-woven fabric, and the layup angle is [±45°]. M40 / 90 D / 0 M40 / 0 M40 / 90 D / [±45] M40 The specific layer design is as follows: 1) [±45] M401) Refers to M40J woven fabric with a layup angle of 45° and a single layer thickness of 0.2mm; 2) 0 M40 : Refers to M40J non-woven carbon fiber fabric with a layup angle of 0° and a single layer thickness of 0.1mm; 3) 90 D : Refers to high thermal conductivity carbon fiber nonwoven fabric with a layup angle of 90° and a thermal conductivity of 600W / (m·K) or higher, with a single layer thickness of 0.1mm; 4) The total thickness of the six layers is 0.8mm, [±45] M40 For the bonding surface with the aluminum honeycomb core, the 0° direction is the length direction of the aluminum heat pipe 11, that is, along the direction in which the aluminum heat pipe 11 is embedded. More specifically, in this embodiment, in order to meet the thermal management requirements of the antenna assembly, four aluminum heat pipes 11 are embedded in the aluminum honeycomb core interlayer. After verification, the above-mentioned layup method can make the antenna mounting plate 2 have the best overall performance in terms of specific stiffness, thermal conductivity, flatness under high and low temperature conditions, and weight. For example, the thermal conductivity of the carbon fiber panel perpendicular to the length direction of the aluminum heat pipe 11 can reach 100W / (mK) (the heat expansion capacity per unit width is 80W / (m·K)*mm).

[0087] In addition, in this embodiment, multiple arrayed waveguide insertion holes 9 are provided on the carbon fiber panel, which enables the installation of large-scale arrayed waveguide SAR antennas. Moreover, a reinforcing beam 12 is provided at the position of the waveguide insertion hole 9 in the aluminum honeycomb core sandwich layer. Because the waveguide assembly of the SAR antenna has extremely high requirements for the positional accuracy, dimensional accuracy, and opening depth of the waveguide insertion hole 9, the arrayed opening method will also lead to a loss of strength and stiffness of the antenna mounting plate 2. The reinforcing beam 12 is provided at the position of the waveguide insertion hole 9 in the aluminum honeycomb core sandwich layer to meet the depth requirements of the waveguide insertion hole 9 (because the carbon fiber panel is too thin, the depth requirements of the waveguide insertion hole 9 are met by using the sum of the wall thickness of the reinforcing beam 12 and the thickness of the carbon fiber panel). In addition, it can effectively compensate for the structural strength and stiffness loss caused by the arrayed waveguide insertion hole 9. At the same time, the reinforcing beam 12 can provide sufficient support stiffness for the carbon fiber panel to avoid the problem of poor processing technology due to insufficient local structural stiffness during the processing of waveguide openings after the composite molding of the structural plate, which affects the positional accuracy and dimensional accuracy of the waveguide insertion hole 9.

[0088] In this embodiment, the aforementioned reinforcing beam 12 is a C-shaped beam made of carbon fiber T300 / woven fabric layup. The web thickness of the C-shaped beam is 0.8 mm, and the flange is locally thickened on the outside after the C-shaped section is laid up. The flange thickness is 1.6 mm. The length and embedding position of the C-shaped beam can be adjusted according to the waveguide insertion requirements.

[0089] As an improvement, a segmented metal support structure (made of aluminum in this embodiment) is provided within the C-shaped beam at predetermined intervals. This fully utilizes the metal support structure to support the internal filling of the reinforcing beam 12, giving the carbon fiber C-shaped beam good support stiffness. It also reduces the thermal mismatch between the metal support structure and the carbon fiber C-shaped beam along the length of the C-shaped beam. This is because the metal support structure can release thermal deformation at intervals, preventing overall thermal deformation of the metal support structure from causing warping of the antenna mounting plate 2 structure and affecting the dimensional stability of the antenna mounting plate 2. Furthermore, the excellent machinability of the metal better ensures the fitting accuracy between the metal support structure and the C-shaped beam and provides constraint on the carbon fiber panel material. As an improvement, the metal support structure includes a base plate and multiple ribs set on the base plate, forming a comb shape. Waveguide insertion holes 9 are located between adjacent ribs of the metal support structure. Thus, the metal support structure must be accurately inserted into the C-shaped beam according to the position of the waveguide insertion holes 9 using positioning fixtures to ensure that each waveguide insertion hole 9 is located in the center of two ribs of the metal support structure. It should be noted that the length of the base plate and the distribution of the ribs in the metal support structure can be adjusted according to actual needs. The "comb teeth" of the metal support structure provide supporting rigidity for each waveguide insertion hole 9 during machining, while ensuring the dimensional depth requirements of the waveguide insertion hole 9 in the height direction. Moreover, in this embodiment, the waveguide insertion hole 9 is obtained by integral machining after the carbon fiber panel is laminated onto the aluminum honeycomb with the pre-embedded reinforcing beam 12. This further ensures the positional accuracy, shape accuracy, and opening depth of the waveguide insertion hole 9.

[0090] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A satellite structure based on structural reuse, characterized in that, It includes a rectangular cylindrical structure consisting of an antenna mounting plate, a first outer side plate, a second outer side plate, and a base plate, as well as a first main partition, a second main partition, a third main partition, and a fourth main partition; The first and second main partitions are arranged in parallel at one end of the rectangular cylindrical structure chamber to form the first mounting cavity. The third and fourth main partitions are arranged in parallel at the other end of the rectangular cylindrical structure chamber to form a second mounting cavity; A third mounting cavity is formed between the second main partition and the third main partition; Electronic device boxes are installed in the first and second mounting cavities, forming a plug-in type single-unit mounting structure. The first main partition, the second main partition, the third main partition, and the fourth main partition are not only the core load-bearing components of the entire satellite structure, but also together with the electronic equipment box, they constitute the installation and packaging structure of the electronic equipment unit, realizing the integration of the electronic equipment box and the satellite structure. The electronic equipment box has a "C" shaped structure, and the "C" shaped structure is detachably connected to the partitions in the first and second mounting cavities. The third mounting cavity is used to install non-plug-in equipment, including battery packs for power supply and distribution systems, sensors, actuators, tanks, and pipelines for control and propulsion systems. The antenna mounting plate is located on the ground of the main structure of the satellite. The antenna mounting plate is connected to the first main partition, the second main partition, the third main partition, and the fourth main partition. The antenna mounting plate is not only the core load-bearing component of the entire satellite structure, but also used for the integrated installation of equipment including SAR antenna units, antenna waveguides, TR components, and power supplies. The outer side of the antenna mounting plate is used to install SAR antenna units, and the inner side is used to install equipment including antenna waveguides, TR components, and power supplies. The antenna mounting plate is a carbon fiber panel aluminum honeycomb sandwich structure with embedded aluminum heat pipes. The aluminum heat pipes are embedded in the aluminum honeycomb core sandwich structure. A reinforcing beam is provided in the aluminum honeycomb core sandwich structure at the position corresponding to the waveguide insertion hole. The reinforcing beam is a C-shaped beam made of carbon fiber woven fabric. The outer surfaces of the first and second outer plates are used to provide mounting interfaces for star table equipment, including solar panels. In the cylindrical structure, the first outer side plate and the second outer side plate are adjacent to each other, and star-rocket docking joints are provided at the junctions of the antenna mounting plate, the bottom plate, and the main partition plate, as well as at the junctions of the first outer side plate, the bottom plate, and the main partition plate.

2. A satellite structure based on structural reuse according to claim 1, characterized in that, The rectangular cylindrical structure extends out from two opposite sides of the antenna mounting plate, and the extended portion is supported by the antenna support structure.

3. A satellite structure based on structural reuse according to claim 1, characterized in that, The antenna mounting plate is the same length as the rectangular cylindrical structure, and a fixed antenna array is mounted on the antenna mounting plate. Deployable antenna arrays that protrude from the rectangular cylindrical structure are mounted on the two opposite sides of the fixed antenna array in the longitudinal direction.

4. A satellite structure based on structural reuse according to claim 1, characterized in that, The electronic device enclosure includes an enclosure base plate and two guide rail plates arranged opposite to each other on the longitudinal sides of the enclosure base plate; The guide rail plate is equipped with mounting interfaces including electronic device inserts, locking strips, and sealing strips.

5. A satellite structure based on structural reuse according to claim 4, characterized in that, The bottom plate of the insertion box has an aluminum honeycomb sandwich structure.

6. A satellite structure based on structural reuse according to any one of claims 1 to 5, characterized in that, The carbon fiber panel in the aluminum honeycomb sandwich structure is composed of polyacrylonitrile-based carbon fiber woven fabric, polyacrylonitrile-based carbon fiber unidirectional prepreg, and pitch-based high thermal conductivity carbon fiber unidirectional prepreg mixed and layered in a centrally symmetrical manner. The length direction of the aluminum heat pipe is orthogonal to the layup direction of the asphalt-based high thermal conductivity carbon fiber unidirectional prepreg. The polyacrylonitrile-based carbon fiber woven fabric is located on the outermost layer of the carbon fiber panel; The polyacrylonitrile-based carbon fiber unidirectional prepreg is located in the middle layer of the carbon fiber panel; The pitch-based high thermal conductivity carbon fiber unidirectional prepreg is located between the polyacrylonitrile-based carbon fiber woven fabric and the polyacrylonitrile-based carbon fiber unidirectional prepreg. The high thermal conductivity refers to a thermal conductivity of 600 W / (m·K) or higher.

7. A satellite structure based on structural reuse according to claim 6, characterized in that, The polyacrylonitrile-based carbon fiber woven fabric is an M40J woven fabric; The polyacrylonitrile-based carbon fiber unidirectional prepreg is carbon fiber M40J non-woven fabric; The asphalt-based high thermal conductivity carbon fiber unidirectional prepreg is a high thermal conductivity carbon fiber nonwoven fabric. And the ply angle is [±45] M40 / 90 D / 0 M40 / 0 M40 / 90 D / [±45] M40 .

8. A satellite structure based on structural reuse according to claim 6, characterized in that, The carbon fiber panel is provided with multiple arrayed waveguide insertion holes.

9. A satellite structure based on structural reuse according to claim 8, characterized in that, A segmented metal support structure is provided inside the C-shaped beam.

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