Satellite constellation system and communication control method

Abstract

The embodiment of the invention provides a satellite constellation system and a communication control method, the system comprises a plurality of load satellites which are in inter-satellite communication connection, and each load satellite comprises a comprehensive electronic subsystem, a communication navigation subsystem, an attitude and orbit control subsystem and a power supply and distribution subsystem. During an on-orbit task, a spaceborne computer of the comprehensive electronic subsystem can obtain information of a current task stage, calculates communication target parameters according to a communication mode corresponding to the current task stage, and generates an attitude adjustment instruction based on communication attitude parameters corresponding to the communication target parameters; and controlling the attitude and orbit control subsystem to adjust the inter-satellite communication module and / or the ground communication module to a communication attitude associated with the azimuth information. According to the system, data processing and communication processes can be dispersed to a plurality of load satellites through inter-satellite communication, and the communication attitude requirement of the inter-satellite communication process is automatically adapted, so that the problem of low timeliness of the satellite system data processing and communication processes is solved.

Description

Technical Field

[0001] This application relates to the field of intelligent satellite technology, and particularly to a satellite constellation system and a communication control method. Background Art

[0002] A satellite system is a system that uses artificial satellites orbiting the Earth to achieve various functions in cooperation with ground equipment. Depending on the functions to be achieved, the satellite system can carry satellite payloads corresponding to the functions to be achieved. Among them, satellite payloads generally refer to various devices and instruments installed on satellites, which are used to perform specific tasks and collect information about the Earth or outer space.

[0003] After carrying a specific satellite payload, the satellite system can perform on-orbit tasks according to design requirements. For example, the satellite system can provide services such as agricultural resource investigation, agricultural production process monitoring, data collection and exchange for application scenarios such as smart agriculture, Internet of Things, emergency disaster relief, and smart city, to meet the needs of industries such as agriculture, ocean, logistics, water conservancy, earthquake, meteorology, environmental protection, and transportation in specific regions.

[0004] However, due to the limited processing capacity, payload capacity, and communication capacity of the satellite system, the satellite system cannot achieve full coverage of a large area in the face of application scenarios in a large area. Moreover, in the face of on-orbit tasks in a large area, the data interaction between the satellite system and ground equipment is frequent, resulting in the satellite being in a high-load state for a long time, which will not only reduce the timeliness of the data processing and communication process of the satellite system, but also shorten the on-orbit operation life of the satellite. Summary of the Invention

[0005] In view of this, an embodiment of this application provides a satellite constellation system and a communication control method to solve the problem of low timeliness in the data processing and communication process of the satellite system.

[0006] According to one aspect of this application, a satellite constellation system is provided. The system includes multiple payload satellites, and communication connections are established between the multiple payload satellites through inter-satellite communication. The payload satellite includes:

[0007] An integrated electronics subsystem, including an on-board computer, the on-board computer has an on-board management application built in, and the on-board computer executes satellite control by running the on-board management application;

[0008] A communication and navigation subsystem, connected to the integrated electronics subsystem; the communication and navigation subsystem includes a ground communication module and an inter-satellite communication module. The ground communication module is configured to establish a communication connection with ground equipment; the inter-satellite communication module is configured to establish a communication connection with at least one of the multiple payload satellites;

[0009] The attitude and orbit control subsystem includes at least one attitude adjustment component configured to adjust the operating attitude of the payload satellite;

[0010] The power supply and distribution subsystem is connected to the integrated electronic subsystem, the communication and navigation subsystem, and the attitude and orbit control subsystem, and is configured to provide energy input to the integrated electronic subsystem, the communication and navigation subsystem, and the attitude and orbit control subsystem;

[0011] The on-board computer is further configured to:

[0012] Obtain current mission phase information, where the current mission phase information includes the current mission phase and the corresponding communication method for the current mission phase;

[0013] Calculate communication target parameters according to the communication method, where the communication target parameters include the communication target device and the azimuth information of the communication target device;

[0014] Calculate communication attitude parameters based on the communication target parameters;

[0015] Generate an attitude adjustment instruction based on the communication attitude parameters and send the attitude adjustment instruction to the attitude and orbit control subsystem; the attitude adjustment instruction is used to control the attitude adjustment component to adjust the inter-satellite communication module and / or the earth communication module to the communication attitude associated with the azimuth information.

[0016] Optionally, it further includes a structure subsystem configured to carry satellite components; the integrated electronic subsystem, the communication and navigation subsystem, the attitude and orbit control subsystem, and the power supply and distribution subsystem are arranged on the structure subsystem.

[0017] Optionally, it further includes a thermal control subsystem, and the thermal control subsystem includes an active thermal control module and a passive thermal control module; the passive thermal control module includes one or more combinations of a heat insulation layer, a heat insulation pad, and thermal control materials; the active thermal control module includes a heater and a temperature detection component; the heater and the temperature detection component are connected to the on-board computer;

[0018] The on-board computer is configured to:

[0019] Determine the current working component according to the current mission phase information;

[0020] Receive the current temperature collected by the temperature detection component in the deployment space of the current working component;

[0021] Obtain the working temperature range of the current working component;

[0022] If the current temperature is not within the operating temperature range, send a temperature control instruction to the heater, where the temperature control instruction is used to control the heater to generate a temperature rise.

[0023] Optionally, the on-board computer is further configured to:

[0024] Receive data to be transmitted according to the current mission phase information, where the data to be transmitted includes inter-satellite communication data and satellite-ground communication data;

[0025] Send the inter-satellite communication data to the inter-satellite communication module to transmit the inter-satellite communication data to the payload satellite serving as the communication target device through the inter-satellite communication module;

[0026] Send the satellite-ground communication data to the ground communication module to transmit the satellite-ground communication data to the ground device serving as the communication target device through the ground communication module.

[0027] Optionally, the inter-satellite communication module includes an inter-satellite laser communication unit; the inter-satellite laser communication unit includes a laser, a driving mechanism, a transmitting and receiving optical antenna, and a tracking and detection component; the laser is connected to the transmitting and receiving optical antenna through an optical fiber; the movable end of the driving mechanism is connected to the transmitting and receiving optical antenna and the tracking and detection component; the laser is also connected to the on-board computer through a cable;

[0028] The on-board computer is further configured to:

[0029] Parse the azimuth information of the communication target device from the communication target parameters, where the communication target device is one of the multiple payload satellites;

[0030] Calculate the optical signal transmission path according to the azimuth information;

[0031] Calculate the target driving angle of the driving component based on the optical signal transmission path;

[0032] Generate an angle adjustment instruction according to the target driving angle, and send the angle adjustment instruction to the driving mechanism so that the driving mechanism adjusts the optical signal emission direction of the transmitting and receiving optical antenna to coincide with the optical signal transmission path.

[0033] Optionally, the inter-satellite communication module further includes an inter-satellite electromagnetic communication unit; the inter-satellite electromagnetic communication unit includes an electrical signal transceiver antenna and a conversion circuit; the electrical signal transceiver antenna is connected to the on-board computer through the conversion circuit;

[0034] The on-board computer is further configured to:

[0035] Obtain the inter-satellite communication data;

[0036] Determine the data type of the inter-satellite communication data according to the data source of the inter-satellite communication data;

[0037] If the data type is the first type, send the inter-satellite communication data to the inter-satellite electromagnetic communication unit;

[0038] If the data type is the second type, send the inter-satellite communication data to the inter-satellite laser communication unit.

[0039] Optionally, the tracking and detection component includes a photosensitive array, and the photosensitive array includes a plurality of photosensitive chips; the photosensitive chips are configured to detect light intensity signals;

[0040] The on-board computer is further configured to:

[0041] Obtain the light intensity signals collected by the plurality of photosensitive chips;

[0042] Calculate the light signal deflection amount according to the light intensity signal and the position of the photosensitive chip in the photosensitive array;

[0043] Generate a light signal tracking instruction according to the deflection amount, and the light signal tracking instruction includes a tracking direction, and the tracking direction is determined according to the light intensities detected by the plurality of photosensitive chips;

[0044] Send the light signal tracking instruction to the driving mechanism.

[0045] Optionally, the ground communication module is further configured to:

[0046] Receive the measurement and control uplink signal sent by the ground equipment;

[0047] Demodulate and frame synchronize the measurement and control uplink signal to obtain uplink data;

[0048] Output the uplink data as an uplink data frame;

[0049] Analyze the uplink data frame to obtain satellite-ground communication data, and the satellite-ground communication data includes remote control PCM data, clock data, and locking signals;

[0050] Transmit the satellite-ground communication data to the integrated electronic subsystem.

[0051] Optionally, the attitude and orbit control subsystem further includes an attitude detection component, and the attitude detection component is connected to the on-board computer; the attitude detection component is configured to collect the current attitude information of the payload satellite;

[0052] The on-board computer is further configured to:

[0053] Parse the communication method corresponding to the current task stage from the current task stage information;

[0054] If the communication method includes inter-satellite communication, obtain the current attitude information and the azimuth information of the communication target device;

[0055] Calculate the attitude adjustment amount according to the current attitude information and the azimuth information;

[0056] Generate the attitude adjustment instruction according to the attitude adjustment amount.

[0057] According to another aspect of the present application, there is provided a satellite constellation communication control method, which is applied to the above satellite constellation system, and the method includes:

[0058] Obtain the current task stage information, where the current task stage information includes the current task stage and the communication method corresponding to the current task stage;

[0059] Calculate the communication target parameters according to the communication method, where the communication target parameters include the communication target device and the azimuth information of the communication target device;

[0060] Calculate the communication attitude parameters based on the communication target parameters;

[0061] Generate an attitude adjustment instruction based on the communication attitude parameters, and send the attitude adjustment instruction to the attitude and orbit control subsystem; the attitude adjustment instruction is used to control the attitude adjustment component to adjust the inter-satellite communication module and / or the ground communication module to the communication attitude associated with the azimuth information.

[0062] According to another aspect of the present application, there is provided a computer device, including a storage medium, a processor, and a computer program stored on the storage medium and executable on the processor, and when the processor executes the program, the above satellite constellation communication control method is implemented.

[0063] According to still another aspect of the present application, there is provided a storage medium, on which a computer program is stored, and when the program is executed by a processor, the above satellite constellation communication control method is implemented.

[0064] With the above technical solution, the embodiments of the present application provide a satellite constellation system and a communication control method. The system includes multiple payload satellites that establish inter-satellite communication connections. The payload satellites include an integrated electronics subsystem, a communication and navigation subsystem, an attitude and orbit control subsystem, and a power supply and distribution subsystem. During the on-orbit mission, the on-board computer of the integrated electronics subsystem can obtain the current mission phase information, calculate the communication target parameters according to the communication method corresponding to the current mission phase, and generate an attitude adjustment instruction based on the communication attitude parameters corresponding to the communication target parameters, controlling the attitude and orbit control subsystem to adjust the inter-satellite communication module and / or the communication module for earth communication to the communication attitude associated with the azimuth information. The system can disperse the data processing and communication processes to multiple payload satellites through inter-satellite communication and automatically adapt to the communication attitude requirements of the inter-satellite communication process to solve the problem of low timeliness in the data processing and communication processes of the satellite system.

[0065] The above description is only an overview of the technical solution of the present application. In order to be able to understand the technical means of the present application more clearly, it can be implemented according to the content of the specification. And in order to make the above and other purposes, features and advantages of the present application more obvious and understandable, the following specifically gives the specific embodiments of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0066] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The schematic embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation of the present application. In the drawings:

[0067] Figure 1 It is a schematic structural diagram of the satellite constellation system provided by the embodiment of the present application;

[0068] Figure 2 It is a schematic structural diagram of the payload satellite provided by the embodiment of the present application;

[0069] Figure 3 It is a schematic structural diagram of the navigation subsystem provided by the embodiment of the present application;

[0070] Figure 4 It is a schematic structural diagram of the control subsystem provided by the embodiment of the present application;

[0071] Figure 5 It is a schematic structural diagram of the power supply and distribution subsystem provided by the embodiment of the present application;

[0072] Figure 6 It is a schematic flow diagram of the communication control method provided by the embodiment of the present application;

[0073] Figure 7 It is a schematic structural diagram of the inter-satellite laser communication unit provided by the embodiment of the present application;

[0074] Figure 8Schematic diagram of the data transmission process provided by the embodiments of the present application. Detailed implementation manners

[0075] The present application will be described in detail below with reference to the accompanying drawings and in combination with embodiments. It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.

[0076] In the embodiments of the present application, the satellite system refers to a system that uses artificial satellites orbiting the earth and cooperates with ground equipment to achieve various functions. According to the different functions achieved, the satellite system can carry satellite payloads corresponding to the functions achieved. Among them, satellite payloads generally refer to various devices and instruments installed on satellites, which are used to perform specific tasks and collect information on the earth or cosmic space.

[0077] Due to the limited processing capacity, payload capacity, and communication capacity of the satellite system, when the satellite system faces application scenarios in a large area, it is impossible to achieve full coverage of the area. Moreover, when facing on-orbit tasks in a large area, the data interaction between the satellite system and ground equipment is frequent, resulting in the satellite being in a high-load state for a long time, which will not only reduce the timeliness of the data processing and communication process of the satellite system, but also shorten the on-orbit operation life of the satellite.

[0078] Therefore, in order to alleviate the problem of low timeliness in the data processing and communication process of the satellite system, in some embodiments, a satellite constellation system can be constructed based on multiple satellites. Among them, the satellite constellation system is a distributed satellite system composed of multiple satellites, and these satellites work together to form a whole to achieve specific task objectives, such as Figure 1 as shown. Compared with a single satellite, the satellite constellation system has a wider coverage range and stronger functions, and can provide global or regional services.

[0079] The satellites included in the satellite constellation system can carry payloads for the functions achieved, so the satellites can also be called payload satellites. The payloads carried by the payload satellites generally refer to various devices and instruments installed on the satellites, which are used to perform specific tasks and collect information on the earth or cosmic space. According to the different functions achieved, the types of payloads carried by the payload satellites are also different.

[0080] In some embodiments, the satellite constellation system can achieve continuous coverage of a specific area through the distribution of multiple satellites in different orbital planes. By optimizing the orbital planes and phase differences of the satellites, the coverage gaps are reduced and the coverage efficiency is improved.

[0081] The satellite constellation system can also be applied to fields such as communication, navigation, remote sensing, and environmental monitoring through communication and collaboration among multiple payload satellites and the interaction support of the ground control system.

[0082] In some embodiments, the satellite constellation system includes multiple payload satellites, and communication connections are established among the multiple payload satellites through inter-satellite communication. The number of payload satellites included in the satellite constellation system can be determined based on specific mission requirements and the analysis results of comprehensive constellation orbit design, constellation energy efficiency analysis, illumination condition analysis, and payload mission analysis, etc.

[0083] In some embodiments, orbit analysis is required when performing orbit design. For example, the primary goal of the satellite constellation system design is to provide comprehensive optical coverage of the design area. On this basis, the revisit period should be shortened as much as possible, and the revisit frequency should be increased to ensure the working duration of the satellite within the territory. Correspondingly, the selection of ground stations should ensure that each satellite in the constellation has at least 2 measurement and control arcs per day. The half field of view angle of the optical payload is 1.145°, and the ground width should be no less than 20 km. The push-broom imaging work starts under illumination conditions within the mission territory. The revisit period should be no less than 1 time / day.

[0084] Combined with the orbit analysis results, orbit design is performed. For example, the ground mission target of the satellite constellation system is Area A, and the total area of Area A is 8.5149 million square kilometers. The longitude ranges from 35° west to 74° west, and the latitude ranges from 5° north to 35° south. Then the orbit altitude is selected as 600 km, and the semi-major axis of the orbit is 6978137 m. The half field of view angle of the optical payload is 1.145°, and the ground width is about 24 km. The orbit type is set as a sun-synchronous orbit, and the inclination is 97.714°. The constellation contains 108 satellites, 12 orbital planes, the ascending nodes of the orbital planes are evenly distributed along the equator, and the right ascension of the ascending nodes between the orbital planes is about 30°. On average, 9 satellites are evenly distributed in each orbital plane. The inter-satellite phase interval in the same orbital plane is about 40°.

[0085] Since the payload satellite needs to operate in the space environment after being launched into the space environment and it is difficult to provide energy supply through external power supply, after performing orbit design, it is also necessary to perform energy efficiency analysis on the satellite constellation system. For example, according to the orbit design results, referring to the satellite layout, orbital plane distribution, and constellation sub-satellite point coverage, under the condition of ensuring that there are satellites in the airspace within the mission area throughout the whole time, the optical payload in the satellite constellation system can perform comprehensive push-broom coverage of the entire mission area within 2 days, and the coverage rate can reach 99.82% within 2 days.

[0086] Correspondingly, based on the orbit and energy efficiency analysis results, the ground observation stations can also be designed. For example, the ground observation stations adopt a triangular layout within the mission area. The longitude and latitude of the stations can be: Station 1, 68.8229° west longitude, 1.26882° north latitude; Station 2, 35.5982° west longitude, 6.25803° south latitude; Station 3, 54.9167° west longitude, 30.2367° south latitude. The measurement and control constraints of the stations are: the minimum elevation angle is 5°, and the shortest arc duration is 200 seconds. For each station, the number of measurement and control arcs with a duration of more than 200 seconds for all satellites within the constellation within a single day is not less than 2 times. For each station, there are measurement and control arcs with a duration of more than 600 seconds for all satellites within the constellation within a single day, which can be used for data downlink. The average measurement and control duration for all measurement and control arcs of each satellite is more than 400 seconds, and the average measurement and control duration for all measurement and control arcs of all satellites within the constellation is greater than 500 seconds.

[0087] After performing orbit design and energy efficiency analysis, illumination condition analysis can also be carried out. For example, starting from 4:00:00 UTC on September 8, 2023, the J2 orbit prediction model is used to analyze the illumination characteristics of the first satellite's mission orbit for one year. Through analysis, the change in the solar angle of a single orbital plane can be determined, and it can be known that the orbital solar angle fluctuates between 16° and 28° within one year. Among them, the orbital solar angle is positive when the angle between the sun direction and the orbital plane is biased towards the orbital normal direction. Correspondingly, the local time of the descending node of the first satellite is 10:30. During the one-year mission period, the maximum eclipse time per orbit is approximately 34.57 minutes, with an average of approximately 34.131 minutes, and the maximum eclipse time per day is approximately 8.07 hours. Based on the illumination condition analysis results, it is also possible to analyze the eclipse, penumbra, and sunlight within a day, and determine the eclipse, penumbra, and sunlight time periods on the day with the longest eclipse.

[0088] Payload analysis can include narrowband communication payload mission analysis and optical camera payload mission analysis. Among them, the narrowband communication payload is used to verify the feasibility of the user link in the Ultra High Frequency (UHF) radio wave band, the C-band feeder link, and the communication system, and at the same time verify the frequency compatibility with other communication systems. Conduct data service demonstration and verification for services such as data exchange, data collection, Automatic Identification System (AIS), and satellite broadcasting, conduct verification of the wide-area augmentation broadcast function of space-based navigation, and enable frequency resources. Cooperate with several miniaturized terminal prototypes and ground stations (including gateway stations and information processing centers) of the ground verification system to complete satellite-ground verification tests, etc.

[0089] The mission analysis of the optical camera payload can be input according to requirements. For example, the resolution of the optical camera can be sub-meter level, with a resolution of 1m@500km. According to this resolution index, the optical camera is analyzed and designed by comprehensively considering requirements such as miniaturization, light weight, low power consumption of the camera, and achieving high imaging quality with a large swath as much as possible.

[0090] Based on the analysis results such as the integrated constellation orbit design, constellation energy efficiency analysis, illumination condition analysis, and payload mission analysis, the payload satellite can be overall designed. That is, as Figure 2 shown, in some embodiments, the payload satellite includes: an integrated electronics subsystem, a communication and navigation subsystem, an attitude and orbit control subsystem, a power supply and distribution subsystem, etc. For example, the payload satellite can adopt a frame-panel structure, with attitude control using a zero-momentum three-axis stabilization control method and a thermal control strategy combining passive and active thermal control, a design life of 5 years, and a launch mass of 130 kg. Then the payload satellite can include parts such as a satellite platform and a payload. The satellite platform includes an attitude and orbit control subsystem, a thermal control subsystem, a structure and mechanism subsystem, an integrated electronics subsystem, a communication and navigation subsystem, and a power supply and distribution subsystem, etc. The payload can include an Internet of Things payload subsystem, a sub-meter resolution optical satellite subsystem, an inter-satellite laser communication subsystem, etc.

[0091] Among them, the integrated electronics subsystem includes an on-board computer, and the on-board computer has an on-board management application built in. The on-board computer executes satellite control by running the on-board management application. In some embodiments, satellite control can include control items such as on-board management, attitude and orbit control calculation, energy and thermal control management, orbit prediction, and payload mission management.

[0092] To meet satellite control, the on-board computer of the integrated electronics subsystem needs to meet the set parameter indicators. For example, the processing capacity of the processor of the on-board computer is not less than 150 MIPS, the FLASH capacity is 3M×8bit, and the MRAM capacity is 8M×8bit. And, the on-board computer supports communication interfaces such as RS422 and CAN, and supports the OC instruction output function. The on-board computer can also perform analog telemetry acquisition, and the time base accuracy requirement is ≤2×10 -6 , and the time base stability requirement is ≤2×10 -6 / day. It supports external interrupt items such as GNSS second pulse interruption, remote control interruption, and telemetry interruption.

[0093] In some embodiments, according to mission requirements, the integrated electronics subsystem can support specific tasks and functions. For example, the integrated electronics subsystem can transmit a downlink signal for measurement and control to the ground measurement and control station to guide the ground station to capture the satellite, and at the same time transmit the satellite telemetry information to the ground. And receive the uplink remote control signal of the ground measurement and control station, complete demodulation, and give the processed data to the on-board computer in the integrated electronics subsystem.

[0094] The integrated electronic subsystem can also be responsible for the functions of parsing and verifying uplink telecommand information, and realizing the functions of telecommand decoding, Cyclic Redundancy Check (CRC), direct command, and indirect pulse sending. In addition, it can realize the functions of downlink telemetry data framing, storage, playback, scrambling, and code rate switching. The integrated electronic subsystem should also have the functions of generating and maintaining a high-stability clock, collecting analog and temperature telemetry, receiving GPS / BD positioning, generating GPS / BD second pulse signals, and assisting the software to complete the time synchronization calibration of the entire satellite.

[0095] The integrated electronic subsystem can also provide a hardware operation platform for the attitude and orbit control application software and the overall satellite data management software, and jointly complete the satellite attitude and orbit control functions with the attitude and orbit control module. The integrated electronic subsystem also provides test interfaces, with functions of software uploading, button reset, quasi-disabled watchdog, and monitoring the operation of on-board software. It realizes the management of telecommand and telemetry, time information broadcasting, etc. through the Controller Area Network (CAN) bus and RS422 serial port. In addition, the integrated electronic subsystem can also have data storage and management functions and X-band data downlink functions.

[0096] The integrated electronic subsystem can perform the above tasks and realize the above functions through the on-board computer and the on-board applications running on the on-board computer. For example, the on-board computer can include computer boards A / B and function boards, integrating functions such as on-board management, attitude and orbit control calculation, energy and thermal control management, orbit prediction, and payload mission management.

[0097] The on-board computer can receive and process Pulse Code Modulation (PCM) code data of telecommands, perform descrambling and CRC verification, and output ordinary direct commands and telecommand data through the authorized machine. After the downlink overall satellite telemetry is framed by the on-board application, it is output to the transponder module. It can provide CAN bus and RS422 interfaces to collect data and output control for other module single machines and internal system modules, and receive Global Navigation Satellite System (GNSS) signals to complete the time synchronization calibration of the entire satellite.

[0098] The integrated electronic sub-system takes the on-board computer as the core and is equipped with functional boards to provide a hardware channel for the up-link and down-link TT&C information of the entire satellite, process the up-link telecommand information, generate the down-link telemetry information, provide a hardware operation platform for the entire satellite data management software and the attitude and orbit control application, and receive GNSS signals and data for use by the application program. For example, the on-board computer can complete functions such as computer calculation and processing, asynchronous RS422 communication, telecommand instruction parsing, telemetry data transmission, clock management, etc., and the functional requirements of Field-Programmable Gate Array (FPGA) products; complete the address decoding work of the CPU processor and each memory; complete the management work of synchronous / asynchronous serial communication, and the serial port has independent receive and transmit caches for each path, and each path of RS422 communication has the function of simultaneous reception and transmission; complete the drive of power devices, including heater drive, complete the acquisition of analog quantities, complete the power distribution of the computer processor board, and generate control right signals.

[0099] The communication and navigation sub-system is connected to the integrated electronic sub-system and is used to realize the communication connection relationship between the payload satellite and the ground equipment as well as between the payload satellites. To this end, the communication and navigation sub-system includes a ground communication module and an inter-satellite communication module. The ground communication module is configured to establish a communication connection with the ground equipment; the inter-satellite communication module is configured to establish a communication connection with at least one of multiple payload satellites.

[0100] After multiple payload satellites are launched into the space environment, inter-satellite communication can be carried out according to the mission phase. When performing inter-satellite communication, some payload satellites act as the transmitting end and some payload satellites act as the receiving end. To meet the communication requirements, the communication and navigation sub-system should meet the set TT&C technical indicators and the data transmission and storage indicators. For example, the TT&C technical indicators can include that the TT&C system is X-band TT&C; the code rate requirements are 8192bps for telemetry and 2000bps for telecommand; the bit error rate: telemetry ≤ 1×10 -5 , telecommand ≤ 1×10 -6 ; the modulation modes of the telecommand and telemetry signals: Binary Phase Shift Keying (BPSK). The spreading code rate of the telecommand and telemetry: 3.069Mcps; EIRP: ≥ -12dBW; G / T: ≥ -35dB / K. The data transmission and storage indicators can include the frequency band: X-band; the downlink rate: 600 / 900 / 1200Mbps (switchable by command); the modulation mode: QPSK / 8PSK / 16QAM (automatically switched with the rate); the coding mode: LDPC 7 / 8 channel coding; the effective isotropic radiated power (EIRP) of data transmission: ≥ 26dBW; the storage capacity: ≥ 6Tbits; support 4:1 and 2:1 compression modes.

[0101] In addition to the communication function, the communication and navigation subsystem may also have a navigation function. That is, the communication and navigation subsystem may be built-in with navigation components, such as GNSS components. Among them, the real-time position accuracy of the GNSS component is better than 10m (synthesized by three axes, 1σ); the real-time speed accuracy is better than 0.02m / s (1σ, flight direction); the time calibration accuracy is better than 100ns.

[0102] The communication and navigation subsystem can realize tasks and functions such as remote control, telemetry, and its own telemetry and command processing. Among them, remote control means receiving the X-band measurement and control uplink signal transmitted by the ground measurement and control station, demodulating and frame synchronizing it, then outputting the restored data as an uplink data frame, parsing the uplink data frame, and sending the remote control PCM data, clock pulse, and locking signal to the integrated electronic subsystem.

[0103] That is, in some embodiments, the ground communication module is further configured to receive the measurement and control uplink signal sent by the ground device, and perform demodulation and frame synchronization on the measurement and control uplink signal to obtain uplink data. Then output the uplink data as an uplink data frame, and parse the uplink data frame to obtain satellite-ground communication data and transmit the satellite-ground communication data to the integrated electronic subsystem. Among them, the satellite-ground communication data includes remote control PCM data, clock pulse data, and locking signal.

[0104] Telemetry means that the communication and navigation subsystem can receive the telemetry PCM data and clock pulse from the integrated electronic subsystem, modulate the downlink data frame, and send it to the ground measurement and control station in real time through the downlink channel. Self-telemetry and command processing means that both transponders can complete self-telemetry acquisition and send it to the integrated electronic processing, and can receive the command data from the integrated electronic to control their own states.

[0105] In some embodiments, the communication and navigation subsystem may include a measurement and control subsystem, a navigation subsystem, and a fixed storage and data transmission subsystem. Among them, the measurement and control subsystem may include X-band transponders (A / B machines), X-band power division microwave networks, X-band power division microwave networks, X-band transceiver antennas, high-frequency cables, etc.

[0106] The measurement and control subsystem may include a measurement and control transponder, and the measurement and control transponder can make corresponding changes according to the changes of the measurement and control frequency points and indicators. The measurement and control transponder adopts a dual-machine integrated structure, and the two single machines are independent on the electrical interface. Structurally, each machine is divided into two parts, a radio frequency part and a baseband part, and the radio frequency part is shielded to ensure EMC characteristics.

[0107] In some embodiments, the baseband part of the measurement and control transponder adopts an FPGA architecture and an Advanced RISC Machine (ARM) architecture based on reduced instruction set computing, and may include AD, DA, FPGA, ARM, Flash, and other peripheral interfaces and configuration chips. Among them, the FPGA can receive the uplink intermediate frequency signal used for analog-to-digital conversion (AD), identify the uplink signal frequency point; complete the demodulation and other processing of the uplink telecommand signal, recover the PCM and send it to the integrated electronics; complete the modulation of the telemetry information and send it to the radio frequency for downlink transmission.

[0108] The ARM can implement 422 serial bus communication, receive instructions, collect internal status information, and return the local telemetry. The radio frequency channel of the measurement and control transponder down-converts the X-band uplink signal to an intermediate frequency of about 70 MHz for baseband sampling for signal processing; up-converts the 20 MHz intermediate frequency signal sent from the baseband to the X-band, and performs filtering and amplification; the transmit channel can be independently switched and is controlled by the baseband, providing AGC and power telemetry for the whole machine. The measurement and control transponder can be powered by a secondary power supply, with the receiver powered on continuously and the transmitter not powered on continuously.

[0109] In some embodiments, the navigation subsystem based on BD / GPS orbit determination receiver subsystem includes two antennas, which respectively receive the signals of the BD / GPS navigation constellations output by the two antennas, output positioning, orbit determination, and 1PPS information, and can complete the rapid acquisition of BD and GPS navigation satellites and provide multiple high-precision pulse per second (PPS) signals. The navigation subsystem can also collect the temperatures of important heat-generating parts and output them through the RS422 bus. And perform real-time positioning and orbit determination calculations, outputting the position coordinates in the WGS84 and J2000 coordinate systems; when the whole machine is not positioned, orbit extrapolation can be performed.

[0110] Such as Figure 3As shown, the subsystem composition may include 1 GNSS receiver and 2 GNSS antennas, and 2 high-frequency cables. The GNSS receiver in the navigation subsystem can utilize the BD / GPS navigation signals output by the navigation antenna, first perform pre-filtering and low-noise amplification, and then perform down-conversion processing and digital quantization processing on the multi-channel RF signals, and output the quantization results to the high-dynamic baseband navigation signal processing SOC. The high-dynamic baseband navigation signal processing SOC completes the real-time acquisition, tracking, and positioning solution of 12-channel GPS L1CA code navigation signals and 12-channel BD BII code navigation signals. The ARM chip that has been verified by long-term flight is used to receive the PVT solution results, GPS L1CA code original observables, and BD B1C code original observables output by the high-dynamic baseband navigation signal processing SOC, and uses the DMC-based dynamic orbit integration algorithm and Kalman filtering algorithm to complete the accurate determination and accurate orbit extrapolation of the satellite orbit.

[0111] In some embodiments, the fixed storage and data transmission subsystem is used to complete the storage and downlink tasks of the whole satellite payload data and the whole satellite telemetry data. For example, it provides the functions of payload data and satellite telemetry data storage; formats the payload data and satellite telemetry data according to the CCSDS format; provides users with a flexible business data read-write mode; performs channel coding, scrambling, etc. on the downlink data transmission data; performs 16QAM, 8PSK, and QPSK modulation on the data transmission signals; for service satellites, it must have a data compression function, with compression ratios of 4:1 and 2:1, while retaining the uncompressed storage working mode, which can be switched by command, and the default working state is the data compression mode; amplifies the power of the modulated signals for downlink data transmission; completes the RF signal transmission and ground transmission through the antenna, etc.

[0112] The fixed storage and data transmission subsystem may include a fixed storage and data transmission integrated machine. The fixed storage and data transmission integrated machine includes a power module, a control module, a fixed storage module, a data transmission terminal, and a data transmission power amplifier. Among them, the data transmission terminal includes a baseband and an RF. The power module and the power amplifier can be integrated in a box body to convert the primary power into secondary power to supply power to the fixed storage module, the control module, the data transmission terminal, and the data transmission power amplifier. The whole satellite provides 2 channels of primary power for the fixed storage and data transmission integrated machine, the data transmission terminal and the data transmission power amplifier share 1 channel of primary power, and the fixed storage module and the control module share one channel of primary power.

[0113] The baseband module in the data transmission terminal can receive the downlink data stream stored in the fixed storage, and communicate in a handshake manner. Frame the data, scramble the data domain, perform LDPC coding after scrambling, then complete intermediate-frequency digital modulation in the FPGA, and convert the digital signal into an analog signal through the DA to output the intermediate frequency. It is mainly composed of an FPGA, an ARM, and a high-speed DA. The FPGA completes the main data processing, the DA realizes the digital-to-analog conversion, and the ARM mainly realizes the communication with the control module.

[0114] The solid state storage module mainly realizes the storage of payload data and engineering telemetry. The effective storage capacity of the data is not less than 6 Tb, and it can provide convenient data reading and writing operations, including storage, playback, real-time transmission, etc., as well as the management of the memory. The input interface of the solid state storage adopts the CXP (CoaXPress) interface (a total of 10 channels), and the communication rate of each CXP is 2500 Mbps (after 8B / 10B encoding), and it has the data processing ability to input data from 5 CXP interfaces simultaneously. At the same time, it has 1 asynchronous 422 interface to receive the engineering telemetry data of the integrated electronics. The solid state storage has a data output interface, which uses the GTX interface to communicate with the solid state storage data transmission all-in-one machine in a handshake manner, and the data output rate is 2.5 Gbps (effective data rate), which can meet the downlink data rate of 1200 Mbps.

[0115] The attitude and orbit control subsystem includes at least one attitude adjustment component, and the attitude adjustment component is configured to adjust the operating attitude of the payload satellite. As Figure 4 shown, in some embodiments, the attitude and orbit control subsystem can implement the attitude and orbit control function based on the attitude and orbit control application. The attitude and orbit control application can be set in the integrated electronics module and centrally managed by the integrated electronics.

[0116] In order to adjust the operating attitude of the payload satellite, the attitude and orbit control subsystem can first perform initial attitude capture, that is, after the satellite separation, reduce the separation angular velocity of the satellite within a specified time, eliminate the initial attitude deviation, and use medium and low-precision attitude measurement components to achieve the solar panel orientation to the sun to ensure energy supply. Then perform high-precision and high-stability attitude control. The attitude and orbit control subsystem can overcome various disturbance torques acting on the satellite body during the normal orbital operation of the satellite to meet the pointing accuracy and stability requirements of the mission.

[0117] In some embodiments, the attitude and orbit control subsystem can have the ability of attitude maneuver control to achieve goals such as remote sensing payload function, data transmission function, energy acquisition and orbit control. The attitude and orbit control analysis can also complete the attitude re-capture after the satellite is out of control for a short time through attitude re-capture. For example, first make the solar panel orient to the sun to ensure energy supply. After troubleshooting, re-implement high-precision three-axis stable pointing control.

[0118] The attitude and orbit control subsystem can also independently execute orbit control. For example, at the end of the satellite's life, it has the ability to actively deorbit. Throughout the satellite's life cycle, the attitude and orbit control subsystem can telemeter and transmit the working status data of the subsystem and individual units, receive ground remote control commands and relevant data injection, and correctly implement ground control of the subsystem. In addition, the attitude and orbit control subsystem can also perform fault diagnosis and isolation. That is, the attitude and orbit control subsystem should have a certain fault diagnosis ability. Within the scope of the system reliability redundancy design, it can switch the working status of components autonomously or remotely, or perform system reconfiguration: in case of emergency, it can enter the safe mode autonomously or remotely: with the participation of the ground, it can re-complete attitude capture and restore the three-axis stability of the satellite.

[0119] The power supply and distribution subsystem is connected to the integrated electronic subsystem, the communication and navigation subsystem, and the attitude and orbit control subsystem. The power supply and distribution subsystem is configured to provide energy input to the integrated electronic subsystem, the communication and navigation subsystem, and the attitude and orbit control subsystem.

[0120] The power supply and distribution subsystem can provide the satellite with an unregulated primary bus power supply and a secondary power distribution power supply during ground tests and various ground experiments. During the orbit transfer and on-orbit phases, it provides the satellite's various instruments and equipment with an unregulated primary bus power supply and a secondary power distribution power supply. For example, during illumination, it uses the solar array to generate electricity to supply power to the on-board equipment, stabilize the primary bus voltage, and charge the battery: during the shadow period, the battery releases electrical energy to provide an unregulated primary bus voltage for the satellite; short-term high-current loads are jointly powered by the solar array and the battery: the solar array thermal knife is directly powered by the battery pack

[0121] The power supply and distribution subsystem can also implement power management and control during on-orbit operation, including autonomous control of entering and leaving the shadow, control of the unregulated primary power supply bus and the secondary power distribution power supply: and providing transformation and interfaces for the telemetry and remote control required by the power module. The power supply and distribution subsystem can be managed and controlled by the on-board application, and the power supply and distribution subsystem realizes the response of the hardware function.

[0122] In some embodiments, the power supply and distribution subsystem can also provide an over-discharge protection circuit for the lithium-ion battery pack; distribution and switch control of the satellite platform and each on-board unit; control and protection of the unlocking current and its control circuit for the solar wing thermal knife; establishing an electrical connection path for each on-board device; providing an electrical connection between the satellite and the ground test equipment; implementing functions such as a low-impedance electrical conduction path protection between the chassis of each electrical unit and the satellite "ground".

[0123] Such as Figure 5As shown, the power supply and distribution subsystem may include a power supply subsystem and an overall circuit subsystem. The power supply subsystem includes a Power Control and Distribution Unit (PCDU), a lithium-ion battery pack, and a solar array circuit, enabling the power supply subsystem to supply power to satellite platform equipment and payloads, meeting the power requirements of the satellite during its entire lifespan and in various operating modes. The overall circuit subsystem includes a low-frequency cable network, cable brackets, and grounding stakes, enabling the overall circuit subsystem to establish electrical connection paths for on-board equipment, provide electrical connections between the satellite and ground test equipment, and implement low-impedance electrical conduction paths between the casings of each electrical unit and the satellite ground.

[0124] In addition to the above subsystems, in some embodiments, the satellite constellation system may further include a structure subsystem configured to carry satellite components; the integrated electronics subsystem, the communication and navigation subsystem, the attitude and orbit control subsystem, and the power supply and distribution subsystem are disposed on the structure subsystem.

[0125] For example, the structure subsystem may include a satellite structure and a solar panel structure. The satellite structure may include a main load-bearing cylinder, structural appendages, and directly affiliated assembly parts. The main load-bearing cylinder is integrally formed of carbon fiber with a rectangular cross-section, which can provide installation space and positions for the payload and instrument equipment of each subsystem of the satellite, and withstand the mechanical loads during ground transportation and launch, providing support for on-board equipment.

[0126] The satellite structure can ensure the strength and stiffness of the entire satellite during the active launch stage, ensure the space and positions for the installation of all on-board units inside and outside the satellite; meet the field of view and installation accuracy requirements of the payload and special equipment; meet the heat dissipation requirements of the entire satellite by the thermal control subsystem; meet the correct installation, connection, and unlocking requirements between the satellite and the launch vehicle; meet the requirements for satellite hoisting, turning over, and transportation.

[0127] The solar panel structure may include brackets for carrying the solar array, clamping and release devices, hinges, microswitches, etc. During the satellite launch phase, the clamping and release devices can ensure that the solar array is in a stowed state and is clamped and fixed to the satellite sidewall, ensuring that the satellite envelope does not exceed the dynamic envelope of the launch vehicle and can withstand the launch load environment. After the satellite is in orbit, the clamping and release devices are unlocked, and the solar array is unfolded and locked in a specified position through hinges. Microswitches are installed on one side of each folding solar panel hinge for monitoring the deployment state of the solar array.

[0128] In some embodiments, the satellite constellation system also includes a thermal control subsystem, which includes an active thermal control module and a passive thermal control module; the passive thermal control module includes an insulation layer, an insulation pad, and one or more combinations of thermal control materials; the active thermal control module includes a heater and a temperature detection component; the heater and the temperature detection component are connected to the onboard computer.

[0129] The satellite thermal control subsystem can adapt to the hot and cold environment of the satellite in space, provide a good working temperature environment for satellite units, and can quickly take away the heat generated by active units such as integrated electronics, gyroscopes, PCDU, and three-axis micro-flywheels. When the ambient temperature of the unit is low, it will heat it to ensure that its temperature index is within the required range.

[0130] In some embodiments, the thermal control subsystem may include devices for temperature control, such as heaters, thermistors, multi-layer insulation components, insulation pads, thermal control cables, sockets, and thermal control coating materials. The thermal control subsystem can be mainly passive thermal control, supplemented by active thermal control, and combine thermal analysis calculations with ground tests through satellite onboard computers to maintain key components within a specific operating temperature range. The thermal control subsystem should also have sufficient design margins, no single point failures, high reliability, and high safety. In addition, thermal control devices and materials should be as insensitive to space and ground environmental conditions as possible.

[0131] In order to perform satellite temperature control, the onboard computer can determine the current working component according to the current mission phase information. Then receive the current temperature collected by the temperature detection component in the deployment space of the current working component. Then obtain the working temperature range of the current working component; if the current temperature is not in the working temperature range, send a temperature control instruction to the heater, and the temperature control instruction is used to control the heater to generate temperature rise.

[0132] In order to realize satellite-to-ground and inter-satellite communications, the onboard computer is also configured to execute a satellite constellation system communication control method, such as Figure 6 As shown, the method includes:

[0133] S101. Obtain current task phase information.

[0134] The current mission phase information includes the current mission phase and the communication mode corresponding to the current mission phase. The current mission phase can be determined according to the current time, the operating position of the payload satellite, and the operating state of the payload satellite. For example, a satellite flight program may include four phases, namely, a launch phase, a state establishment phase, an on-orbit test phase, and an on-orbit operation phase.

[0135] Among them, the launch phase is from rocket ignition until the satellite-rocket separation phase. The state establishment phase refers to the period from satellite-rocket separation to the establishment of the satellite's normal operating mode. The main tasks in this phase are: rate damping, deployment of the solar array, solar acquisition, establishment of the satellite's normal attitude, and normal operation of the platform system, etc. The on-orbit test phase is the mission phase carried out before the formal execution of the set TT&C mission after the satellite's state is normal and stable. In this phase, functional tests will be carried out on all modules of the satellite to check the various functions of the satellite, and the performance of the satellite will be evaluated in combination with the usage situation in the on-orbit application phase.

[0136] The on-orbit test of the satellite includes the on-orbit test of the platform and the on-orbit test of the payload. First, the on-orbit test of the platform is carried out, and then the on-orbit test of the payload is carried out. The long-term on-orbit stable operation phase refers to the on-orbit mission carried out after the on-orbit test work of the satellite is completed and through the acceptance review. Therefore, the current mission phase of the satellite can be determined according to the current time.

[0137] After determining the current mission phase, the on-board computer can call the mission planning data from the stored database and determine the communication method to be adopted in the current mission phase based on the mission planning data. Among them, the communication method can be satellite-ground communication or inter-satellite communication, and in the communication method, it can also include the target device that needs to transmit data during communication. For example, when the communication method is satellite-ground communication, a nearest ground device among multiple ground devices deployed on the ground can be selected as the communication target device according to the position of the current payload satellite.

[0138] S102. Calculate communication target parameters according to the communication method.

[0139] After obtaining the current mission phase information, the on-board computer can extract the current mission phase and the corresponding communication method from the current mission phase information, and then calculate the communication target parameters according to the communication method. Among them, the communication target parameters include the communication target device and the azimuth information of the communication target device.

[0140] For different communication methods, the corresponding communication target devices are different, and according to the operation process of the satellite system, at different time points, the communication target devices have different azimuth information. For example, when the communication method is inter-satellite communication, the on-board computer can determine other payload satellites that communicate with the current payload satellite according to the current mission phase, that is, the target payload satellites. Then, according to the current mission phase, determine the current position (or current direction) of the target payload satellite, so as to calculate and obtain the communication target parameters.

[0141] S103. Calculate communication attitude parameters based on the communication target parameters.

[0142] After calculating and obtaining the communication target parameters, the on-board computer can calculate the communication attitude parameters based on the communication target parameters. Among them, the communication attitude parameters are used to characterize the operating attitude that the payload satellite needs to satisfy to complete the communication process.

[0143] In some embodiments, the inter-satellite communication module includes an inter-satellite laser communication unit. As Figure 7 shown, the inter-satellite laser communication unit includes a laser, a driving mechanism, a transmitting and receiving optical antenna, and a tracking and detection component. The laser is connected to the transmitting and receiving optical antenna through an optical fiber; the movable end of the driving mechanism is connected to the transmitting and receiving optical antenna and the tracking and detection component; the laser is also connected to the on-board computer through a cable.

[0144] The inter-satellite laser communication unit can realize inter-satellite communication based on the inter-satellite laser communication technology. Among them, inter-satellite laser communication is a technology that uses laser as an information carrier to establish a high-speed and high-bandwidth communication link between satellites. Inter-satellite laser communication can use laser as an information carrier, load information by modulating the light intensity, phase or frequency of the laser, and then send the modulated laser signal to the receiving end, and the receiving end restores the original information through demodulation. The carrier frequency of inter-satellite laser communication is extremely high, the available bandwidth is much larger than that of microwave communication, and the single-wave rate is expected to reach the order of 400 Gbit / s. Therefore, high transmission rate between satellites can be achieved. Moreover, the optical antenna and transceiver required for inter-satellite laser communication are small in size, light in weight, and low in power consumption, which are suitable for the miniaturization and lightweight of satellite payloads. The laser beam of inter-satellite laser communication has a small divergence angle and good directivity, is not easily captured and monitored, and has high confidentiality and anti-interference ability.

[0145] Due to the narrow beam characteristic of inter-satellite laser communication, it is required that the transmitting end and the receiving end need to be accurately aligned. And the payload satellites move at high speed in orbit and the relative positions are constantly changing. Therefore, the transmitting end and the receiving end must have high-precision beam capture and tracking capabilities. In some embodiments, the payload satellite can quickly capture the laser signal of the other party through a wide-angle optical system. And use a high-precision tracking system, such as a fast steering mirror, a micro-electro-mechanical system (MEMS), etc., to adjust the beam direction in real time to ensure that the beam is always aligned with the target.

[0146] In some embodiments, the tracking and detection component includes a photosensitive array, and the photosensitive array includes a plurality of photosensitive chips; the photosensitive chips are configured to detect light intensity signals. Correspondingly, the on-board computer may first obtain the light intensity signals collected by the plurality of photosensitive chips, and then calculate the deflection amount of the optical signal according to the light intensity signals and the positions of the photosensitive chips in the photosensitive array. Then, generate an optical signal tracking instruction according to the deflection amount, and send the optical signal tracking instruction to the driving mechanism. Wherein, the optical signal tracking instruction includes a tracking direction, and the tracking direction is determined according to the light intensities detected by the plurality of photosensitive chips.

[0147] Through the tracking and detection component, after a payload satellite establishes a communication connection with other payload satellites, the photosensitive chips in the tracking and detection component can detect the light intensity signals, and based on the change of the optical signals, track the position of the payload satellite. For example, the tracking and detection component includes 9 photosensitive chips in a 3×3 rectangular array. The 9 photosensitive chips can detect the light signal intensity in real time. When the light signal intensity detected by the No. 2 chip at the top is higher than that of the No. 5 chip in the middle, it indicates that the optical signal transmission path is biased in the upper direction. Therefore, the driving mechanism can be controlled to drive the optical transceiver antenna and the tracking and detection component to deflect a certain amount in the upper direction, so that the optical signal with the highest intensity is concentrated at the position of the No. 5 chip in the middle, realizing signal tracking and ensuring that the light beam is always aligned with the target.

[0148] When performing inter-satellite communication based on inter-satellite laser communication technology, the payload satellite can, after determining the communication target device, plan the inter-satellite communication path according to the azimuth information corresponding to the communication target device, and thus determine the operating attitude that the current payload satellite needs to maintain according to the inter-satellite communication path, that is, calculate and obtain the communication attitude parameters. Obviously, the communication attitude parameters are used to make the payload satellite maintain a specific attitude during operation. For example, when performing inter-satellite laser communication, the operating attitude corresponding to the communication attitude parameters can make the optical transceiver antenna of the current payload satellite align with the optical transceiver antenna of another payload satellite.

[0149] Therefore, in some embodiments, the on-board computer can parse the azimuth information of the communication target device from the communication target parameters. Wherein, the communication target device is one of the plurality of payload satellites. Then calculate the optical signal transmission path according to the azimuth information, and determine the communication attitude information according to the optical signal transmission path. The communication attitude information is used to represent the satellite operating attitude in which the optical signal emission direction of the optical transceiver antenna coincides with the transmission path.

[0150] S104. Generate an attitude adjustment instruction based on the communication attitude parameters, and send the attitude adjustment instruction to the attitude and orbit control subsystem.

[0151] After calculating the communication attitude parameters, the on-board computer can generate attitude adjustment instructions based on the communication attitude parameters. By sending the attitude adjustment instructions to the attitude and orbit control subsystem, the attitude and orbit control subsystem adjusts the operating attitude of the current payload satellite to meet the requirements of space-ground or inter-satellite communication. Among them, the attitude adjustment instructions are used to control the attitude adjustment component to adjust the inter-satellite communication module and / or the ground communication module to the communication attitude associated with the azimuth information.

[0152] In some embodiments, when the payload satellites communicate through inter-satellite laser communication technology, after calculating the optical signal transmission path, the target driving angle of the driving component can be calculated based on the optical signal transmission path. Then, an angle adjustment instruction is generated according to the target driving angle, and the angle adjustment instruction is sent to the driving mechanism, so that the driving mechanism adjusts the optical signal emission direction of the optical transceiver antenna to coincide with the optical signal transmission path.

[0153] In order to generate attitude adjustment instructions, in some embodiments, the attitude and orbit control subsystem further includes an attitude detection component, and the attitude detection component is connected to the on-board computer; the attitude detection component is configured to collect the current attitude information of the payload satellite. The attitude detection component may include detection components such as gyroscopes, magnetometers, star sensors, and sun sensors for determining the operating attitude of the satellite. Through the attitude detection component and the attitude adjustment component, the attitude and orbit control subsystem can achieve an attitude measurement accuracy of 0.005°, an attitude control accuracy of 0.03°, an attitude stability of 0.003° / s, an attitude side-sway ability of ±40°, an attitude maneuverability of 180° / 300s, an orbit maintenance accuracy of ±5 km in the nominal orbit. A phase maintenance accuracy of less than or equal to 0.1°, an average thrust of 0.5 N, and a total system impulse higher than 900 Ns.

[0154] Based on this attitude and orbit control subsystem, the on-board computer can parse the communication method corresponding to the current mission phase from the current mission phase information, and then judge the communication method corresponding to the current mission phase. If the communication method includes inter-satellite communication, the current attitude information and the azimuth information of the communication target device are obtained. Then, the attitude adjustment amount is calculated according to the current attitude information and the azimuth information, and the attitude adjustment instruction is generated according to the attitude adjustment amount.

[0155] By applying the technical solutions described in the above embodiments, the system includes multiple payload satellites that establish inter-satellite communication connections. The payload satellites include an integrated electronics subsystem, a communication and navigation subsystem, an attitude and orbit control subsystem, and a power supply and distribution subsystem. During the on-orbit mission, the on-board computer of the integrated electronics subsystem can obtain the current mission phase information, calculate the communication target parameters according to the communication method corresponding to the current mission phase, and generate an attitude adjustment instruction based on the communication attitude parameters corresponding to the communication target parameters, controlling the attitude and orbit control subsystem to adjust the inter-satellite communication module and / or the earth communication module to the communication attitude associated with the azimuth information. The system can disperse the data processing and communication processes to multiple payload satellites through inter-satellite communication and automatically adapt to the communication attitude requirements of the inter-satellite communication process to solve the problem of low timeliness in the data processing and communication processes of the satellite system.

[0156] Further, as a refinement and extension of the specific implementation manner of the above embodiments, in order to fully illustrate the specific implementation process of this embodiment, some embodiments of the present application also provide a satellite constellation system. On the basis of the above embodiments, the satellite constellation system can also select corresponding communication modules for different transmission data, that is, the on-board computer of the satellite constellation system is further configured to execute a communication control method, such as Figure 8 shown, and this method includes:

[0157] S201. Receive the data to be transmitted according to the current mission phase information.

[0158] In different mission phases, the payload satellites can transmit different data. For the sake of convenience of description, the data that needs to be transmitted during the communication process is called the data to be transmitted. Obviously, the data to be transmitted includes inter-satellite communication data and satellite-ground communication data. Among them, the inter-satellite communication data refers to the data transmitted between multiple payload satellites, such as measurement and control data, connection data, control instructions, etc. The satellite-ground communication data refers to the data transmitted between the payload satellite and the ground equipment, such as the uplink data sent by the ground equipment to the payload satellite and the downlink data sent by the payload satellite to the ground equipment.

[0159] After obtaining the current mission phase information, the on-board computer can execute the corresponding on-orbit mission according to the current mission phase information. As the on-orbit mission is executed, the payload satellite can generate the data to be transmitted. The data to be transmitted can be collected by other devices on the payload satellite, such as the image data captured by the payload camera, etc.; the data to be transmitted can also be generated by the on-board computer. For example, when multi-satellite collaborative control is required, the on-board computer will generate control instructions for controlling other payload satellites and convert the control instructions into the data to be transmitted. It can be seen that the data to be transmitted can be inter-satellite communication data, can also be satellite-ground communication data, or can include both inter-satellite communication data and satellite-ground communication data.

[0160] S202. Send the inter-satellite communication data to the inter-satellite communication module, so as to transmit the inter-satellite communication data to the payload satellite serving as the communication target device through the inter-satellite communication module.

[0161] After obtaining the data to be transmitted, the on-board computer can read the data to be transmitted and determine the inter-satellite communication data and the space-ground communication data in the data to be transmitted. For the inter-satellite communication data, the on-board computer can enable the inter-satellite communication module and send the inter-satellite communication data to the inter-satellite communication module, so as to transmit the inter-satellite communication data to the payload satellite serving as the communication target device through the inter-satellite communication module.

[0162] For example, for an on-orbit measurement and control mission, payload satellite A needs to cooperate with payload satellite B to completely cover the mission area. Therefore, when performing an on-orbit measurement and control mission, the on-board computer of payload satellite A can generate an image acquisition instruction for controlling payload satellite B to perform image acquisition. Then, the image acquisition instruction is sent to payload satellite B through the inter-satellite communication module.

[0163] S203. Send the space-ground communication data to the space-ground communication module, so as to transmit the space-ground communication data to the ground device serving as the communication target device through the space-ground communication module.

[0164] Similarly, after obtaining the data to be transmitted, the on-board computer can send the space-ground communication data in the data to be transmitted to the space-ground communication module and transmit the space-ground communication data to the ground device serving as the communication target device through the space-ground communication module.

[0165] By applying the technical solution of this embodiment, the payload satellite can enable different communication modules for different communication data in the data to be transmitted, which can enable the payload satellite to support multiple communication methods, meet the requirements of inter-satellite communication and space-ground communication, and improve communication timeliness.

[0166] In some embodiments, when the data to be transmitted includes inter-satellite communication data, the payload satellite can also use different communication methods to transmit the data according to the data type of the inter-satellite communication data. For example, the payload satellite can support both inter-satellite laser communication and inter-satellite electromagnetic communication. Correspondingly, on the basis of including an inter-satellite laser communication unit, the inter-satellite communication module can also include an inter-satellite electromagnetic communication unit; the inter-satellite electromagnetic communication unit includes an electrical signal transceiver antenna and a conversion circuit; the electrical signal transceiver antenna is connected to the on-board computer through the conversion circuit.

[0167] In order to perform inter-satellite communication, the on-board computer can also obtain the inter-satellite communication data and determine the data type of the inter-satellite communication data according to the data source of the inter-satellite communication data. Among them, the data source can include a device acquisition source and a computer generation source.

[0168] Since the data collected by the device is in the form of image frames, data frames, etc., the corresponding data volume is relatively large, and a relatively high communication bandwidth is required to quickly complete data transmission. Therefore, the data sourced from device collection is more suitable for transmission via inter-satellite laser communication.

[0169] The data generated by the computer is generally in the form of control instructions, etc. This type of data has a small volume and does not require a relatively high communication bandwidth. Moreover, data such as control instructions is associated with the control process. For example, when payload satellite A establishes a laser communication connection with payload satellite B, it may be necessary to simultaneously adjust the operating postures of payload satellite A and payload satellite B. However, when the laser communication connection is not established, control instructions for adjusting the posture cannot be transmitted, while the electromagnetic communication connection does not require posture adjustment. Therefore, for the data generated by the on-board computer, it is more suitable for transmission via inter-satellite electromagnetic communication.

[0170] For ease of description, the data type corresponding to the data generated by the on-board computer is referred to as the first type; while the data type corresponding to the data collected by the device is referred to as the second type. Therefore, after determining the data type of the inter-satellite communication data, the data can be sent to different communication units according to different data types. That is, if the data type is the first type, the inter-satellite communication data is sent to the inter-satellite electromagnetic communication unit to send the inter-satellite communication data to other payload satellites via inter-satellite electromagnetic communication. If the data type is the second type, the inter-satellite communication data is sent to the inter-satellite laser communication unit to send the inter-satellite communication data to other payload satellites via inter-satellite laser communication.

[0171] Furthermore, some embodiments of the present application also provide a satellite constellation communication control method applied to the above satellite constellation system. The method includes:

[0172] Obtain the current task phase information, where the current task phase information includes the current task phase and the corresponding communication method for the current task phase;

[0173] Calculate communication target parameters according to the communication method, where the communication target parameters include the communication target device and the azimuth information of the communication target device;

[0174] Calculate communication attitude parameters based on the communication target parameters;

[0175] Generate an attitude adjustment instruction based on the communication attitude parameters and send the attitude adjustment instruction to the attitude and orbit control subsystem; the attitude adjustment instruction is used to control the attitude adjustment component to adjust the inter-satellite communication module and / or the communication module to the ground to the communication attitude associated with the azimuth information.

[0176] By applying the technical solution of this embodiment, the communication control method can obtain the current task stage information, calculate the communication target parameters according to the communication method corresponding to the current task stage, generate an attitude adjustment instruction based on the communication attitude parameters corresponding to the communication target parameters, and control the attitude and orbit control subsystem to adjust the inter-satellite communication module and / or the communication module for earth observation to the communication attitude associated with the azimuth information. The method can disperse the data processing and communication processes to multiple payload satellites through inter-satellite communication and automatically adapt to the communication attitude requirements during the inter-satellite communication process, so as to solve the problem of low timeliness in the data processing and communication processes of the satellite system.

[0177] An embodiment of the present application further provides a computer device, which may specifically be a personal computer, a server, a network device, etc. The computer device includes a bus, a processor, a memory, and a communication interface, and may further include an input / output interface and a display device. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program, and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store location information. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, the steps in the method embodiments are implemented.

[0178] Those skilled in the art can understand that the structure of the above computer device is only a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components, or combine certain components, or have different component arrangements.

[0179] In one embodiment, a computer-readable storage medium is further provided. The computer-readable storage medium may be non-volatile or volatile, and stores a computer program. When the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0180] In one embodiment, a computer program product is further provided, including a computer program. When the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0181] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data for analysis, stored data, displayed data, etc.) involved in the present application are all information and data authorized by the user or fully authorized by all parties.

[0182] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods.

[0183] Among them, any reference to a memory, database, or other medium used in the embodiments provided in the present application may include at least one of non-volatile and volatile memories. Non-volatile memory may include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetoresistive random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc.

[0184] Volatile memory may include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM), etc.

[0185] The databases involved in the embodiments provided in the present application may include at least one of relational databases and non-relational databases. Non-relational databases may include distributed databases based on blockchain, etc., without limitation. The processors involved in the embodiments provided in the present application may be general-purpose processors, graphics processors, digital signal processors, programmable logic devices, data processing logics based on quantum computing, etc., without limitation.

[0186] The technical features of the above embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered to be within the scope described in this specification.

[0187] The above-described embodiments merely represent several implementation manners of the present application. The description thereof is relatively specific and detailed, but it should not be construed as a limitation to the patent scope of the present application. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present application, several modifications and improvements can still be made, and these all fall within the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the appended claims.

Claims

1. A satellite constellation system, characterized in that: The system includes a plurality of payload satellites, and communication connection is established between the plurality of payload satellites through inter-satellite communication; the payload satellites include: An integrated electronic subsystem, comprising an onboard computer, wherein the onboard computer has a built-in satellite management application, and the onboard computer performs satellite control by running the satellite management application; a communication and navigation subsystem connected to the integrated electronic subsystem; the communication and navigation subsystem comprises a ground communication module and an inter-satellite communication module, the ground communication module is configured to establish a communication connection with ground equipment; the inter-satellite communication module is configured to establish a communication connection with at least one of the plurality of payload satellites; an attitude and orbit control subsystem, comprising at least one attitude adjustment component, wherein the attitude adjustment component is configured to adjust the operating attitude of the payload satellite; a power supply and distribution subsystem, connected to the integrated electronic subsystem, the communication and navigation subsystem, and the attitude and orbit control subsystem, wherein the power supply and distribution subsystem is configured to provide energy input to the integrated electronic subsystem, the communication and navigation subsystem, and the attitude and orbit control subsystem; The onboard computer is further configured to: Acquire current task stage information, the current task stage information including the current task stage and the communication mode corresponding to the current task stage; Calculating communication target parameters according to the communication mode, wherein the communication target parameters include a communication target device and position information of the communication target device; Calculating communication posture parameters based on the communication target parameters; Generate an attitude adjustment instruction based on the communication attitude parameter, and send the attitude adjustment instruction to the attitude and orbit control subsystem; the attitude adjustment instruction is used to control the attitude adjustment component to adjust the inter-satellite communication module and / or the ground communication module to a communication attitude associated with the orientation information.

2. The system according to claim 1, characterized in that It also includes a structural subsystem configured to carry satellite components; the integrated electronic subsystem, the communication and navigation subsystem, the attitude and orbit control subsystem and the power supply and distribution subsystem are arranged on the structural subsystem.

3. The system according to claim 1, characterized in that It also includes a thermal control subsystem, the thermal control subsystem includes an active thermal control module and a passive thermal control module; the passive thermal control module includes a thermal insulation layer, a thermal insulation pad and one or more combinations of thermal control materials; the active thermal control module includes a heater and a temperature detection component; the heater and the temperature detection component are connected to the onboard computer; The onboard computer is configured as follows: Determine the current working component according to the current task stage information; Receiving the current temperature collected by the temperature detection component in the deployment space of the current working component; Obtaining the operating temperature range of the current operating component; If the current temperature is not within the operating temperature range, a temperature control instruction is sent to the heater, where the temperature control instruction is used to control the heater to generate a temperature rise.

4. The system according to claim 1, characterized in that The onboard computer is further configured to: receiving data to be transmitted according to the current mission phase information, wherein the data to be transmitted includes inter-satellite communication data and satellite-to-ground communication data; Sending the intersatellite communication data to the intersatellite communication module, so as to transmit the intersatellite communication data to a payload satellite as the communication target device through the intersatellite communication module; The satellite-to-ground communication data is sent to the ground communication module, so that the satellite-to-ground communication data is transmitted to the ground device as the communication target device through the ground communication module.

5. The system according to claim 4, characterized in that The intersatellite communication module includes an intersatellite laser communication unit; the intersatellite laser communication unit includes a laser, a driving mechanism, a transceiver optical antenna, and a tracking and detection component; the laser is connected to the transceiver optical antenna through an optical fiber; the active end of the driving mechanism is connected to the transceiver optical antenna and the tracking and detection component; the laser is also connected to the onboard computer through a cable; The onboard computer is further configured to: parsing the position information of the communication target device from the communication target parameters, wherein the communication target device is one of the plurality of payload satellites; Calculate the optical signal transmission path according to the orientation information; Calculating a target driving angle of the driving component based on the optical signal transmission path; An angle adjustment instruction is generated according to the target driving angle, and the angle adjustment instruction is sent to the driving mechanism, so that the driving mechanism adjusts the optical signal emission direction of the transceiver optical antenna to coincide with the optical signal transmission path.

6. The system according to claim 5, characterized in that The intersatellite communication module further includes an intersatellite electromagnetic communication unit; the intersatellite electromagnetic communication unit includes an electric signal transceiver antenna and a conversion circuit; the electric signal transceiver antenna is connected to the onboard computer via the conversion circuit; The onboard computer is further configured to: Acquiring the intersatellite communication data; Determining the data type of the inter-satellite communication data according to the data source of the inter-satellite communication data; If the data type is the first type, sending the inter-satellite communication data to the inter-satellite electromagnetic communication unit; If the data type is the second type, the inter-satellite communication data is sent to the inter-satellite laser communication unit.

7. The system according to claim 5, characterized in that The tracking detection component includes a photosensitive array, and the photosensitive array includes a plurality of photosensitive chips; the photosensitive chips are configured to detect light intensity signals; The onboard computer is further configured to: Acquire light intensity signals collected by a plurality of the photosensitive chips; Calculate the light signal deflection amount according to the light intensity signal and the position of the photosensitive chip on the photosensitive array; Generate a light signal tracking instruction according to the deflection amount, wherein the light signal tracking instruction includes a tracking direction, and the tracking direction is determined according to the light intensity detected by the plurality of photosensitive chips; The optical signal tracking instruction is sent to the driving mechanism.

8. The system according to claim 1, characterized in that The ground communication module is further configured as follows: Receiving a measurement and control uplink signal sent by the ground equipment; Performing demodulation and frame synchronization on the measurement and control uplink signal to obtain uplink data; Outputting the uplink data as an uplink data frame; Parsing the uplink data frame to obtain satellite-to-ground communication data, wherein the satellite-to-ground communication data includes remote control PCM data, code clock data, and a locking signal; The satellite-to-ground communication data is transmitted to the integrated electronic subsystem.

9. The system according to claim 1, characterized in that The attitude and orbit control subsystem further comprises an attitude detection component, which is connected to the onboard computer; the attitude detection component is configured to collect current attitude information of the payload satellite; The onboard computer is further configured to: Parsing the communication mode corresponding to the current task stage from the current task stage information; If the communication method includes inter-satellite communication, obtaining the current posture information and the position information of the communication target device; Calculating a posture adjustment amount according to the current posture information and the orientation information; The posture adjustment instruction is generated according to the posture adjustment amount.

10. A satellite constellation communication control method, characterized in that: Applied to the satellite constellation system according to any one of claims 1 to 9, the method comprising: Acquire current task stage information, the current task stage information including the current task stage and the communication mode corresponding to the current task stage; Calculating communication target parameters according to the communication mode, wherein the communication target parameters include a communication target device and position information of the communication target device; Calculating communication posture parameters based on the communication target parameters; An attitude adjustment instruction is generated based on the communication attitude parameter, and the attitude adjustment instruction is sent to the attitude and orbit control subsystem; the attitude adjustment instruction is used to control the attitude adjustment component to adjust the intersatellite communication module and / or the ground communication module to the communication attitude associated with the orientation information.

Images