Satellite autonomous pipeline control method based on differential interference SAR imaging task

Abstract

This invention relates to the field of remote sensing satellite orbit control technology, and discloses a satellite autonomous pipeline control method based on differential interferometric SAR imaging missions. The method includes: acquiring initial satellite orbit parameters; employing a multi-objective optimization algorithm for orbit optimization under a high-order gravity field; sampling and constructing a reference orbit point set; calculating orbit control deviations based on the actual orbit and the reference orbit; generating orbit control triggering rules and avoidance strategies through ground system simulation; executing orbit control strategy generation and control onboard system; and evaluating orbit control effectiveness and the evolution trend of orbit control deviations through the ground system. Existing technologies mainly rely on ground command injection, making it difficult for satellites to achieve efficient autonomous orbit control when performing heavy-orbit differential interferometric SAR imaging missions, and hindering the decoupling of orbit control and imaging tasks. This invention improves the efficiency and autonomy of orbit control, the execution efficiency of imaging missions, and the safety of on-orbit operation by constructing a closed-loop control system encompassing satellite-ground collaboration, strategy formulation, command execution, and effect evaluation.

Description

Technical Field

[0001] This invention relates to the field of remote sensing satellite on-orbit operation technology, and in particular to a satellite autonomous pipeline control method based on differential interferometric SAR imaging mission. Background Technology

[0002] Currently, in order to acquire high-precision mapping products and high-precision deformation monitoring products, SAR satellite systems must possess excellent orbit control and stability. Among these, high-precision spatial baseline preservation and estimation capabilities are prerequisites for differential interferometric SAR (D-InSAR) technology to achieve high-precision surface deformation monitoring, while good orbit regression characteristics are key conditions for ensuring multi-temporal image registration and deformation comparative analysis. This places higher demands on the accuracy, autonomy, and response speed of the satellite orbit control system.

[0003] However, in traditional methods, the orbit control and maintenance of SAR satellites typically rely entirely on ground-based command-based orbit control. While this method offers high predictability and scheduling capabilities on the ground, it lacks onboard autonomy, has cumbersome operational procedures, and insufficient real-time performance, failing to meet the high responsiveness and adaptability requirements of mission scenarios such as rapid revisiting and high-frequency imaging. Furthermore, due to the inherent latency of the satellite-to-ground link and operational delays, ground control methods struggle to ensure timely compatibility between orbital accuracy and imaging mission windows, thus limiting the satellite's practical effectiveness in complex missions.

[0004] Therefore, it is urgent to construct a pipeline control method that can autonomously perform high-precision orbit control judgment and execution on orbit, under the premise of meeting the operational requirements of differential interferometric SAR satellites and the resource constraints of ground stations, so as to achieve autonomous, efficient and safe operation of orbit control tasks and comprehensively improve the actual use efficiency of SAR satellites in orbit. Summary of the Invention

[0005] To address the aforementioned technical shortcomings, the present invention aims to propose a satellite autonomous pipeline control method based on differential interferometric SAR imaging missions. This method addresses the problem that existing technologies largely rely on ground command injection, which is particularly problematic in high-response scenarios such as frequent revisits and high-precision imaging. This makes it difficult to achieve efficient autonomy in orbit control and decoupling from the imaging mission. This application improves pipeline maintenance accuracy, imaging mission execution efficiency, and on-orbit operational safety by constructing an integrated closed-loop control system that integrates satellite-ground collaboration, strategy formulation, command execution, and effect evaluation.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: The present invention provides a satellite autonomous pipeline control method based on differential interferometric SAR imaging mission.

[0007] The satellite autonomous pipeline control method based on differential interferometric SAR imaging mission includes:

[0008] Step S10: Obtain the initial orbital parameters of the satellite, use a multi-objective optimization algorithm to optimize the orbit under the action of a higher-order gravity field to obtain a reference orbit, and set the pipe radius r with the reference orbit as the center. 管道 Construct a strict regression pipeline that satisfies both periodic regression characteristics and track control tolerance constraints;

[0009] Step S20: Construct a virtual formation configuration coordinate system based on the reference orbit. Divide the orbital period T of the reference orbit into T / Δt time intervals according to the preset sampling time interval Δt. Record the position and velocity of the reference orbit at each time interval and form a virtual formation sampling point set P. k ;

[0010] Step S30: In the virtual formation configuration coordinate system, for the virtual formation sampling point set P k Each sampling point k defines a track control deviation vector. Track control deviation vector From the normal deviation component E N and radial deviation component E R constitute;

[0011] Step S40: Through the collaboration of the preset ground telemetry and control system and the operation control system, complete the operation simulation analysis for the satellite to obtain the orbit control command set;

[0012] Step S50: Set orbit control triggering rules in the satellite attitude and orbit control subsystem, and execute the calculation and execution tasks of the autonomous orbit control strategy based on the orbit control triggering rules and the orbit control command set.

[0013] Step S60: The ground control system receives feedback data after executing the autonomous orbit control strategy during a preset daily fixed time period and evaluates the evolution trend of orbit control effect and orbit control deviation.

[0014] Preferably, in step S10, the initial orbital parameters of the satellite are obtained, a reference orbit is obtained by using a multi-objective optimization algorithm to optimize the orbit under the action of a higher-order gravity field, and the pipe radius r is set with the reference orbit as the center. 管道 The steps for constructing a rigorous regression pipeline that satisfies both periodic regression characteristics and track control tolerance constraints include:

[0015] Step S101: Obtain the initial orbital parameters of the satellite, including: obtaining the six orbital parameters {a0,e0,i0,Ω0,ω0,M0} of the SAR satellite after it enters orbit, where a0 is the semi-major axis of the initial orbit, e0 is the initial orbital eccentricity, i0 is the initial orbital inclination, Ω0 is the right ascension of the ascending node of the initial orbit, ω0 is the argument of the initial orbital perigee, and M0 is the initial orbital mean perigee angle.

[0016] Step S102: Based on the initial orbital parameters, introduce higher-order harmonic coefficients from the Earth's non-spherical gravity model to model the gravitational perturbation acceleration model;

[0017] Step S103: Pre-construct the orbit optimization objective function, and perform joint optimization of orbit seeking based on the gravity perturbation acceleration model and the satellite's initial orbital parameters in conjunction with the orbit optimization objective function; wherein, the orbit optimization objective function includes a first objective function f1, a second objective function f2, and a third objective function f3; the first objective function is used to minimize the orbital period regression error, the second objective function is used to minimize the propulsion energy consumption, and the third objective function is used to minimize the probability of conflict with the imaging mission window;

[0018] Step S104: Combine the above three objectives to form the trajectory optimization objective function of the multi-objective optimization problem. The non-dominated sorting particle swarm optimization algorithm is used to perform orbit optimization and obtain the reference orbit;

[0019] Step S105: Using the reference orbit as the center trajectory, pre-set the tolerance radius r. max A strict regression pipeline is constructed, which serves as the basis for subsequent track control criteria and deviation calculation, limiting the allowable deviation range of the track.

[0020] Preferably, in step S30, the track control deviation vector satisfy:

[0021]

[0022] in, This is the current actual orbital point of the satellite. For the k-th reference orbit sampling point, the track control deviation vector Used to determine whether the track control has been triggered. It is the normal unit vector. It is a radial unit vector.

[0023] Preferably, in step S40, the step of completing the operational simulation analysis of the satellite through the collaboration of a preset ground telemetry and control system and the operation control system to obtain the orbit control command set specifically includes: completing the operational simulation analysis of the satellite through the collaboration of a preset ground telemetry and control system and the operation control system. The operational simulation analysis includes: telemetry and control window simulation analysis, mission conflict analysis, trigger latitude zone determination and command redundancy evaluation analysis, which aims to determine the on-orbit operation requirements of the differential interferometric SAR satellite and the resource constraints of the ground station, and clarify the triggering rules for the satellite's autonomous orbit control.

[0024] Preferably, in step S50, the orbit control triggering rules specifically include: setting a command to trigger autonomous orbit control at a fixed location (latitude arpeggio or sub-satellite point area) every day; setting a command to trigger the generation of orbit control strategy N hours before triggering autonomous orbit control; and setting a command to trigger the cancellation of satellite payload mission N minutes before and after orbit control.

[0025] The computational tasks for the autonomous orbit control strategy specifically include:

[0026] When the satellite enters the orbit control preparation state and is in stable on-orbit operation, at the orbit control strategy generation time T Nh Obtain the pre-execution time T of the track control system k The corresponding satellite ephemeris information includes orbital position and velocity data in the absolute inertial frame; the satellite ephemeris information is transformed into spatial coordinates and mapped to the virtual formation configuration coordinate system in step S20 to obtain the position and velocity expression of the orbit control pre-trigger point in the virtual formation configuration coordinate system;

[0027] Based on the virtual formation sampling point set P in step S20 k Select the nominal track segment closest to the track control trigger point time, and construct a spatial ellipse equation model of the target track in the configuration coordinate system; based on the spatial ellipse equation model, use parameter fitting and undetermined coefficient method to extract the track offset characteristics of this track segment in the configuration coordinate system, and obtain the virtual formation configuration parameter set; the virtual formation configuration parameter set is used to characterize the deviation characteristics of the current track state relative to the ideal regression trajectory;

[0028] Based on the track control deviation vector obtained in step S30 A mapping relationship is established between the virtual formation configuration parameter set and the two, and the control adjustment quantities are classified and determined. The control adjustment quantities are divided into two categories: in-plane control quantities and out-of-plane control quantities. Specifically, in-plane control quantities are used to correct the semi-major axis, eccentricity vector and relative orbital phase; out-of-plane control quantities are used to eliminate deviations in the out-of-plane direction of the orbit.

[0029] By quantifying and combining in-plane and out-of-plane control quantities, the speed correction requirement under the current track control window is generated.

[0030] Preferably, in step S50, the execution task of the autonomous orbit control strategy specifically includes:

[0031] Generate orbit control strategy: Based on the in-plane and out-of-plane control quantities obtained from the calculation task of the autonomous orbit control strategy, the orbit control strategy is further constructed by combining the current operating environment parameters of the propulsion system; among which, the operating environment parameters include the current temperature and pressure of the tank, the currently estimated remaining propulsion dose, the calibration coefficient of the thruster, and the status feedback information of the attitude control system.

[0032] Collision and rendezvous risk screening: After the orbit control strategy is generated, the ground system receives and acquires the strategy content at fixed times each day, and screens for collision and rendezvous risks during the orbit control execution period by combining historical telemetry and control windows. Specifically, this includes: performing orbit extrapolation operations to generate predicted ephemeris from the start of control to 24 hours after the end of control; performing rendezvous calculations with this predicted ephemeris against all on-orbit objects or constellation systems in the preset orbital environment database to determine if the rendezvous distance is lower than a preset safety threshold. If it is lower than the threshold, a cancellation command block is automatically generated and injected into the satellite via the ground link to terminate the mission; otherwise, the onboard strategy remains unchanged.

[0033] Propulsion Execution and Attitude Management: When the clock enters the orbit control ignition time, the satellite attitude control system will actively switch to propulsion attitude mode. During propulsion execution, the following process control tasks need to be completed: start the designated thruster and execute multi-pulse tangential propulsion or single-pulse normal correction; monitor the current, voltage, temperature and pressure changes of the thruster in real time; monitor the propellant consumption and integral accumulation of propulsion in real time; and determine in real time whether the attitude stability is maintained within the preset attitude control threshold range.

[0034] Track control execution information recording and task recovery: After the propulsion operation is completed, the system will automatically exit the propulsion attitude mode and restore the attitude conditions required for the operational task. At the same time, the system will automatically generate an event log file for this track control strategy execution, which includes: actual thruster ignition time, total propulsion execution duration, cumulative velocity increment, actual propellant consumption, attitude change process data, and abnormal event markers and logs.

[0035] Preferably, step S60, in which the ground control system receives feedback data after executing the autonomous orbit control strategy and evaluates the evolution trend of orbit control effect and orbit control deviation during a preset daily fixed time period, specifically includes:

[0036] After the satellite completes its autonomous orbit control strategy, the ground control system acquires the actual orbit data through telemetry reception and orbit determination processing, including six orbit parameters, instantaneous velocity vector, and instantaneous position vector. Error analysis is performed between the actual orbit data and the reference orbit data. The effectiveness of the satellite's autonomous orbit control is evaluated based on the pipe diameter normal deviation, radial deviation, and total pipe diameter deviation, and an error loss function is constructed.

[0037] Based on the constructed error loss function, a long short-term memory network pre-trained with this function is used to predict the trend of orbit control deviation over the next 24 hours. The prediction results are then used to determine whether the direction of deviation change exceeds the warning threshold; if it does, an early orbit control warning is triggered, the ground control system enters orbit control preparation mode, and the calculation task window for the autonomous orbit control strategy is reopened.

[0038] This invention provides a satellite autonomous pipeline control system based on differential interferometric SAR imaging mission, comprising:

[0039] The orbit construction and optimization module is used to obtain the initial orbital parameters of the satellite, employ a multi-objective optimization algorithm to optimize the orbit under the action of a higher-order gravity field to obtain a reference orbit, and set the pipe radius r with the reference orbit as the center. 管道 Construct a strict regression pipeline that satisfies both periodic regression characteristics and track control tolerance constraints;

[0040] The virtual formation generation module is used to construct a virtual formation configuration coordinate system based on a reference orbit. It divides the orbital period T of the reference orbit into T / Δt time intervals according to a preset sampling time interval Δt, records the position and velocity of the reference orbit at each time interval, and forms a virtual formation sampling point set P. k ;

[0041] The track control deviation determination module is used to determine the virtual formation sampling point set P in the virtual formation configuration coordinate system. k Each sampling point k defines a track control deviation vector. Track control deviation vector From the normal deviation component E N and radial deviation component E R constitute;

[0042] The ground simulation scheduling module is used to complete the operational simulation analysis of the satellite through the collaboration of the preset ground telemetry and control system and the operation control system, and obtain the orbit control command set;

[0043] The autonomous orbit control execution module is used to set orbit control triggering rules in the satellite attitude and orbit control subsystem, and to execute the calculation and execution tasks of the autonomous orbit control strategy according to the orbit control triggering rules and the orbit control command set.

[0044] The track control effect evaluation module is used to receive feedback data after the execution of autonomous track control strategies through the ground telemetry and control system at preset daily fixed time periods and to evaluate the evolution trend of track control effect and track control deviation.

[0045] The present invention also provides a computer program product, including a satellite autonomous pipeline control program based on differential interferometric SAR imaging mission, wherein the satellite autonomous pipeline control program based on differential interferometric SAR imaging mission, when executed by a processor, implements the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission.

[0046] The beneficial effects of this invention are as follows: Existing technologies mainly rely on ground command injection, making it difficult for satellites to achieve efficient and autonomous orbit control when performing heavy-orbit differential interferometric SAR imaging missions, and hindering the decoupling of orbit control and imaging tasks. This invention improves the efficiency and autonomy of orbit control, the execution efficiency of imaging tasks, and the safety of on-orbit operation by constructing an integrated closed-loop control system that integrates satellite-ground coordination, strategy formulation, command execution, and effect evaluation. Attached Figure Description

[0047] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0048] Figure 1 This is a flowchart illustrating the first embodiment of a satellite autonomous pipeline control method based on differential interferometric SAR imaging mission according to the present invention.

[0049] Figure 2 This is a schematic diagram of the first strictly regressive pipeline navigation of a first embodiment of a satellite autonomous pipeline control method based on differential interferometric SAR imaging mission according to the present invention.

[0050] Figure 3 This is a schematic diagram of the second strictly regressive pipeline navigation of the first embodiment of a satellite autonomous pipeline control method based on differential interferometric SAR imaging mission according to the present invention.

[0051] Figure 4 This is a statistical diagram illustrating the on-orbit verification of a satellite autonomous pipeline control method based on a differential interferometric SAR imaging mission, according to a first embodiment of the present invention.

[0052] Figure 5 This is a schematic diagram of the continuous re-orbit image effect under a strictly regressed orbit in the first embodiment of the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission of the present invention.

[0053] Figure 6 This is a schematic diagram of the equipment for a satellite autonomous pipeline control method based on differential interferometric SAR imaging mission according to the present invention. Detailed Implementation

[0054] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0055] Example 1: As Figure 1 The diagram shown is a flowchart of the first embodiment of the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission of the present invention, which proposes the first embodiment of the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission of the present invention.

[0056] In the first embodiment, the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission includes:

[0057] Step S10: Obtain the initial orbital parameters of the satellite, use a multi-objective optimization algorithm to optimize the orbit under the action of a higher-order gravity field to obtain a reference orbit, and set the pipe radius r with the reference orbit as the center. 管道 Construct a strict regression pipeline that satisfies both periodic regression characteristics and track control tolerance constraints;

[0058] It should be noted that in step S10, the initial orbital parameters of the satellite are obtained, a multi-objective optimization algorithm is used to optimize the orbit under the action of a higher-order gravity field to obtain a reference orbit, and the pipe radius r is set with the reference orbit as the center. 管道 The steps for constructing a rigorous regression pipeline that satisfies both periodic regression characteristics and track control tolerance constraints include:

[0059] Step S101: Obtain the initial orbital parameters of the satellite, including: obtaining the six orbital parameters {a0,e0,i0,Ω0,ω0,M0} of the SAR satellite after it enters orbit, where a0 is the semi-major axis of the initial orbit, e0 is the initial orbital eccentricity, i0 is the initial orbital inclination, Ω0 is the right ascension of the ascending node of the initial orbit, ω0 is the argument of the initial orbital perigee, and M0 is the initial orbital mean perigee angle.

[0060] Step S102: Based on the initial orbital parameters, introduce higher-order harmonic coefficients from the Earth's non-spherical gravity model to model the gravitational perturbation acceleration model;

[0061] Step S103: Pre-construct the orbit optimization objective function, and perform joint optimization of orbit seeking based on the gravity perturbation acceleration model and the satellite's initial orbital parameters in conjunction with the orbit optimization objective function; wherein, the orbit optimization objective function includes a first objective function f1, a second objective function f2, and a third objective function f3; the first objective function is used to minimize the orbital period regression error, the second objective function is used to minimize the propulsion energy consumption, and the third objective function is used to minimize the probability of conflict with the imaging mission window;

[0062] Step S104: Combine the above three objectives to form the trajectory optimization objective function of the multi-objective optimization problem. The non-dominated sorting particle swarm optimization algorithm is used to perform orbit optimization and obtain the reference orbit;

[0063] Step S105: Using the reference orbit as the center trajectory, pre-set the tolerance radius r. max A strict regression pipeline is constructed, which serves as the basis for subsequent track control criteria and deviation calculation, limiting the allowable deviation range of the track.

[0064] It is understood that the above steps S101 to S105 together constitute the "orbit control boundary construction stage" in the on-board autonomous orbit control mechanism of the present invention. Its core purpose is to provide orbital foundation support for the accuracy, autonomy and business compatibility of subsequent orbit control strategies based on physical modeling and multi-objective optimization methods.

[0065] It should be understood that by introducing a high-order gravity model and a multi-objective optimization algorithm, this invention not only improves the long-term stability and predictability of the reference orbit, but also enables the orbit control criteria to have higher spatial accuracy and scheduling flexibility, ensuring that subsequent orbit control operations have executable and adaptive control capabilities.

[0066] Step S20: Construct a virtual formation configuration coordinate system based on the reference orbit. Divide the orbital period T of the reference orbit into T / Δt time intervals according to the preset sampling time interval Δt. Record the position and velocity of the reference orbit at each time interval and form a virtual formation sampling point set P. k ;

[0067] It should be noted that this step is a crucial foundation for constructing the autonomous orbit control spatial criterion model based on the reference orbit. The derived orbit control criteria, deviation vector calculation, and control quantity generation all rely on the constructed set of sampling points to provide a reference benchmark for position and velocity. This step is closely linked to the reference orbit result generated in step S10 and serves as a bridge connecting the "orbit optimization stage" and the "control criterion stage."

[0068] Understandably, by periodically discretizing the reference track into standard sampling points and introducing a spatial configuration coordinate system, this invention can efficiently establish a sampling criterion system for spatial error analysis, significantly enhancing the sensitivity and spatial representation capability of track control deviation determination. This provides a reliable track geometry foundation for the subsequent realization of high-precision, autonomous track control logic. Furthermore, the spatial distribution and velocity characteristics of the sampling points facilitate subsequent advanced judgment tasks such as dynamic configuration reconstruction, configuration parameter extraction, and track control window matching, laying a data foundation for building spatial decision-making capabilities for track control tasks.

[0069] Step S30: In the virtual formation configuration coordinate system, for the virtual formation sampling point set P k Each sampling point k defines a track control deviation vector. Track control deviation vector From the normal deviation component E N and radial deviation component E R constitute;

[0070] It should be noted that in step S30, the track control deviation vector satisfy:

[0071]

[0072] in, This is the current actual orbital point of the satellite. For the k-th reference orbit sampling point, the track control deviation vector Used to determine whether the track control has been triggered. It is the normal unit vector. It is a radial unit vector;

[0073] For example, such as Figure 2 As shown, P(t) represents the actual position of the satellite trajectory. k P represents the current virtual formation reference trajectory position of the satellites. R (t k The ) represents the origin of the Earth-fixed system coordinates corresponding to the reference trajectory position, R represents the required control pipeline radius of 200m, and E represents the total deviation of the satellite from the strictly regressed pipeline reference point in terms of pipe diameter. For example... Figure 3 As shown, P(t), P(t) k ), P R (t k )and Figure 2 The expressions are the same, R represents the direction from the Earth's center to P. R (t kThe vector at the origin is T, which is perpendicular to R and points in the direction of the satellite's trajectory. N is the vector determined by the right-hand rule and is perpendicular to the orbital plane. E represents the total deviation of the satellite's diameter from the strictly regressed pipe reference point, expressed as the normal component of the pipe diameter E. N and radial component E R Together constitute, that is

[0074] Understandably, this step transforms the "abstract orbital position deviation" into a "determinable control trigger quantity," simplifying the three-dimensional orbital offset into deviation indicators in two independent dimensions: spatial errors within the orbital plane (radial) and outside the orbital plane (normal). This gives the orbital control judgment clear criterion logic and physical meaning. Simultaneously, the deviation vector, calculated using the k-th sampling point as the reference, is correlated with the virtual formation trajectory point set constructed in step S20, forming an orbital control triggering reference system indexed by orbital timing and containing spatial errors.

[0075] Step S40: Through the collaboration of the preset ground telemetry and control system and the operation control system, complete the operation simulation analysis for the satellite to obtain the orbit control command set;

[0076] It should be noted that in step S40, the step of completing the operational simulation analysis of the satellite and obtaining the orbit control command set through the collaboration of the preset ground telemetry and control system and the operation control system specifically includes: completing the operational simulation analysis of the satellite through the collaboration of the preset ground telemetry and control system and the operation control system. The operational simulation analysis includes: telemetry and control window simulation analysis, mission conflict analysis, trigger latitude zone determination and command redundancy evaluation analysis, which aims to determine the on-orbit operation requirements of the differential interferometric SAR satellite and the resource constraints of the ground station, and clarify the triggering rules for the satellite's autonomous orbit control.

[0077] The complete process of simulation analysis can be understood as follows: First, the ground control system simulates the satellite-to-ground rendezvous for the next few days based on the satellite's current orbital parameters and the geographical locations of each control station. Visibility analysis is performed on each orbit with all control stations, fully considering the minimum elevation angle constraint (usually set to 3 degrees) and the tracking capability of the control antennas. Under the premise of meeting the minimum visibility duration, the time periods during which each control station can establish a link with the satellite each day are identified, and these time periods are further sorted chronologically to form a daily "available control window table." Subsequently, the preferred time periods with high data link stability and low communication load are selected as candidate loading windows for future orbit control commands, leaving operational margin for orbit control triggering and ground command access. Next, the ground control system loads the scheduling plans for imaging and data transmission tasks, and analyzes the periodicity and occupancy of tasks based on historical satellite scheduling data. For the candidate time points of daily orbit control, the system determines whether there is any overlap in the time periods of imaging or data transmission tasks before or after that time point. If a conflict exists, the system will classify it according to its severity, such as minor conflict, moderate conflict, or complete overlap, and decide whether to postpone or advance the orbit control command based on task priority. To ensure that orbit control and imaging tasks do not interfere with each other in time, the system further establishes an "avoidance window" for orbit control tasks. For example, it stipulates that no payload tasks should be scheduled within N minutes before and after the orbit control execution time (determined based on the actual on-orbit usage constraints of the satellite), and this window information is shared synchronously with the command scheduling system.

[0078] Based on the above two analyses, the system further integrates the orbit design results and the distribution of telemetry and control windows to determine the most suitable orbital position for triggering orbit control. This position is typically characterized by the latitude argument in the satellite's nadir trajectory. The operation and control system will select latitude segments with high orbit control execution safety, strong sensitivity to orbital errors, and no impact on the main imaging target area, based on the operational patterns of each orbital cycle, as fixed trigger positions for the orbit control mission. Furthermore, this trigger position must also meet certain ground visibility conditions to ensure that ground telemetry and control stations can continuously acquire telemetry information during orbit control execution, facilitating subsequent effect confirmation and real-time monitoring of orbit control events. Finally, the ground system also needs to comprehensively evaluate the actual capacity and redundancy of the satellite-to-ground command link. Specifically, this includes: calculating whether the data bandwidth of each ground station can complete the generation, scheduling, transmission, and injection of commands within the time limit before orbit control triggering; assessing whether backup stations or redundant links are available in case of primary link failure; and determining whether the current telemetry and control task load is too heavy, thus affecting the timely transmission of commands. If the assessment results indicate a potential risk of command congestion or delay, the system will take measures such as generating backup commands in advance, setting backup injection times, or using other link resources to ensure that orbit control commands can be successfully injected and confirmed before being triggered on the satellite.

[0079] It should be understood that the operational simulation mechanism described in this step not only solves the technical bottlenecks of "conflicts in temporary ground scheduling and link instability leading to command failure" in traditional track control methods, but also constructs a three-in-one track control pre-planning mechanism by organically coupling task scheduling, link control, and track control strategies. This mechanism integrates "optimal selection of track control window—avoidance of business conflicts—link injection guarantee." Through this mechanism, the success rate of track control command injection can be significantly improved, the planning and determinism of track control execution can be enhanced, and the operability of track control tasks and the overall scheduling efficiency of the system can be significantly improved in high-density business scenarios. This becomes one of the fundamental guarantees for achieving a closed-loop system engineering of a space-ground joint autonomous track control system.

[0080] Step S50: Set orbit control triggering rules in the satellite attitude and orbit control subsystem, and execute the calculation and execution tasks of the autonomous orbit control strategy based on the orbit control triggering rules and the orbit control command set.

[0081] It should be noted that in step S50, the orbit control triggering rules specifically include: setting a command to trigger autonomous orbit control at a fixed location every day; setting a command to trigger the generation of orbit control strategy N hours before the triggering of autonomous orbit control; setting a command to trigger the cancellation of satellite payload tasks N minutes before and after orbit control; the calculation task of autonomous orbit control strategy specifically includes: when the satellite enters the orbit control preparation state and is in stable on-orbit operation, at the orbit control strategy generation time T... Nh Obtain the pre-execution time T of the track control system k The corresponding satellite ephemeris information includes orbital position and velocity data in the absolute inertial frame. The satellite ephemeris information is transformed into spatial coordinates and mapped to the virtual formation configuration coordinate system in step S20 to obtain the position and velocity representation of the orbit control pre-trigger point in the virtual formation configuration coordinate system. Based on the virtual formation sampling point set P in step S20... k Select the nominal track segment closest to the track control trigger point time, and construct a spatial ellipse equation model of the target track in the configuration coordinate system. Based on the spatial ellipse equation model, use parameter fitting and the undetermined coefficient method to extract the track offset characteristics of this segment in the configuration coordinate system, and obtain a virtual formation configuration parameter set to characterize the deviation characteristics of the current track state relative to the ideal regression trajectory. Based on the track control deviation vector obtained in step S30... A mapping relationship is established between the virtual formation configuration parameter set and the virtual formation configuration parameter set. The control adjustment quantities are classified into two categories: in-plane control quantities and out-of-plane control quantities. Specifically, in-plane control quantities are used to correct the semi-major axis, eccentricity vector and relative orbital phase; out-of-plane control quantities are used to eliminate deviations in the out-of-plane direction of the orbit. By quantizing and combining the in-plane and out-of-plane control quantities, the speed correction requirement under the current orbit control window is generated.

[0082] In step S50, the execution tasks of the autonomous orbit control strategy specifically include: generating the orbit control strategy: based on the in-plane and out-of-plane control quantities obtained from the calculation task of the autonomous orbit control strategy, and further combined with the current operating environment parameters of the propulsion system, the orbit control strategy is constructed; wherein, the operating environment parameters include the current temperature and pressure of the tank, the currently estimated remaining propulsion dose, the calibration coefficient of the thruster, and the status feedback information of the attitude control system; collision and rendezvous risk screening: after the orbit control strategy is generated, the ground system obtains the content of the strategy at a fixed time every day, and screens the collision and rendezvous risks during the orbit control execution period in combination with the historical telemetry and control window, specifically including: orbit extrapolation operation before executing the orbit control strategy, generating a predicted ephemeris from the start time to 24 hours after the end time of orbit control; performing rendezvous calculations with the predicted ephemeris and all on-orbit celestial bodies or constellation systems in the preset orbit environment database, and determining whether the rendezvous distance is lower than the preset safety threshold. If it is lower than the preset safety threshold, it automatically... A command block to cancel orbit control is generated and injected into the satellite via the ground link to terminate the mission; otherwise, the onboard strategy remains unchanged. Propulsion execution and attitude management: When the clock enters the orbit control ignition time, the satellite attitude control system will actively switch to propulsion attitude mode. During propulsion execution, the following process control tasks are performed: starting the designated thruster, performing multi-pulse tangential propulsion or single-pulse normal correction; real-time monitoring of thruster current, voltage, temperature, and pressure changes; real-time monitoring of propellant consumption and integral accumulation of propulsion; real-time determination of whether attitude stability remains within the preset attitude control threshold range. Orbit control execution information recording and mission recovery: After the propulsion operation is completed, the satellite automatically exits the propulsion attitude mode, restores to the attitude conditions required for the mission, and automatically generates an event log file for this orbit control strategy execution, including: actual thruster ignition time, total propulsion execution duration, cumulative velocity increment, actual propellant consumption, attitude change process data, abnormal event markers, and logs.

[0083] Understandably, step S50 combines orbit control triggering rules with control criteria, and each step is designed with the principles of space-ground linkage and autonomy as the priority, thereby enhancing the real-time performance, adaptability, and mission assurance capabilities of orbit control.

[0084] It should be understood that this invention, through collaborative modeling of the orbit control deviation vector and orbit control configuration parameters, combined with the satellite-ground collaboration mechanism, not only achieves high-precision execution of orbit control tasks, but also possesses three-dimensional capabilities for pre-orbit assessment, in-orbit monitoring, and post-orbit prediction. This constitutes a highly robust closed-loop scheduling method for satellite on-orbit orbit control, which is significantly superior to the static ground command mechanism in the prior art. It is especially suitable for remote sensing satellite scenarios where frequent revisits and highly sensitive services place strict requirements on orbit accuracy.

[0085] The satellite autonomous pipeline control method based on differential interferometric SAR imaging mission was implemented in orbit. Statistical verification during in-orbit operation from December 2, 2024 to January 16, 2025 showed that the pipeline radius met the 200m requirement with a probability of 99.97% within 46 days. (See attached data.) Figure 4 Meanwhile, multiple D-InSAR images of the same region observed under the same mode and wavefront show consistent imaging angles, swath widths, and ground feature characteristics. (See...) Figure 5 This invention constructs an autonomous pipeline control method with high precision, high autonomy, and high reliability through on-board autonomous decision-making and ground-based collaborative support. It can achieve long-term stable maintenance of satellite orbit without affecting payload missions, and continuously ensure the ability to acquire high-precision remote sensing products.

[0086] Step S60: The ground control system receives feedback data after executing the autonomous orbit control strategy during a preset daily fixed time period and evaluates the evolution trend of orbit control effect and orbit control deviation.

[0087] It should be noted that in step S60, the ground control system receives feedback data after executing the autonomous orbit control strategy and evaluates the orbit control effect and the evolution trend of orbit control deviation during a preset daily fixed time period. Specifically, this includes: after the satellite completes the execution of the autonomous orbit control strategy, the ground control system obtains the actual orbit data after control through telemetry reception and orbit determination processing, including six orbit parameters and instantaneous velocity and position vectors; performs error analysis on the actual orbit data and reference orbit data after control, evaluates the satellite's autonomous orbit control effect from the pipe diameter normal deviation, radial deviation, and total pipe diameter deviation, and constructs an error loss function. Based on the constructed error loss function, a long short-term memory network pre-trained with this error loss function is used to predict the trend of orbit control deviation in the next 24 hours. The prediction results are used to determine whether the direction of deviation change exceeds the warning threshold. If it does, an early orbit control warning is triggered, the ground control system enters the orbit control preparation state, and the window for calculating the autonomous orbit control strategy is reopened.

[0088] It should be understood that the main purpose of this step is to use the threshold of the total diameter deviation as a threshold to predict the trend of the total diameter deviation of the satellite in this orbit. If it may exceed the threshold, the ground system will monitor and enter the orbit control preparation state, and reopen the window for calculating the autonomous orbit control strategy.

[0089] Example 2: Furthermore, the present invention provides a satellite autonomous pipeline control system based on differential interferometric SAR imaging missions, employing a satellite autonomous pipeline control method based on differential interferometric SAR imaging missions as described in the above embodiments, which can solve a technical problem in satellite autonomous pipeline control based on differential interferometric SAR imaging missions. Compared with the prior art, the beneficial effects of the satellite autonomous pipeline control system based on differential interferometric SAR imaging missions provided by the present invention are the same as the beneficial effects of the satellite autonomous pipeline control method based on differential interferometric SAR imaging missions provided in the above embodiments, and other technical features in the satellite autonomous pipeline control system based on differential interferometric SAR imaging missions are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0090] Example 3: This invention provides a satellite autonomous pipeline control device based on differential interferometric SAR imaging missions. Please refer to... Figure 6A satellite autonomous pipeline control device based on differential interferometric SAR imaging mission includes: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, which, when executed by the at least one processor, enable the at least one processor to execute the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission described in Embodiment 1 above. The satellite autonomous pipeline control device based on differential interferometric SAR imaging mission in this embodiment of the invention may include, but is not limited to, mobile terminals such as mobile phones, laptops, digital broadcast receivers, PDAs (Personal Digital Assistants), PADs (Portable Application Description), PMPs (Portable Media Players), and vehicle terminals (e.g., vehicle navigation terminals), as well as fixed terminals such as digital TVs and desktop computers. This satellite autonomous pipeline control device based on differential interferometric SAR imaging mission is merely an example and should not impose any limitations on the functionality and scope of use of the embodiments of the invention. A satellite autonomous pipeline control device for differential interferometric SAR imaging missions may include a processing unit 1001 (e.g., a central processing unit, graphics processing unit, etc.), which can perform various appropriate actions and processes according to a program stored in read-only memory (ROM) 1002 or a program loaded from storage device 1003 into random access memory (RAM) 1004. The RAM 1004 also stores various programs and data required for the operation of the satellite autonomous pipeline control device for differential interferometric SAR imaging missions. The processing unit 1001, ROM 1002, and RAM 1004 are interconnected via a bus 1005. An input / output (I / O) interface 1006 is also connected to the bus. Typically, the following systems can be connected to I / O interface 1006: input devices 1007 including, for example, touchscreens, touchpads, keyboards, mice, image sensors, microphones, accelerometers, gyroscopes, etc.; output devices 1008 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; storage devices 1003 including, for example, magnetic tapes, hard disks, etc.; and communication devices 1009. Communication device 1009 allows a satellite autonomous pipeline control device for a differential interferometric SAR imaging mission to exchange data with other devices wirelessly or via wired communication. Although a satellite autonomous pipeline control device for a differential interferometric SAR imaging mission with various systems is shown in the figure, it should be understood that implementation or possession of all the systems shown is not required.It can be implemented alternatively or with more or fewer systems.

[0091] Example 4: This invention also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission described above. The computer program product provided by this invention can solve the technical problem of satellite autonomous pipeline control based on differential interferometric SAR imaging mission. Compared with the prior art, the beneficial effects of the computer program product provided by this invention are the same as those of the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission provided in the above embodiments, and will not be repeated here.

[0092] In particular, according to the embodiments disclosed in this invention, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of this invention include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via a communication device, or installed from storage device 1003, or installed from ROM 1002. When the computer program is executed by processing device 1001, it performs the functions defined in the methods of the embodiments disclosed in this invention.

[0093] It should be understood that the various parts disclosed in this invention can be implemented using hardware, software, firmware, or a combination thereof. In the description of the above embodiments, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0094] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A satellite autonomous pipeline control method based on differential interferometric SAR imaging mission, characterized in that, The methods include: Step S10: Obtain the initial orbital parameters of the satellite, use a multi-objective optimization algorithm to optimize the orbit under the action of a higher-order gravity field to obtain a reference orbit, and set the pipe radius r with the reference orbit as the center. 管道 Construct a strict regression pipeline that satisfies both periodic regression characteristics and track control tolerance constraints; Step S20: Construct a virtual formation configuration coordinate system based on the reference orbit. Divide the orbital period T of the reference orbit into T / Δt time intervals according to the preset sampling time interval Δt. Record the position and velocity of the reference orbit at each time interval to form a virtual formation sampling point set P. k ; Step S30: In the virtual formation configuration coordinate system, for the virtual formation sampling point set P k For each sampling point k, define the track control deviation vector. Track control deviation vector From the normal deviation component E N and radial deviation component E R constitute; Step S40: Through the collaboration of the preset ground telemetry and control system and the operation control system, complete the operation simulation analysis for the satellite to obtain the orbit control command set; Step S50: Set orbit control triggering rules in the satellite attitude and orbit control subsystem, and execute the calculation and execution tasks of the autonomous orbit control strategy based on the orbit control triggering rules and the orbit control command set; Step S60: The ground control system receives feedback data after executing the autonomous orbit control strategy during a preset daily fixed time period, and evaluates the evolution trend of orbit control effect and deviation.

2. The satellite autonomous pipeline control method based on differential interferometric SAR imaging mission as described in claim 1, characterized in that, In step S10, the initial orbital parameters of the satellite are obtained, and a reference orbit is obtained by using a multi-objective optimization algorithm to optimize the orbit under the action of a higher-order gravity field. The pipe radius r is then set with the reference orbit as the center. 管道 The steps for constructing a rigorous regression pipeline that satisfies both periodic regression characteristics and track control tolerance constraints include: Step S101: Obtain the initial orbital parameters of the satellite, which include six orbital parameters after SAR insertion: {a0,e0,i0,Ω0,ω0,M0}, where a0 is the semi-major axis of the initial orbit, e0 is the initial orbital eccentricity, i0 is the initial orbital inclination, Ω0 is the right ascension of the ascending node of the initial orbit, ω0 is the argument of the initial orbital perigee, and M0 is the initial orbital mean perigee angle. Step S102: Based on the initial orbital parameters, introduce higher-order harmonic coefficients from the Earth's non-spherical gravity model to model the gravitational perturbation acceleration model; Step S103: Pre-construct the orbit optimization objective function, and perform joint optimization of orbit seeking based on the gravity perturbation acceleration model and the satellite's initial orbital parameters in conjunction with the orbit optimization objective function; wherein, the orbit optimization objective function includes a first objective function f1, a second objective function f2, and a third objective function f3; the first objective function is used to minimize the orbital period regression error, the second objective function is used to minimize the propulsion energy consumption, and the third objective function is used to minimize the probability of conflict with the imaging mission window; Step S104: Use the non-dominated sorting particle swarm optimization algorithm to perform orbit optimization on the first objective function f1, the second objective function f2 and the third objective function f3 to obtain the reference orbit; Step S105: Using the reference orbit as the center trajectory, pre-set the tolerance radius r. max A strict regression pipeline is constructed, which serves as the basis for subsequent track control criteria and deviation calculation, limiting the allowable deviation range of the track.

3. The satellite autonomous pipeline control method based on differential interferometric SAR imaging mission as described in claim 1, characterized in that, In step S30, the track control deviation vector satisfy: in in, This is the current actual orbital point of the satellite. For the k-th reference orbit sampling point, the track control deviation vector Used to determine whether the track control has been triggered. It is the normal unit vector. It is a radial unit vector.

4. The satellite autonomous pipeline control method based on differential interferometric SAR imaging mission as described in claim 1, characterized in that, In step S40, the operation simulation analysis of the satellite is completed through the collaboration of the preset ground telemetry and control system and the operation control system to obtain the orbit control command set. Specifically, this includes: completing the operation simulation analysis of the satellite through the collaboration of the preset ground telemetry and control system and the operation control system. The operation simulation analysis includes: telemetry and control window simulation analysis, mission conflict analysis, trigger latitude zone determination and command redundancy evaluation analysis, which aims to determine the on-orbit operation requirements of the differential interferometric SAR satellite and the resource constraints of the ground station, and clarify the triggering rules for the satellite's autonomous orbit control.

5. The satellite autonomous pipeline control method based on differential interferometric SAR imaging mission as described in claim 1, characterized in that, In step S50, the orbit control triggering rules specifically include: setting a command to trigger autonomous orbit control at a fixed location every day; setting a command to generate an orbit control strategy N hours before triggering autonomous orbit control; and setting a command to cancel the satellite payload mission N minutes before and after orbit control. The computational tasks for the autonomous orbit control strategy specifically include: When the satellite enters the orbit control preparation state and is in stable on-orbit operation, at the orbit control strategy generation time T Nh Obtain the pre-execution time T of the track control system k The corresponding satellite ephemeris information includes orbital position and velocity data in the absolute inertial frame; the satellite ephemeris information is transformed into spatial coordinates and mapped to the virtual formation configuration coordinate system in step S20 to obtain the position and velocity expression of the orbit control pre-trigger point in the virtual formation configuration coordinate system; Based on the virtual formation sampling point set P in step S20 k Select the nominal track segment closest to the track control trigger point time, and construct a spatial ellipse equation model of the target track in the configuration coordinate system; based on the spatial ellipse equation model, use parameter fitting and undetermined coefficient method to extract the track offset characteristics of the nominal track segment in the configuration coordinate system, and obtain the virtual formation configuration parameter set; the virtual formation configuration parameter set is used to characterize the deviation characteristics of the current track state relative to the ideal regression trajectory. Based on the track control deviation vector obtained in step S30 A mapping relationship is established between the virtual formation configuration parameter set and the two, and the control adjustment quantities are classified and determined. The control adjustment quantities are divided into two categories: in-plane control quantities and out-of-plane control quantities. Specifically, in-plane control quantities are used to correct the semi-major axis, eccentricity vector and relative orbital phase; out-of-plane control quantities are used to eliminate deviations in the out-of-plane direction of the orbit. By quantifying and combining in-plane and out-of-plane control quantities, the speed correction requirement under the current track control window is generated.

6. The satellite autonomous pipeline control method based on differential interferometric SAR imaging mission as described in claim 5, characterized in that, In step S50, the specific tasks of executing the autonomous orbit control strategy include: Generate orbit control strategy: Based on the in-plane and out-of-plane control quantities obtained from the autonomous orbit control strategy calculation task, and combined with the current operating environment parameters of the propulsion system, construct the orbit control strategy; among which, the operating environment parameters include the current temperature and pressure of the tank, the estimated remaining propulsion dose, the calibration coefficient of the thruster, and the state feedback information of the attitude control system; Collision and rendezvous risk screening: After the orbit control strategy is generated, the ground system receives and acquires the strategy content at fixed times every day, and screens for collision and rendezvous risks during the orbit control execution period in conjunction with historical telemetry and control windows. Specifically, this includes: orbit extrapolation before executing the orbit control strategy to generate a predicted ephemeris from the start time to 24 hours after the end time of orbit control; performing rendezvous calculations with the predicted ephemeris and all on-orbit objects or constellation systems in the preset orbital environment database to determine whether the rendezvous distance is lower than a preset safety threshold; if it is lower than the threshold, an orbit control cancellation command block is automatically generated and injected into the satellite through the ground link to terminate the mission; otherwise, the on-board strategy remains unchanged. Propulsion Execution and Attitude Management: When the clock enters the orbit control ignition time, the satellite attitude control system will actively switch to propulsion attitude mode. During propulsion execution, the following process control tasks need to be completed: start the designated thruster and execute multi-pulse tangential propulsion or single-pulse normal correction; monitor the current, voltage, temperature and pressure changes of the thruster in real time; monitor the propellant consumption and integral accumulation of propulsion in real time; and determine in real time whether the attitude stability is maintained within the preset attitude control threshold range. Track control execution information recording and task recovery: After the propulsion operation is completed, the system will automatically exit the propulsion attitude mode and restore the attitude conditions required for the business task; at the same time, the system will automatically generate an event log file for this track control strategy execution, which includes: the actual ignition time of the thruster, the total propulsion execution time, the cumulative speed increment, the actual amount of propellant consumed, attitude change process data, and abnormal event markers and logs.

7. The satellite autonomous pipeline control method based on differential interferometric SAR imaging mission as described in claim 6, characterized in that, In step S60, the ground control system receives feedback data after executing the autonomous orbit control strategy and evaluates the evolution trend of orbit control effect and orbit control deviation during a preset daily fixed time period. This step specifically includes: After the satellite completes the execution of its autonomous orbit control strategy, the ground control system acquires the actual orbit data after control through telemetry reception and orbit determination processing, including six orbit parameters, instantaneous velocity vector, and instantaneous position vector. Error analysis is performed on the actual orbit data after control and the reference orbit data. The satellite's autonomous orbit control effect is evaluated from the pipe diameter normal deviation, radial deviation, and total pipe diameter deviation, and an error loss function is constructed. Based on the constructed error loss function, a long short-term memory network pre-trained with this function is used to predict the trend of track control deviation in the next 24 hours. The prediction results are combined to determine whether the direction of deviation change exceeds the warning threshold. If it does, the track control warning prompt is triggered in advance, the ground telemetry and control system will enter the track control preparation state, and the calculation task window of the autonomous track control strategy will be reopened.

8. A satellite autonomous pipeline control system based on differential interferometric SAR imaging mission, applied to the satellite autonomous pipeline control method based on differential interferometric SAR imaging mission as described in any one of claims 1-7, characterized in that, The satellite autonomous pipeline control system based on differential interferometric SAR imaging mission includes: The orbit construction and optimization module is used to obtain the initial orbital parameters of the satellite, employ a multi-objective optimization algorithm to optimize the orbit under the action of a higher-order gravity field to obtain a reference orbit, and set the pipe radius r with the reference orbit as the center. 管道 Construct a strict regression pipeline that satisfies both periodic regression characteristics and track control tolerance constraints; The virtual formation generation module is used to construct a virtual formation configuration coordinate system based on a reference orbit. It divides the orbital period T of the reference orbit into T / Δt time intervals according to a preset sampling time interval Δt, records the position and velocity of the reference orbit at each time interval, and forms a virtual formation sampling point set P. k ; The track control deviation determination module is used to determine the virtual formation sampling point set P in the virtual formation configuration coordinate system. k Each sampling point k defines a track control deviation vector. Track control deviation vector From the normal deviation component E N and radial deviation component E R constitute; The ground simulation scheduling module is used to complete the operational simulation analysis of the satellite through the collaboration of the preset ground telemetry and control system and the operation control system, and obtain the orbit control command set; The autonomous orbit control execution module is used to set orbit control triggering rules in the satellite attitude and orbit control subsystem, and to execute the calculation and execution tasks of the autonomous orbit control strategy according to the orbit control triggering rules and the orbit control command set. The track control effect evaluation module is used to receive feedback data after the execution of autonomous track control strategies through the ground telemetry and control system at preset daily fixed time periods and to evaluate the evolution trend of track control effect and track control deviation.

9. A satellite autonomous pipeline control device based on differential interferometric SAR imaging mission, characterized in that, The satellite autonomous pipeline control device based on differential interferometric SAR imaging mission includes: a memory, a processor, and a satellite autonomous pipeline control program based on differential interferometric SAR imaging mission stored in the memory and executable on the processor. When the satellite autonomous pipeline control program based on differential interferometric SAR imaging mission is executed by the processor, it implements a satellite autonomous pipeline control method based on differential interferometric SAR imaging mission according to any one of claims 1 to 7.

10. A computer program product, characterized in that, The computer program product includes a satellite autonomous pipeline control program based on differential interferometric SAR imaging mission. When the satellite autonomous pipeline control program based on differential interferometric SAR imaging mission is executed by the processor, it implements a satellite autonomous pipeline control method based on any one of claims 1 to 7.

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