Method and system for ensuring inter-satellite link continuity under application background of electric push orbital transfer

Abstract

The invention provides a method for ensuring inter-satellite link continuity under an electric push orbital transfer background, and belongs to the technical field of satellite-borne electronic equipment. S1, adjusting an initial track; s2, constellation configuration deployment; s3, starting an autonomous control mode; s4, updating track information in real time; s5, calculating orbit maintenance parameters; s6, judging whether a control threshold value is reached or not; s7, if the threshold value is reached, calculating an orbit control strategy and generating a data block and telemetry data, otherwise, continuing to calculate a maintenance parameter; s8, judging whether the orbit control conflicts with the link establishment task or not; s9, if yes, correcting a link pointing angle; if no conflict exists, the software autonomously controls orbit control; s10, judging whether an orbit control moment is reached or not, if so, performing orbit maneuver and forming an inter-satellite link, otherwise, continuing judgment; s11, after orbit control is finished, evaluating precision according to orbit determination data and errors; and S12, updating the orbit information in real time through an on-satellite GNSS or a ground injection orbit. Errors caused by electric push orbital transfer are counteracted in the pointing calculation process, and the continuity of inter-satellite links is guaranteed.

Description

Technical Field

[0001] The present invention belongs to the technical field of satellite-borne electronic equipment, and relates to a method and system for ensuring the continuity of an inter-satellite link in the context of electric propulsion orbit change application, and specifically, to a satellite autonomous orbit change method. Background Art

[0002] Microsatellites generally operate in low-Earth orbit or ultra-low orbit. Since this orbital plane can greatly improve the practical performance of satellite payloads, most of the current mainstream microsatellite constellations use this orbit. However, compared with higher orbits, this orbit has greater air resistance caused by the thinner atmosphere, so more frequent orbit changes are required to maintain the orbit.

[0003] As the actuator of satellite orbit change, the propulsion system is mainly divided into two systems: chemical propulsion and electric propulsion. Traditional satellite orbit change operations are generally operated by the ground and use chemical propulsion systems. However, since microsatellites have strict constraints on the weight of the entire satellite, microsatellites generally use electric propulsion technology with a lighter overall weight. In addition, since the number of microsatellite constellations is currently large, it is impossible to rely entirely on ground control stations to maintain the orbits of all satellites. Therefore, the autonomous orbit maintenance function on the satellite is a necessary condition for the normal operation of large-scale constellations.

[0004] The Chinese patent with publication number CN113998150A discloses a fully electric propulsion orbit maintenance system for ultra-low-orbit satellites, including an electric propulsion system that completes the distribution of thrust parameters and the generation of thrust according to the orbit maintenance control law transmitted by the satellite management unit. The satellite management unit comprehensively determines the orbit information of the ultra-low-orbit satellite, generates the satellite space trajectory error after processing, and then determines the orbit maintenance control law through the orbit maintenance algorithm based on the satellite space trajectory error, and sends the orbit maintenance control law to the electric propulsion system to complete the orbit maintenance control.

[0005] However, if the orbit change task is triggered autonomously on the satellite, there may be a conflict with the inter-satellite link establishment on the satellite. If the two are executed at the same time, the orbit change operation will have the greatest impact on the link pointing accuracy in the inter-satellite link. Therefore, it is necessary to properly resolve the impact of the orbit change on the link pointing accuracy in the inter-satellite link establishment. Summary of the invention

[0006] In view of the defects in the prior art, the object of the present invention is to provide a method and system for ensuring the continuity of inter-satellite links in the context of electric propulsion orbit change applications.

[0007] A method for ensuring intersatellite link continuity in the context of electric propulsion orbit change provided by the present invention includes: Early orbit insertion steps and on-orbit operation steps; Early orbital steps include: S1: Initial orbit adjustment after the satellite enters orbit and undergoes intersatellite separation in the active phase; S2: Each satellite determines its own orbital position according to the arrangement in the constellation configuration, and completes the constellation configuration deployment; The on-orbit operation steps include: S3: In the normal orbital operation state, the ground determines the satellite attitude and orbit control state through telemetry, and the satellite autonomous control parameters are added, and the satellite starts the autonomous control mode; S4: The satellite updates the satellite orbit information in real time through the onboard GNSS positioning broadcast or the orbit parameters recorded on the ground; S5: Satellite attitude and orbit control application software calculates orbit maintenance parameters; S6: The satellite attitude and orbit control application software determines whether the control threshold is reached; S7: If the satellite attitude and orbit control application software determines that the control threshold has been reached, the attitude and orbit control application software autonomously calculates the orbit control strategy and generates orbit control data blocks and telemetry data in a specified format; otherwise, the attitude and orbit control application software continues to calculate orbit maintenance parameters; S8: The satellite service software receives the orbit control data and telemetry data sent by the attitude and orbit control application software, and determines whether the orbit control conflicts with the inter-satellite link establishment task; S9: If the satellite service software determines that the orbit control and inter-satellite link establishment tasks conflict, the satellite attitude and orbit control application software outputs the satellite orbit prediction data and attitude data in the orbit change state to the satellite service software. After receiving the satellite orbit prediction data and attitude data output by the attitude and orbit control application software, the satellite service software forwards them to the link pointing angle calculation module to correct the link pointing angle; if there is no conflict, the satellite service software starts to autonomously control the orbit control; S10: The satellite service software determines whether the current time has reached the control time. If it has reached the orbit control time, the satellite orbit maneuver and intersatellite link establishment are realized under the coordinated control of the satellite service subsystem and the control subsystem to form an intersatellite link. If it has not reached the time, it returns to query whether the current time meets the condition of reaching the control time. S11: After the orbit control is completed, the autonomous orbit control and ground accuracy are evaluated based on the orbit determination data, intersatellite link pointing angle error, and transmit and receive phase angle error; S12: Update orbit information in real time through onboard GNSS or ground-based orbit parameters.

[0008] Preferably, in step S3, each satellite performs autonomous orbit control after completing configuration phase deployment. In the early stage after launch, the orbital elements of the satellite are noted by the ground, and the satellite calculates the control amount and implements control accordingly. After success, the satellite autonomously measures and determines the orbit based on GNSS data, calculates the control amount and implements control, so as to achieve long-term autonomous orbit maintenance without the support of ground measurement and control system.

[0009] Preferably, in step S3, the satellite autonomous control parameters are added on the ground, and the onboard autonomous orbit maintenance function can be enabled / disabled under the intervention of the ground system.

[0010] Preferably, in step S3, the autonomous control mode in which the satellite is turned on is one of the mission modes of the satellite service software, and the other two modes are the emergency orbit control mission mode and the conventional mission mode; the condition for turning on the autonomous orbit control mission mode is that the satellite service and attitude and orbit control related telemetry are normal after the satellite enters orbit, and the priority order of the three tasks is: emergency orbit control>conventional mission>autonomous orbit control.

[0011] Preferably, the control threshold in step S6 is a closed-loop control process of the attitude and orbit control application software. When the positioning and orbit determination is valid, the attitude and orbit control application software automatically compares the deviation between the orbit determination data and the nominal orbit. If the threshold is exceeded, the attitude and orbit control automatically executes the autonomous orbit control task if the autonomous orbit control allows. The threshold parameters can be modified by the ground injection parameters.

[0012] Preferably, the autonomous orbit maintenance strategy in step S7 is that the satellite attitude and orbit control application software calculates the orbit using absolute position maintenance, and the attitude and orbit control application software has the ability to calculate and generate the autonomous orbit control strategy according to the orbit maintenance position constraint and the autonomous orbit prediction information, and outputs the control data to the satellite service software in a specified format; The specified format orbit control data block output under autonomous orbit control is mainly the parameter data for configuring the Hall electric thrusters, including the start time, end time, Hall electric thruster preheating time, and thruster vector setting parameters.

[0013] Preferably, in step S7, the satellite generates telemetry data in a specified format, and the telemetry data can transmit the orbit control process information in real time / delayed manner through ground continuous measurement and control / relay continuous measurement and control / short message measurement and control channels.

[0014] Preferably, in step S8, the satellite service software determines whether the orbit control task conflicts with the inter-satellite link establishment task. This process is that the satellite service software makes a comprehensive judgment based on the orbit control data packet, thruster working status, task queue status, energy security and other planning requirements to determine whether to allow / prohibit orbit control, and sends the status to the attitude and orbit control application software.

[0015] Preferably, in step S10, the intersatellite link includes a laser link and a microwave link, and the two different physical links are both guided by the link pointing calculation module to guide the rotation drive mechanism to drive the laser head or antenna to perform link establishment and maintenance operations.

[0016] A system for ensuring intersatellite link continuity in the context of electric propulsion orbit change application, comprising: Early Orbital Insertion Module and On-Orbit Operation Module; The early orbital modules include: Module M1: Initial orbit adjustment after the satellite enters orbit and performs intersatellite separation in the active phase; Module M2: Each satellite determines its own orbital position according to the arrangement in the constellation configuration, and completes the constellation configuration deployment; The modules in orbit include: Module M3: When the satellite is in normal operation on orbit, the ground determines the satellite attitude and orbit control status through telemetry, and the satellite autonomous control parameters are added, and the satellite starts the autonomous control mode; Module M4: The satellite updates the satellite orbit information in real time through the onboard GNSS positioning broadcast or the orbit parameters recorded on the ground; Module M5: Satellite attitude and orbit control application software calculates orbit maintenance parameters; Module M6: Satellite attitude and orbit control application software determines whether the control threshold is reached; Module M7: If the satellite attitude and orbit control application software determines that the control threshold has been reached, the attitude and orbit control application software will autonomously calculate the orbit control strategy and generate orbit control data blocks and telemetry data in a specified format; otherwise, the attitude and orbit control application software will continue to calculate orbit maintenance parameters; Module M8: The satellite service software receives the orbit control data and telemetry data sent by the attitude and orbit control application software, and determines whether the orbit control conflicts with the intersatellite link establishment task; Module M9: If the satellite service software determines that the orbit control and inter-satellite link establishment tasks conflict, the satellite attitude and orbit control application software outputs the satellite orbit prediction data and attitude data in the orbit change state to the satellite service software. After receiving the satellite orbit prediction data and attitude data output by the attitude and orbit control application software, the satellite service software forwards them to the link pointing angle calculation module to correct the link pointing angle; if there is no conflict, the satellite service software starts to autonomously control the orbit control; Module M10: The satellite service software determines whether the current time has reached the control time. If it has reached the orbit control time, the satellite orbit maneuver and intersatellite link establishment are realized under the coordinated control of the satellite service subsystem and the control subsystem to form an intersatellite link; if it has not reached the time, it returns to query whether the current time meets the condition of reaching the control time; Module M11: After the orbit control is completed, the autonomous orbit control and ground accuracy are evaluated based on the orbit determination data, intersatellite link pointing angle error, and transmit and receive phase angle error; Module M12: Update orbit information in real time through onboard GNSS or ground-based orbit parameters.

[0017] Compared with the prior art, the present invention has the following beneficial effects: 1. By solving the impact of electric propulsion orbit change on the link pointing in intersatellite link establishment, a method for ensuring the continuity of intersatellite links in the context of electric propulsion orbit change is provided, with electric propulsion as an important condition for orbit change operation; 2. By adding the variable factor of continuous orbit change in the orbit change state in the digital transmission link pointing calculation, the influence of the orbit change operation on the link pointing accuracy is corrected; 3. The satellite orbit prediction data and attitude data received are sent to the intersatellite link pointing calculation module through the satellite service software, which offsets the pointing error caused by the electric propulsion orbit change during the calculation of the intersatellite link pointing, and effectively ensures the continuity of the intersatellite link. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings: Figure 1 The figure is a flow chart of the method for ensuring the continuity of intersatellite links in the context of electric propulsion orbit change applications. DETAILED DESCRIPTION

[0019] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0020] A method for ensuring the continuity of intersatellite links in the context of electric propulsion orbit change applications. Satellite attitude and orbit control application software calculates the effective time and power of an electric propulsion controller to execute propulsion by comparing real-time orbit data with predetermined orbit data, generates a corresponding command parameter package to send to the satellite service software, and specifies the sending time and sending interval. At the same time, the attitude and orbit control application software generates satellite orbit prediction data and attitude data in the orbit change state at a time interval of 0.2s; the satellite service software packages the command parameter package into an on-board command format according to the command sending requirements, and sends the command to the electric propulsion controller to execute the command.

[0021] like Figure 1 As shown, a method for ensuring intersatellite link continuity in the context of electric propulsion orbit change application includes: Early orbit insertion steps and on-orbit operation steps; Early orbital steps include: S1: Initial orbit adjustment after the satellite enters orbit and undergoes intersatellite separation in the active phase; S2: Each satellite determines its own orbital position according to the arrangement in the constellation configuration, and completes the constellation configuration deployment; The on-orbit operation steps include: S3: In the normal orbital operation state, the ground determines the satellite attitude and orbit control state through telemetry, and the satellite autonomous control parameters are added, and the satellite starts the autonomous control mode; After each satellite has completed the configuration phase deployment, autonomous orbit control is carried out. In the early stage after launch, the orbital elements of the satellite are noted by the ground, and the satellite calculates the control amount and implements the control accordingly. After success, the satellite will autonomously measure and determine the orbit based on GNSS data, calculate the control amount and implement the control, so as to achieve long-term autonomous orbit maintenance without the support of the ground measurement and control system. Satellite autonomous control parameters are added on the ground. Under the intervention of the ground system, the onboard autonomous orbit maintenance function can be enabled / disabled; The autonomous control mode of the satellite is one of the mission modes of the satellite service software. The other two modes are the emergency orbit control mission mode and the conventional mission mode. The autonomous orbit control mission mode is enabled when the satellite service and attitude and orbit control related telemetry are normal after entering orbit. The priority order of the three tasks is: emergency orbit control > conventional mission > autonomous orbit control. S4: The satellite updates the satellite orbit information in real time through the onboard GNSS positioning broadcast or the orbit parameters recorded on the ground; S5: Satellite attitude and orbit control application software calculates orbit maintenance parameters; S6: The satellite attitude and orbit control application software determines whether the control threshold is reached; The control threshold is a closed-loop control process of the attitude and orbit control application software. When the positioning and orbit determination are valid, the attitude and orbit control application software automatically compares the deviation between the orbit determination data and the nominal orbit. If the deviation exceeds the threshold, the attitude and orbit control automatically executes the autonomous orbit control task if the autonomous orbit control allows. The threshold parameters can be modified by the ground injection parameters. S7: If the satellite attitude and orbit control application software determines that the control threshold has been reached, the attitude and orbit control application software autonomously calculates the orbit control strategy and generates orbit control data blocks and telemetry data in a specified format; otherwise, the attitude and orbit control application software continues to calculate orbit maintenance parameters; The autonomous orbit maintenance strategy is that the satellite attitude and orbit control application software calculates the orbit using absolute position maintenance, and the attitude and orbit control application software has the ability to calculate and generate the autonomous orbit control strategy based on the orbit maintenance position constraints and autonomous orbit prediction information, and output the control data to the satellite service software in the specified format; The specified format orbit control data block output under autonomous orbit control is mainly the parameter data for configuring the Hall electric thruster, including the start time, end time, Hall electric thruster preheating time, and thruster vector setting parameters; The satellite generates telemetry data in a specified format, which can transmit orbit control process information in real time or with delay through ground continuous measurement and control / relay continuous measurement and control / short message measurement and control channels; S8: The satellite service software receives the orbit control data and telemetry data sent by the attitude and orbit control application software, and determines whether the orbit control conflicts with the inter-satellite link establishment task; The satellite service software determines whether the orbit control task conflicts with the intersatellite link establishment task. This process is that the satellite service software makes a comprehensive judgment based on the orbit control data packet, thruster working status, task queue status, energy security and other planning requirements to determine whether to allow / prohibit orbit control, and sends the status to the attitude and orbit control application software; S9: If the satellite service software determines that the orbit control and inter-satellite link establishment tasks conflict, the satellite attitude and orbit control application software outputs the satellite orbit prediction data and attitude data in the orbit change state to the satellite service software. After receiving the satellite orbit prediction data and attitude data output by the attitude and orbit control application software, the satellite service software forwards them to the link pointing angle calculation module to correct the link pointing angle; if there is no conflict, the satellite service software starts to autonomously control the orbit control; S10: The satellite service software determines whether the current time has reached the control time. If it has reached the orbit control time, the satellite orbit maneuver and intersatellite link establishment are realized under the coordinated control of the satellite service subsystem and the control subsystem to form an intersatellite link; if it has not reached the time, it returns to query whether the current time meets the condition of reaching the control time; Intersatellite links include laser links and microwave links. Both of these different physical links are guided by the link pointing calculation module to guide the rotating drive mechanism to drive the laser head or antenna to perform link establishment and maintenance operations.

[0022] S11: After the orbit control is completed, the autonomous orbit control and ground accuracy are evaluated based on the orbit determination data, intersatellite link pointing angle error, and transmit and receive phase angle error; S12: Update orbit information in real time through onboard GNSS or ground-based orbit parameters; The present invention also provides a system for ensuring the continuity of inter-satellite links in the context of electric propulsion orbit change applications. The system for ensuring the continuity of inter-satellite links in the context of electric propulsion orbit change applications can be implemented by executing the process steps of the method for ensuring the continuity of inter-satellite links in the context of electric propulsion orbit change applications, that is, those skilled in the art can understand the method for ensuring the continuity of inter-satellite links in the context of electric propulsion orbit change applications as a preferred implementation of the system for ensuring the continuity of inter-satellite links in the context of electric propulsion orbit change applications.

[0023] A system for ensuring intersatellite link continuity in the context of electric propulsion orbit change application, comprising: Early Orbital Insertion Module and On-Orbit Operation Module; The early orbital modules include: Module M1: Initial orbit adjustment after the satellite enters orbit and performs intersatellite separation in the active phase; Module M2: Each satellite determines its own orbital position according to the arrangement in the constellation configuration, and completes the constellation configuration deployment; The modules in orbit include: Module M3: When the satellite is in normal operation on orbit, the ground determines the satellite attitude and orbit control status through telemetry, and the satellite autonomous control parameters are added, and the satellite starts the autonomous control mode; Module M4: The satellite updates the satellite orbit information in real time through the onboard GNSS positioning broadcast or the orbit parameters recorded on the ground; Module M5: Satellite attitude and orbit control application software calculates orbit maintenance parameters; Module M6: Satellite attitude and orbit control application software determines whether the control threshold is reached; Module M7: If the satellite attitude and orbit control application software determines that the control threshold has been reached, the attitude and orbit control application software will autonomously calculate the orbit control strategy and generate orbit control data blocks and telemetry data in a specified format; otherwise, the attitude and orbit control application software will continue to calculate orbit maintenance parameters; Module M8: The satellite service software receives the orbit control data and telemetry data sent by the attitude and orbit control application software, and determines whether the orbit control conflicts with the intersatellite link establishment task; Module M9: If the satellite service software determines that the orbit control and inter-satellite link establishment tasks conflict, the satellite attitude and orbit control application software outputs the satellite orbit prediction data and attitude data in the orbit change state to the satellite service software. After receiving the satellite orbit prediction data and attitude data output by the attitude and orbit control application software, the satellite service software forwards them to the link pointing angle calculation module to correct the link pointing angle; if there is no conflict, the satellite service software starts to autonomously control the orbit control; Module M10: The satellite service software determines whether the current time has reached the control time. If it has reached the orbit control time, the satellite orbit maneuver and intersatellite link establishment are realized under the coordinated control of the satellite service subsystem and the control subsystem to form an intersatellite link; if it has not reached the time, it returns to query whether the current time meets the condition of reaching the control time; Module M11: After the orbit control is completed, the autonomous orbit control and ground accuracy are evaluated based on the orbit determination data, intersatellite link pointing angle error, and transmit and receive phase angle error; Module M12: Update orbit information in real time through onboard GNSS or ground-based orbit parameters.

[0024] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0025] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A method for ensuring intersatellite link continuity in the context of electric propulsion orbit change application, characterized in that: include: Early orbit insertion steps and on-orbit operation steps; The early orbital insertion steps include: S1: Initial orbit adjustment after the satellite enters orbit and undergoes intersatellite separation in the active phase; S2: Each satellite determines its own orbital position according to the arrangement in the constellation configuration, and completes the constellation configuration deployment; The on-orbit operation step comprises: S3: In the normal orbital operation state, the ground determines the satellite attitude and orbit control state through telemetry, and the satellite autonomous control parameters are added, and the satellite starts the autonomous control mode; S4: The satellite updates the satellite orbit information in real time through the onboard GNSS positioning broadcast or the orbit parameters recorded on the ground; S5: Satellite attitude and orbit control application software calculates orbit maintenance parameters; S6: The satellite attitude and orbit control application software determines whether the control threshold is reached; S7: If the satellite attitude and orbit control application software determines that the control threshold has been reached, the attitude and orbit control application software autonomously calculates the orbit control strategy and generates orbit control data blocks and telemetry data in a specified format; otherwise, the attitude and orbit control application software continues to calculate orbit maintenance parameters; S8: The satellite service software receives the orbit control data and telemetry data sent by the attitude and orbit control application software, and determines whether the orbit control conflicts with the inter-satellite link establishment task; S9: If the satellite service software determines that the orbit control and inter-satellite link establishment tasks conflict, the satellite attitude and orbit control application software outputs the satellite orbit prediction data and attitude data in the orbit change state to the satellite service software. After receiving the satellite orbit prediction data and attitude data output by the attitude and orbit control application software, the satellite service software forwards them to the link pointing angle calculation module to correct the link pointing angle; if there is no conflict, the satellite service software starts to autonomously control the orbit control; S10: The satellite service software determines whether the current time has reached the control time. If it has reached the orbit control time, the satellite orbit maneuver and intersatellite link establishment are realized under the coordinated control of the satellite service subsystem and the control subsystem to form an intersatellite link. If it has not reached the time, it returns to query whether the current time meets the condition of reaching the control time. S11: After the orbit control is completed, the autonomous orbit control and ground accuracy are evaluated based on the orbit determination data, intersatellite link pointing angle error, and transmit and receive phase angle error; S12: Update orbit information in real time through onboard GNSS or ground-based orbit parameters.

2. The method for ensuring intersatellite link continuity in the context of electric propulsion orbit change according to claim 1 is characterized in that: In step S3, each satellite performs autonomous orbit control after completing configuration phase deployment. In the early stage after launch, the orbital elements of the satellite are noted by the ground, and the satellite calculates the control amount and implements control accordingly. After success, the satellite autonomously measures and determines the orbit based on GNSS data, calculates the control amount and implements control, so as to achieve long-term autonomous orbit maintenance without the support of ground measurement and control system.

3. The method for ensuring intersatellite link continuity in the context of electric propulsion orbit change according to claim 1, characterized in that: In step S3, the satellite autonomous control parameters are added on the ground, and the autonomous orbit maintenance function on the satellite can be enabled / disabled under the intervention of the ground system.

4. The method for ensuring intersatellite link continuity in the context of electric propulsion orbit change according to claim 1, characterized in that: The autonomous control mode of the satellite in step S3 is one of the mission modes of the satellite service software, and the other two modes are the emergency orbit control mission mode and the conventional mission mode; The condition for activating the autonomous orbit control mission mode is that the satellite services and attitude and orbit control related telemetry are normal after entering orbit. The priority order of the three tasks is: emergency orbit control > conventional tasks > autonomous orbit control.

5. The method for ensuring intersatellite link continuity in the context of electric propulsion orbit change according to claim 1, characterized in that: The control threshold in step S6 is a closed-loop control process of the attitude and orbit control application software. When the positioning and orbit determination are valid, the attitude and orbit control application software automatically compares the deviation between the orbit determination data and the nominal orbit. If the deviation exceeds the threshold, the attitude and orbit control automatically executes the autonomous orbit control task if the autonomous orbit control allows. The threshold parameters can be modified by the ground injection parameters.

6. The method for ensuring intersatellite link continuity in the context of electric propulsion orbit change according to claim 1, characterized in that: As described in step S7, the autonomous orbit maintenance strategy is that the satellite attitude and orbit control application software calculates the orbit using absolute position maintenance, and the attitude and orbit control application software has the ability to calculate and generate the autonomous orbit control strategy according to the orbit maintenance position constraint and the autonomous orbit prediction information, and outputs the control data to the satellite service software in a specified format; The specified format orbit control data block output under autonomous orbit control is mainly the parameter data for configuring the Hall electric thrusters, including the start time, end time, Hall electric thruster preheating time, and thruster vector setting parameters.

7. The method for ensuring intersatellite link continuity in the context of electric propulsion orbit change according to claim 1, characterized in that: As described in step S7, the satellite generates telemetry data in a specified format, and the telemetry data can transmit the orbit control process information in real time / delayed manner through the ground continuous measurement and control / relay continuous measurement and control / short message measurement and control channel.

8. The method for ensuring intersatellite link continuity in the context of electric propulsion orbit change according to claim 1, characterized in that: As described in step S8, the satellite service software determines whether the orbit control task conflicts with the intersatellite link establishment task. This process is that the satellite service software makes a comprehensive judgment based on the orbit control data packet, thruster working status, task queue status, energy security and other planning requirements to determine whether to allow / prohibit orbit control, and sends the status to the attitude and orbit control application software.

9. The method for ensuring intersatellite link continuity in the context of electric propulsion orbit change according to claim 1, characterized in that: As described in step S10, the intersatellite link includes a laser link and a microwave link. Both of the two different physical links are guided by the link pointing calculation module to guide the rotation drive mechanism to drive the laser head or antenna to perform link establishment and maintenance operations.

10. A system for ensuring intersatellite link continuity in the context of electric propulsion orbit change application, characterized in that: include: Early Orbital Insertion Module and On-Orbit Operation Module; The early orbital entry module comprises: Module M1: Initial orbit adjustment after the satellite enters orbit and performs intersatellite separation in the active phase; Module M2: Each satellite determines its own orbital position according to the arrangement in the constellation configuration, and completes the constellation configuration deployment; The on-orbit operation module comprises: Module M3: When the satellite is in normal operation on orbit, the ground determines the satellite attitude and orbit control status through telemetry, and the satellite autonomous control parameters are added, and the satellite starts the autonomous control mode; Module M4: The satellite updates the satellite orbit information in real time through the onboard GNSS positioning broadcast or the orbit parameters recorded on the ground; Module M5: Satellite attitude and orbit control application software calculates orbit maintenance parameters; Module M6: Satellite attitude and orbit control application software determines whether the control threshold is reached; Module M7: If the satellite attitude and orbit control application software determines that the control threshold has been reached, the attitude and orbit control application software will autonomously calculate the orbit control strategy and generate orbit control data blocks and telemetry data in a specified format; otherwise, the attitude and orbit control application software will continue to calculate orbit maintenance parameters; Module M8: The satellite service software receives the orbit control data and telemetry data sent by the attitude and orbit control application software, and determines whether the orbit control conflicts with the intersatellite link establishment task; Module M9: If the satellite service software determines that the orbit control and inter-satellite link establishment tasks conflict, the satellite attitude and orbit control application software outputs the satellite orbit prediction data and attitude data in the orbit change state to the satellite service software. After receiving the satellite orbit prediction data and attitude data output by the attitude and orbit control application software, the satellite service software forwards them to the link pointing angle calculation module to correct the link pointing angle; if there is no conflict, the satellite service software starts to autonomously control the orbit control; Module M10: The satellite service software determines whether the current time has reached the control time. If it has reached the orbit control time, the satellite orbit maneuver and intersatellite link establishment are realized under the coordinated control of the satellite service subsystem and the control subsystem to form an intersatellite link; if it has not reached the time, it returns to query whether the current time meets the condition of reaching the control time; Module M11: After the orbit control is completed, the autonomous orbit control and ground accuracy are evaluated based on the orbit determination data, intersatellite link pointing angle error, and transmit and receive phase angle error; Module M12: Update orbit information in real time through onboard GNSS or ground-based orbit parameters.

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