Low-orbit satellite measurement and control method, satellite, electronic equipment and medium

Abstract

The invention relates to the technical field of low-orbit satellite measurement and control, and provides a low-orbit satellite measurement and control method, a satellite, electronic equipment and a medium, and the method comprises the steps: obtaining the space measurement and control signals of a reference satellite and a to-be-positioned satellite, and the orbit position data of the reference satellite; determining orbit information of the satellite to be positioned based on the space measurement and control signal and the orbit position data; calculating orbit information of other satellites to be positioned through a preset orbit positioning method and the orbit information of the positioned satellites through AI to obtain networking information of the whole satellite constellation; telemetry data sent and received through networking information among satellites are monitored in real time through AI sensing; and performing satellite measurement and control based on telemetry data. Therefore, measurement and control tasks are completed on the satellite, construction of ground measurement and control satellite stations can be reduced, manual uninterrupted measurement and control management can be reduced, economic cost can be reduced, pollution of space electromagnetic interference environment and harm to human bodies can be reduced, and intelligentization, modularization, fast response and low cost of a satellite measurement and control system can be realized.

Description

Technical Field

[0001] The present invention relates to the field of low-orbit satellite measurement and control technology, and in particular to a low-orbit satellite measurement and control method, a satellite, an electronic device and a medium. Background Art

[0002] With the development of giant low-orbit satellite constellations, the number of low-orbit satellite launches is huge, and the number of satellites in orbit is huge. The construction scale of satellite ground measurement and control systems and the investment in manpower and financial resources have also increased accordingly. In addition, the current model of relying solely on ground management personnel to carry out fault diagnosis work is restricted by the work experience and ability level of personnel, which is bound to affect the accuracy and effectiveness of anomaly detection and fault location.

[0003] With the strong support of national policies, the network communication and measurement and control communication frequency bands of low-orbit satellite constellations range from L-band to Ka-band. The construction of a large number of ground measurement and control systems and space link transmission will cause mutual interference between the ground communication systems in various frequency bands and the low-orbit satellite measurement and control systems, affecting the remote sensing monitoring and satellite motion status of the low-orbit constellation, and increasing electromagnetic pollution. When the satellite itself fails, how to intelligently and quickly identify the fault risk and restore the communication payload capacity is also a major challenge. Summary of the invention

[0005] The present invention provides a low-orbit satellite measurement and control method, a satellite, an electronic device and a medium, so as to solve the defects of the satellite ground measurement and control system in the prior art, such as the huge construction scale and investment in manpower and financial resources, the inability to quickly identify satellite faults due to electromagnetic pollution, etc., and realize the intelligence, modularization, fast response and low cost of the satellite measurement and control system.

[0006] The present invention provides a low-orbit satellite measurement and control method, comprising: Acquiring space tracking and control signals of a reference satellite and a satellite to be positioned and orbital position data of the reference satellite; Determining orbit information of the satellite to be positioned based on the space tracking and control signal and the orbit position data; The orbital information of other satellites to be located is calculated through AI using the preset orbital positioning method and the orbital information of the located satellites to obtain the networking information of the entire satellite constellation; Real-time monitoring of telemetry data sent and received between satellites in the entire satellite constellation through the networking information through AI perception; Satellite measurement and control is performed based on the telemetry data.

[0007] In a possible implementation, the method further includes: receiving a ranging signal sent by a ground measurement and control station and feeding back a response signal in response to the ranging signal; The reference distance from the reference satellite to the ground is obtained based on the time delay data of the ranging signal and the response signal and the propagation speed of the electromagnetic wave in the medium.

[0008] In a possible implementation, the method further includes: The space measurement and control signal includes ranging signal delay data, and the ranging signal delay data includes a ranging phase difference and a ranging factor; Calculating the distance between the satellite to be positioned and the reference satellite based on the ranging signal delay data and the propagation speed of the electromagnetic wave in space; The orbit information of the satellite to be positioned is determined based on the distance between the satellite to be positioned and a reference satellite and the orbit position data.

[0009] In a possible implementation, the method further includes: When the preset orbit positioning method is a dual-satellite positioning method, obtaining a first time difference and a first frequency shift difference between the satellite to be positioned sending and receiving ranging signals to and from its two adjacent positioned satellites; Obtaining a standard time difference and a standard frequency shift difference between the reference satellite sending and receiving ranging signals to and from its two adjacent satellites; When the first time difference is the same as the standard time difference and the first frequency shift difference is the same as the standard frequency shift difference, obtaining a first spherical curve based on the standard time difference and the standard frequency shift difference and obtaining a second spherical curve based on the first time difference and the first frequency shift difference; Determine the intersection of the first spherical curve and the second spherical curve as the position information of the satellite to be positioned; The orbit information of the satellite to be positioned is determined based on the position information of the satellite to be positioned and the orbit information of two adjacent positioned satellites, and the networking information of the entire satellite constellation is obtained.

[0010] In a possible implementation, the method further includes: When the preset orbit positioning method is the three-star positioning method, obtaining a second time difference and a second frequency shift difference of the satellite to be positioned sending and receiving ranging signals to and from the reference satellite; Obtaining a third spherical curve based on the second time difference and the second frequency shift difference; Determine the intersection of the first spherical curve, the second spherical curve and the third spherical curve as the position information of the satellite to be positioned; The orbital information of the satellite to be positioned is determined based on the position information of the satellite to be positioned, the orbital information of two adjacent positioned satellites, and the orbital information of the reference satellite, and the networking information of the entire satellite constellation is obtained.

[0011] In a possible implementation, the method further includes: Obtain telemetry data sent and received in real time between satellites in the entire satellite constellation through networking information; The telemetry data is converted into a telemetry data physical quantity.

[0012] In a possible implementation, the method further includes: Based on the physical quantity of the telemetry data, AI perception is used to monitor the satellite's operating status in real time.

[0013] The present invention also provides a satellite, comprising the following modules: An acquisition module, used to acquire space tracking and control signals of a reference satellite and a satellite to be positioned and orbital position data of the reference satellite; A determination module, configured to determine the orbit information of the satellite to be positioned based on the space tracking and control signal and the orbit position data; The calculation module is used to calculate the orbital information of other satellites to be located through AI using the preset orbital positioning method and the orbital information of the located satellites to obtain the networking information of the entire satellite constellation; A measurement and control module, used for real-time monitoring of telemetry data sent and received between satellites in the entire satellite constellation through the networking information through AI perception; The measurement and control module is also used to perform satellite measurement and control based on the telemetry data.

[0014] The present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, it implements any of the above-described low-orbit satellite measurement and control methods.

[0015] The present invention also provides a non-transitory computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, it implements any of the low-orbit satellite measurement and control methods described above.

[0016] The present invention also provides a computer program product, including a computer program, which, when executed by a processor, implements any of the above-mentioned low-orbit satellite measurement and control methods.

[0017] The low-orbit satellite measurement and control method, satellite, electronic device and medium provided by the present invention obtain the space measurement and control signals of the reference satellite and the satellite to be positioned and the orbital position data of the reference satellite; determine the orbital information of the satellite to be positioned based on the space measurement and control signals and the orbital position data; calculate the orbital information of other satellites to be positioned through AI through the preset orbital positioning method and the orbital information of the positioned satellite, and obtain the networking information of the entire satellite constellation; monitor the telemetry data sent and received between the satellites in the entire satellite constellation through the networking information in real time through AI perception; and perform satellite measurement and control based on the telemetry data. Compared with the huge construction scale and human and financial investment of the satellite ground measurement and control system in the prior art, and the defects such as electromagnetic pollution and inability to quickly identify satellite failures, this solution completes the measurement and control tasks on the satellite, can provide continuous management for low-orbit measurement and control, reduce the construction of ground measurement and control satellite stations, reduce the uninterrupted measurement and control management of ground manpower, reduce the investment of manpower and material resources, reduce economic costs, and at the same time reduce the pollution of the space electromagnetic interference environment and harm to the human body, so as to realize the intelligence, modularization, fast response and low cost of the satellite measurement and control system. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 It is one of the flow charts of the low-orbit satellite measurement and control method provided by the present invention.

[0020] Figure 2 This is the second flow chart of the low-orbit satellite measurement and control method provided by the present invention.

[0021] Figure 3 This is a schematic diagram of the dual-star positioning principle provided by the present invention.

[0022] Figure 4 The present invention provides a three-star positioning principle diagram.

[0023] Figure 5 It is a structural diagram of the comprehensive system of low-orbit satellite measurement and control mission planning and execution process provided by the present invention.

[0024] Figure 6 It is a schematic diagram of the internal interface of the AI ​​perception algorithm management system provided by the present invention.

[0025] Figure 7 It is a schematic diagram of the structure of the satellite provided by the present invention.

[0026] Figure 8 It is a structural schematic diagram of the electronic device provided by the present invention. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] To facilitate understanding of the embodiments of the present invention, specific embodiments will be further explained below in conjunction with the accompanying drawings. The embodiments do not constitute a limitation on the embodiments of the present invention.

[0029] Figure 1 It is one of the flow charts of the low-orbit satellite measurement and control method provided by the present invention, such as Figure 1 As shown, the method includes the following: S11, acquiring space tracking and control signals of a reference satellite and a satellite to be positioned and orbital position data of the reference satellite.

[0030] S12. Determine the orbital information of the satellite to be positioned based on the space tracking and control signal and the orbital position data.

[0031] In the embodiments of the present invention, the relevant terms are first explained: Doppler shift: When a mobile station moves in a certain direction at a constant speed, the phase and frequency will change due to the difference in propagation distance. This change is usually called Doppler shift.

[0032] Phase: Phase is the position of a wave at a particular moment in its cycle: a measure of whether it is at a peak, a trough, or some point in between. Phase describes the measure of change in a signal's waveform, usually measured in degrees (angles), also called the phase angle.

[0033] Elevation: Elevation refers to the distance from a certain point along the plumb line to the absolute base surface, which is called absolute elevation, or elevation for short.

[0034] Ephemeris: Ephemeris is a table of the precise position or trajectory of a celestial body over time in GPS measurement, which is a function of time. In specific applications, there are "broadcast ephemeris" and post-processed "precision ephemeris".

[0035] Orbital elements: Orbital elements (also called orbital elements or orbital parameters) are a set of parameters used to describe the state of a celestial body in its orbit.

[0036] Star sensor: Star sensor is an optical attitude control sensor. Star sensor is equivalent to the eyes of satellite, playing the role of navigation and satellite attitude control. By solving the quaternion output by star sensor, the position of satellite and its attitude in space can be accurately known.

[0037] In an embodiment of the present invention, the measurement and control system of the low-orbit satellite is modularized and integrated into the satellite in a chip-based manner. The first satellite launched is used as a reference satellite, and ranging and telemetry instructions are sent through the ground measurement and control system to accurately send the reference satellite to a preset orbital position.

[0038] Using the reference satellite as the measurement and control system, the on-board link measurement and control and monitoring of the second satellite launched is carried out, and the orbital information of the second satellite is determined by transmitting and receiving space measurement and control signals and orbital position.

[0039] Specifically, the space tracking and control signals of the reference satellite and the satellite to be positioned and the orbital position data of the reference satellite are obtained, and the positions and observation values ​​of adjacent satellites at any time are calculated based on the initial position and velocity vector of the reference satellite to achieve orbit measurement and orbit determination between adjacent satellites. Among them, the orbital position of the reference satellite has been determined when the reference satellite is sent, and the distance between the reference satellite and the ground is determined by the following method: The ranging signal is sent out via the uplink of the ground station and transmitted back to the ground station via the reference satellite transponder. By recording the time delay data of the ranging signal during this process and multiplying it by the propagation speed of the electromagnetic wave in the medium, we can get twice the distance from the satellite to the ground station.

[0040]

[0041] In the above formula, λ is the propagation speed of electromagnetic waves in the corresponding medium. The ranging system can only measure the phase difference x of the ranging, but cannot measure the ranging factor with an integer multiple period (that is, the value of n in the above formula). Therefore, when calculating the satellite-to-earth distance, an R0 is often preset as the initial iterative data. The value of R0 is generally close to the true value R. The maximum difference between R0 and R is determined by the ranging factor with the smallest frequency.

[0042] S13. Using a preset orbital positioning method and the orbital information of the located satellite, the orbital information of other satellites to be located is calculated through AI to obtain the networking information of the entire satellite constellation.

[0043] In the embodiment of the present invention, the preset orbital positioning methods include a dual-satellite positioning method and a triple-satellite positioning method, wherein the dual-satellite positioning method determines the specific position of the satellite by measuring the time difference and frequency shift difference between the signal transmitted by the satellite and the two adjacent satellites (the satellite refers to the satellite to be orbited, and the adjacent satellite refers to the satellite whose orbital position is determined by the reference satellite), and the triple-satellite positioning method determines the specific orbital position of the satellite by measuring the time difference between the signal transmitted by the satellite to the reference satellite and the two adjacent satellites. Thus, the orbital information of other satellites to be positioned can be calculated by the orbital information of the positioned satellite, and by analogy, the entire satellite constellation can be networked, and the networking information of the entire satellite constellation can be obtained, including the position and elevation information on the measurement and control satellite.

[0044] S14. Real-time monitoring of telemetry data sent and received between satellites in the entire satellite constellation through the networking information through AI perception.

[0045] Through the networking information of the entire satellite constellation, satellites can send and receive telemetry data to each other through AI perception. Through real-time monitoring of telemetry data, telemetry monitoring, orbit measurement, orbit determination, orbit prediction, motion trajectory tracking and maintenance, multi-satellite co-location, orbit position adjustment, end-of-life deorbit, payload management, fault diagnosis and recovery, etc. can be realized between Starlink.

[0046] S15. Perform satellite measurement and control based on the telemetry data.

[0047] In the embodiment of the present invention, for example, the telemetry data is satellite attitude and orbit measurement and control, and the measurement data is read by various star sensors, and the attitude of the satellite is determined and adjusted based on these measurement data. The star sensor is a high-precision space attitude measurement device that uses stars as a reference system and the starry sky as a working object. By detecting stars at different positions on the celestial sphere and performing calculations, the satellite is provided with an accurate spatial orientation and reference. The onboard computer determines the attitude of the satellite through the observation values ​​of the star sensor and its own orbital position. If there is an abnormality, it can be adjusted in time to complete the satellite attitude and orbit monitoring in the constellation.

[0048] The low-orbit satellite measurement and control method provided by the present invention obtains the space measurement and control signals of the reference satellite and the satellite to be positioned and the orbital position data of the reference satellite; determines the orbital information of the satellite to be positioned based on the space measurement and control signals and the orbital position data; calculates the orbital information of other satellites to be positioned through AI through the preset orbital positioning method and the orbital information of the positioned satellite, and obtains the networking information of the entire satellite constellation; monitors the telemetry data sent and received between the satellites in the entire satellite constellation through the networking information in real time through AI perception; and performs satellite measurement and control based on the telemetry data. Compared with the construction scale and human and financial investment of the satellite ground measurement and control system in the prior art, and the defects such as electromagnetic pollution and inability to quickly identify satellite failures, this method completes the measurement and control tasks on the satellite, can provide continuous management for low-orbit measurement and control, reduce the construction of ground measurement and control satellite stations, reduce the uninterrupted measurement and control management of ground manpower, reduce the investment of manpower and material resources, reduce economic costs, and at the same time reduce the pollution of the space electromagnetic interference environment and harm to the human body, so as to realize the intelligence, modularization, fast response and low cost of the satellite measurement and control system.

[0049] Figure 2 FIG. 2 is a flow chart of the low-orbit satellite measurement and control method provided by the present invention. Figure 2 As shown, the method includes the following: S21, receiving a ranging signal sent by a ground measurement and control station and feeding back a response signal in response to the ranging signal.

[0050] In an embodiment of the present invention, the measurement and control system of the low-orbit satellite is modularized and integrated into the satellite mother body in a chip-based manner. The first satellite launched is used as a reference satellite, and ranging and telemetry instructions are sent through the ground measurement and control system to accurately send the reference satellite to a preset orbital position.

[0051] Furthermore, a ranging signal is sent to the reference satellite via an uplink of the ground station, and a response signal fed back by the reference satellite in response to the ranging signal is received.

[0052] S22. Obtain a reference distance from the reference satellite to the ground based on the time delay data of the ranging signal and the response signal and the propagation speed of the electromagnetic wave in the medium.

[0053] By recording the time delay data of the ranging signal during this process and then multiplying it by the propagation speed of the electromagnetic wave in the medium, we can get twice the distance from the satellite to the ground station.

[0054]

[0055] In the above formula, is the reference distance from the satellite to the ground station, λ is the propagation speed of electromagnetic waves in the corresponding medium, and the ranging system can only measure the phase difference x of the ranging, and n is the ranging factor.

[0056] S23, acquiring space tracking and control signals of a reference satellite and a satellite to be positioned and orbital position data of the reference satellite.

[0057] Obtain the space tracking and control signals of the reference satellite and the satellite to be positioned and the orbital position data of the reference satellite, calculate the position and observation value of the adjacent satellite at any time according to the initial position and velocity vector of the reference satellite, and realize the orbit measurement and orbit determination between adjacent satellites. Among them, the orbital position of the reference satellite has been determined when the reference satellite is sent, and the space tracking and control signals include the ranging signal delay data, and the ranging signal delay data includes the ranging phase difference and ranging factor.

[0058] S24. Calculate the distance between the satellite to be positioned and the reference satellite using a first formula based on the ranging signal delay data and the propagation speed of electromagnetic waves in space.

[0059] Using the reference satellite as an emulation of the ground measurement and control system, the on-board link measurement, control and monitoring of the second satellite launched is carried out. By transmitting and receiving ranging signals and based on the orbital position, the orbital information of the second satellite is determined.

[0060] Specifically, the distance between the satellite to be positioned and the reference satellite is calculated by a first formula based on the ranging signal delay data and the propagation speed of electromagnetic waves in space. The first formula is: ; in, is the distance between the satellite to be positioned and the reference satellite, λ is the propagation speed of electromagnetic waves in space, x is the phase difference of ranging, and n is the ranging factor.

[0061] S25. Determine the orbital information of the satellite to be positioned based on the distance between the satellite to be positioned and a reference satellite and the orbital position data.

[0062] Since the relative distance between the satellite to be positioned and the reference satellite remains unchanged, once the orbital position data of the reference satellite is known, the orbital information of the satellite to be positioned can be calculated based on the orbital position data of the reference satellite and the distance between the satellite to be positioned and the reference satellite.

[0063] S26. Calculate the orbit information of other satellites to be positioned by using a preset orbit positioning method and the orbit information of the positioned satellites to obtain the networking information of the entire satellite constellation.

[0064] In the embodiment of the present invention, the preset orbital positioning methods include a dual-satellite positioning method and a triple-satellite positioning method, wherein the dual-satellite positioning method determines the specific position of the satellite by measuring the time difference and frequency shift difference between the signal transmitted by the satellite and the two adjacent satellites (the satellite refers to the satellite to be orbited, and the adjacent satellite refers to the satellite whose orbital position is determined by the reference satellite), and the triple-satellite positioning method determines the specific orbital position of the satellite by measuring the time difference between the signal transmitted by the satellite to the reference satellite and the two adjacent satellites. Thus, the orbital information of other satellites to be positioned can be calculated by the orbital information of the positioned satellite, and by analogy, the entire satellite constellation can be networked, and the networking information of the entire satellite constellation can be obtained, including the position and elevation information on the measurement and control satellite.

[0065] Specifically, the principle of the dual-satellite positioning method is as follows: Figure 3 As shown in the figure, as long as the time difference and frequency shift of the signal transmitted and received by the local satellite to the two adjacent satellites are measured to be the same as the time and frequency shift of the signal transmitted and received by the reference satellite and its neighboring satellite, a curve can be drawn above the earth. The time difference of the signals of all low-orbit satellites on this curve reaching the neighboring satellite is the same and equal to the measured value of the reference satellite and the neighboring satellite; the Doppler frequency shift difference of the signal transmitted by the local satellite to the neighboring satellite is measured, and a curve can also be drawn above the earth. The Doppler frequency shift difference of the signal transmitted by the local satellite to the neighboring satellite is the same and equal to the measured value of the reference satellite and the neighboring satellite. The intersection of the above two curves is the location of the local satellite. The principle of the three-star positioning method is as follows: Figure 4 As shown in the figure, in the dual-star positioning, the time difference and frequency shift of the signals transmitted and received by the local star to the reference star are measured to produce another curve. The intersection of the above three curves is the location of the local star.

[0066] It should be noted that the conditions required for the dual-star positioning method are as follows: Satellite conditions: There should be at least one neighboring satellite near the main satellite, with the same frequency band and polarization mode as the main satellite.

[0067] Reference satellite conditions: In order to correct the influence of various error factors on positioning, such as the unknown characteristics of the on-board forwarding equipment and the satellite ephemeris error, the positioning system requires more than two reference satellites, which are distributed in the vicinity of the target satellite.

[0068] Satellite reception conditions: Use a parabolic antenna and have the ability to receive signals from two satellites at the same time.

[0069] The conditions required for the Samsung positioning method are as follows: Satellite conditions: There should be two neighboring satellites near this satellite, which can establish a measurement and control link with the reference satellite and have the same frequency band and polarization mode.

[0070] Reference satellite conditions: In order to correct the influence of various error factors on positioning, such as the unknown characteristics of the on-board forwarding equipment and the satellite ephemeris error, the positioning system requires more than two reference satellites. At the same time, reference satellites are required for reference and they are distributed in the vicinity of the target satellite.

[0071] Ground receiving station conditions: Use a parabolic antenna and have the ability to receive downlink signals from three satellites at the same time.

[0072] S27. Acquire telemetry data sent and received in real time between satellites in the entire satellite constellation through networking information.

[0073] S28, converting the telemetry data into a physical quantity of telemetry data.

[0074] S29. Perform AI perception and real-time monitoring of the satellite's operating status based on the physical quantity of the telemetry data.

[0075] The following is a unified description of S27-S29: Satellites are in a high vacuum, strong radiation, and weightless space environment for a long time. When satellite signals are transmitted, electromagnetic radiation will interact with the electrons, ions, atoms, and neutrons that make up the Earth's plasma environment and atmosphere to varying degrees. As a result, the signal will change direction, refract and bend, and the propagation speed will also change. In addition, the atmosphere also affects the signal polarization and magnetic field strength.

[0076] According to the embodiments of the present invention, the measurement data can be read according to the various sensors of the satellite attitude and orbit measurement and control system, and the AI ​​computing power module can then determine and adjust the attitude of the satellite according to these measurement data. The star sensor is a high-precision space attitude measurement device that uses stars as a reference system and the starry sky as a working object. By detecting stars at different positions on the celestial sphere and performing calculations, accurate spatial orientation and reference are provided for the satellite. The onboard computer determines the attitude of the satellite through the observation values ​​of the star sensor and its own orbital position. The ground station injects the orbital data of the reference satellite onto the satellite, and completes the orbit determination and operation monitoring of the satellite in the constellation through the inter-satellite measurement and control link and orbit determination technology.

[0077] The amplitude of the satellite's north-south motion depends only on the orbital inclination, while the east-west motion depends on the drift rate, longitude and eccentricity. The task of the satellite's motion trajectory is to control these four orbital elements in a timely manner. The first-order approximation of the motion of a satellite in this orbit relative to the earth in the east-west (longitude) and north-south (latitude) directions is:

[0078] Obviously, usually when the longitude and latitude of the satellite reach the allowed boundaries, appropriate control is applied to the satellite. Different maintenance accuracy requirements have correspondingly different control cycles, and the control strategies may also be different.

[0079] Through the AI ​​perception calculation of the embodiment of the present invention, the real-time processing and forwarding of satellite telemetry information is controlled, and the telemetry data between satellites is received and processed in real time through the measurement and control equipment of the local satellite and the neighboring satellites, and the original data is encoded and converted into the physical quantity of telemetry data. According to actual needs, the data content is packaged again according to the internal protocol format and forwarded to other business software for use. Through the AI ​​perception algorithm, the satellite operation status is monitored in real time, the changes in telemetry parameters are detected, and the parameter anomalies are accurately located, the satellite on-orbit faults are discovered in time and alarms are issued. In the event of a serious fault, the original emergency plan will be activated to perform self-inspection and maintenance of the entire satellite.

[0080] Through the AI ​​perception calculation of the embodiment of the present invention, orbital parameters are used to calculate orbital control timing and control quantity, calculate tracking forecasts for measurement and control equipment, calculate satellite payload coverage areas, and adjust the on-orbit working status of on-board components. Figure 5 As shown. The AI ​​perception measurement and control information exchange of low-orbit satellites sends spacecraft measurement data to adjacent satellites, including sending various measurement data (including telemetry data and external measurement data), sending command loop comparison information, sending equipment working status, and sending link monitoring information; it receives spacecraft remote control information sent by adjacent satellites in real time, including the remote control information of the receiving center, the measurement and control equipment usage requirements of the receiving center, the link monitoring information of the receiving center, and the orbital roots of the receiving center.

[0081] Figure 6 This is a schematic diagram of the internal interface of the AI ​​perception algorithm management system provided by the present invention. The interface is described below: (1) The original telemetry information is transmitted to the telemetry parameter detection and control computer through the AI ​​data processing and distribution interface. The telemetry information initiated by the AI ​​telemetry command is used for AI fault diagnosis, and AI measurement and control monitoring and remote control information command sending, data storage and correlation analysis are performed at the same time. (2) The external original information is used for orbit calculation and prediction through the AI ​​data processing and distribution interface, and the orbit data is transmitted to the control computer.

[0082] It should be noted that the transmitting and receiving parabolic antenna in the onboard measurement and control system of the embodiment of the present invention is replaced with a hybrid phased array antenna or an electronically scanned phased array antenna, which improves the stability of the measurement and control system and avoids interference from neighboring satellites caused by sidelobe transmission and reception.

[0083] The reference star in the embodiment of the present invention can use a satellite with known ephemeris in synchronous earth orbit as a reference, and use the original measurement and control system to send instructions to the low-orbit constellation satellite. After the first satellite is determined, through dual-star or triple-star positioning technology and with the help of AI computing power monitoring, remote measurement and control of the satellites in the low-orbit constellation network can be achieved.

[0084] The overall alternative scheme of the embodiment of the present invention is to establish a corresponding ground measurement and control station system based on point-to-point measurement and control, which is convenient for manual query and monitoring.

[0085] The embodiments of the present invention take advantage of the measurement and control communication link control, and can be combined with Beidou networking technology to introduce multiple reference stars, reduce clock signal errors, and use the spherical distance formula to perform precise orbit determination and positioning, and implement monitoring of the motion trajectory of constellation satellites.

[0086] The embodiment of the present invention uses AI perception technology to realize telemetry monitoring, orbit measurement, orbit determination, orbit prediction, satellite motion tracking, multi-satellite co-location, orbit position adjustment, end-of-life deorbit, payload management, fault diagnosis and recovery and other functions on low-orbit satellite constellations. It relies on AI perception management to carry out fault diagnosis work, and uses computer systems to intelligently, efficiently, safely and reliably perform satellite on-orbit measurement and control work. By monitoring and diagnosing the status of satellites, the accuracy of fault judgment and the timeliness of abnormal handling are improved, thereby ensuring the safety of satellite operation and the normal development of application services. It can save a lot of ground measurement and control satellite station construction and greatly reduce economic costs. Reduce the mutual interference between the ground frequency band communication systems and the low-orbit satellite measurement and control systems caused by space link transmission, and avoid more geomagnetic environment pollution. The present invention has high requirements for satellite payload technology. In addition to meeting the original transponder business, it also needs to have the on-board integration capability of the measurement and control system, advanced AI computing power, and high intelligent capabilities.

[0087] The satellite provided by the present invention is described below. The satellite described below and the low-orbit satellite measurement and control method described above can be referenced to each other.

[0088] Figure 7 It is a schematic diagram of the structure of the satellite provided by the present invention, which specifically includes: The acquisition module 701 is used to acquire the space tracking and control signals of the reference satellite and the satellite to be positioned and the orbital position data of the reference satellite; A determination module 702 is used to determine the orbit information of the satellite to be positioned based on the space tracking and control signal and the orbit position data; The calculation module 703 is used to calculate the orbit information of other satellites to be located through AI using a preset orbit positioning method and the orbit information of the located satellite to obtain the networking information of the entire satellite constellation; The measurement and control module 704 is used to monitor in real time through AI perception the telemetry data sent and received between the satellites in the entire satellite constellation through the networking information; The measurement and control module 704 is further used to perform satellite measurement and control based on the telemetry data. For detailed description, please refer to the relevant description corresponding to the above method embodiment, which will not be repeated here.

[0089] Figure 8An example of a physical structure diagram of an electronic device is shown in FIG. Figure 8 As shown, the electronic device may include: a processor 810, a communication interface 820, a memory 830 and a communication bus 840, wherein the processor 810, the communication interface 820 and the memory 830 communicate with each other through the communication bus 840. The processor 810 may call the logic instructions in the memory 830 to execute the low-orbit satellite measurement and control method, which includes: obtaining the space measurement and control signals of the reference satellite and the satellite to be positioned and the orbital position data of the reference satellite; determining the orbital information of the satellite to be positioned based on the space measurement and control signals and the orbital position data; calculating the orbital information of other satellites to be positioned through AI through the preset orbital positioning method and the orbital information of the positioned satellite, and obtaining the networking information of the entire satellite constellation; real-time monitoring of the telemetry data sent and received between the satellites in the entire satellite constellation through the networking information through AI perception; and performing satellite measurement and control based on the telemetry data.

[0090] In addition, the logic instructions in the above-mentioned memory 830 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on this understanding, the technical solution of the present invention is essentially or the part that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions to enable a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program codes.

[0091] On the other hand, the present invention also provides a computer program product, which includes a computer program. The computer program can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the low-orbit satellite measurement and control method provided by the above methods, which includes: obtaining space measurement and control signals of a reference satellite and a satellite to be positioned and orbital position data of the reference satellite; determining the orbital information of the satellite to be positioned based on the space measurement and control signals and the orbital position data; calculating the orbital information of other satellites to be positioned through AI using a preset orbital positioning method and the orbital information of the positioned satellite to obtain the networking information of the entire satellite constellation; real-time monitoring of the telemetry data sent and received between the satellites in the entire satellite constellation through the networking information through AI perception; and performing satellite measurement and control based on the telemetry data.

[0092] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to execute the low-orbit satellite measurement and control method provided by the above-mentioned methods, the method comprising: obtaining space measurement and control signals of a reference satellite and a satellite to be positioned and orbital position data of the reference satellite; determining the orbital information of the satellite to be positioned based on the space measurement and control signals and the orbital position data; calculating the orbital information of other satellites to be positioned through AI using a preset orbital positioning method and the orbital information of the positioned satellite to obtain the networking information of the entire satellite constellation; monitoring the telemetry data sent and received between the satellites in the entire satellite constellation through the networking information in real time through AI perception; and performing satellite measurement and control based on the telemetry data.

[0093] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0094] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0095] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A low-orbit satellite measurement and control method, characterized in that: include: Acquiring space tracking and control signals of a reference satellite and a satellite to be positioned and orbital position data of the reference satellite; Determining orbit information of the satellite to be positioned based on the space tracking and control signal and the orbit position data; The orbital information of other satellites to be located is calculated through AI using the preset orbital positioning method and the orbital information of the located satellites to obtain the networking information of the entire satellite constellation; Real-time monitoring of telemetry data sent and received between satellites in the entire satellite constellation through the networking information through AI perception; Satellite measurement and control is performed based on the telemetry data.

2. The method according to claim 1, characterized in that Before acquiring the space tracking and control signals of the reference satellite and the satellite to be positioned and the orbital position data of the reference satellite, the method includes: receiving a ranging signal sent by a ground measurement and control station and feeding back a response signal in response to the ranging signal; The reference distance from the reference satellite to the ground is obtained based on the time delay data of the ranging signal and the response signal and the propagation speed of the electromagnetic wave in the medium.

3. The method according to claim 2, characterized in that The space measurement and control signal includes ranging signal delay data, and the ranging signal delay data includes a ranging phase difference and a ranging factor; The determining the orbital information of the satellite to be positioned based on the space tracking and control signal and the orbital position data comprises: Calculating the distance between the satellite to be positioned and the reference satellite based on the ranging signal delay data and the propagation speed of the electromagnetic wave in space; The orbit information of the satellite to be positioned is determined based on the distance between the satellite to be positioned and a reference satellite and the orbit position data.

4. The method according to claim 3, characterized in that The orbital information of other satellites to be positioned is calculated by AI using the preset orbital positioning method and the orbital information of the positioned satellite to obtain the networking information of the entire satellite constellation, including: When the preset orbit positioning method is a dual-satellite positioning method, obtaining a first time difference and a first frequency shift difference between the satellite to be positioned sending and receiving ranging signals to and from its two adjacent positioned satellites; Obtaining a standard time difference and a standard frequency shift difference between the reference satellite sending and receiving ranging signals to and from its two adjacent satellites; When the first time difference is the same as the standard time difference and the first frequency shift difference is the same as the standard frequency shift difference, obtaining a first spherical curve based on the standard time difference and the standard frequency shift difference and obtaining a second spherical curve based on the first time difference and the first frequency shift difference; Determine the intersection of the first spherical curve and the second spherical curve as the position information of the satellite to be positioned; The orbit information of the satellite to be positioned is determined based on the position information of the satellite to be positioned and the orbit information of two adjacent positioned satellites, and the networking information of the entire satellite constellation is obtained.

5. The method according to claim 4, characterized in that The orbital information of other satellites to be positioned is calculated by AI using the preset orbital positioning method and the orbital information of the positioned satellite to obtain the networking information of the entire satellite constellation, including: When the preset orbit positioning method is the three-star positioning method, obtaining a second time difference and a second frequency shift difference of the satellite to be positioned sending and receiving ranging signals to and from the reference satellite; Obtaining a third spherical curve based on the second time difference and the second frequency shift difference; Determine the intersection of the first spherical curve, the second spherical curve and the third spherical curve as the position information of the satellite to be positioned; The orbital information of the satellite to be positioned is determined based on the position information of the satellite to be positioned, the orbital information of two adjacent positioned satellites, and the orbital information of the reference satellite, and the networking information of the entire satellite constellation is obtained.

6. The method according to claim 5, characterized in that The real-time monitoring of telemetry data sent and received by satellites in the entire satellite constellation through the networking information by AI perception includes: Obtain telemetry data sent and received in real time between satellites in the entire satellite constellation through networking information; The telemetry data is converted into a telemetry data physical quantity.

7. The method according to claim 6, characterized in that The performing satellite measurement and control based on the telemetry data comprises: Based on the physical quantity of the telemetry data, AI perception is used to monitor the satellite's operating status in real time.

8. A satellite, characterized in that: include: An acquisition module, used to acquire space tracking and control signals of a reference satellite and a satellite to be positioned and orbital position data of the reference satellite; A determination module, configured to determine the orbit information of the satellite to be positioned based on the space tracking and control signal and the orbit position data; The calculation module is used to calculate the orbital information of other satellites to be located through AI using the preset orbital positioning method and the orbital information of the located satellites to obtain the networking information of the entire satellite constellation; A measurement and control module, used for real-time monitoring of telemetry data sent and received between satellites in the entire satellite constellation through the networking information through AI perception; The measurement and control module is also used to perform satellite measurement and control based on the telemetry data.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the low-orbit satellite measurement and control method as described in any one of claims 1 to 7 is implemented.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the low-orbit satellite measurement and control method as described in any one of claims 1 to 7 is implemented.

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