Time-division and partition-based satellite-borne information system and satellite remote sensing autonomous scheduling method

Abstract

The application provides a time and area division satellite borne information system, a GNSS navigation module is used for receiving satellite signals, pre-processing is carried out, navigation information of navigation satellites is solved, the navigation information is sent to a core processing module, and mode control information of the core processing module is received; the core processing module comprises a plurality of core parallel processing units, the core parallel processing units are used for operating and processing data information of each functional module, the core parallel processing units are mutually transmitted operation processing information and internally synchronized by an LVDS bus; a satellite-ground measurement and control information processing module receives telemetry information of the core processing module, frames telemetry data packets periodically and downloads to a ground measurement and control station; and an uplink remote control instruction of the ground measurement and control station is received. A satellite telemetry autonomous scheduling method is also provided. Thus, the application can realize information isolation, comprehensive utilization and telemetry information reasonable planning of a satellite system level.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite, in particular to a time and zone division satellite-borne information system and a satellite telemetry autonomous scheduling method. BACKGROUND

[0002] Low-orbit satellite communication emerged in the 1990s along with the development of ground mobile communication technology, and several well-known global communication satellite systems were born; in the 21st century, the development and maturity of information technology helped mobile satellite constellation enter a stage of vigorous development.

[0003] With the development of aerospace business, mobile satellite constellation not only needs to realize a single function task, but also needs to have multiple payload function tasks, so the satellite electronic system needs to integrate the limited resources on the satellite and equip with a reasonable time and zone division algorithm. Time and zone division information processing technology is a comprehensive mechanical and electrical technology developed along with the progress of microelectronic technology and the development of spacecraft application needs, which is an information system with efficient collection, processing and storage; spatial zoning divides the internal storage space into non-overlapping areas, so that each task has its own unique storage space; time zoning refers to the system time being divided into multiple time windows, and each task is allocated with reasonable processing time, so as to realize satellite system-level information isolation and sharing and comprehensive utilization.

[0004] The existing satellite information system is mainly realized by using centralized architecture, and does not process information in time and zone division according to the task characteristics of multi-functional satellite, so it cannot adapt to satellite constellation system with multiple complex function configurations. SUMMARY

[0005] The present application relates to the technical field of satellite, in particular to a time and zone division satellite-borne information system and a satellite telemetry autonomous scheduling method.

[0006] In order to achieve the above-mentioned purpose, on the one hand, the present application provides a time and zone division satellite-borne information system, which comprises a GNSS navigation module, a core processing module and a satellite-ground TT&C information processing module, wherein:

[0007] The GNSS navigation module is used for receiving satellite signals, pre-processing the satellite signals to solve the navigation information of navigation satellites, sending the navigation information to the core processing module, and receiving the mode control information of the core processing module;

[0008] The core processing module includes multiple core parallel processing units, which are used to perform calculations on data information of each functional module. The core parallel processing units transmit calculation processing information to each other through the LVDS bus and perform internal synchronization processing; wherein, each functional module includes at least the GNSS navigation module and the satellite-to-ground measurement and control information processing module;

[0009] The satellite-to-ground measurement and control information processing module is used to frame telemetry data packets and periodically transmit them to the ground measurement and control station based on the telemetry information received from the core processing module; and is used to receive uplink remote control instructions from the ground measurement and control station.

[0010] Furthermore, the core processing module is used to receive the navigation information, calculate the star time information and the orbital position information of the satellite through positioning and orbit determination operations, and send mode control information to the GNSS navigation module via the satellite-ground measurement and control information processing module to switch the navigation mode;

[0011] The core processing module is used to send satellite telemetry packets to the satellite-ground measurement and control information processing module, and receive ground instructions from the satellite-ground measurement and control information processing module, and parse, process and distribute the ground instructions.

[0012] Furthermore, the functional modules also include a navigation enhancement payload, a broadband communication payload, an energy terminal, a laser communication payload, a feed service payload, and a thermal control terminal;

[0013] The core processing module is further configured to send time and orbit information to the navigation enhancement payload via the satellite-to-ground measurement and control information processing module, and to receive power information of the navigation enhancement payload;

[0014] The core processing module is further configured to send time information and communication service setting instructions to the broadband communication payload based on the communication effect evaluation information received from the broadband communication payload;

[0015] The core processing module is further configured to analyze the current energy status and the health status of the energy terminal according to the solar current and the load information of the energy terminal, and send a battery setting instruction to the energy terminal based on the analysis result;

[0016] The core processing module is further configured to calculate laser link establishment accuracy based on laser pointing angle and intensity information received from the laser communication payload, and send laser pointing and configuration information to the laser communication payload based on the laser link establishment accuracy;

[0017] The core processing module is further configured to calculate antenna pointing accuracy based on actual antenna pointing position information received from the feeding service payload, and send feeding antenna pointing adjustment information to the feeding service payload based on the antenna pointing accuracy;

[0018] The core processing module is further configured to determine whether a heater switch is required based on the thermistor resistance value received from the thermal control terminal and a preset thermal control autonomous management strategy, and if required, send a corresponding heater control instruction to the thermal control terminal.

[0019] Furthermore, the satellite-to-ground measurement and control information processing module is also used to send the direct discrete instructions in the uplink remote control instructions to the lower computer, and to verify the indirect instructions in the uplink remote control instructions and then send them to the core processing module.

[0020] Furthermore, the core processing module also has a fault detection mechanism, which is implemented based on information synchronization between the multiple core parallel processing units. The information synchronization operation between the multiple core parallel processing units is:

[0021] Each of the core parallel processing units receives important data sent by other core parallel processing units and combines the important data with its own important data to form an important data list;

[0022] Each of the core parallel processing units receives other important data lists sent by other core parallel processing units, and forms an important data matrix with the important data lists of its own;

[0023] Each of the core parallel processing units determines whether the corresponding important data is real data according to the number of occurrences of the important data in the important data matrix.

[0024] Furthermore, each of the core parallel processing units respectively determines whether the number of occurrences of each important data in the important data matrix is ​​not less than a preset number threshold, and if so, determines that the corresponding important data is real data; wherein, the number threshold is the number of core parallel processing units of the core processing module minus one.

[0025] Furthermore, the storage resources of the core parallel processing unit are divided into a plurality of independent task storage modules according to different task requirements, and each task storage module stores task information corresponding to the task requirement.

[0026] Furthermore, the processor task cycle of the core parallel processing unit is divided into different time slices according to the running time of each task to be executed; and each task to be executed is configured with a priority of task execution order.

[0027] On the other hand, the present invention also provides a satellite telemetry autonomous scheduling method based on any of the above-mentioned onboard information systems, comprising the steps of:

[0028] Establishing multiple virtual channels for satellite telemetry downlink operation, each of the virtual channels occupies a fixed number of telemetry bytes, and the multiple virtual information are respectively configured with corresponding priorities;

[0029] According to the priority, setting the execution frequency corresponding to the virtual channel;

[0030] Calculating a time-sharing efficiency ratio corresponding to each telemetry packet according to the telemetry packet length and telemetry packet priority of each satellite telemetry packet;

[0031] The telemetry packets are sorted according to the time-sharing efficiency ratio, and the number of bytes occupied by the telemetry packets is gradually accumulated according to the sorting until the virtual channel is filled; wherein, each virtual channel is transmitted according to the corresponding priority.

[0032] Furthermore, the time-sharing efficiency ratio is the ratio of the telemetry packet length to the telemetry packet priority.

[0033] The present invention is suitable for providing information processing support for various types of services within mobile satellite constellations. Spatial partitioning divides internal storage space into non-overlapping areas, allowing each task to have its own dedicated storage space. Time partitioning divides system time into multiple time windows, allocating a reasonable amount of processing time to each task. Furthermore, an information synchronization method based on LVDS interface interconnection enables information synchronization between multiple parallel processors, while a dynamic, adaptive telemetry downlink method enables autonomous switching of telemetry priorities. Thus, the present invention achieves satellite system-level information isolation, comprehensive utilization, and rational planning of telemetry information. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 A framework diagram of the time-sharing and partitioned satellite-borne information system provided in one embodiment of the present invention;

[0035] Figure 2 A specific flow chart of information synchronization performed by the core parallel processing unit of the time-sharing and partitioned onboard information system provided by one embodiment of the present invention;

[0036] Figure 3 A schematic diagram of storage space partitioning of the core parallel processing unit of the time-sharing and partitioned onboard information system provided by one embodiment of the present invention;

[0037] Figure 4 A schematic diagram of time partitioning of the core parallel processing unit of the time-sharing and partitioned onboard information system provided in one embodiment of the present invention. DETAILED DESCRIPTION

[0038] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0039] It should be noted that references to "one embodiment," "an embodiment," "an example embodiment," etc., in this specification indicate that the described embodiment may include specific features, structures, or characteristics, but not every embodiment must include these specific features, structures, or characteristics. Furthermore, such references do not necessarily refer to the same embodiment. Furthermore, when specific features, structures, or characteristics are described in conjunction with an embodiment, whether or not explicitly described, it is understood that incorporating such features, structures, or characteristics into other embodiments is within the knowledge of those skilled in the art.

[0040] In addition, certain words are used in the specification and subsequent claims to refer to specific components or parts. It should be understood by those with ordinary knowledge in the relevant field that manufacturers may use different nouns or terms to refer to the same component or part. This specification and subsequent claims do not use differences in names as a way to distinguish components or parts, but rather use differences in the functions of components or parts as the criteria for distinction. The words "including" and "comprising" mentioned throughout the specification and subsequent claims are open-ended terms and should be interpreted as "including but not limited to". In addition, the word "connect" here includes any direct and indirect electrical connection means. Indirect electrical connection means include connection through other devices.

[0041] Figure 1 A time-sharing and partitioned satellite-borne information system 100 provided in one embodiment of the present invention is shown, comprising a GNSS navigation module 10, a core processing module 20, and a satellite-to-ground measurement and control information processing module 30, wherein:

[0042] The GNSS navigation module 10 is configured to receive satellite signals, pre-process the satellite signals, calculate navigation information of navigation satellites, transmit the navigation information to the core processing module 20, and receive mode control information from the core processing module 20; the core processing module 20 includes a plurality of core parallel processing units, which are configured to perform operation processing on data information of each functional module, transmit operation processing information between the core parallel processing units through an LVDS bus, and perform internal synchronization processing; each functional module includes at least the GNSS navigation module 10 and a satellite-ground TT&C information processing module 30; the satellite-ground TT&C information processing module 30 is configured to periodically transmit telemetry data packets to a ground TT&C station 50 according to telemetry information received from the core processing module 20, and receive uplink remote control instructions from the ground TT&C station 50.

[0043] The GNSS navigation module 10 of the embodiment is configured to receive satellite signals of the Beidou navigation satellite 41 and satellite signals of the GPS satellite 42, perform radio frequency signal filtering and amplification on the received satellite signals, and calculate corresponding navigation information; specifically, the navigation information of the embodiment is position and time signals of navigation satellites; that is, after the GNSS navigation module receives satellite signals of the Beidou navigation and / or GPS, the GNSS navigation module calculates the position and time signals of the Beidou navigation and / or GPS through radio frequency signal filtering and amplification, transmits the navigation information to the core processing module 20 for processing, and receives mode control information from the core parallel processing units; after receiving the mode control information, the GNSS navigation module switches to a corresponding working mode according to the mode control information, such as a single Beidou satellite mode, a single GPS satellite mode, and a navigation satellite combination mode.

[0044] The core processing module 20 of the embodiment includes four identical core parallel processing units, namely a first core parallel processing unit 201, a second core parallel processing unit 202, a third core parallel processing unit 203, and a fourth core parallel processing unit 204; of course, the core processing module can include three, five, six, or the like core parallel processing units in other examples, that is, the number of core parallel processing units is not limited in the embodiment.

[0045] The four core parallel processing units transmit processing information between each other through an LVDS bus and perform internal synchronization processing; that is, after the core processing module 20 receives any information that needs to be processed, each core parallel processing unit transmits operation processing information between each other and performs internal synchronization processing.

[0046] The core processing module 20 receives navigation information sent by the GNSS navigation module, calculates the satellite time information and the satellite's orbital position information through positioning and orbit determination operations, and sends mode control information to the GNSS navigation module 10 via the satellite-ground measurement and control information processing module 30 to switch navigation modes. Furthermore, the core processing module 20 is also used to send satellite telemetry packets to the satellite-ground measurement and control information processing module 30, and receive ground commands from the satellite-ground measurement and control information processing module 30, parsing, processing, and distributing the ground commands. The parsing and processing of ground commands must be performed and processed synchronously in each core parallel processing unit.

[0047] In this embodiment, each functional module further includes a navigation enhancement payload 111 , a broadband communication payload 112 , an energy terminal 113 , a laser communication payload 114 , a feed service payload 115 and a thermal control terminal 116 .

[0048] The core processing module 20 is further configured to send time and orbit information to the navigation enhancement payload 111 via the satellite-ground tracking and control information processing module 30 , and to receive power information of the navigation enhancement payload 111 ; the power information is specifically used for navigation enhancement.

[0049] The core processing module 20 is also used to send time information and communication service setting instructions to the broadband communication payload 112 based on the communication effect evaluation information received from the broadband communication payload 112; specifically, the core processing module 20 receives the communication effect evaluation information of the broadband communication payload 112, and sends time information and communication service setting instructions to the broadband communication payload 112 via the satellite-to-ground measurement and control information processing module 30.

[0050] The core processing module 20 is also used to analyze the current energy status and the health status of the energy terminal 113 based on the solar current and the load information of the energy terminal 113, and send a battery setting instruction to the energy terminal 113 based on the analysis results; specifically, the core processing module 20 collects the solar current and the load information of the energy terminal 113, calculates the current energy balance and usage, determines the health status of the energy terminal 113, and uses the above information as a basis to send a battery setting instruction to each terminal load via the satellite-ground measurement and control information processing module 30.

[0051] The core processing module 20 is also used for calculating laser chain establishment accuracy according to the laser pointing angle and intensity information received from the laser communication payload 114, and sending laser pointing and configuration information to the laser communication payload 114 based on the laser chain establishment accuracy; specifically, the core processing module 20 collects the laser pointing angle and intensity information from the laser communication payload, calculates the laser chain establishment accuracy, and sends the laser pointing and configuration information to the laser communication payload 114 via the satellite-ground TT&C information processing module 30 based on the calculation result, so that the laser communication payload 114 completes the autonomous laser chain establishment function based on the information fed back by the core processing module 20.

[0052] The core processing module 20 is also used for calculating antenna pointing accuracy according to the actual antenna pointing position information received from the feeder service payload 115, and sending feeder antenna pointing adjustment information to the feeder service payload 115 based on the antenna pointing accuracy; specifically, the core processing module 20 collects the actual antenna pointing position information from the feeder service payload, calculates the antenna pointing accuracy, and sends the feeder antenna pointing adjustment information to the feeder service payload 115 via the satellite-ground TT&C information processing module 30 to complete the self-calibration function of the feeder antenna.

[0053] The core processing module 20 is also used for determining whether a heater switch is needed according to the thermistor resistance value received from the thermal control terminal 116 and a preset thermal control autonomous management strategy, and sending a corresponding heater control instruction to the thermal control terminal 116 if needed. Specifically, the core processing module 20 collects the thermistor resistance value collected by the thermal control terminal 116, determines whether the corresponding heater needs to be turned on or off according to the corresponding resistance value in combination with the preset thermal control autonomous management strategy, and sends a heater control instruction to the thermal control terminal 116 via the satellite-ground TT&C information processing module 30, so that the thermal control terminal 116 controls the corresponding heater to be turned on or off in response to the heater control instruction.

[0054] The satellite-ground TT&C information processing module 30 of the embodiment is specifically divided into a telemetry main / backup module and a remote control main / backup module, wherein the telemetry main / backup module works in cold backup mode and the remote control main / backup module works in hot backup mode. The satellite-ground TT&C information processing module 30 receives telemetry information from the core processing module 20, periodically transmits telemetry data packets to the ground control station 50, and receives uplink remote control instructions from the ground control station 50.

[0055] Furthermore, the satellite-ground measurement and control information processing module 30 is further configured to transmit direct discrete instructions within the uplink remote control instructions to the lower computer, and to verify indirect instructions within the uplink remote control instructions before transmitting them to the core processing module 20. Furthermore, the satellite-ground measurement and control information processing module 30 receives instruction information from all core parallel processing units, screens out instruction information from faulty core parallel processing units, and transmits correct instructions to the lower computer via the integrated electronic system bus. The specific method for screening out faulty core parallel processing units will be further described below.

[0056] The core processing module 20 of this embodiment also has a fault detection mechanism. The fault detection mechanism is implemented based on information synchronization between multiple core parallel processing units. The information synchronization operation between multiple core parallel processing units is as follows:

[0057] Each core parallel processing unit receives important data sent by other core parallel processing units, and combines it with its own important data to form an important data list; each core parallel processing unit receives other important data lists sent by other core parallel processing units, and forms an important data matrix with its own important data list; each core parallel processing unit determines whether the corresponding important data is real data based on the number of occurrences of important data in the important data matrix.

[0058] The fault detection mechanism described above is implemented by exchanging important data between core parallel processing units via the LVDS bus. Specifically, each core parallel processing unit can determine the faulty unit after completing two rounds of information exchange.

[0059] The first round of information interaction requires each core parallel processing unit to send its own important data to other core parallel processing units. This embodiment will be explained by taking the core processing module 20 including four core parallel processing units as an example, that is, each core parallel processing unit sends its own important data to the other three core parallel processing units, and each core parallel processing unit saves the three copies of important data received from the other three core parallel processing units, and together with its own important data forms an important data list containing four units; wherein, the important data can be the data interacted between the core parallel processing unit and each functional module, such as the aforementioned data such as the calculation processing results of each functional module in the data exchange, or other pre-specified interaction data or important data generated by the core parallel processing unit through self-running test; in this first round of information interaction, each core parallel processing unit obtains an important data list containing four units; and then enters the next round of information interaction.

[0060] In the second round of information interaction, each core parallel processing unit is required to send the important data list formed in the previous round of information interaction to other core parallel processing units, that is, each core parallel processing unit sends its own important data list to the other three core parallel processing units. Each core parallel processing unit saves the three received important data lists and forms an important data matrix with its own important data list.

[0061] After completing the above two rounds of information interaction, each core parallel processing unit interprets the important data matrix formed by itself. When the number of appearances of the same important data in the matrix reaches a certain number, it can be determined that the important data is real data, and the core parallel processing unit that generates the important data is a normally operating processing unit; on the contrary, if the number of appearances of a certain important data in the important data matrix in the matrix does not reach a certain number, the important data is determined to be untrue. At this time, it can be determined that the core parallel processing unit that generates the important data is not operating normally and is a faulty unit.

[0062] Specifically, each core parallel processing unit determines whether the number of occurrences of each important data item in the important data matrix is ​​no less than a preset number threshold. If so, the corresponding important data item is determined to be authentic data. The number threshold is the number of core parallel processing units in the core processing module 20 minus one. In this embodiment, the number threshold is 4-1=3, meaning that each of the four core parallel processing units determines the number of occurrences of each important data item in the important data matrix. If any important data item appears fewer than three times, the data item is determined to be authentic data, meaning that the core parallel processing unit that generated the data item is a faulty unit.

[0063] See also Figure 2 , assuming that the important data of module i (i-th core parallel processing unit) is D i If the second core parallel processing unit 202 fails, the lists sent by the other three core parallel processing units are unknown. After completing the first round of information exchange, the important data lists formed by the first core parallel processing unit 201, the third core parallel processing unit 203, and the fourth core parallel processing unit 204 are L1 = [D1, α, D3, D4], L3 = [D1, β, D3, D4], and L4 = [D1, γ, D3, D4], respectively. The important data received by the second core parallel processing unit 202 is erroneous data. Due to the failure of the second core parallel processing unit 202 itself, the important data list it formed is unpredictable, namely L2 = [w, x, y, z]. After the second information exchange, the important data matrix formed by the second core parallel processing unit 202 is unpredictable. In the second round of information exchange, the important data matrix formed by the first core parallel processing unit 201 is:

[0064]

[0065] The important data matrix formed by the third core parallel processing unit 203 is:

[0066]

[0067] The important data matrix formed by the fourth core parallel processing unit 204 is:

[0068]

[0069] The normal first core parallel processing unit 201, the third core parallel processing unit 203 and the fourth core parallel processing unit 204 can trust the important data in each column of the matrix whose occurrence frequency is greater than or equal to 3, and each normal core parallel processing unit can identify the faulty second core parallel processing unit 202; further, the fault information of the second core parallel processing unit 202 can be sent to the satellite-ground TT&C information processing module 30, and the satellite-ground TT&C information processing module 30 can perform fault processing and recovery on the second core parallel processing unit 202.

[0070] Figure 2 The specific process of screening the faulty unit through information interaction of each core parallel processing unit is as follows:

[0071] Each core parallel processing unit of the core processing module obtains its own important data through operation, then judges whether the exchange deadline time arrives through the first timer, if the exchange deadline time arrives, sends its own important data to other core parallel processing units, and receives the important data of other core parallel processing units, and merges the received important data with its own important data to form an important data list L_i; judges whether the predetermined exchange deadline time arrives through the second timer, which can be the same as or different from the exchange deadline time of the first timer; when the exchange deadline time of the second timer arrives, the second round of information exchange is entered, each core parallel processing unit sends its own important data list to other core parallel processing units, and receives the important data list of other core parallel processing units, after collecting all the important data lists, an important data matrix D_i is formed, then information judgment is performed on D_i, specifically, whether the occurrence frequency of each important data in D_i reaches a preset frequency threshold is judged, if a certain important data does not reach the preset frequency threshold, the core parallel processing unit generating the important data is determined as a faulty unit, and the code corresponding to the faulty unit is sent to the satellite-ground TT&C information processing module, and the satellite-ground TT&C information processing module performs fault processing and recovery on it.

[0072] Furthermore, in this embodiment, the storage resources of the core parallel processing units are divided into multiple independent task storage modules based on different task requirements. Each task storage module stores task information corresponding to the task requirements. Specifically, storage resource partitioning is employed for each core parallel processing unit. This storage resource partitioning involves dividing the storage resources of each core parallel processing unit into multiple independent modules based on different task requirements. These task storage modules are independent and uncoupled, ensuring real-time and accurate information acquisition.

[0073] See also Figure 3 , with respect to the onboard information system tasks of this embodiment, they can be specifically divided into the following multiple task storage modules:

[0074] GNSS solution information storage module: used to store the position and time information of Beidou and GPS satellites, and the mode information of the GPS navigation module;

[0075] Measurement and control modulation and demodulation information storage module: used to store downlink telemetry information to be sent to the ground station in clear / confidential state, and uplink command information from the ground station to be distributed after demodulation;

[0076] Navigation augmentation management information storage module: used to store navigation augmentation power information, as well as the time and orbit information that needs to be sent to the navigation augmentation payload;

[0077] Inter-partition interaction information storage module: used to store information about interactions between different partitions;

[0078] Laser communication management information storage module: used to store the pointing angle and intensity information of the laser communication payload, as well as calibration instructions to be sent to the laser communication payload;

[0079] Broadband communication management information storage module: used to store communication effect evaluation information of broadband communication loads and communication service setting instructions to be sent to broadband communication loads;

[0080] Energy management information storage module: used to store solar current and energy real-time load information, energy load calculation coefficient, DOD threshold and other binding parameters, and battery setting instructions to be sent to the energy terminal;

[0081] Thermal control management information storage module: used to store binding parameters such as the real-time temperature value of each temperature measurement point, the real-time on / off status of the heater circuit, the upper and lower thresholds of the thermistor, the thermal control circuit switch instructions, and the status setting instructions to be sent to the thermal control circuit;

[0082] Feeding service management information storage module: used to store the position information of the feeding service load antenna and the direction setting instructions to be sent to the feeding service terminal;

[0083] Satellite management information storage module: used to store the status table of each device on the satellite (power-on status / health status / duty status), initialization program control sequence, satellite-rocket separation program control sequence and initialization parameters of various software functions, etc., and is used to periodically refresh and store important data on the satellite;

[0084] Reserved mission information storage module: This storage module is a reserved storage area used to store tasks for newly added software functions of satellites in orbit.

[0085] Furthermore, the core parallel processing units of this embodiment divide the processor task cycle into different time slices based on the runtime of each pending task; and each pending task is assigned a priority for task execution. In other words, each core parallel processing unit employs time-sharing of computing resources. This time-sharing of computing resources involves assigning different priorities, high, medium, and low, to each task. The processor task cycle is then divided into different time slices based on the runtime of each task, allowing high-priority tasks to preempt the execution of low-priority tasks.

[0086] See also Figure 4 The high-priority tasks set in this embodiment include: telemetry tasks, command processing tasks, time system tasks, software on-orbit maintenance tasks, satellite-rocket separation program control tasks, bus management tasks, and important data storage and recovery tasks; medium-priority tasks include: thermal control autonomous management function, energy autonomous management function, and FDIR management function; low-priority tasks include: broadband communication management, laser communication management, feed service management, and other payload business management functions.

[0087] Satellites that previously used the CCSDS telemetry packet format used a virtual channel scheduling strategy to transmit telemetry packets in separate packets. The telemetry format slot occupied by each telemetry packet was not fixed, allowing for the addition or removal of telemetry packets as needed. However, the priority of virtual channels and telemetry packets could not be adaptively adjusted. To address this issue, the present invention also provides a method for autonomous satellite telemetry scheduling based on the aforementioned onboard information system. This method is used to achieve autonomous switching of telemetry priorities, adapt to changes in telemetry transmission priorities during operational mode transitions and before and after faults, and reduce the frequency of ground control operations.

[0088] The satellite telemetry autonomous scheduling method comprises the steps of: establishing a plurality of virtual channels for satellite telemetry downlink operation, each virtual channel occupying a fixed number of telemetry bytes, and the plurality of virtual information being respectively configured with corresponding priorities; setting the execution frequency of the virtual channel according to the priority; calculating the time-sharing efficiency ratio corresponding to the telemetry packet according to the telemetry packet length and the telemetry packet priority of each satellite telemetry packet; sorting each telemetry packet according to the time-sharing efficiency ratio, and gradually accumulating the number of bytes occupied by the telemetry packet according to the sorting until the virtual channel is filled; wherein each virtual channel is downlinked according to the corresponding priority. Specifically, the time-sharing efficiency ratio is the ratio of the telemetry packet length and the telemetry packet priority.

[0089] For example, taking 3 virtual channels as an example, VC1 is high priority, priority is α; VC2 is medium priority, priority is β; VC3 is low priority, priority is γ; further set the execution frequency of the virtual channel according to the priority, such as the execution frequency of VC1 is The execution frequency of VC2 is The execution frequency of VC3 is The telemetry of the satellite includes time-sharing partition information system telemetry packets, navigation enhancement load telemetry packets, wideband communication load telemetry packets, energy terminal load telemetry packets, laser communication load telemetry packets, feeder service load telemetry packets, and thermal control terminal load telemetry packets, each with a length of R i and a priority of K i (i is the telemetry packet number); define the time-sharing efficiency ratio of each telemetry packet as η i , η i = R i / K i ; the number of virtual channel telemetry bytes is T, the time-sharing efficiency ratio of the telemetry packet is sorted from high to low, and the number of bytes occupied by the telemetry packet is gradually accumulated until the virtual channel is filled.

[0090] According to the following formula

[0091]

[0092] The first n telemetry packets are arranged in the virtual channel VC1 for execution, and the remaining virtual channels are filled by the same calculation, and the virtual channels are downlinked according to their priorities.

[0093] To sum up, the present invention adopts an information system architecture that can be used for multi-functional constellation satellites, utilizes time-sharing and partitioning processing technology, can serve the satellite's multi-functional business types, provide information resource support for the satellite, and adopts multiple low-cost processing units for parallel processing to avoid a single low-cost processing unit being knocked over by a single particle in orbit and causing mission failure, thereby reducing costs while improving the overall reliability of the information system; adopts a partition information synchronization and fault judgment method based on LVDS interface interconnection, and each parallel processing unit exchanges important data in real time through the LVDS interface. Each unit finds the faulty unit by analyzing the acquired important data matrix and making a comprehensive judgment, and uses the satellite-to-ground measurement and control information processing module to isolate / restore the faulty unit; adopts a dynamic and adaptive telemetry downlink method, and adopts a satellite telemetry autonomous scheduling method based on time-sharing dynamic priority to realize autonomous switching of telemetry priority, adapt to the telemetry downlink resource allocation under various work business conversions, and achieve reasonable allocation of telemetry resources.

[0094] Those skilled in the art will appreciate that the embodiments of the present application can be provided as methods, systems, or computer program products. Therefore, the present application can adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment in combination with software and hardware. Moreover, the present application can adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to magnetic disk storage and optical storage, etc.) that contain computer-usable program code.

[0095] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems) and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0096] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0097] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0098] Of course, the present invention may have many other embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art may make various corresponding changes and modifications based on the present invention, but these corresponding changes and modifications should all fall within the scope of protection of the claims attached to the present invention.

[0099] The contents not described in detail in the specification of the present invention belong to the common knowledge of professionals in this field.

Claims

1. A time-sharing and zone-sharing satellite-borne information system, characterized in that: It includes GNSS navigation module, core processing module and satellite-ground measurement and control information processing module, among which: The GNSS navigation module is used to receive satellite signals, pre-process the satellite signals to calculate navigation information of navigation satellites, send the navigation information to the core processing module, and receive mode control information of the core processing module; The core processing module includes multiple core parallel processing units, which are used to perform calculations on data information of each functional module. The core parallel processing units transmit calculation processing information to each other through the LVDS bus and perform internal synchronization processing; wherein, each functional module includes at least the GNSS navigation module and the satellite-to-ground measurement and control information processing module; The storage resources of the core parallel processing unit are divided into multiple independent task storage modules according to different task requirements, and each task storage module stores task information corresponding to the task requirement; The processor task cycle of the core parallel processing unit is divided into different time slices according to the running time of each task to be executed; and each task to be executed is configured with a priority of task execution order; The satellite-to-ground measurement and control information processing module is used to frame telemetry data packets and periodically transmit them to the ground measurement and control station based on the telemetry information received from the core processing module; and is used to receive uplink remote control instructions from the ground measurement and control station.

2. The time-sharing and partitioned satellite-borne information system according to claim 1, characterized in that: The core processing module is used to receive the navigation information, calculate the star time information and the orbital position information of the satellite through positioning and orbit determination operations, and send mode control information to the GNSS navigation module via the satellite-ground measurement and control information processing module to switch the navigation mode; The core processing module is used to send satellite telemetry packets to the satellite-ground measurement and control information processing module, and receive ground instructions from the satellite-ground measurement and control information processing module, and parse, process and distribute the ground instructions.

3. The time-sharing and partitioned satellite-borne information system according to claim 1, characterized in that: The functional modules also include a navigation enhancement payload, a broadband communication payload, an energy terminal, a laser communication payload, a feed service payload, and a thermal control terminal; The core processing module is further configured to send time and orbit information to the navigation enhancement payload via the satellite-to-ground measurement and control information processing module, and to receive power information of the navigation enhancement payload; The core processing module is further configured to send time information and communication service setting instructions to the broadband communication payload based on the communication effect evaluation information received from the broadband communication payload; The core processing module is further configured to analyze the current energy status and the health status of the energy terminal according to the solar current and the load information of the energy terminal, and send a battery setting instruction to the energy terminal based on the analysis result; The core processing module is further configured to calculate laser link establishment accuracy based on laser pointing angle and intensity information received from the laser communication payload, and send laser pointing and configuration information to the laser communication payload based on the laser link establishment accuracy; The core processing module is further configured to calculate antenna pointing accuracy based on actual antenna pointing position information received from the feeding service payload, and send feeding antenna pointing adjustment information to the feeding service payload based on the antenna pointing accuracy; The core processing module is further configured to determine whether a heater switch is required based on the thermistor resistance value received from the thermal control terminal and a preset thermal control autonomous management strategy, and if required, send a corresponding heater control instruction to the thermal control terminal.

4. The time-sharing and partitioned satellite-borne information system according to claim 1, characterized in that: The satellite-to-ground measurement and control information processing module is further configured to send direct discrete instructions in the uplink remote control instructions to the lower computer, and to verify indirect instructions in the uplink remote control instructions before sending them to the core processing module.

5. The time-sharing and partitioned satellite-borne information system according to claim 1, characterized in that: The core processing module also has a fault detection mechanism, which is implemented based on information synchronization between the multiple core parallel processing units. The information synchronization operation between the multiple core parallel processing units is as follows: Each of the core parallel processing units receives important data sent by other core parallel processing units and combines the important data with its own important data to form an important data list; Each of the core parallel processing units receives other important data lists sent by other core parallel processing units, and forms an important data matrix with the important data lists of its own; Each of the core parallel processing units determines whether the corresponding important data is real data according to the number of occurrences of the important data in the important data matrix.

6. The time-sharing and zone-sharing satellite-borne information system according to claim 5, characterized in that: Each of the core parallel processing units determines whether the number of occurrences of each important data in the important data matrix is ​​not less than a preset number threshold. If so, it determines that the corresponding important data is real data; wherein, the number threshold is the number of core parallel processing units of the core processing module minus one.

7. A satellite telemetry autonomous scheduling method based on the onboard information system according to any one of claims 1 to 6, characterized in that: Including steps: Establishing multiple virtual channels for satellite telemetry downlink operation, each of the virtual channels occupies a fixed number of telemetry bytes, and the multiple virtual channels are respectively configured with corresponding priorities; According to the priority, setting the execution frequency corresponding to the virtual channel; Calculating a time-sharing efficiency ratio corresponding to each telemetry packet according to the telemetry packet length and telemetry packet priority of each satellite telemetry packet; The telemetry packets are sorted according to the time-sharing efficiency ratio, and the number of bytes occupied by the telemetry packets is gradually accumulated according to the sorting until the virtual channel is filled; wherein, each virtual channel is transmitted according to the corresponding priority.

8. The satellite telemetry autonomous scheduling method according to claim 7, characterized in that: The time-sharing efficiency ratio is a ratio of the telemetry packet length to the telemetry packet priority.

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