Rigid-flexible combined board and satellite and satellite system applicable to rigid-flexible combined board

Abstract

The utility model provides a rigid-flexible board and a satellite and a satellite system to which the rigid-flexible board is applicable, the rigid-flexible board is suitable for connecting each subsystem in the satellite to realize information interaction among the subsystems, and the rigid-flexible board comprises a rigid board comprising a signal transmission line; and a plurality of flexible plates, one end of each flexible plate is electrically connected with the rigid plate, and the other end of each flexible plate is electrically connected with the corresponding subsystem. The rigid-flexible combined board is electrically connected with each subsystem of the satellite through each flexible board electrically connected with one rigid board, so that data interaction among the subsystems in the satellite is realized, complicated and disordered data cables in the prior art can be integrated, and more concise and effective spatial layout in the satellite is realized.

Description

Technical Field

[0001] This application relates primarily to the field of satellites, and more particularly to a rigid-flexible composite plate and satellites and satellite systems applicable to it. Background Technology

[0002] Currently, the mainstream satellite backbone network assembly technology adopts conventional cable network design, resulting in a large number of cables in the satellite. This not only occupies a lot of space inside the satellite, but also makes it difficult to achieve automated assembly, reducing the satellite manufacturing efficiency and increasing the requirements and difficulty of quality inspection.

[0003] Furthermore, some satellite structures employ multiple rigid and flexible plates connected in complex ways to achieve internal data exchange. However, this approach requires the sequential installation of each rigid and flexible plate during assembly, which presents challenges such as high automation difficulty, slow assembly speed, and a complex assembly process that indirectly increases the risk of collisions during assembly, leading to a decrease in the quality of the finished product.

[0004] Therefore, existing satellite cable networks and rigid and flexible plate technologies cannot meet the needs of mass-producing satellites. Utility Model Content

[0005] The technical problem to be solved by this application is to provide a rigid-flexible composite board and its applicable satellites and satellite systems, which improves the manufacturing efficiency and quality of satellites by integrating the internal circuitry of the satellite.

[0006] To address the aforementioned technical problems, this application provides a rigid-flexible composite board suitable for connecting various subsystems in a satellite to enable information exchange between them. The rigid-flexible composite board includes: a rigid board containing signal transmission lines; and multiple flexible boards, one end of each flexible board being electrically connected to the rigid board, and the other end of each flexible board being electrically connected to the corresponding subsystem.

[0007] Optionally, the flexible panel includes at least one plug disposed at the other end, each plug being used for information data corresponding to a function of the interactive subsystem.

[0008] Optionally, the flexible panel also includes a flexible region, the top and bottom layers of which are each covered with an anti-abrasion layer.

[0009] Optionally, the satellite also includes an extension function module for implementing corresponding extension functions, and the rigid-flexible plate also includes at least one connector disposed on the rigid plate for electrical connection with the extension function module.

[0010] Optionally, the rigid plate is provided with metallized mounting holes for fixing the rigid-flexible plate to the satellite shell.

[0011] Optionally, the signal wiring of the flexible board includes differential signal wiring.

[0012] Optionally, differential signal routing is carried out in accordance with equal length, equal width, and equal spacing, wherein the positive and negative signals of the same signal are distributed on the same layer of the flexible board; and / or the adjacent layers of the same flexible board use ground signal copper as the characteristic impedance reference plane.

[0013] Alternatively, the flexible sheet may be made of polyimide.

[0014] Optionally, each layer edge of the rigid board has more than 10 mil of gridless printed lines, and / or each layer edge of the flexible board has more than 10 mil of gridless printed lines.

[0015] Optionally, the length of the rigid plate is set according to the location of each subsystem.

[0016] Optionally, the length can range from 1 meter to 1.5 meters.

[0017] Optionally, when the satellite is a flat-panel satellite, the width of the rigid plate is set according to the thickness of the satellite.

[0018] Optionally, the width ranges from 20 cm to 40 cm.

[0019] Optionally, the thickness of the rigid plate shall not exceed 5 cm.

[0020] Optionally, the extension length of the flexible sheet shall not exceed 30 cm.

[0021] Optionally, the subsystem includes an energy subsystem, a space service subsystem, a payload subsystem, and an attitude and orbit control subsystem.

[0022] To address the aforementioned technical problems, this application provides a satellite comprising: multiple subsystems for implementing multiple functions; and the aforementioned rigid-flexible composite plate for connecting the various subsystems.

[0023] Optionally, in the above-mentioned satellite, the satellite is a flat-panel satellite, and the width direction of the rigid-flexible plate is parallel to the thickness direction of the satellite.

[0024] To address the aforementioned technical problems, this application provides a satellite system comprising multiple satellites as described above, wherein the satellites are adapted to communicate with each other.

[0025] The satellite of this application can be manufactured using the following satellite manufacturing method, including the following steps: designing and manufacturing a rigid-flexible composite plate and a shell according to the functional requirements of the satellite. The rigid-flexible composite plate includes a rigid plate and multiple flexible plates. The rigid plate contains signal transmission lines, and one end of each flexible plate is electrically connected to the rigid plate. The rigid plate is fixedly connected to the shell. The various subsystems of the satellite are fixed to their corresponding preset positions on the shell. Each flexible plate is electrically connected to its corresponding subsystem.

[0026] Compared with existing technologies, this application has the following advantages: By electrically connecting each flexible plate, which is electrically connected to a rigid plate, to each subsystem of the satellite, data interaction between the various subsystems within the satellite is achieved. This integrates the complex and messy data cables of existing technologies, resulting in a simpler and more efficient spatial layout within the satellite. The connectors installed on the rigid plate enable functional expansion of the satellite, ensuring that all connection cables for devices requiring interaction within the satellite are consolidated onto a single rigid-flex plate. The metallized mounting holes, wear-resistant layer, and grid-free printed lines effectively prevent damage to the rigid-flex plate during automated assembly, thereby improving the finished product quality. By limiting the length, width, and thickness of the rigid plate, as well as the extension length of the flexible plate, the internal spatial layout of the satellite can be further optimized, thus optimizing the overall size of the satellite. By setting the width direction of the rigid-flex plate installed in the flat-panel satellite parallel to the thickness direction of the flat-panel satellite, the internal space of the flat-panel satellite can be fully utilized, avoiding the space occupation by messy data cables and effectively reducing the overall size of the flat-panel satellite. Attached Figure Description

[0027] The accompanying drawings are included to provide a further understanding of this application; they are incorporated into and constitute a part of this application. The drawings illustrate embodiments of this application and, together with this specification, serve to explain the principles of this application. In the drawings:

[0028] Figure 1 This is a schematic diagram of a rigid-flexible composite plate according to an embodiment of this application;

[0029] Figure 2 This is a side view of a rigid-flexible composite plate in its installation state according to an embodiment of this application;

[0030] Figure 3 This is a schematic diagram of a satellite centering system and a rigid-flexible composite plate according to an embodiment of this application; and

[0031] Figure 4 This is a schematic flowchart of a satellite manufacturing method according to an embodiment of this application. Detailed Implementation

[0032] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely some examples or embodiments of this application. For those skilled in the art, these drawings can be applied to other similar scenarios without creative effort. Unless obvious from the context or otherwise specified, the same reference numerals in the drawings represent the same structures or operations.

[0033] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0034] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this application. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0035] In the description of this application, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is usually based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this application and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this application; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0036] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0037] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, these terms have no special meaning and therefore should not be construed as limiting the scope of protection of this application. In addition, although the terminology used in this application is selected from commonly known and used terms, some terms mentioned in this application's specification may have been chosen by the applicant according to his or her judgment, and their detailed meanings are explained in the relevant sections of this description. Moreover, this application should be understood not only through the actual terms used, but also through the meaning implied by each term.

[0038] It should be understood that when a component is referred to as "on another component," "connected to another component," "coupled to another component," or "in contact with another component," it may be directly on, connected to, coupled to, or in contact with that other component, or there may be an insert component. In contrast, when a component is referred to as "directly on another component," "directly connected to," "directly coupled to," or "directly in contact with" another component, there is no insert component. Similarly, when a first component is referred to as "electrically contacting" or "electrically coupled to" a second component, there is an electrical path between the first and second components that allows current to flow. This electrical path may include capacitors, coupled inductors, and / or other components that allow current to flow, even without direct contact between the conductive components. Flowcharts are used in this application to illustrate the operations performed by a system according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, various steps may be processed in reverse order or simultaneously. Simultaneously, other operations may be added to these processes, or one or more operations may be removed from these processes.

[0039] This application refers to Figures 1-2A structural schematic diagram of a rigid-flexible plate 10 is presented. This plate is suitable for connecting various subsystems within a satellite to enable information exchange between them. Preferably, the subsystems include an energy subsystem, a satellite service subsystem, a payload subsystem, and an attitude and orbit control subsystem. It should be noted that the manufacturing and installation of the rigid-flexible plate 10 utilize automated production lines and / or industrial robots, enabling rapid and large-scale mass production of the rigid-flexible plate 10 and satellites equipped with it. For example, in the "Thousand Sails Constellation" program, more than 500 satellites for networking are required to be launched annually; these satellites can utilize the rigid-flexible plate 10 for efficient mass production.

[0040] First refer to Figure 1 The rigid-flexible composite plate 10 includes a rigid plate 11 containing signal transmission lines, multiple flexible plates 12, and multiple connectors 13. Preferably, the rigid plate 11 is provided with metallized mounting holes (not shown in the figure) for fixing the rigid-flexible composite plate 10 to the satellite's casing. The metallized mounting holes can prevent screws from scratching and wearing the rigid plate 11 during automated assembly, thereby improving the quality of the finished product from automated assembly.

[0041] Preferably, the length of the rigid plate 11 along the a-a' extension direction is set according to the position of each subsystem. Preferably, the length of the rigid plate 11 is set to a range of 1 meter to 1.5 meters. Preferably, when the satellite is a flat-panel satellite, the width of the rigid plate 11 along the b-b' extension direction is set according to the thickness of the satellite. Preferably, the width of the rigid plate 11 is in the range of 20 centimeters to 40 centimeters. Preferably, the thickness of the rigid plate 11 along the c-c' extension direction is no more than 5 centimeters. For example, for the networking satellites in the "Qianfan Constellation" plan, if the networking satellites are flat-panel satellites, the length of the rigid-flexible plate 10 is 1.1 meters, the width is 28 centimeters, and the thickness is 3.4 centimeters, thereby further optimizing the overall size of the networking satellites, and thus enabling the launch of multiple satellites in one launch, such as 18 satellites in one launch, by stacking networking satellites.

[0042] Continue to refer to Figure 1Each flexible board 12 has one end electrically connected to a rigid board 11, and the other end electrically connected to a corresponding subsystem. The flexible board 12 includes at least one plug 121 and a flexible area 122 located at its other end (i.e., the end electrically connected to the subsystem). Each plug 121 is used to exchange information data corresponding to a function of the subsystem. Preferably, the signal wiring of the flexible board 12 includes differential signal wiring. Specifically, the differential signal wiring is routed with equal length, equal width, and equal spacing, wherein the positive and negative signals of the same signal are distributed on the same layer of the flexible board 12, or adjacent layers of the same flexible board 12 use ground signal copper as the characteristic impedance reference surface, or the positive and negative signals of the same signal are distributed on the same layer of the flexible board 12 and adjacent layers of the same flexible board 12 use ground signal copper as the characteristic impedance reference surface. It should be noted that in this embodiment, the characteristic impedance of the flexible board 12 for CANA and CANB signals is designed to be 120Ω ± 10%, and the characteristic impedance of other signals is designed to be 100Ω ± 10%. Preferably, the flexible plate 12 is made of polyimide (PI), thereby enabling arbitrary bending of the flexible plate 12 body. For example, see reference... Figure 2 , Figure 2 An example is shown showing the positional state of the flexible panel 12 when it is connected to the subsystem, such as... Figure 2 As shown, multiple flexible plates 12 are extended along the c-c' extension direction, i.e. the thickness direction of the rigid plate 11, to realize electrical connection of the subsystems dispersed around the rigid plate 11.

[0043] Preferably, the top and bottom layers of the flexible region 122 of the flexible plate 12 are each covered with an anti-wear layer. This anti-wear layer can prevent the flexible plate 12 from being worn during movement in the automated assembly process, or from being scratched by parts or installation equipment during installation, effectively improving the yield of the rigid-flexible composite plate 10 and its satellite. It should be noted that, in this embodiment, the flexible region 122 of the flexible plate 12 is the area of ​​the flexible plate that can be bent arbitrarily. For example, in one embodiment, the flexible region 122 can be all areas of the flexible plate 12 except for the plug 121.

[0044] Preferably, the extension length of the flexible plate 12 is no more than 30 cm. For example, Figure 1 If the extension direction of the flexible plate 12 is the b-b' extension direction, then the length of the flexible plate 12 in the b-b' extension direction shall not exceed 30 cm. By limiting the extension length of the flexible plate 12, the subsystem can be brought closer to the rigid-flexible plate 10, thereby optimizing the structural space within the satellite and resulting in a smaller overall size for the satellite.

[0045] Preferably, in this embodiment, each layer edge of the rigid plate 11 has a meshless printed line of more than 10 mils, or each layer edge of the flexible plate 12 has a meshless printed line of more than 10 mils, or both the rigid plate 11 and the flexible plate 12 have the above-mentioned meshless printed line design. In this way, the tear resistance of the flexible area 122 in the flexible plate 12 can be improved.

[0046] Continue to refer to Figure 1 Connector 13 is mounted on rigid plate 11 and is used for electrical connection with the satellite's expansion function module, which is used to implement corresponding expansion functions. It should be noted that in this embodiment, the rigid-flexible plate 10 corresponding to the satellite includes connector 13. In other embodiments where the satellite only has a subsystem and no expansion function module, the corresponding rigid-flexible plate 10 may not include connector 13. Through the aforementioned rigid-flexible plate 10, all devices in the satellite that need to exchange data can be connected, thereby achieving unified integration of data cables between various devices, reducing the space occupied by data cables within the satellite, and further optimizing the overall structure of the satellite.

[0047] Another aspect of this application refers to Figure 3 A satellite 100 is also proposed, comprising a rigid-flexible plate 10 and multiple subsystems 20, wherein the rigid-flexible plate 10 is used to connect the various subsystems 20. Preferably, the satellite 100 is a flat-panel satellite, and the width direction, i.e., the b-b' extension direction, of the rigid-flexible plate 10 is parallel to the thickness direction of the satellite 100. For example, the flat surface of the flat-panel satellite is... Figure 3 The rigid-flexible composite plate 10 is vertically arranged on the flat plate along the b-b' extension direction, thereby reducing the space occupied by the rigid-flexible composite plate 10 inside the satellite and achieving further compactness of the overall satellite size. It should be noted that other arrangements of the subsystem 20 and the rigid-flexible composite plate 10 can be referred to the specific content of the above embodiment, and will not be repeated here. Furthermore, Figure 3 The illustration only shows four subsystems 20 and their respective arrangements on both sides of the rigid-flexible composite plate 10, thereby improving the utilization rate of the rigid-flexible composite plate 10 and the utilization rate of the satellite's internal space. However, it does not limit other arrangements of the subsystems 20, such as the subsystems 20 being arranged only on one side of the rigid-flexible composite plate 10. To better illustrate the structure of the satellite 100 proposed in this application, another aspect of this application is referenced. Figure 4A satellite manufacturing method 200 is also proposed. This satellite manufacturing method 200 includes the following steps: Step S1 is to design and manufacture the rigid-flexible composite plate 10 and the shell according to the functional requirements of the satellite 100. Step S2 is to fix the rigid plate 11 to the shell. Step S3 is to fix each subsystem 20 of the satellite 100 to its corresponding preset position on the shell. Step S4 is to electrically connect each flexible plate 12 to its corresponding subsystem 20. It should be noted that the satellite manufacturing method 200 employs automated assembly and manufacturing methods. Combined with the settings described above, it can significantly improve the quality of the rigid-flexible composite plate 10. Therefore, frequent quality inspections of the rigid-flexible composite plate 10 during the manufacturing process are unnecessary (or even eliminated altogether), thereby greatly improving the manufacturing efficiency of the rigid-flexible composite plate 10. Furthermore, when performing performance testing on the assembled satellite 100, if there are performance problems related to the rigid-flexible bonding plate 10, the original rigid-flexible bonding plate 10 can be directly removed from the satellite 100 and replaced with a new rigid-flexible bonding plate 10 before performance testing. There is no need to perform fault analysis on the original rigid-flexible bonding plate 10, thereby accelerating the mass production of the satellite 100.

[0048] Another aspect of this application proposes a satellite system comprising multiple satellites 100, which are adapted to communicate with each other. This satellite system, having the rigid-flexible hybrid design proposed in this application for satellite design, possesses the advantages of the embodiments described above, which will not be repeated here.

[0049] The basic concepts have been described above. Obviously, for those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application, and therefore remain within the spirit and scope of the exemplary embodiments of this application.

[0050] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0051] Similarly, it should be noted that, in order to simplify the description of the present application and thus aid in the understanding of one or more embodiments, the foregoing description of the embodiments of the present application sometimes combines multiple features into a single embodiment, drawing, or description thereof. However, this disclosure method does not imply that the subject matter of the present application requires more features than those mentioned in the claims. In fact, the embodiments contain fewer features than all the features of the single embodiments disclosed above.

[0052] In some embodiments, numbers describing the quantity of components and attributes are used. It should be understood that such numbers used in the description of embodiments are modified in some examples with the terms "approximately," "approximately," or "generally." Unless otherwise stated, "approximately," "approximately," or "generally" indicates that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, which may be changed depending on the characteristics required by individual embodiments. In some embodiments, numerical parameters should take into account specified significant digits and employ a general method of digit reservation. Although the numerical ranges and parameters used to confirm their breadth of scope in some embodiments of this application are approximate values, in specific embodiments, such values ​​are set as precisely as feasible.

[0053] Although this application has been described with reference to specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, any changes or modifications to the above embodiments within the essential spirit of this application will fall within the scope of the claims of this application.

Claims

1. A rigid-flexible composite board, characterized in that, Suitable for connecting various subsystems in a satellite to enable information exchange between the various subsystems, the rigid-flexible composite plate includes: A rigid plate containing signal transmission lines; and Multiple flexible plates, one end of each flexible plate is electrically connected to the rigid plate, and the other end of each flexible plate is electrically connected to the corresponding subsystem.

2. The rigid-flexible composite plate as described in claim 1, characterized in that, The flexible board includes at least one plug disposed at the other end, each plug being used to exchange information data corresponding to a function of the subsystem.

3. The rigid-flexible composite plate as described in claim 2, characterized in that, The flexible board also includes a flexible region, the top and bottom layers of which are each covered with an anti-wear layer.

4. The rigid-flexible composite plate as described in claim 1, characterized in that, The satellite also includes an extended function module, which is used to implement corresponding extended functions. The rigid-flexible composite plate also includes at least one connector disposed on the rigid plate, the connector being used for electrical connection with the extended functional module.

5. The rigid-flexible composite plate as described in claim 1, characterized in that, The rigid plate is provided with metallized mounting holes for fixing the rigid-flexible plate to the satellite shell.

6. The rigid-flexible composite plate as described in claim 1, characterized in that, The signal wiring of the flexible board includes differential signal wiring.

7. The rigid-flexible composite plate as described in claim 6, characterized in that, The differential signal wiring is routed according to equal length, equal width, and equal spacing, wherein, The positive and negative signals of the same signal are distributed in the same layer of the flexible plate; and / or The adjacent layers of the same flexible board use ground signal copper cladding as the characteristic impedance reference plane.

8. The rigid-flexible composite plate as described in claim 1, characterized in that, The flexible plate is made of polyimide.

9. The rigid-flexible composite plate as described in claim 1, characterized in that, The rigid plate has more than 10 mil of grid-free printed lines on each edge, and / or the flexible plate has more than 10 mil of grid-free printed lines on each edge.

10. The rigid-flexible composite plate as described in claim 1, characterized in that, The length of the rigid plate is set according to the location of each of the subsystems.

11. The rigid-flexible composite plate as described in claim 10, characterized in that, The length ranges from 1 meter to 1.5 meters.

12. The rigid-flexible composite plate as described in claim 1, characterized in that, When the satellite is a flat-panel satellite, the width of the rigid plate is set according to the thickness of the satellite.

13. The rigid-flexible composite plate as described in claim 12, characterized in that, The width ranges from 20 cm to 40 cm.

14. The rigid-flexible composite plate as described in claim 1, characterized in that, The thickness of the rigid plate is no more than 5 centimeters.

15. The rigid-flexible composite plate as described in claim 1, characterized in that, The extension length of the flexible plate is no more than 30 centimeters.

16. The rigid-flexible composite plate as described in claim 1, characterized in that, The subsystems include the energy subsystem, the space service subsystem, the payload subsystem, and the attitude and orbit control subsystem.

17. A satellite, characterized in that, The satellites include: Multiple subsystems are used to implement multiple functions; and The rigid-flexible composite plate as described in any one of claims 1-16 is used to connect the various subsystems.

18. The satellite as claimed in claim 17, characterized in that, The satellite is a flat-panel satellite, and the width direction of the rigid-flexible composite plate is parallel to the thickness direction of the satellite.

19. A satellite system, characterized in that, The satellite system includes: Multiple satellites as described in any one of claims 17-18, wherein the satellites are adapted to communicate with each other.

Images