A digital satellite system modeling method for remote sensing satellite task constraint checking

Abstract

The application relates to a digital satellite system modeling method for remote sensing satellite task constraint verification, which comprises the following steps: establishing a basic support layer of a digital satellite system to provide modular simulation support services; establishing a model layer of the digital satellite system to realize simulation operation calculation of each simulation subsystem and generate simulation test data; establishing a service layer of the digital satellite system, which forms a command control interface interacting with a command and dispatch system, a measurement and control data transmission plan interface interacting with an operation and control system and a measurement and control instruction interface interacting with a measurement and control system on the basis of the basic support layer and the model layer; and completing system integration of the basic support layer, the model layer and the service layer based on a remote sensing satellite task constraint verification process. The digital satellite system established by the application is used for remote sensing satellite task constraint verification, and simultaneously considers satellite on-orbit constraints and star-ground resource window constraints such as measurement and control, data transmission arc segment, energy balance, data balance, sunlight avoidance and the like.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of satellite design, and relates to a digital satellite system modeling method for remote sensing satellite task constraint verification, which is suitable for the task constraint verification link before task injection, control, data transmission and observation of an on-orbit remote sensing satellite. BACKGROUND

[0002] The digital satellite system is a result of digital model modeling of satellite task planning, attitude control, data transmission and other main functional domains according to three different levels and different granularities of system level, application level and engineering level, and integrated after modeling, and can realize full-digital ultra-real-time simulation of the whole-satellite working mode without the aid of space vehicle hardware devices, simulating the theoretical running state of the satellite in orbit.

[0003] The digital satellite system of a remote sensing satellite needs to include key functional domains such as attitude control, integrated electronics, data transmission and camera imaging of the satellite, and runs through the whole process of satellite application demand planning, task planning, instruction control, ground observation, on-orbit operation management and information processing, data transmission, ground processing application, and is a complex information system driven by typical application scenarios of remote sensing satellites and on-orbit use strategies of the satellites.

[0004] The on-orbit tasks of a remote sensing satellite mainly include control, data transmission and observation tasks, and before task injection, it is necessary to judge whether the observation task sequence to be injected satisfies the control, data transmission arc segment and other satellite-ground resource window constraints between the satellite and the ground station; confirm whether the execution process of the ground observation task carried out by the satellite according to the established mode strategy satisfies the energy balance, data balance, sunlight avoidance and other on-orbit capability constraints of the satellite; estimate the satellite attitude maneuvering situation, sunlight illumination situation and observation data generation and downlink situation in the task execution process.

[0005] In recent years, remote sensing satellite technology has developed rapidly, and satellite working modes have become increasingly complex. The task constraint verification method based on the most stringent static constraint parameters and fixed control files that has been generally used in the past is gradually difficult to match the actual task constraints of the satellite, resulting in the situation that the task of the remote sensing satellite to be injected satisfies the actual satellite capability and satellite-ground resource window constraints, but cannot pass the ground task constraint verification, causing the satellite user to be difficult to realize efficient control of the on-orbit remote sensing satellite.

[0006] At present, the research is mainly to establish a digital satellite system for remote sensing satellite observation task efficiency simulation evaluation, and there is no digital satellite system modeling method for remote sensing satellite task constraint verification, considering satellite-ground resource window constraints such as control, data transmission arc segment, energy balance, data balance, sunlight avoidance and on-orbit constraints of the satellite. SUMMARY

[0007] The technical problem solved by this invention is to overcome the shortcomings of the existing technology and propose a digital satellite system modeling method for constraint verification of remote sensing satellite missions.

[0008] The solution of the present invention is:

[0009] A digital satellite system modeling method for remote sensing satellite mission constraint verification includes:

[0010] (1) Establish a basic support layer for the digital satellite system. The basic support layer provides modular simulation support services, including storage and access services for various types of simulation data for data use, integrated operation and calling services for all simulation models for simulation operation, and basic computing tools for the operation of the digital satellite system.

[0011] (2) Establish a model layer for the digital satellite system. The model layer provides a componentized simulation model, including satellite digital models at three levels: system level, application level, and engineering level. Under the integrated operation and scheduling of the basic support layer, the model layer realizes the simulation operation calculation of each simulation subsystem and generates simulation test data. Each simulation subsystem includes the satellite system, operation and control system, application system, observation object, and observation environment.

[0012] (3) Establish a service layer for the digital satellite system. Based on the basic support layer and the model layer, the service layer forms a command and control interface that interacts with the command and dispatch system, a telemetry and control data transmission plan interface that interacts with the operation and control system, and a telemetry and control command interface that interacts with the telemetry and control system by calling various service interfaces and model interfaces.

[0013] (4) Based on the remote sensing satellite mission constraint verification process, complete the system integration of the basic support layer, model layer and service layer to obtain a digital satellite system that can form a sequence of telemetry, data transmission and observation mission instructions that meet the constraints of remote sensing satellite space-ground resource window and on-orbit operation constraints.

[0014] Preferably, all simulation models are developed and assembled using standardized model component interfaces, compiled and packaged into cross-platform dynamic link libraries, thereby achieving modularization, standardization and componentization of simulation models.

[0015] Preferably, the system-level satellite digital model includes a remote sensing satellite model, an observation target model, an observation environment model, a space-based information link resource model, a ground telemetry and control resource model, and a ground data transmission resource model;

[0016] Among them, the remote sensing satellite model is responsible for extrapolating and predicting the orbit information of the simulated satellite; the observation target model is responsible for defining the geometric dimensions, trajectory, geographical latitude and longitude, and observation priority of the target to be observed in the application scenario; the observation environment model is responsible for defining the sea state and cloud cover conditions of the observation area in the application scenario; the space-based information link resource model is responsible for extrapolating and predicting the orbit information of the relay telemetry and control satellite and calculating the relay arc; the ground telemetry and control resource model is responsible for setting the geographical latitude and longitude of the ground telemetry and control station and calculating the telemetry and control arc; and the ground data transmission resource model is responsible for setting the geographical latitude and longitude of the ground data transmission station and calculating the data transmission arc.

[0017] Preferably, the application-level satellite digital model includes an observation time window constraint model, an attitude maneuver constraint model, a data transmission capability constraint model, a telemetry and control capability constraint model, a data balance constraint model, an energy balance constraint model, and a sunlight avoidance constraint model.

[0018] The model comprises several key components: an observation time window constraint model, an attitude maneuver constraint model, and a telemetry and tracking capability constraint model. The observation time window constraint model defines the constraints on the remote sensing satellite's maximum payload imaging observation duration and the overlap of observation periods, and checks whether the observation time windows of each simulation mission meet the requirements. The attitude maneuver constraint model defines the constraints on the remote sensing satellite's maximum angular velocity and angular acceleration, and checks whether the attitude maneuver sequences of each simulation mission meet the requirements. The data transmission capability constraint model defines the data transmission channel rate settings and the maximum envelope range of the data transmission antenna beam, and checks whether the satellite-to-ground data transmission windows of each simulation mission meet the requirements. The telemetry, tracking, and command capability constraint model defines the telemetry, tracking, and command channel rate settings of the remote sensing satellite. The system is responsible for defining the maximum envelope range of the telemetry and control antenna beam and checking whether the ground-based telemetry and control window specified in each simulation mission meets the requirements; the data balance constraint model is responsible for defining the maximum storage capacity of onboard data of the remote sensing satellite and checking whether the observation data of each simulation mission can be completely stored and transmitted; the energy balance constraint model is responsible for defining the maximum discharge depth of the remote sensing satellite and checking whether the power generation and consumption of each simulation mission meet the energy balance requirements; and the sunlight avoidance constraint model is responsible for defining the constraints of the remote sensing satellite on the sunlight irradiating the satellite surface and checking whether the solar vector azimuth from the sunlight to the satellite in each simulation mission meets the requirements.

[0019] Preferably, the engineering-grade satellite digital model includes a ground mission planning model, an on-board mission management model, an attitude control model, an energy model, a telemetry and control model, an imaging payload model, a data storage model, and a data transmission model;

[0020] The system comprises several components: a ground mission planning model (GRM) and an onboard mission management model. The GRM receives observation mission requests from users and generates macro instruction sequences according to the remote sensing satellite's operating mode. The onboard mission management model defines the processes, events, logic, and relationships of remote sensing satellite imaging, data transmission, and telemetry / control missions. It processes the macro instruction sequences generated by the GRM, confirms the format validity and conflict resolution of the instructions, and then sequentially calls the attitude control model, imaging payload model, energy model, telemetry / control model, data storage model, and data transmission model according to the instruction content. The attitude control model, under the call of the onboard mission management model, outputs the attitude angles, angular velocities, and angular acceleration sequences for each simulation mission in the roll, pitch, and yaw directions, and provides the angle sequences of the solar vector with respect to the satellite's roll, pitch, and yaw mechanical coordinate axes. The imaging payload model, under the call of the onboard mission management model, calculates the imaging window and the amount of observation data generated for the imaging mission. The energy model, under the call of the mission management model, calculates the energy output based on the required parameters. The attitude control model's simulation results are used to calculate the effective illumination area of ​​the satellite's solar array and output simulated power generation, as well as simulated power consumption based on the rated power consumption of the satellite equipment under different operating modes. The telemetry, tracking, and command (TT&C) model, under the call of the onboard mission management model, calculates the upload time for TT&C tasks and the theoretical available window of the satellite relative to ground TT&C stations and relay TT&C satellites, based on the simulation results of the attitude control model, the TT&C channel rate setting of the remote sensing satellite, and the maximum envelope range of the TT&C antenna beam. The data storage model, under the call of the onboard mission management model, records or erases the observation data volume of each imaging simulation task output by the imaging payload model and transmits the corresponding task's data volume to the data transmission model as needed. The data transmission model, under the call of the onboard mission management model, calculates the data download time for data transmission tasks and the theoretical available window of the satellite relative to ground data transmission stations, based on the data transmission channel rate setting, the maximum envelope range of the data transmission antenna beam, and the output results of the attitude control model and the data storage model.

[0021] Preferably, the command and control interface is responsible for accepting the user's telemetry, telemetry, data transmission and observation mission requirements, serving as input for the system-level and engineering-level satellite digital models, and feeding back the mission simulation operation results. The mission simulation operation results include the satellite's theoretical on-orbit operation status for each mission sequence, constraint conflict status, macro instruction sequences to be confirmed and uploaded after conflict resolution, and mission content.

[0022] Preferably, the telemetry, tracking, and command (TT&C) data transmission planning interface is responsible for receiving available windows from ground data transmission stations designated by the operation and control system and from ground TT&C stations, serving as input to the data transmission capability constraint model and TT&C capability constraint model in the application-level satellite digital model during mission simulation.

[0023] Preferably, the measurement and control command interface is responsible for transmitting the macro command sequence to be uploaded to the measurement and control system.

[0024] Preferably, the digital satellite system mission constraint verification process includes seven stages: application scenario input, ground mission planning, satellite working mode strategy modeling, mission operation status simulation, mission constraint checking, mission constraint conflict resolution, and mission instruction generation and verification. The specific implementation is as follows:

[0025] (4.1) Application scenario input stage: Based on the mission of the remote sensing satellite, design typical application scenarios. Through the command and control interface and telemetry and data transmission plan interface of the digital satellite system service layer, call the system-level satellite digital model to construct the scenario scenario elements, including the start and end time of the simulation scenario, the target object to be observed, the environment to be observed, and the space-based relay satellite and ground telemetry and data transmission station resources to be used.

[0026] (4.2) The ground mission planning stage calls the ground mission planning model in the engineering-level satellite digital model through the command and control interface of the digital satellite system service layer, receives a series of telemetry, telemetry, data transmission and observation mission requirements from users, and obtains the preliminary macro instruction sequence based on the satellite orbit, target position, target priority and observation environment conditions defined in the system-level satellite digital model.

[0027] (4.3) In the satellite working mode strategy modeling stage, the on-board mission management model of the engineering-grade satellite digital model is used to process the macro instruction sequence formed in step (4.2). After checking the legality of the macro instruction format and the conflict resolution, the timing and content of calling the engineering-grade satellite digital model are formed according to the observation area, imaging mode, scanning path, and mission timing strategy under different working modes of remote sensing satellites. This is then handed over to the mission operation status simulation stage in step (4.4) for processing.

[0028] (4.4) The mission operation status simulation stage calls the engineering-grade satellite digital model according to the calling sequence and content formed in step (4.3) to obtain the attitude maneuver sequence, solar vector sequence, imaging window, imaging data generation, power generation, power consumption, time for uploading telemetry and control commands, time for imaging data transmission, and actual available telemetry and control and data transmission windows within the simulation time of each telemetry, control, data transmission and observation mission. These are then handed over to the mission constraint check stage in step (4.5) for processing.

[0029] (4.5) The task constraint check step is based on the application-level satellite digital model. The simulation results of the task operation status obtained in step (4.4) are checked for remote sensing satellite on-orbit constraints. The macro instruction sequence of the preliminary plan obtained in step (4.2) is judged in turn to determine whether it meets the constraints of the observation time window, attitude maneuvering, data transmission capability, telemetry and control capability, data balance, energy balance and sunlight avoidance for satellite on-orbit use. If there are cases where the constraints are not met, the task constraint conflict resolution step (4.6) is entered to adjust the task. Otherwise, the task constraint conflict resolution step (4.7) is entered.

[0030] (4.6) In the task constraint conflict resolution stage, in response to the constraint conflicts that occur in the observation, data transmission, and telemetry and control tasks, and taking into account the satellite on-orbit constraints, ground telemetry and control data transmission constraints, logical matching between different tasks and timing conflicts, a new macro instruction sequence is formed by adjusting the multi-task time window and task parameters, and then returning to step (4.3).

[0031] (4.7) In the task instruction generation and verification process, the on-board task management model of the engineering-grade satellite digital model is called to process the macro instruction sequence that has passed the task constraint verification, check the format legality of the instruction sequence, and feed the macro instruction sequence and task content back to the command and dispatch system for confirmation through the command and control interface of the service layer. After confirmation by the command and dispatch system, the macro instruction sequence is transmitted to the telemetry and control system through the telemetry and control instruction interface of the digital satellite system service layer.

[0032] Preferably, the implementation process of the remote sensing satellite on-orbit constraint check described in step (4.5) specifically includes:

[0033] 1) Determine whether the payload imaging period meets the observation time window constraint. If yes, proceed to step 2); otherwise, the constraint condition is not met.

[0034] 2) Determine whether the satellite attitude meets the sunlight avoidance constraint. If yes, proceed to step 3); otherwise, the constraint is not met.

[0035] 3) Determine whether the attitude maneuver path satisfies the attitude maneuver constraints. If yes, proceed to step 4); otherwise, the constraints are not satisfied.

[0036] 4) Determine whether the satellite's power generation and consumption meet the energy balance constraints. If yes, proceed to step 5); otherwise, the constraints are not met.

[0037] 5) Determine whether the data storage and data erasure status of the satellite solid storage meet the data balance constraints. If yes, proceed to step 6); otherwise, the constraints are not met.

[0038] 6) Determine whether the data transmission time and data transmission window of the data transmission task meet the data transmission capacity constraints. If yes, proceed to step 7); otherwise, the constraints are not met.

[0039] 7) Determine whether the transmission time and transmission window of the measurement and control command of the measurement and control task meet the measurement and control capability constraints. If yes, proceed to step 8); otherwise, the constraints are not met.

[0040] The advantages of this invention compared to the prior art are:

[0041] This invention proposes a digital satellite system modeling method for remote sensing satellite mission constraint verification. This method is designed for remote sensing satellite mission constraint verification, and simultaneously considers space-ground resource window constraints such as telemetry, telemetry and control (TT&C), data transmission arcs, energy balance, data balance, and sunlight avoidance, as well as satellite on-orbit constraints. It comprehensively designs the interface interaction mode between the TT&C, operations control, and command and dispatch systems in the remote sensing satellite space-ground control system and the digital satellite system. It supports the reasonable guidance of the command and dispatch system to adjust the mission sequence arrangement based on multiple on-orbit constraints of the remote sensing satellite, and obtains mission sequences and uplink command codewords that simultaneously meet the observation requirements of the command and dispatch system, the TT&C system's TT&C arc resources, the operations control system's data transmission arc resources, and the satellite's own observation and transmission capabilities. It can cover the entire ground control process, including the remote sensing satellite command and dispatch system issuing mission requirements, the operations control system completing mission sequence compilation, and the TT&C system preparing uplink mission commands. Attached Figure Description

[0042] Figure 1 This invention relates to the architecture of a remote sensing satellite digital satellite system.

[0043] Figure 2 This invention comprises the architecture-level, application-level, and engineering-level satellite digital models of the remote sensing satellite digital satellite system.

[0044] Figure 3 This is the implementation process for mission constraint verification of the digital satellite system according to the present invention. Detailed Implementation

[0045] The invention will now be further described with reference to the accompanying drawings.

[0046] To meet the high-efficiency control requirements of satellite users for in-orbit remote sensing satellites, more refined dynamic simulation methods can be used to verify the mission constraints of remote sensing satellite uploading tasks. Based on the satellite's main functions, digital models at the system, application, and engineering levels are developed to build a remote sensing satellite digital system. This involves modeling the satellite's basic functions, all operating modes, main technical indicators, key subsystem functions, and usage constraints. This allows for a full-process simulation from the satellite receiving the sequence of tasks to be uploaded from the ground to the satellite completing the task and transmitting the data. The simulation also provides the mission constraint verification results and theoretical execution status of the current task sequence to be executed.

[0047] This invention proposes a digital satellite system modeling method for constraint verification of remote sensing satellite missions. The overall implementation steps are as follows:

[0048] (1) Establish the basic support layer of the remote sensing satellite digital satellite system. The basic support layer provides modular simulation support services, including storage and access services for various types of simulation data for data use, integrated operation and calling services for all simulation models for simulation operation, and basic computing tools for the operation of the digital satellite system.

[0049] (2) Establishing a model layer for the remote sensing satellite digital satellite system. The model layer provides component-based simulation model services, constructing satellite digital models at three levels: system-level, application-level, and engineering-level. Under the integrated operation and scheduling of the basic support layer, it realizes the simulation operation and calculation of simulation subsystems such as satellite system, operation and control system, application system, observation object, and observation environment, generating simulation test data. All simulation models are developed and assembled using standardized model component interface specifications, compiled and packaged into cross-platform dynamic link libraries, realizing the modularization, standardization, and componentization of simulation models.

[0050] (2.1) The system-level satellite digital model mainly constructs a remote sensing satellite model and a space-based Earth observation simulation environment consisting of the observation target, observation environment, space-based information link resources, ground telemetry and control resources, and ground data transmission resources. It mainly includes the remote sensing satellite model, observation target model, observation environment model, space-based information link resource model, ground telemetry and control resource model, and ground data transmission resource model. Specifically, the remote sensing satellite model is responsible for extrapolating and predicting the orbital information of the simulated satellite; the observation target model is responsible for defining the geometric dimensions, trajectory, geographical latitude and longitude, and observation priority of the target under the application scenario; the observation environment model is responsible for defining the sea state and cloud cover conditions of the observation area under the application scenario; the space-based information link resource model is responsible for extrapolating and predicting the orbital information of the relay telemetry and control satellite and calculating the relay arc; the ground telemetry and control resource model is responsible for setting the geographical latitude and longitude of the ground telemetry and control station and calculating the telemetry and control arc; and the ground data transmission resource model is responsible for setting the geographical latitude and longitude of the ground data transmission station and calculating the data transmission arc.

[0051] (2.2) The application-level satellite digital model mainly performs refined and dynamic simulation modeling of the on-orbit capability constraints of remote sensing satellites during imaging, telemetry, tracking, and data transmission missions. This includes observation time window constraint models, attitude maneuver constraint models, data transmission capability constraint models, telemetry and tracking capability constraint models, data balance constraint models, energy balance constraint models, and sunlight avoidance constraint models. Specifically, the observation time window constraint model defines the constraints on the remote sensing satellite's maximum payload imaging observation duration and the overlap of observation periods, and checks whether the observation time windows of each simulation mission meet the requirements; the attitude maneuver constraint model defines the constraints on the remote sensing satellite's maximum angular velocity and angular acceleration, and checks whether the attitude maneuver sequences of each simulation mission meet the requirements; the data transmission capability constraint model defines the data transmission channel rate settings and the maximum envelope range of the data transmission antenna beam, and checks whether the satellite-to-ground data transmission windows of each simulation mission meet the requirements; the telemetry and tracking capability constraint model defines the telemetry and tracking channel rate settings of the remote sensing satellite. The system is responsible for defining the maximum envelope range of the telemetry and control antenna beam and checking whether the ground-based telemetry and control window specified in each simulation mission meets the requirements; the data balance constraint model is responsible for defining the maximum storage capacity of onboard data of the remote sensing satellite and checking whether the observation data of each simulation mission can be completely stored and transmitted; the energy balance constraint model is responsible for defining the maximum discharge depth of the remote sensing satellite and checking whether the power generation and consumption of each simulation mission meet the energy balance requirements; and the sunlight avoidance constraint model is responsible for defining the constraints of the remote sensing satellite on the sunlight irradiating the satellite surface and checking whether the solar vector azimuth from the sunlight to the satellite in each simulation mission meets the requirements.

[0052] (2.3) Engineering-grade satellite digital models mainly involve high-precision simulation modeling of the performance and key technical indicators of various subsystems of remote sensing satellites. These models primarily include ground mission planning models, onboard mission management models, attitude control models, energy models, telemetry and control models, data transmission models, and imaging payload models, covering the functions and performance of each major satellite subsystem. The system comprises several modules: a ground mission planning model (receiving observation mission requests from users and generating macro instruction sequences according to the remote sensing satellite's operating mode), an on-board mission management model (defining the processes, events, logic, and relationships of different types of missions such as remote sensing satellite imaging, data transmission, and telemetry and control), a data storage model (processing macro instruction sequences generated by the ground mission planning model, verifying the format validity and conflict resolution of the instructions, and then sequentially calling the attitude control model, imaging payload model, energy model, telemetry and control model, data storage model, and data transmission model according to the instruction content), an attitude control model (outputting attitude angles, angular velocities, and angular acceleration sequences in the roll, pitch, and yaw directions for each simulation mission under the call of the on-board mission management model, and providing the angle sequences of the solar vector with respect to the mechanical coordinate axes in the roll, pitch, and yaw directions), an imaging payload model (calculating the imaging window and total data output for the imaging mission under the call of the on-board mission management model), and an energy model (calculating the energy output for the mission management model under the call of the mission management model). Based on the simulation results of the attitude control model, the simulated power generation is output by calculating the effective illumination area of ​​the satellite's solar array, and the simulated power consumption is output according to the rated power consumption of the satellite equipment in different operating modes. The telemetry, tracking, and command (TT&C) model, under the call of the on-board mission management model, is responsible for calculating the upload time of the TT&C mission and the theoretical available window of the satellite with respect to the ground TT&C station and relay TT&C satellite, based on the simulation results of the attitude control model, the TT&C channel rate setting of the remote sensing satellite, and the maximum envelope range of the TT&C antenna beam. The data storage model, under the call of the on-board mission management model, is responsible for recording or erasing the observation data volume of each imaging simulation mission output by the imaging payload model, and transferring the corresponding data volume of the mission to the data transmission model as needed. The data transmission model, under the call of the on-board mission management model, is responsible for calculating the data download time of the data transmission mission and the theoretical available window of the satellite with respect to the ground data transmission station, based on the data transmission channel rate setting, the maximum envelope range of the data transmission antenna beam, and the output results of the attitude control model and the data storage model.

[0053] (3) Establish the service layer of the remote sensing satellite digital satellite system. Based on the basic support layer and the model layer, the service layer faces different external system interfaces such as command and dispatch system, operation and control system and telemetry and control system. By calling various service interfaces and model interfaces, it forms command and control interface, telemetry and control data transmission plan interface and telemetry and control command interface.

[0054] The digital satellite system service layer primarily interacts with command and dispatch systems, operation and control systems, and telemetry and control systems through control and data interfaces. The specific implementation is as follows:

[0055] (3.1) For the command and dispatch system, the digital satellite system service layer sets up a command and control interface, which is responsible for accepting the user's telemetry, data transmission and observation mission requirements, serving as the input for the system-level and engineering-level satellite digital models, and feeding back the mission simulation operation results, including the satellite's on-orbit theoretical operation status, constraint conflict situation, macro instruction sequence to be confirmed and uploaded after conflict resolution, and mission content for each mission sequence.

[0056] (3.2) For the operation and control system, the digital satellite system service layer sets up a telemetry and control data transmission plan interface, which is responsible for receiving the available windows of the ground data transmission stations designated by the operation and control system and the ground telemetry and control stations, and serves as the input of the data transmission capability constraint model and the telemetry and control capability constraint model during the mission simulation process;

[0057] (3.3) For the telemetry, tracking and control system, the digital satellite system service layer sets up a telemetry and control command interface, which is responsible for transmitting the macro command sequence to be uploaded to the telemetry and control system.

[0058] (4) Based on the remote sensing satellite mission constraint verification process, the system integration of the basic support layer, model layer and service layer is completed. After application scenario input, ground mission planning, satellite working mode strategy modeling, mission operation status simulation, mission constraint checking, mission constraint conflict resolution, mission command generation and verification, the sequence of telemetry, data transmission and observation mission commands that meet the space-ground resource window constraints and on-orbit operation constraints of remote sensing satellites is finally obtained.

[0059] The digital satellite system mission constraint verification process includes seven stages: application scenario input, ground mission planning, satellite operating mode strategy modeling, mission operation status simulation, mission constraint checking, mission constraint conflict resolution, and mission instruction generation and verification. For example... Figure 3 As shown, the specific implementation is as follows:

[0060] (4.1) The application scenario input stage receives the simulation task requirements provided by the command and control interface and the telemetry and data transmission plan interface of the digital satellite system service layer, and the available data transmission and telemetry and control resources and windows provided by the operation and control system based on the constraints of data transmission and telemetry and control resources. Based on this, the system-level satellite digital model is called to construct the scenario scenario elements such as the start and end time of the simulation scenario, the target object to be observed, the environment to be observed, and the space-based relay satellite and ground telemetry and data transmission station resources to be used. (4.2) The ground mission planning stage calls the ground mission planning model through the command and control interface of the digital satellite system service layer, receives a series of telemetry, data transmission and observation task requirements input by the user, and obtains the preliminary macro instruction sequence based on the satellite orbit, target position, target priority and observation environment conditions defined in the system-level satellite digital model.

[0061] (4.3) In the satellite working mode strategy modeling stage, the on-board mission management model of the digital satellite system is used to process the macro instruction sequence formed in step (4.2). After checking the legality of the macro instruction format and the conflict resolution, the timing and content of calling the engineering-level satellite digital model are formed according to the usage strategy of observation area, imaging mode, scanning path, mission timing, etc. in different working modes of remote sensing satellites. This is then handed over to the mission operation status simulation stage in step (4.4) for processing.

[0062] (4.4) The mission operation status simulation stage calls the engineering-grade satellite digital model according to the calling sequence and content formed in step (4.3) to obtain the attitude maneuver sequence, solar vector sequence, imaging window, imaging data generation, power generation, power consumption, time for uploading telemetry and control commands, time for imaging data transmission, and actual available telemetry and control and data transmission windows within the simulation time of each telemetry, control, data transmission and observation mission. These are then handed over to the mission constraint check stage in step (4.5) for processing.

[0063] (4.5) The task constraint check step is based on the application-level satellite digital model of the digital satellite system. The simulation results of the task operation status obtained in step (4.4) are checked for remote sensing satellite on-orbit constraints. It is determined in turn whether the planning results obtained in step (4.2) meet the constraints of the observation time window, attitude maneuvering, data transmission capability, telemetry and control capability, data balance, energy balance, and sunlight avoidance for satellite on-orbit use. If there are any cases where the constraints are not met, the task constraint conflict resolution step (4.6) is entered to adjust the task. Otherwise, the current task planning status is handed over to the task instruction generation and verification step (4.7).

[0064] (4.6) Task constraint conflict resolution step: Based on the task constraint check results in step (4.5), for the constraint conflicts that occur in tasks such as observation, data transmission, and telemetry and control, and taking into account the satellite on-orbit constraints, ground telemetry and control data transmission constraints, logical matching and timing conflicts between different tasks, a new macro instruction sequence is formed through processing methods such as multi-task time window adjustment and task parameter adjustment, and then returned to step (4.3) for reprocessing;

[0065] (4.7) The mission instruction generation and verification process calls the on-board mission management model to process the macro instruction sequence that has passed the mission constraint verification, checks the format legality of the instruction sequence, and feeds back the macro instruction sequence and mission content to the command and dispatch system for confirmation through the command and control interface of the digital satellite system service layer. After confirmation by the command and dispatch system, the macro instruction sequence is transmitted to the telemetry and control system through the telemetry and control instruction interface of the digital satellite system service layer.

[0066] The task constraint check described in step (4.5) specifically includes the following implementation process:

[0067] 1) Determine whether the payload imaging period meets the observation time window constraint in the satellite simulation on-orbit operation performance. If so, continue to judge the sunlight avoidance constraint. Otherwise, end the task constraint check and enter the specific step (4.6). The task that has problems with excessively long observation time and overlapping windows will resolve the conflict.

[0068] 2) Determine whether the satellite attitude conforms to the sunlight avoidance constraint in the simulated on-orbit operation. If so, continue to judge the attitude maneuver constraint. Otherwise, end the task constraint check and proceed to the specific step (4.6) to resolve the conflict of the task where the satellite is abnormally positioned due to sunlight.

[0069] 3) Determine whether the attitude maneuver path conforms to the attitude maneuver constraints in the satellite simulation on-orbit operation performance. If yes, continue to judge the energy balance constraints. Otherwise, end the task constraint check and proceed to the specific step (4.6). Resolve the conflict of tasks that cannot complete the specified path maneuver within the specified time.

[0070] 4) Determine whether the satellite's power generation and consumption meet the energy balance constraints in the simulated on-orbit operation. If so, continue to judge the data balance constraints. Otherwise, end the task constraint check and proceed to the specific step (4.6) to start resolving the conflict of the problem of excessive satellite discharge depth.

[0071] 5) Determine whether the satellite's data storage and data erasure in the simulated on-orbit operation meet the data balance constraints. If so, continue to judge the data transmission capability constraints. Otherwise, end the task constraint check and proceed to specific steps (4.6) to resolve the conflict of the task that cannot completely store task data before the start of data transmission.

[0072] 6) Determine whether the data transmission time and data transmission window of the data transmission task meet the data transmission capability constraints in the satellite simulation on-orbit operation performance. If yes, continue to judge the measurement and control capability constraints. Otherwise, end the task constraint check and proceed to specific steps (4.6) to resolve the conflict of the problem task that could not complete the data transmission within the available data transmission window on the ground.

[0073] 7) Determine whether the transmission time and transmission window of the telemetry and control command in the satellite simulation on-orbit operation meet the telemetry and control capability constraints. If so, the current task command sequence is handed over to step (4.7) for processing. Otherwise, the task constraint check ends and the specific step (4.6) is entered to resolve the conflict of the problem task that cannot complete the transmission of telemetry and control commands within the available telemetry and control window on the ground.

[0074] The task conflict resolution process described in step (4.6) is as follows: Prioritize the conflict resolution of observation tasks. By adjusting the observation task window, observation target, target observation order, payload imaging strategy settings, and deleting tasks with lower priority, a new observation task sequence is obtained. This sequence is then processed by the ground task planning model to obtain the data transmission task sequence corresponding to the observation task and the measurement and control task sequence corresponding to the observation and data transmission tasks. Finally, the macro instruction sequence corresponding to the observation, data transmission, and measurement and control task sequences is processed in step (4.3).

[0075] Figure 1 This invention relates to the architecture of a remote sensing satellite digital satellite system. Figure 2 This invention comprises the system-level, application-level, and engineering-level satellite digital models of the remote sensing satellite digital satellite system.

[0076] This invention presents a digital satellite system modeling method for remote sensing satellite mission constraint verification. It considers both space-ground resource window constraints such as telemetry and control, data transmission arcs, energy balance, data balance, and sunlight avoidance, as well as satellite on-orbit constraints. This method yields task sequences and uplink command codes that simultaneously satisfy the observation requirements of the command and dispatch system, the telemetry and control arc resources of the telemetry and control system, the data transmission arc resources of the operation and control system, and the satellite's own observation and transmission capabilities. It can cover the entire ground control process, including the remote sensing satellite command and dispatch system issuing mission requirements, the operation and control system completing mission sequence compilation, and the telemetry and control system preparing launch mission commands.

[0077] The parts not described in this invention are well-known technologies in the field.

Claims

1. A digital satellite system modeling method for constraint verification of remote sensing satellite missions, characterized in that, include: (1) Establish a basic support layer for the digital satellite system. The basic support layer provides modular simulation support services, including storage and access services for various types of simulation data for data use, integrated operation and calling services for all simulation models for simulation operation, and basic computing tools for the operation of the digital satellite system. (2) Establish a model layer for the digital satellite system. The model layer provides a componentized simulation model, including satellite digital models at three levels: system level, application level, and engineering level. Under the integrated operation and scheduling of the basic support layer, the model layer realizes the simulation operation calculation of each simulation subsystem and generates simulation test data. Each simulation subsystem includes the satellite system, operation and control system, application system, observation object, and observation environment. (3) Establish a service layer for the digital satellite system. Based on the basic support layer and the model layer, the service layer forms a command and control interface that interacts with the command and dispatch system, a telemetry and control data transmission plan interface that interacts with the operation and control system, and a telemetry and control command interface that interacts with the telemetry and control system by calling various service interfaces and model interfaces. (4) Based on the remote sensing satellite mission constraint verification process, complete the system integration of the basic support layer, model layer and service layer to obtain a digital satellite system that can form a sequence of telemetry, data transmission and observation mission instructions that meet the constraints of remote sensing satellite space-ground resource window and on-orbit operation constraints; Application-level satellite digital models include observation time window constraint models, attitude maneuver constraint models, data transmission capability constraint models, telemetry and control capability constraint models, data balance constraint models, energy balance constraint models, and sunlight avoidance constraint models. The model comprises several key components: an observation time window constraint model, an attitude maneuver constraint model, and a telemetry and tracking capability constraint model. The observation time window constraint model defines the constraints on the remote sensing satellite's maximum payload imaging observation duration and the overlap of observation periods, and checks whether the observation time windows of each simulation mission meet the requirements. The attitude maneuver constraint model defines the constraints on the remote sensing satellite's maximum angular velocity and angular acceleration, and checks whether the attitude maneuver sequences of each simulation mission meet the requirements. The data transmission capability constraint model defines the data transmission channel rate settings and the maximum envelope range of the data transmission antenna beam, and checks whether the satellite-to-ground data transmission windows of each simulation mission meet the requirements. The telemetry, tracking, and command capability constraint model defines the telemetry, tracking, and command channel rate settings of the remote sensing satellite. The system is responsible for defining the maximum envelope range of the telemetry and control antenna beam and checking whether the ground-based telemetry and control window specified in each simulation mission meets the requirements; the data balance constraint model is responsible for defining the maximum storage capacity of onboard data of the remote sensing satellite and checking whether the observation data of each simulation mission can be completely stored and transmitted; the energy balance constraint model is responsible for defining the maximum discharge depth of the remote sensing satellite and checking whether the power generation and consumption of each simulation mission meet the energy balance requirements; and the sunlight avoidance constraint model is responsible for defining the constraints of the remote sensing satellite on the sunlight irradiating the satellite surface and checking whether the solar vector azimuth from the sunlight to the satellite in each simulation mission meets the requirements.

2. The digital satellite system modeling method for constraint verification of remote sensing satellite missions according to claim 1, characterized in that, All simulation models are developed and assembled using standardized model component interfaces, compiled and packaged into cross-platform dynamic link libraries, realizing the modularization, standardization and componentization of simulation models.

3. The digital satellite system modeling method for constraint verification of remote sensing satellite missions according to claim 1, characterized in that, The system-level satellite digital model includes remote sensing satellite model, observation target model, observation environment model, space-based information link resource model, ground telemetry and control resource model, and ground data transmission resource model; Among them, the remote sensing satellite model is responsible for extrapolating and predicting the orbit information of the simulated satellite; the observation target model is responsible for defining the geometric dimensions, trajectory, geographical latitude and longitude, and observation priority of the target to be observed in the application scenario; the observation environment model is responsible for defining the sea state and cloud cover conditions of the observation area in the application scenario; the space-based information link resource model is responsible for extrapolating and predicting the orbit information of the relay telemetry and control satellite and calculating the relay arc; the ground telemetry and control resource model is responsible for setting the geographical latitude and longitude of the ground telemetry and control station and calculating the telemetry and control arc; and the ground data transmission resource model is responsible for setting the geographical latitude and longitude of the ground data transmission station and calculating the data transmission arc.

4. The digital satellite system modeling method for constraint verification of remote sensing satellite missions according to claim 1, characterized in that, Engineering-grade satellite digital models include ground mission planning models, on-board mission management models, attitude control models, energy models, telemetry and control models, imaging payload models, data storage models, and data transmission models; The system comprises several components: a ground mission planning model (GRM) and an onboard mission management model. The GRM receives observation mission requests from users and generates macro instruction sequences according to the remote sensing satellite's operating mode. The onboard mission management model defines the processes, events, logic, and relationships of remote sensing satellite imaging, data transmission, and telemetry / control missions. It processes the macro instruction sequences generated by the GRM, confirms the format validity and conflict resolution of the instructions, and then sequentially calls the attitude control model, imaging payload model, energy model, telemetry / control model, data storage model, and data transmission model according to the instruction content. The attitude control model, under the call of the onboard mission management model, outputs the attitude angles, angular velocities, and angular acceleration sequences for each simulation mission in the roll, pitch, and yaw directions, and provides the angle sequences of the solar vector with respect to the satellite's roll, pitch, and yaw mechanical coordinate axes. The imaging payload model, under the call of the onboard mission management model, calculates the imaging window and the amount of observation data generated for the imaging mission. The energy model, under the call of the mission management model, calculates the energy output based on the required parameters. The attitude control model's simulation results are used to calculate the effective illumination area of ​​the satellite's solar array and output simulated power generation, as well as simulated power consumption based on the rated power consumption of the satellite equipment under different operating modes. The telemetry, tracking, and command (TT&C) model, under the call of the onboard mission management model, calculates the upload time for TT&C tasks and the theoretical available window of the satellite relative to ground TT&C stations and relay TT&C satellites, based on the simulation results of the attitude control model, the TT&C channel rate setting of the remote sensing satellite, and the maximum envelope range of the TT&C antenna beam. The data storage model, under the call of the onboard mission management model, records or erases the observation data volume of each imaging simulation task output by the imaging payload model and transmits the corresponding task's data volume to the data transmission model as needed. The data transmission model, under the call of the onboard mission management model, calculates the data download time for data transmission tasks and the theoretical available window of the satellite relative to ground data transmission stations, based on the data transmission channel rate setting, the maximum envelope range of the data transmission antenna beam, and the output results of the attitude control model and the data storage model.

5. The digital satellite system modeling method for constraint verification of remote sensing satellite missions according to claim 1, characterized in that, The command and control interface is responsible for receiving users' telemetry, telemetry, data transmission and observation mission requirements, serving as input for system-level and engineering-level satellite digital models, and feeding back mission simulation results. The mission simulation results include the satellite's theoretical on-orbit operation status for each mission sequence, constraint conflict status, macro instruction sequences to be confirmed and uploaded after conflict resolution, and mission content.

6. The digital satellite system modeling method for constraint verification of remote sensing satellite missions according to claim 1, characterized in that, The telemetry, tracking, and command (TT&C) data transmission planning interface is responsible for receiving data from ground data transmission stations designated by the operations and control system and uploading data from ground TT&C stations. It serves as the input to the data transmission capability constraint model and the TT&C capability constraint model in the application-level satellite digital model during mission simulation.

7. The digital satellite system modeling method for constraint verification of remote sensing satellite missions according to claim 1, characterized in that, The measurement and control command interface is responsible for transmitting the macro command sequence to be uploaded to the measurement and control system.

8. The digital satellite system modeling method for constraint verification of remote sensing satellite missions according to claim 1, characterized in that, The digital satellite system mission constraint verification process includes seven stages: application scenario input, ground mission planning, satellite operating mode strategy modeling, mission operation status simulation, mission constraint checking, mission constraint conflict resolution, and mission instruction generation and verification. The specific implementation is as follows: (4.1) Application scenario input stage: Based on the mission of the remote sensing satellite, design typical application scenarios. Through the command and control interface and telemetry and data transmission plan interface of the digital satellite system service layer, call the system-level satellite digital model to construct the scenario scenario elements, including the start and end time of the simulation scenario, the target object to be observed, the environment to be observed, and the space-based relay satellite and ground telemetry and data transmission station resources to be used. (4.2) The ground mission planning stage calls the ground mission planning model in the engineering-level satellite digital model through the command and control interface of the digital satellite system service layer, receives a series of telemetry, telemetry, data transmission and observation mission requirements from users, and obtains the preliminary macro instruction sequence based on the satellite orbit, target position, target priority and observation environment conditions defined in the system-level satellite digital model. (4.3) In the satellite working mode strategy modeling stage, the on-board mission management model of the engineering-grade satellite digital model is used to process the macro instruction sequence formed in step (4.2). After checking the legality of the macro instruction format and the conflict resolution, the timing and content of calling the engineering-grade satellite digital model are formed according to the observation area, imaging mode, scanning path, and mission timing strategy under different working modes of remote sensing satellites. This is then handed over to the mission operation status simulation stage in step (4.4) for processing. (4.4) The mission operation status simulation stage calls the engineering-grade satellite digital model according to the calling sequence and content formed in step (4.3) to obtain the attitude maneuver sequence, solar vector sequence, imaging window, imaging data generation, power generation, power consumption, time for uploading telemetry and control commands, time for imaging data transmission, and actual available telemetry and control and data transmission windows within the simulation time of each telemetry, control, data transmission and observation mission. These are then handed over to the mission constraint check stage in step (4.5) for processing. (4.5) The task constraint check step is based on the application-level satellite digital model. The simulation results of the task operation status obtained in step (4.4) are checked for remote sensing satellite on-orbit constraints. The macro instruction sequence of the preliminary plan obtained in step (4.2) is judged in turn to determine whether it meets the constraints of the observation time window, attitude maneuvering, data transmission capability, telemetry and control capability, data balance, energy balance and sunlight avoidance for satellite on-orbit use. If there are cases where the constraints are not met, the task constraint conflict resolution step (4.6) is entered to adjust the task. Otherwise, the task constraint conflict resolution step (4.7) is entered. (4.6) In the task constraint conflict resolution stage, in response to the constraint conflicts that occur in the observation, data transmission, and telemetry and control tasks, and taking into account the satellite on-orbit constraints, ground telemetry and control data transmission constraints, logical matching between different tasks and timing conflicts, a new macro instruction sequence is formed by adjusting the multi-task time window and task parameters, and then returning to step (4.3). (4.7) In the task instruction generation and verification process, the on-board task management model of the engineering-grade satellite digital model is called to process the macro instruction sequence that has passed the task constraint verification, check the format legality of the instruction sequence, and feed the macro instruction sequence and task content back to the command and dispatch system for confirmation through the command and control interface of the service layer. After confirmation by the command and dispatch system, the macro instruction sequence is transmitted to the telemetry and control system through the telemetry and control instruction interface of the digital satellite system service layer.

9. A digital satellite system modeling method for constraint verification of remote sensing satellite missions according to claim 8, characterized in that, The implementation process of the remote sensing satellite on-orbit constraint check described in step (4.5) specifically includes: 1) Determine whether the payload imaging period meets the observation time window constraint. If yes, proceed to step 2); otherwise, the constraint condition is not met. 2) Determine whether the satellite attitude meets the sunlight avoidance constraint. If yes, proceed to step 3); otherwise, the constraint is not met. 3) Determine whether the attitude maneuver path satisfies the attitude maneuver constraints. If yes, proceed to step 4); otherwise, the constraints are not satisfied. 4) Determine whether the satellite's power generation and consumption meet the energy balance constraints. If yes, proceed to step 5); otherwise, the constraints are not met. 5) Determine whether the data storage and data erasure status of the satellite solid storage meet the data balance constraints. If yes, proceed to step 6); otherwise, the constraints are not met. 6) Determine whether the data transmission time and data transmission window of the data transmission task meet the data transmission capacity constraints. If yes, proceed to step 7); otherwise, the constraints are not met. 7) Determine whether the transmission time and transmission window of the measurement and control command of the measurement and control task meet the measurement and control capability constraints. If yes, proceed to step 8); otherwise, the constraints are not met.

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