Multifunctional flat panel satellite system

Abstract

The present application provides a multifunctional flat-panel satellite system, which has a launch state and an on-orbit operation state. When in the launch state, the equipment outside the payload cabin is folded relative to the satellite to the ground, so that the multifunctional flat-panel satellite system is flattened; when in the on-orbit operation state, the equipment outside the payload cabin is unfolded relative to the satellite to the ground, so as to realize the corresponding functions of the multifunctional flat-panel satellite system, thereby achieving a higher space utilization rate. And through the design of the flat-panel satellite basic platform, the networked intelligent module, the flat-panel replaceable payload module and the comprehensive processing module, starting from the payload adaptability design and the satellite platform standardization and unified design, without changing the satellite platform design of the flat-panel satellite, it can adapt to a variety of payload types (including but not limited to: communication, navigation, remote sensing, etc.), and make full use of the functions of the payload carried, so as to effectively adapt to the mass production and launch needs of satellites in different fields.

Description

Technical Field

[0001] The present application mainly relates to the field of satellite technology, and in particular to a multifunctional flat-panel satellite system. Background Art

[0002] The flat-panel satellite configuration has the characteristics of large equipment installation surface and multiple heat dissipation surfaces, which plays a very positive role in meeting the existing large-scale and rapid deployment of satellite launch needs. However, the current flat-panel satellites are either not suitable for large payloads such as phased array antennas and high-precision cameras, or cannot fully utilize the functions of the payloads they carry, and have many shortcomings. Summary of the invention

[0003] The purpose of the present application is to provide a multifunctional flat-panel satellite system to overcome the problem that the current flat-panel satellites have insufficient payload types and single functions.

[0004] To achieve the above-mentioned purpose, in a first aspect, the present application provides a multifunctional flat-panel satellite system, which has a launch state and an on-orbit operation state, and includes: a flat-panel satellite basic platform, a networked intelligent module, a flat-panel replaceable payload module, and a comprehensive processing module;

[0005] The flat-plate replaceable payload module includes a plurality of payload external equipment, one or more of the plurality of payload external equipment being capable of being folded or unfolded relative to an equipment mounting surface;

[0006] The flat-panel satellite basic platform is mechanically, electrically and thermally connected to the networked intelligent module, the flat-panel replaceable payload module and the integrated processing module, and the integrated processing module is electrically connected to the multiple payload off-board equipment;

[0007] When the multifunctional flat-panel satellite system is in a launching state, one or more of the plurality of payload external equipment are folded relative to the equipment mounting surface so that the multifunctional flat-panel satellite system is flattened;

[0008] When the multifunctional flat-panel satellite system is in an on-orbit operation state, one or more of the plurality of payload external equipment are unfolded relative to the equipment installation surface to realize the corresponding function of the multifunctional flat-panel satellite system.

[0009] In some embodiments, the device mounting surface is the satellite-to-ground surface of the flat-panel satellite base platform;

[0010] The networked intelligent module is used to provide general hardware resources for network communication and intelligent computing;

[0011] The comprehensive processing module is used to realize the payload signal and information processing function matching the multiple payload external equipment.

[0012] In some embodiments, the payload extravehicular equipment includes a phased array antenna and / or a periscope imaging device;

[0013] The adjacent array antennas and / or periscope imaging equipment are installed on the ground of the satellite and packaged into a flat structure.

[0014] In some embodiments, the payload external equipment includes a foldable synthetic aperture radar phased array antenna, and the foldable synthetic aperture radar phased array antenna has a folded state and an unfolded state;

[0015] The foldable synthetic aperture radar phased array antenna comprises at least two antenna panels foldably connected; wherein:

[0016] When the foldable synthetic aperture radar phased array antenna is in a folded state, the at least two antenna panels are folded, connected and fixed to the satellite ground, so that the multifunctional flat-panel satellite system is flattened;

[0017] When the foldable synthetic aperture radar phased array antenna is in an unfolded state, one of the at least two antenna panels is fixed to the satellite facing the ground, and the remaining antenna panels extend along a preset direction to the edge of the flat-panel satellite base platform or beyond the edge of the flat-panel satellite base platform to realize the corresponding functions of the multifunctional flat-panel satellite system.

[0018] In some embodiments, the payload external device includes a foldable imaging device, wherein the foldable imaging device has a folded state and an unfolded state;

[0019] The foldable imaging device comprises a first imaging component, a second imaging component and a foldable light shield which are foldably connected, wherein the foldable light shield is arranged between the first imaging component and the second imaging component and can move relatively;

[0020] When the foldable imaging device is in a folded state, one side of the first imaging component is fixed to the satellite-to-ground, and all or part of the surface of the second imaging component is attached to the satellite-to-ground, so that the multifunctional flat-panel satellite system is flattened;

[0021] When the foldable imaging device is in an unfolded state, the second imaging component extends to a preset position in a direction perpendicular to the first imaging component, and an imaging space is formed between the second imaging component, the foldable light shield and the first imaging component to realize the corresponding functions of the multifunctional flat-panel satellite system.

[0022] In some embodiments, the flat-panel satellite base platform is provided with an electrical connector and a fixed bracket, the fixed bracket is mounted on the flat-panel satellite base platform, the electrical connector is mounted on the fixed bracket, and the electrical connector is used to adapt to the thermal and electrical performance requirements of each payload compartment external equipment.

[0023] In some embodiments, the general hardware resources provided by the networked intelligent module include any one or a combination of the following:

[0024] Shared laser and microwave intersatellite link terminals, on-board routers and switches, satellite-to-ground link terminals and on-board intelligent computers.

[0025] In some embodiments, the integrated processing module includes a baseboard, a power management board, a software reconstruction control board, a multifunctional software storage board, a signal processing board, and a general computing board;

[0026] The power management board, the software reconstruction control board, the multifunctional software storage board, the signal processing board and the general computing board are plugged into the slots of the baseboard;

[0027] The power management board is powered by the baseboard;

[0028] The multifunctional software storage board, the signal processing board and the general computing board are used to provide software and computing power for the payload function;

[0029] The software reconstruction control panel is used to control the software reconstruction corresponding to the load function.

[0030] In some embodiments, the software reconstruction control board is configured to control one or more software units in the multifunctional software storage board to be replaced to the signal processing board and the general computing board; and,

[0031] The software reconstruction control board is configured to control the remaining software units to cache the data generated by the operation into the cache unit during the replacement process, wherein the software unit is obtained by decomposing the software corresponding to the load function.

[0032] In some embodiments, there are one or more cache units, each of which is used to cache data generated by the execution of one or more corresponding software units.

[0033] In some embodiments, the software reconstruction control board is configured to control the capacity of the cache unit according to a load function.

[0034] In some embodiments, the corresponding functions of the multifunctional flat-panel satellite system include any one or a combination of the following:

[0035] Communications, navigation, radar detection, synthetic aperture radar imaging, visible light imaging, hyperspectral imaging, and infrared imaging.

[0036] Compared with the prior art, this application has the following advantages:

[0037] The present application provides a multifunctional flat-panel satellite system, which has a launch state and an on-orbit operation state. When in the launch state, the equipment outside the payload cabin is folded relative to the satellite to the ground, so that the multifunctional flat-panel satellite system is flattened; when in the on-orbit operation state, the equipment outside the payload cabin is unfolded relative to the satellite to the ground, so as to realize the corresponding functions of the multifunctional flat-panel satellite system, thereby achieving a higher launch and carrier space utilization rate. And through the design of the flat-panel satellite basic platform, networked intelligent module, flat-panel replaceable payload module and comprehensive processing module, starting from the payload adaptability design and the satellite platform standardization and unified design, without changing the satellite platform design of the flat-panel satellite, it can adapt to a variety of payload types (including but not limited to: communication, navigation, remote sensing, etc.), and make full use of the functions of the payload carried, so as to effectively adapt to the mass production and launch needs of satellites in different fields. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The accompanying drawings are included to provide a further understanding of the present application. They are included and constitute a part of the present application. The accompanying drawings illustrate embodiments of the present application and together with the present specification serve to explain the principles of the present application. In the accompanying drawings:

[0039] Figure 1 This is a schematic diagram of the overall connection structure of a multifunctional flat-panel satellite system provided by the present application as an example;

[0040] Figure 2 It is a schematic diagram of the internal structure of a flat-plate replaceable load module exemplarily provided in the present application;

[0041] Figure 3 This is a schematic structural diagram of a multifunctional flat-panel satellite system provided by the present application when it is in a launching state and an on-orbit operation state;

[0042] Figure 4 This is one of the structural schematic diagrams of a multifunctional flat-panel satellite system provided by the present application when it is in a launching state;

[0043] Figure 5 This is one of the structural schematic diagrams of a multifunctional flat-panel satellite system provided by the present application when it is in an on-orbit operation state;

[0044] Figure 6 This is the second structural schematic diagram of a multifunctional flat-panel satellite system in a launching state provided by the present application as an example;

[0045] Figure 7 This is the second structural schematic diagram of a multifunctional flat-panel satellite system provided by the present application when it is in an on-orbit operation state;

[0046] Figure 8 is a schematic diagram of a flat-panel satellite basic platform exemplarily provided in the present application;

[0047] Fig. 9 is a schematic diagram of a networked intelligent module exemplarily provided by the present application;

[0048] Fig.10 is a schematic diagram of an integrated processing module exemplarily provided in the present application;

[0049] Fig.11 is a schematic diagram of a first reconstruction method exemplarily provided in this application;

[0050] Fig.12 It is a schematic diagram of a second reconstruction method exemplarily provided in this application. DETAILED DESCRIPTION

[0051] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for the description of the embodiments. Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. Unless it is obvious from the language environment or otherwise explained, the same reference numerals in the figures represent the same structure or operation.

[0052] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0053] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0054] The directional terms mentioned in the embodiments of the present application, such as "upper", "lower", "side", "top", "bottom", etc., only refer to the directions with reference to the accompanying drawings. Therefore, the directional terms used are for better and clearer explanation and understanding of the embodiments of the present application, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the embodiments of the present application.

[0055] The “electromechanical and thermal connection” mentioned in the embodiments of the present application refers to the mechanical connection, electrical connection and thermal connection between the corresponding two modules.

[0056] Combined with reference Figure 1 , Figure 2 , Figure 1 1 is a schematic diagram of the overall connection structure of the multifunctional flat-panel satellite system 1000. Figure 2 Schematic diagram of the internal structure of the flat-plate replaceable load module 300.

[0057] In some embodiments, the multifunctional flat-panel satellite system 1000 includes a flat-panel satellite basic platform 100 , a networked intelligent module 200 , a flat-panel replaceable payload module 300 , and an integrated processing module 400 .

[0058] The flat-panel satellite basic platform 100 is connected to the networked intelligent module 200, the flat-panel replaceable payload module 300 and the integrated processing module 400 by electromechanical and thermal means. Figure 1 The flat-panel replaceable payload module 300 is electromechanically and thermally connected to the flat-panel satellite basic platform 100, and is electrically connected to the integrated information processing module 400. The integrated information processing module 400 is electromechanically and thermally connected to the flat-panel satellite basic platform 100, and is electrically connected to the networked intelligent module 200. The networked intelligent module 200 is electromechanically and thermally connected to the flat-panel satellite basic platform 100.

[0059] The flat-plate replaceable payload module 300 includes a plurality of payload external equipment 301 , one or more of which can be folded or unfolded relative to an equipment mounting surface.

[0060] In some embodiments, the flat-panel satellite base platform 100 has a satellite-to-ground surface and a satellite-to-sky surface. Any one of the satellite-to-ground surface and the satellite-to-sky surface can be used as an equipment installation surface to facilitate the configuration of multiple payload extravehicular equipment 301. The following description is made by taking the satellite-to-ground surface as an example. Figure 1 Satellite to ground refers to the flat-panel satellite base platform 100 being close to the front of the flat-panel replaceable payload module 300. Figure 2The flat-plate replaceable payload module 300 includes a plurality of payload extravehicular equipment 301, one or more of which can be folded or unfolded on the ground relative to the satellite.

[0061] The integrated processing module 400 is electrically connected to the plurality of payload external devices 301 , and is used to implement payload signal and information processing functions that match the plurality of payload external devices 301 .

[0062] The network intelligent module 200 is used to provide general hardware resources for network communication and intelligent computing.

[0063] When the multifunctional flat-panel satellite system 1000 is in the launch state, one or more of the plurality of payload extravehicular equipment 301 are folded relative to the satellite to the ground, so that the multifunctional flat-panel satellite system 1000 is flattened;

[0064] When the multifunctional flat-panel satellite system 1000 is in an on-orbit operation state, one or more of the plurality of payload extravehicular devices 301 are deployed on the ground relative to the satellite to realize the corresponding functions of the multifunctional flat-panel satellite system 1000 .

[0065] The multifunctional flat-panel satellite system 1000 has a launch state and an on-orbit operation state. When in the launch state, one or more of the payload external equipment 301 are folded relative to the satellite to the ground, so that the multifunctional flat-panel satellite system 1000 is flattened; when in the on-orbit operation state, one or more of the payload external equipment 301 are unfolded relative to the satellite to the ground to realize the corresponding functions of the multifunctional flat-panel satellite system 1000, thereby achieving a higher space utilization rate. The design of the flat-panel satellite basic platform 100, the networked intelligent module 200, the flat-panel replaceable payload module 300 and the integrated processing module 400 is based on the payload adaptability design and the satellite platform standardization and unified design. On the basis of not changing the satellite platform design of the flat-panel satellite, it can adapt to a variety of payload types (including but not limited to: communication, navigation, remote sensing, etc.), and make full use of the functions of the payload carried, so as to effectively adapt to the mass production and launch requirements of satellites in different fields.

[0066] refer to Figure 3 , Figure 4-Figure 5 and Figure 6-Figure 7 The multifunctional flat-panel satellite system 1000 has a launch state and an on-orbit operation state. Figure 3 It is a structural diagram of a multifunctional flat-panel satellite system 1000 provided in an embodiment of the present application when it is in a launching state and an on-orbit operating state. Figure 4 , Figure 6 They are respectively exemplary structural diagrams of a multifunctional flat-panel satellite system 1000 provided in an embodiment of the present application when in a transmitting state, Figure 5 , Figure 7They are schematic diagrams of the structure of a multifunctional flat-panel satellite system 1000 provided in an embodiment of the present application when it is in an on-orbit operation state.

[0067] In some embodiments, the payload extravehicular equipment 301 may include a phased array antenna 3011 and / or a periscope imaging device 3012 .

[0068] refer to Figure 3 , with the side facing upward along the z direction as the satellite to the ground. The payload external equipment 301 may include a phased array antenna 3011. The phased array antenna 3011 is installed on the satellite to the ground and packaged as a flat structure.

[0069] When the multifunctional flat-panel satellite system 1000 is in the transmitting state, refer to Figure 3 , the adjacent array antennas 3011 are packaged into a flat structure so that the multifunctional flat-panel satellite system 1000 is flattened and roughly in the shape of a flat plate.

[0070] When the multifunctional flat-panel satellite system 1000 is in an on-orbit operation state, the phased array antenna 3011 is Figure 3 The structure of has not changed, so continue to refer to Figure 3 The adjacent array antenna 3011 is still a flat structure, which is used to realize the communication and navigation functions of the multifunctional flat-panel satellite system 1000.

[0071] refer to Figure 6 , Figure 7 , with the side of the flat-plate replaceable payload module 300 facing upward along the z direction as the satellite-to-ground. The payload extravehicular equipment 301 may include a periscope imaging device 3012. The periscope imaging device 3012 is installed on the satellite-to-ground and packaged as a flat structure.

[0072] Similarly, when the multifunctional flat-panel satellite system 1000 is in the transmitting state, refer to Figure 6 , the periscope imaging device 3012 is packaged into a flat structure to make the multifunctional flat-panel satellite system 1000 flat. Figure 7 When the multifunctional flat-panel satellite system 1000 is in orbit, the periscope imaging device 3012 is Figure 6 The structure of the periscope imaging device 3012 remains unchanged, that is, the periscope imaging device 3012 is still flat, and is used to realize the all-round optical earth observation and other functions possessed by the multifunctional flat-panel satellite system 1000.

[0073] In some embodiments, the payload cabin external equipment 301 includes a foldable synthetic aperture radar phased array antenna 3013, and the foldable synthetic aperture radar phased array antenna 3013 has a folded state and an unfolded state. Among them, the foldable synthetic aperture radar phased array antenna 3013 includes at least two antenna panels that are foldably connected. When the foldable synthetic aperture radar phased array antenna 3013 is in the folded state, at least two antenna panels are folded and connected and fixed to the satellite to the ground, so that the multifunctional flat-panel satellite system 1000 is flattened. When the foldable synthetic aperture radar phased array antenna is in the unfolded state, one of the at least two antenna panels is fixed to the satellite to the ground, and the remaining antenna panels extend along a preset direction to the edge of the flat-panel satellite basic platform 100 or beyond the edge of the flat-panel satellite basic platform 100 to realize the corresponding functions of the multifunctional flat-panel satellite system 1000.

[0074] The following description is made by taking two antenna panels as an example. For ease of understanding, one of the two antenna panels is marked as a first antenna panel 30131 , and the other is marked as a second antenna panel 30132 .

[0075] Combined with reference Figure 4 , Figure 5 The foldable synthetic aperture radar phased array antenna 3013 comprises a first antenna panel 30131 and a second antenna panel 30132 which are foldably connected.

[0076] refer to Figure 4 When the foldable synthetic aperture radar phased array antenna 3013 is in the folded state, one side of the first antenna panel 30131 is fixed to the satellite-to-ground. All or part of the surface of the second antenna panel 30132 is attached to the first antenna panel 30131, that is, the first antenna panel 30131 and the second antenna panel 30132 are folded, connected and fixed to the satellite-to-ground, so that the multifunctional flat-panel satellite system 1000 is flattened.

[0077] refer to Figure 5 When the foldable synthetic aperture radar phased array antenna 3013 is in the unfolded state, one side of the first antenna panel 30131 is fixed to the satellite facing the ground, and the second antenna panel 30132 exceeds the edge of the flat-panel satellite basic platform 100 along the preset direction (x direction), that is, the second antenna panel 30132 has no edge connected to the first antenna panel 30131, and exceeds the edge of the flat-panel satellite basic platform 100 in the preset direction.

[0078] It can be understood that, in actual situations, if the preset direction is the length direction of the flat-panel satellite basic platform 100, since the edge of the second antenna panel 30132 along the length direction can exceed the edge of the flat-panel satellite basic platform 100 when the foldable synthetic aperture radar phased array antenna 3013 is in the unfolded state, the length of the foldable synthetic aperture radar phased array antenna 3013 in the unfolded state can be significantly greater than the length of the flat-panel satellite basic platform 100. For example, in some implementations, the length of the foldable synthetic aperture radar phased array antenna 3013 in the unfolded state can reach 2 to 3 times the length of the flat-panel satellite basic platform 100, so that the flat-panel satellite basic platform 100 can match more large payload extravehicular equipment 301 in terms of length, thereby facilitating the realization of the corresponding functions of the multifunctional flat-panel satellite system 1000.

[0079] In some specific implementations, the length of the foldable synthetic aperture radar phased array antenna 3013 when in a folded state is approximately 3320 mm, and the length of the foldable synthetic aperture radar phased array antenna 3013 when in an unfolded state is approximately 6608 mm. Therefore, the folded state of the foldable synthetic aperture radar phased array antenna 3013 can reduce its length by approximately 3288 mm compared to the unfolded state, thereby enabling it to achieve a higher launch carrier space utilization rate when the multifunctional flat-panel satellite system 1000 is in a launching state.

[0080] In some embodiments, the payload external equipment 301 includes a foldable imaging device 3014, and the foldable imaging device 3014 has a folded state and an unfolded state.

[0081] Combined with reference Figure 4 , Figure 5 , Figure 6 , Figure 7 The foldable imaging device 3014 includes a first imaging component 30141, a second imaging component 30142 and a foldable light shield 30143 which are foldably connected. The foldable light shield 30143 is disposed between the first imaging component 30141 and the second imaging component 30142 and can move relative to each other.

[0082] refer to Figure 4 , Figure 6 When the foldable imaging device 3014 is in the folded state, one side of the first imaging component 30141 is fixed to the satellite ground. The entire or partial surface of the second imaging component 30142 is attached to the satellite ground, so that the multifunctional flat-panel satellite system 1000 is flattened.

[0083] refer to Figure 5 , Figure 7When the foldable imaging device 3014 is in the unfolded state, the second imaging component 30142 extends to a preset position in a direction perpendicular to the first imaging component 30141, and an imaging space is formed between the second imaging component 30142, the foldable sunshade 30143 and the first imaging component 30141, which is used to realize the all-weather high-precision earth observation and other functions of the multifunctional flat-panel satellite system 1000.

[0084] The preset position may, for example, refer to the second imaging assembly 30142 reaching a specified height, which is not limited in the present application. The foldable light shield 30143 may include a rotation axis ( Figure 5 The rotating shaft drives the second imaging assembly 30142 to rotate clockwise or counterclockwise, so that the foldable imaging device 3014 can be switched between the folded state and the unfolded state.

[0085] Similarly, in actual situations, since the second imaging component 30142 can extend to a preset position in a direction perpendicular to the first imaging component 30141 when the foldable imaging device 3014 is in the unfolded state, those skilled in the art can flexibly set the height of the foldable imaging device 3014 when it is in the unfolded state. For example, in some implementations, the height of the foldable imaging device 3014 when it is in the unfolded state can be greater than or equal to 1150 mm, which is higher than the usual design height of some flat-panel satellite basic platforms 100, so that the flat-panel satellite basic platform 100 can also match more large-sized payload extravehicular equipment 301 at the height level, thereby facilitating the realization of the corresponding functions of the multifunctional flat-panel satellite system 1000.

[0086] In some specific implementations, the height of the foldable imaging device 3014 when in the folded state is about 150 mm, and the height of the foldable imaging device 3014 when in the unfolded state is about 1150 mm. Therefore, the folded state of the foldable imaging device 3014 can reduce its height by about 1000 mm compared to the unfolded state, thereby enabling it to achieve a higher launch space utilization rate when the multifunctional flat-panel satellite system 1000 is in the launch state.

[0087] In some specific implementations, the multifunctional flat-panel satellite system 1000 can be simultaneously equipped with the above-mentioned foldable synthetic aperture radar phased array antenna 3013 and foldable imaging device 3014. The envelope of the multifunctional flat-panel satellite system 1000 when in the launch state is approximately 3320mm*1745mm*517mm, and the envelope of the multifunctional flat-panel satellite system 1000 when in the on-orbit operation state is approximately 6608mm*17661mm*3847mm (including the unfolding of the sailboard).

[0088] In some embodiments, reference Figure 8The flat-panel satellite basic platform 100 is provided with an electrical connector 101 and a fixed bracket 102. The fixed bracket 102 is installed on the flat-panel satellite basic platform 100, and the electrical connector 101 is installed on the fixed bracket 102. The electrical connector 101 is used to adapt the thermal and electrical performance requirements of each payload external device. As an example, the interior of the flat-panel satellite basic platform 100 can adopt a standardized satellite design, for example, according to the subsystem design of thermal control, energy, attitude and orbit control, satellite services, measurement and control, etc. The structure of the flat-panel satellite basic platform 100 is roughly flat, and the electrical connector interface 101 is used to adapt the thermal and electrical performance requirements of each payload external device 301.

[0089] In some embodiments, reference Fig. 9 The general hardware resources provided by the network intelligent module 200 include any one or a combination of the following: sharable laser and microwave intersatellite link terminals, onboard routers and switches, satellite-to-ground link terminals, and onboard intelligent computers. When different payload extravehicular devices 301 perform different tasks, sharable laser and microwave intersatellite link terminals, onboard routers and switches, satellite-to-ground bidirectional feeder link terminals, onboard intelligent computers, etc. are used to realize intelligent networking between homogeneous or heterogeneous satellites.

[0090] In some embodiments, reference Fig.10 The integrated processing module 400 includes a baseboard 401 , a power management board 402 , a software reconstruction control board 403 , a multi-functional software storage board 404 , a signal processing board 405 and a general computing board 406 .

[0091] The integrated processing module 400 includes a baseboard 401, a power management board 402, a software reconstruction control board 403, a multifunctional software storage board 404, a signal processing board 405 and a general computing board 405, and there can be several of them, and there is no limitation on this.

[0092] refer to Fig.10 , the power management board 402, the software reconstruction control board 403, the multifunctional software storage board 404, the signal processing board 405 and the general computing board 406 are plugged into the slots of the baseboard 401 to provide inter-board communication and power supply. The power management board 402 is powered by the baseboard 401. The multifunctional software storage board 404, the signal processing board 405 and the general computing board 406 are used to provide software and computing power for the payload function. The software reconstruction control board 403 is used to control the software reconstruction corresponding to the payload function.

[0093] In the embodiment of the present application, the integrated processing module 400 realizes different processing software functions such as communication, navigation, remote sensing, etc. on the same signal processing hardware through software reconstruction. Specifically, the multifunctional software storage board 404 can store signal processing such as communication signal baseband processing, navigation signal baseband processing, synthetic aperture radar imaging processing, visible light imaging processing, hyperspectral imaging processing, infrared imaging processing, communication protocol, data security, etc. The software reconstruction control board 403 controls these software to complete reconstruction on the signal processing board 405 and the general computing board 406.

[0094] In some embodiments, the software reconstruction control board 403 can use a cache module in software reconstruction. Specifically, the cache module can be configured in any one or a combination of the multifunctional software storage board 404, the signal processing board 405 and the general computing board 406, or the cache module can also be configured in a newly added independent board, which is not limited. Fig.10 The configuration in the signal processing board 405 and the general computing board 406 shown in FIG. 4 is used as an example for explanation. Specifically, the software reconstruction control board 403 is configured to control one or more software units in the multifunctional software storage board 404 to be replaced to the signal processing board 405 and the general computing board 406. Also, the software reconstruction control board 403 is configured to control the remaining software units to cache the data generated by the operation into the cache unit during the replacement process, wherein the software unit is decomposed from the software corresponding to the load function.

[0095] There may be one or more cache units, each of which is used to cache data generated by the operation of one or more corresponding software units. The software reconstruction control board 403 may be configured to control the capacity of the cache unit according to the load function to carry different load tasks, and to achieve seamless switching between different load tasks to prevent information loss.

[0096] Exemplary, reference Fig.11 , taking a reconstruction process consisting of software modules 1 to N as an example, when the software module K in the signal processing board 405 or the general computing board 406 is to be replaced with the software module N+K, the software reconstruction control board 403 will control the software module N+K in the multifunctional software storage board 404 to start the replacement. During the replacement process, the software modules 1 to K-1 all work normally and cache the generated data in the corresponding cache module K-1. After the software module N+K is replaced, the process continues. The size of each cache module can be controlled by the software reconstruction control board 403.

[0097] For example, refer to Fig.12, taking a reconstruction process consisting of software modules 1 to N as an example, when the software module K in the signal processing board 405 or the general computing board 406 is to be replaced with the software module N+K, the software reconstruction control board 403 will control the software module N+K in the multifunctional software storage board 404 to start the replacement. During the replacement process, the software modules 1 to K-1 all work normally and cache the generated data in a shared cache module. When the software module N+K is replaced, the process continues. The size of the shared cache module can also be controlled by the software reconstruction control board 403.

[0098] In some embodiments, the corresponding functions of the multi-function flat panel satellite system 1000 include any one or a combination of the following: communication, navigation, radar detection, synthetic aperture radar imaging, visible light imaging, hyperspectral imaging, and infrared imaging.

[0099] In other words, the multifunctional flat-panel satellite system 1000 can adapt to a variety of payload types and make full use of the functions of the payload carried, including but not limited to: communication, navigation, radar detection, synthetic aperture radar imaging, visible light imaging, hyperspectral imaging, infrared imaging, etc. Although in actual situations, the payloads related to these functions are often embodied as large payloads, which may affect the overall launch and transportation use space of the satellite when a non-flat-panel configuration is used, in the standardized and unified multifunctional flat-panel satellite system 1000 as described above, since the large payload can also be used as a payload cabin equipment 301 and is adapted to the launch state and on-orbit operation state of the multifunctional flat-panel satellite system 1000 to be unfolded or folded, a higher space utilization rate can be achieved, so that the functions of the large payload carried can be fully utilized, thereby effectively adapting to the mass launch requirements of satellites in different fields such as communication, navigation, radar detection, synthetic aperture radar imaging, visible light imaging, hyperspectral imaging and infrared imaging.

[0100] In addition, the standardized and unified design described in this article supports only changing the flat-panel replaceable payload module 300 to achieve the change between different functions of the satellite, and supports only changing the integrated processing module 400 to achieve the networked and intelligent design of multiple types of satellites, thereby effectively adapting to the mass production needs of satellites in different fields such as communication, navigation, radar detection, synthetic aperture radar imaging, visible light imaging, hyperspectral imaging, and infrared imaging. After these satellites are launched into orbit, they can very efficiently and flexibly realize the coordinated work of satellites with different functions in orbit because they have unified and standardized network communication and intelligent computing functions.

[0101] The basic concepts have been described above. Obviously, for those skilled in the art, the above application disclosure is only an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary embodiments of the present application.

[0102] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0103] Some aspects of the present application may be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software may be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor may be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, memories, data processing units (DPUs), neural network processors (NPUs) or combinations thereof. In addition, various aspects of the present application may be represented as computer products located in one or more computer-readable media, which include computer-readable program codes. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, tapes...), optical disks (e.g., compact disks CDs, digital versatile disks DVDs...), smart cards, and flash memory devices (e.g., cards, sticks, key drives...).

[0104] A computer-readable medium may include a propagated data signal containing computer program code, such as in baseband or as part of a carrier wave. The propagated signal may have a variety of manifestations, including electromagnetic, optical, etc., or a suitable combination. A computer-readable medium may be any computer-readable medium other than a computer-readable storage medium, which may be connected to an instruction execution system, device or apparatus to communicate, propagate or transmit a program for use. The program code on the computer-readable medium may be propagated via any suitable medium, including radio, cable, fiber optic cable, radio frequency signal, or similar medium, or any combination of the above mediums.

[0105] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus help understand one or more application embodiments, in the above description of the embodiments of this application, multiple features are sometimes merged into one embodiment, figure or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than the features mentioned in the claims. In fact, the features of the embodiments are less than all the features of the single embodiment disclosed above.

[0106] In some embodiments, numbers describing the number of components and attributes are used. It should be understood that such numbers used in the description of the embodiments are modified by the modifiers "about", "approximately" or "substantially" in some examples. Unless otherwise specified, "about", "approximately" or "substantially" indicate 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 change according to the required features of individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and adopt the general method of retaining digits. Although the numerical domains and parameters used to confirm the breadth of their range in some embodiments of the present application are approximate values, in specific embodiments, the setting of such numerical values ​​is as accurate as possible within the feasible range.

[0107] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions may be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the essential spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. A multifunctional flat-panel satellite system, the multifunctional flat-panel satellite system having a launch state and an on-orbit operation state, characterized in that: include: Flat-panel satellite basic platform, networked intelligent module, flat-panel replaceable payload module and integrated processing module; The flat-plate replaceable payload module includes a plurality of payload external equipment, one or more of the plurality of payload external equipment being capable of being folded or unfolded relative to an equipment mounting surface; The flat-panel satellite basic platform is electromechanically and thermally connected to the networked intelligent module, the flat-panel replaceable payload module and the integrated processing module. The integrated processing module is electrically connected to the multiple payload off-board devices. The networked intelligent module is used to provide general hardware resources for network communication and intelligent computing. The integrated processing module is used to realize payload signal and information processing functions that match the multiple payload off-board devices. When the multifunctional flat-panel satellite system is in a launching state, one or more of the plurality of payload external equipment are folded relative to the equipment mounting surface so that the multifunctional flat-panel satellite system is flattened; When the multifunctional flat-panel satellite system is in an on-orbit operation state, one or more of the plurality of payload external equipment are deployed relative to the equipment installation surface to realize corresponding functions of the multifunctional flat-panel satellite system; The multifunctional flat-panel satellite system adopts a standardized and unified design, supports only changing the flat-panel replaceable payload module to realize the change of satellite between different functions, and supports only changing the integrated processing module to realize the networking and intelligent design of various types of satellites.

2. The multifunctional flat-panel satellite system according to claim 1, characterized in that: The equipment installation surface is the satellite-to-ground surface of the flat-panel satellite base platform.

3. The multifunctional flat-panel satellite system according to claim 2, characterized in that: The payload extravehicular equipment includes a phased array antenna and / or a periscope imaging device; The phased array antenna and / or periscope imaging device are installed on the ground of the satellite and packaged into a flat structure.

4. The multifunctional flat-panel satellite system according to claim 2, characterized in that: The payload cabin external equipment includes a foldable synthetic aperture radar phased array antenna, and the foldable synthetic aperture radar phased array antenna has a folded state and an unfolded state; The foldable synthetic aperture radar phased array antenna comprises at least two antenna panels foldably connected; wherein: When the foldable synthetic aperture radar phased array antenna is in a folded state, the at least two antenna panels are folded, connected and fixed to the satellite ground, so that the multifunctional flat-panel satellite system is flattened; When the foldable synthetic aperture radar phased array antenna is in an unfolded state, one of the at least two antenna panels is fixed to the satellite facing the ground, and the remaining antenna panels extend along a preset direction to the edge of the flat-panel satellite base platform or beyond the edge of the flat-panel satellite base platform to realize the corresponding functions of the multifunctional flat-panel satellite system.

5. The multifunctional flat-panel satellite system according to claim 2, characterized in that: The payload external equipment includes a foldable imaging device, and the foldable imaging device has a folded state and an unfolded state; The foldable imaging device comprises a first imaging component, a second imaging component and a foldable light shield which are foldably connected, wherein the foldable light shield is arranged between the first imaging component and the second imaging component and can move relatively; When the foldable imaging device is in a folded state, one side of the first imaging component is fixed to the satellite-to-ground, and all or part of the surface of the second imaging component is attached to the satellite-to-ground, so that the multifunctional flat-panel satellite system is flattened; When the foldable imaging device is in an unfolded state, the second imaging component extends to a preset position in a direction perpendicular to the first imaging component, and an imaging space is formed between the second imaging component, the foldable light shield and the first imaging component to realize the corresponding functions of the multifunctional flat-panel satellite system.

6. The multifunctional flat-panel satellite system according to claim 1, characterized in that: The flat-panel satellite basic platform is provided with an electrical connector and a fixing bracket, the fixing bracket is mounted on the flat-panel satellite basic platform, the electrical connector is mounted on the fixing bracket, and the electrical connector is used to adapt to the thermal and electrical performance requirements of each load compartment external equipment.

7. The multifunctional flat-panel satellite system according to claim 1, characterized in that: The general hardware resources provided by the networked intelligent module include any one or a combination of the following: Shared laser and microwave intersatellite link terminals, on-board routers and switches, satellite-to-ground link terminals and on-board intelligent computers.

8. The multifunctional flat-panel satellite system according to claim 1, characterized in that: The integrated processing module includes a baseboard, a power management board, a software reconstruction control board, a multifunctional software storage board, a signal processing board and a general computing board; The power management board, the software reconstruction control board, the multifunctional software storage board, the signal processing board and the general computing board are plugged into the slots of the baseboard; The power management board is powered by the baseboard; The multifunctional software storage board, the signal processing board and the general computing board are used to provide software and computing power for the payload function; The software reconstruction control panel is used to control the software reconstruction corresponding to the load function.

9. The multifunctional flat-panel satellite system according to claim 8, characterized in that: The software reconstruction control board is configured to control one or more software units in the multifunctional software storage board to be replaced to the signal processing board and the general computing board; and, The software reconstruction control board is configured to control the remaining software units to cache the data generated by the operation into the cache unit during the replacement process, wherein the software unit is obtained by decomposing the software corresponding to the load function.

10. The multifunctional flat-panel satellite system according to claim 9, characterized in that: There are one or more cache units, and each cache unit is used to cache data generated by the operation of one or more corresponding software units.

11. The multifunctional flat-panel satellite system according to claim 9, characterized in that: The software reconstruction control board is configured to control the capacity of the cache unit according to a load function.

12. The multifunctional flat-panel satellite system according to claim 1, characterized in that: The corresponding functions of the multifunctional flat-panel satellite system include any one or a combination of the following: Communications, navigation, radar detection, synthetic aperture radar imaging, visible light imaging, hyperspectral imaging, and infrared imaging.

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