Digital satellite system modeling method for remote sensing satellite task constraint verification

Abstract

The invention relates to a remote sensing satellite task constraint verification-oriented digital satellite system modeling method, which comprises the following steps of: establishing a basic support layer of a digital satellite system, and providing modularized simulation support service; establishing a model layer of the digital satellite system, realizing simulation operation calculation of each simulation subsystem, and generating simulation test data; a service layer of the digital satellite system is established, and the service layer forms a command and 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 invention faces remote sensing satellite task constraint verification, and simultaneously considers satellite-ground resource window constraints such as measurement and control, data transmission segmental arc, energy balance, data balance, sunlight avoidance and the like and satellite in-orbit constraints.

Description

Technical Field

[0001] The invention belongs to the technical field of satellite design, and relates to a digital satellite system modeling method for remote sensing satellite mission constraint verification, which is applicable to the mission constraint verification link before ground-based measurement, control, data transmission and observation missions on on-orbit remote sensing satellites. Background Art

[0002] The digital satellite system is the result of digital modeling and comprehensive integration of major functional domains such as satellite mission planning, attitude control, and data transmission at three different levels and with different granularities: system level, application level, and engineering level. It can achieve fully digital ultra-real-time simulation of the entire device's working mode without the aid of spacecraft hardware equipment, and simulate the theoretical operating status of the satellite in orbit.

[0003] The digital satellite system of a remote sensing satellite needs to include key functional areas such as the satellite's attitude control, integrated electronics, data transmission, and camera imaging. It runs through the entire process of satellite application demand planning, mission planning, command control, earth observation, on-orbit operation management and information processing, data transmission, and ground processing applications. It is a complex information system driven by typical application scenarios of remote sensing satellites and satellite on-orbit usage strategies.

[0004] The on-orbit missions of remote sensing satellites mainly include measurement and control, data transmission and observation tasks. Before the mission is launched, it is necessary to determine whether the observation mission sequence to be launched meets the satellite-ground resource window constraints such as measurement and control, data transmission arc between the satellite and the ground station; confirm whether the execution process of the earth observation mission carried out by the satellite according to the established mode strategy meets the satellite's on-orbit capability constraints such as energy balance, data balance, and sunlight avoidance; estimate the satellite's attitude maneuvering, sunlight exposure, and observation data generation and download during the mission execution.

[0005] In recent years, remote sensing satellite technology has developed rapidly, and satellite working modes have become increasingly complex. The mission constraint verification methods based on the most stringent static constraint parameters and fixed control files that were commonly used in the past have gradually become difficult to match the actual mission constraints of satellites, resulting in frequent situations where the missions of remote sensing satellites to be registered, although meeting constraints such as actual satellite capabilities and satellite-to-ground resource windows, cannot pass the ground mission constraint verification, making it difficult for satellite users to achieve efficient control of in-orbit remote sensing satellites.

[0006] Current research is mainly focused on establishing digital satellite systems for remote sensing satellite observation mission effectiveness simulation and evaluation. There is no digital satellite system modeling method for remote sensing satellite mission constraint verification, which takes into account measurement and control, data transmission arc, energy balance, data balance, sunlight avoidance and other satellite-to-earth resource window constraints and satellite on-orbit constraints. Summary of the invention

[0007] The technical problem solved by the present invention is to overcome the deficiencies of the prior art and propose a digital satellite system modeling method for remote sensing satellite mission constraint verification.

[0008] The solution of the present invention is:

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

[0010] (1) Establishing a basic support layer for the digital satellite system, which provides modular simulation support services, including providing storage and access services for various types of simulation data for data use, providing integrated operation and call services for all simulation models for simulation operation, and providing basic computing tools for the operation of the digital satellite system;

[0011] (2) Establishing a model layer of the digital satellite system, the model layer provides componentized simulation models, including satellite digital models at the system level, application level, and engineering level. Under the integrated operation and scheduling of the basic support layer, the model layer implements simulation operation calculations of each simulation subsystem and generates simulation test data. The simulation subsystems include satellite systems, operation and control systems, application systems, observation objects, and observation environments.

[0012] (3) Establishing 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 for interacting with the command and dispatch system, a measurement and control data transmission plan interface for interacting with the operation and control system, and a measurement and control command interface for interacting with the measurement and control system by calling various service interfaces and model interfaces.

[0013] (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 to obtain a digital satellite system that can form measurement, control, data transmission and observation mission instruction sequences that meet the remote sensing satellite space-ground resource window constraints and on-orbit operation constraints.

[0014] Preferably, all simulation models are developed and assembled using standardized model component interfaces, compiled and packaged into dynamic link libraries that run across platforms, to achieve 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 measurement and control resource model, and a ground data transmission resource model;

[0016] Among them, the remote sensing satellite model is responsible for the extrapolation and prediction of the orbital information of the simulated satellite; the observation target model is responsible for defining the geometric size, motion trajectory, geographical longitude and latitude, and observation priority of the target to be observed in the application scenario; the observation environment model is responsible for defining the sea conditions and cloud cover in the observation area in the application scenario; the space-based information link resource model is responsible for the extrapolation and prediction of the orbital information of the relay tracking and control satellite and the calculation of the relay arc; the ground tracking and control resource model is responsible for the geographical longitude and latitude position binding and tracking and control arc calculation of the ground tracking and control station; the ground data transmission resource model is responsible for the geographical longitude and latitude position binding and data transmission arc calculation of the ground data transmission station.

[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 measurement and control capability constraint model, a data balance constraint model, an energy balance constraint model, and a sunlight avoidance constraint model;

[0018] Among them, the observation time window constraint model is responsible for defining the constraints of the remote sensing satellite for the overlap of the maximum payload imaging observation time and the observation period, and checking whether the observation time windows of previous simulation tasks meet the requirements; the attitude maneuver constraint model is responsible for defining the constraints of the maximum angular velocity and angular acceleration of the remote sensing satellite, and checking whether the attitude maneuver sequences of previous simulation tasks meet the requirements; the data transmission capability constraint model is responsible for defining the data transmission channel rate gear and the maximum envelope range of the data transmission antenna beam of the remote sensing satellite, and checking whether the satellite-to-ground data transmission windows of previous simulation tasks meet the requirements; the measurement and control capability constraint model is responsible for defining the measurement and control channel rate gear of the remote sensing satellite and the maximum envelope range of the measurement and control antenna beam, and is responsible for checking whether the satellite-to-ground measurement and control windows specified on the ground in previous simulation missions meet the requirements; the data balance constraint model is responsible for defining the maximum storage capacity of on-board data of the remote sensing satellite, and is responsible for checking whether the observation data of previous simulation missions 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 is responsible for checking whether the power generation and electricity consumption of previous simulation missions meet the energy balance requirements; the sunlight avoidance constraint model is responsible for defining the constraints of the remote sensing satellite on sunlight shining on the satellite surface, and is responsible for checking whether the solar vector orientation from sunlight to the satellite in previous simulation missions meets the requirements.

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

[0020] Among them, the ground mission planning model is responsible for receiving observation mission requirements from users and generating macro instruction sequences according to the working mode of the remote sensing satellite; the on-board mission management model defines the process, events, logic and correlation of remote sensing satellite imaging, data transmission, measurement and control tasks, and is responsible for processing the macro instruction sequence generated by the ground mission planning model. After confirming the format legality and conflict resolution of the instructions, the attitude control model, imaging payload model, energy model, measurement and control model, data storage model and data transmission model are called in sequence according to the instruction content; the attitude control model is responsible for outputting the attitude angle, angular velocity and angular acceleration sequence of the roll, pitch and yaw directions of previous simulation tasks under the call of the on-board mission management model, and providing the angle sequence of the solar vector about the mechanical coordinate axis of the satellite roll, pitch and yaw directions; the imaging payload model is responsible for calculating the imaging window of the imaging task and generating the amount of observation data under the call of the on-board mission management model; the energy model is responsible for, according to the call of the mission management model, The simulation results of the attitude control model are used to output the simulated power generation by calculating the effective illumination area of ​​the satellite solar wing, and the simulated power consumption is output according to the rated power consumption of the satellite equipment in different working modes; the measurement and control model is responsible for calculating the uplink time of the measurement and control task and the theoretical available window of the satellite with respect to the ground measurement and control station and relay measurement and control satellite according to the simulation results of the attitude control model, the measurement and control channel rate gear of the remote sensing satellite and the maximum envelope range of the measurement and control antenna beam under the call of the on-board task management model; the data storage model is responsible for recording or erasing the amount of observation data of previous imaging simulation tasks output by the imaging payload model under the call of the on-board task management model, and passing the data volume of the corresponding task to the data transmission model as needed; the data transmission model is responsible for calculating the data downlink time of the data transmission task and the theoretical available window of the satellite with respect to the ground data transmission station according to the output results of the data transmission channel rate gear, the maximum envelope range of the data transmission antenna beam and the attitude control model and the data storage model under the call of the on-board task management model.

[0021] Preferably, the command and control interface is responsible for accepting the user's measurement and control, data transmission and observation task requirements as input to the system-level and engineering-level satellite digital models, and feeding back the task simulation operation results, which include the satellite's theoretical on-orbit operation status of previous task sequences, constraint conflict conditions, macro instruction sequences to be confirmed after the conflict is resolved, and task contents.

[0022] Preferably, the measurement and control data transmission planning interface is responsible for accepting the available windows received by the ground data transmission station specified by the operation and control system and noted by the ground measurement and control station, as inputs to the data transmission capability constraint model and the measurement and control capability constraint model in the application-level satellite digital model during the mission simulation process.

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

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

[0025] (4.1) Application scenario input phase: Based on the mission of the remote sensing satellite, a typical application scenario is designed. Through the command and control interface and the measurement, control and transmission planning interface of the digital satellite system service layer, the system-level satellite digital model is called to construct the scenario elements of the simulation scenario start and end time, the target object to be observed, the environment to be observed, and the space-based relay satellite and ground measurement, control and transmission station resources to be used;

[0026] (4.2) The ground mission planning phase 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 measurement and control, data transmission, and observation mission requirements from the user, and obtains a preliminary planned 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) The satellite working mode strategy modeling phase uses the on-board task management model of the engineering-level satellite digital model 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 observation area, imaging mode, scanning path, and task timing usage strategy under different working modes of the remote sensing satellite, and then handed over to the task operation status simulation phase in step (4.4) for processing;

[0028] (4.4) The task operation status simulation link calls the engineering-level satellite digital model according to the call sequence and content formed in step (4.3), obtains the attitude maneuver sequence, solar vector sequence, imaging window, imaging data volume, power generation, power consumption, measurement and control instruction injection time, imaging data transmission time, and actually available measurement and control, and data transmission windows within the simulation time of each measurement and control, data transmission and observation task, and hands it over to the task constraint check link in step (4.5) for processing;

[0029] (4.5) Task constraint check phase Based on the application-level satellite digital model, the task operation status simulation results obtained in step (4.4) are checked for on-orbit constraints of the remote sensing satellite, and the macro instruction sequence initially planned in step (4.2) is judged in turn whether it satisfies the observation time window constraint, attitude maneuver constraint, data transmission capability constraint, measurement and control capability constraint, data balance constraint, energy balance constraint, and sunlight avoidance constraint used by the satellite on orbit; if there is a situation where the constraint conditions are not met, then enter step (4.6) task constraint conflict resolution phase to adjust the task, otherwise enter step (4.7);

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

[0031] (4.7) The task instruction generation and verification phase calls the on-board task management model of the engineering-level satellite digital model to process the macro instruction sequence that has passed the task constraint check, checks the format validity of the instruction sequence, and feeds back the macro instruction sequence and task content 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 measurement and control system through the measurement and control instruction interface of the digital satellite system service layer.

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

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

[0034] 2) Determine whether the satellite attitude satisfies the sunlight avoidance constraint. If so, proceed to step 3), otherwise, the constraint condition is not satisfied;

[0035] 3) Determine whether the attitude maneuver path satisfies the attitude maneuver constraint. If so, proceed to step 4), otherwise, the constraint condition is not satisfied;

[0036] 4) Determine whether the satellite power generation and power consumption meet the energy balance constraint. If so, proceed to step 5), otherwise, the constraint condition is not met;

[0037] 5) Determine whether the data stored in the satellite storage and the data erased meet the data balance constraint. If so, proceed to step 6), otherwise, the constraint condition is not met;

[0038] 6) Determine whether the data transmission time and data transmission window of the data transmission task meet the data transmission capacity constraint, if so, proceed to step 7), otherwise, the constraint condition is 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 so, proceed to step 8), otherwise, the constraints are not met.

[0040] The beneficial effects of the present invention compared with the prior art are:

[0041] The present invention proposes a digital satellite system modeling method for remote sensing satellite mission constraint verification. The method is oriented to remote sensing satellite mission constraint verification, and simultaneously considers satellite-to-ground resource window constraints and satellite on-orbit constraints such as measurement and control, digital transmission arc, energy balance, data balance, and sunlight avoidance. The interface interaction mode between the measurement and control, operation and control, and command and dispatch large systems in the remote sensing satellite satellite-to-ground control system and the digital satellite system is comprehensively designed. The method supports reasonably guiding the command and dispatch system to adjust the task sequence arrangement according to multiple constraints on the remote sensing satellite on-orbit, and obtains task sequences and uplink instruction codewords that simultaneously meet the observation requirements of the command and dispatch system, the measurement and control arc resources of the measurement and control system, the digital transmission arc resources of the operation and control system, and the observation and transmission capabilities of the satellite itself. The method can cover the entire ground control process such as the remote sensing satellite command and dispatch system issuing task requirements, the operation and control system completing task sequence compilation, and the measurement and control system preparing satellite mission instructions. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 The remote sensing satellite digital satellite system architecture of the present invention;

[0043] Figure 2 The remote sensing satellite digital satellite system of the present invention is composed of system-level, application-level and engineering-level satellite digital models;

[0044] Figure 3 The present invention provides a digital satellite system mission constraint verification implementation process. DETAILED DESCRIPTION

[0045] The present invention will be further described below in conjunction with the accompanying drawings.

[0046] In order to meet the satellite users' demand for high-efficiency control of in-orbit remote sensing satellites, the task constraints of remote sensing satellite uploading tasks can be verified through more refined dynamic simulation methods, and satellite system-level, application-level and engineering-level digital models can be built according to the main functions of the satellite. A remote sensing satellite digital satellite system can be built to complete the modeling of the satellite's basic functions, all working modes, main technical indicators, key subsystem functional services and usage constraints, thereby realizing the simulation of the entire process from the satellite receiving the ground uploading task sequence to the satellite completing the task and downloading the data, and giving the task constraint verification results and theoretical execution status of the current task sequence to be executed.

[0047] The present invention proposes a digital satellite system modeling method for remote sensing satellite mission constraint verification, and 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 call services for all simulation models for simulation operation, and basic computing tools for digital satellite system operation.

[0049] (2) Establish the model layer of the remote sensing satellite digital satellite system. The model layer provides componentized simulation model services, constructs satellite digital models at the system level, application level, and engineering level, and realizes the simulation operation calculation of simulation subsystems such as satellite system, operation and control system, application system, observation object, and observation environment under the integrated operation and scheduling of the basic support layer, and generates 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, and realize modularization, standardization, and componentization of simulation models.

[0050] (2.1) The system-level satellite digital model mainly constructs the remote sensing satellite model and the space-based earth observation simulation environment composed of the observation target object, observation environment, space-based information link resources, ground measurement 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 measurement and control resource model, and ground data transmission resource model. Among them, the remote sensing satellite model is responsible for the extrapolation and prediction of the orbital information of the simulated satellite, the observation target model is responsible for defining the geometric size, motion trajectory, geographical longitude and latitude of the target to be observed in the application scenario, and the priority of the observation target, the observation environment model is responsible for defining the sea conditions and cloud cover of the observation area in the application scenario, the space-based information link resource model is responsible for the extrapolation and prediction of the orbital information of the relay measurement and control satellite and the calculation of the relay arc, the ground measurement and control resource model is responsible for the geographical longitude and latitude position binding and measurement and control arc calculation of the ground measurement and control station, and the ground data transmission resource model is responsible for the geographical awe altitude position binding and data transmission arc calculation of the ground data transmission station.

[0051] (2.2) The application-level satellite digital model mainly conducts refined and dynamic simulation modeling of the satellite's on-orbit capability constraints during the remote sensing satellite's imaging, measurement and control, data transmission and other missions. It mainly includes the observation time window constraint model, attitude maneuver constraint model, data transmission capability constraint model, measurement and control capability constraint model, data balance constraint model, energy balance constraint model, and sunlight avoidance constraint model. Among them, the observation time window constraint model is responsible for defining the constraints on the maximum payload imaging observation time and the overlap of the observation period of the remote sensing satellite, and checking whether the observation time window of previous simulation tasks meets the requirements; the attitude maneuver constraint model is responsible for defining the constraints on the maximum angular velocity and angular acceleration of the remote sensing satellite, and checking whether the attitude maneuver sequence of previous simulation tasks meets the requirements; the data transmission capability constraint model is responsible for defining the data transmission channel rate gear and the maximum envelope range of the data transmission antenna beam of the remote sensing satellite, and checking whether the satellite-to-ground data transmission window of previous simulation tasks meets the requirements; the measurement and control capability constraint model is responsible for defining the measurement and control channel rate gear of the remote sensing satellite and the maximum envelope range of the measurement and control antenna beam, and is responsible for checking whether the satellite-to-ground measurement and control windows specified on the ground in previous simulation missions meet the requirements; the data balance constraint model is responsible for defining the maximum storage capacity of on-board data of the remote sensing satellite, and is responsible for checking whether the observation data of previous simulation missions 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 is responsible for checking whether the power generation and electricity consumption of previous simulation missions meet the energy balance requirements; the sunlight avoidance constraint model is responsible for defining the constraints of the remote sensing satellite on sunlight shining on the satellite surface, and is responsible for checking whether the solar vector orientation from sunlight to the satellite in previous simulation missions meets the requirements.

[0052] (2.3) The engineering-level satellite digital model mainly performs high-precision simulation modeling on the performance of each subsystem of the remote sensing satellite and key technical indicators. It mainly includes ground mission planning model, on-board mission management model, attitude control model, energy model, measurement and control model, data transmission model, imaging payload model, etc., covering the functions and performance of each major subsystem of the satellite. Among them, the ground mission planning model is responsible for receiving observation mission requirements from users and generating macro instruction sequences according to the working mode of the remote sensing satellite; the on-board mission management model defines the processes, events, logic and relevance of different types of tasks such as remote sensing satellite imaging, data transmission, measurement and control, and is responsible for processing the macro instruction sequences generated by the ground mission planning model. After confirming the format legality and conflict resolution of the instructions, the attitude control model, imaging payload model, energy model, measurement and control model, data storage model and data transmission model are called in sequence according to the instruction content; the attitude control model is responsible for outputting the attitude angle, angular velocity and angular acceleration sequence of the roll, pitch and yaw directions of all simulation tasks under the call of the on-board mission management model, and providing the angle sequence of the sun vector about the mechanical coordinate axis of the satellite roll, pitch and yaw directions; the imaging payload model is responsible for calculating the imaging window and the total amount of data generated of the imaging task under the call of the on-board mission management model; the energy model is responsible for, under the call of the mission management model, According to the simulation results of the attitude control model, the simulated power generation is output by calculating the effective illumination area of ​​the satellite solar wing, and the simulated power consumption is output according to the rated power consumption of the satellite equipment in different working modes; the measurement and control model is responsible for calculating the uplink time of the measurement and control task and the theoretical available window of the satellite with respect to the ground measurement and control station and relay measurement and control satellite according to the simulation results of the attitude control model, the measurement and control channel rate gear of the remote sensing satellite and the maximum envelope range of the measurement and control antenna beam under the call of the on-board task management model; the data storage model is responsible for recording or erasing the amount of observation data of previous imaging simulation tasks output by the imaging payload model under the call of the on-board task management model, and passing the data amount of the corresponding task to the data transmission model as needed; the data transmission model is responsible for calculating the data downlink time of the data transmission task and the theoretical available window of the satellite with respect to the ground data transmission station according to the data transmission channel rate gear, the maximum envelope range of the data transmission antenna beam and the output results of the attitude control model and the data storage model under the call of the on-board task management 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 is oriented to different external system interfaces such as the command and dispatch system, the operation and control system, and the measurement and control system. By calling various service interfaces and model interfaces, it forms the command and control interface, the measurement and control data transmission plan interface, and the measurement and control instruction interface.

[0054] The digital satellite system service layer mainly has control and data interfaces with the command and dispatch system, operation and control system, and measurement and control system. 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 measurement and control, data transmission and observation task requirements as input to the system-level and engineering-level satellite digital models, and feedbacks the task simulation operation results, including the satellite's theoretical on-orbit operation status of previous task sequences, constraint conflict conditions, macro instruction sequences to be confirmed and annotated after conflict resolution, and task contents;

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

[0057] (3.3) For the measurement and control system, the digital satellite system service layer sets up a measurement and control command interface, which is responsible for transmitting the macro instruction sequence to be injected to the measurement 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 check, mission constraint conflict resolution, mission instruction generation and verification, the measurement, control, data transmission and observation mission instruction sequence that meets the remote sensing satellite's satellite-ground resource window constraints and on-orbit operation constraints is finally obtained.

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

[0060] (4.1) The application scenario input link receives the simulation task requirements provided by the command and dispatch system and the available data transmission and measurement and control resources and windows provided by the operation and control system based on the data transmission and measurement and control resource constraints through the command and control interface and the measurement and control data transmission plan interface of the digital satellite system service layer, and calls the system-level satellite digital model to construct 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 measurement and control data transmission station resources to be used; (4.2) The ground task planning link calls the ground task planning model through the command and control interface of the digital satellite system service layer, receives a series of measurement and control, data transmission, and observation task requirements input by the user, and obtains the preliminary planned 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) The satellite working mode strategy modeling phase uses the on-board task management model of the digital satellite system 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 observation area, imaging mode, scanning path, task timing and other usage strategies under different working modes of the remote sensing satellite, and then handed over to the task operation status simulation phase in step (4.4) for processing;

[0062] (4.4) The task operation status simulation link calls the engineering-level satellite digital model according to the call sequence and content formed in step (4.3), obtains the attitude maneuver sequence, solar vector sequence, imaging window, imaging data volume, power generation, power consumption, measurement and control instruction injection time, imaging data transmission time, and actually available measurement and control, and data transmission windows within the simulation time of each measurement and control, data transmission and observation task, and hands it over to the task constraint check link in step (4.5) for processing;

[0063] (4.5) Task constraint check stage Based on the application-level satellite digital model of the digital satellite system, the task operation status simulation results obtained in step (4.4) are checked for the on-orbit constraints of the remote sensing satellite, and the planning results obtained in step (4.2) are judged in turn whether they meet the observation time window constraints, attitude maneuvering constraints, data transmission capability constraints, measurement and control capability constraints, data balance constraints, energy balance constraints, and sunlight avoidance constraints used by the satellite on orbit. If there is a situation where the constraints are not met, enter step (4.6) task constraint conflict resolution stage to adjust the task, otherwise the current task planning situation will be handed over to step (4.7) task instruction generation and verification stage;

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

[0065] (4.7) The task instruction generation and verification link calls the on-board task management model to process the macro instruction sequence that has passed the task constraint check, checks the format validity of the instruction sequence, and feeds back the macro instruction sequence and task 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 measurement and control system through the measurement and control instruction interface of the digital satellite system service layer.

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

[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 perform the sunlight avoidance constraint judgment. Otherwise, end the task constraint check and enter the specific step (4.6) to resolve the conflict of the task with too long observation time and window overlap conflict.

[0068] 2) Determine whether the satellite attitude meets the sunlight avoidance constraint in the satellite simulation on-orbit operation performance. If so, continue to perform attitude maneuver constraint judgment. Otherwise, end the task constraint check and enter the specific step (4.6) to start conflict resolution for tasks where the satellite position is abnormal under sunlight.

[0069] 3) Determine whether the attitude maneuver path meets the attitude maneuver constraint in the satellite simulation on-orbit performance. If so, continue to judge the energy balance constraint. Otherwise, end the task constraint check and enter the specific step (4.6). At the beginning, there is a task that cannot complete the specified path maneuver within the specified time to resolve the conflict;

[0070] 4) Determine whether the satellite power generation and power consumption meet the energy balance constraint in the satellite simulation on-orbit operation performance. If so, continue to perform data balance constraint judgment. Otherwise, end the task constraint check and enter the specific step (4.6) to start conflict resolution for the problem of excessive satellite discharge depth;

[0071] 5) Determine whether the satellite's stored data and erased data meet the data balance constraint during the satellite simulation on-orbit operation. If so, continue to determine the data transmission capability constraint. Otherwise, end the task constraint check and proceed to the specific step (4.6). Start by resolving conflicts with the problem task that cannot fully store the task data before data transmission begins.

[0072] 6) Determine whether the data transmission time and data transmission window of the data transmission task meet the data transmission capability constraint in the satellite simulation on-orbit operation performance. If so, continue to perform the measurement and control capability constraint judgment. Otherwise, end the task constraint check and enter the specific step (4.6), starting with conflict resolution for the problem task that cannot complete data transmission within the available data transmission window on the ground;

[0073] 7) Determine whether the transmission time and transmission window of the TT&C command of the TT&C task in the satellite simulation on-orbit performance meet the TT&C capability constraints. If so, the current task instruction sequence is processed by step (4.7). Otherwise, the task constraint check is terminated and the specific step (4.6) is entered to resolve conflicts with the problem tasks that cannot complete the transmission of TT&C commands within the available TT&C window on the ground.

[0074] The implementation process of the task conflict resolution described in step (4.6) is as follows: give priority to conflict resolution of observation tasks, obtain a new observation task sequence by adjusting the observation task window, observation target object, target observation order, payload imaging strategy setting, deleting low-priority tasks, etc., and submit it to the ground task planning model for processing, 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, and finally submit the macro instruction sequence corresponding to the observation, data transmission, and measurement and control task sequence to step (4.3) for processing.

[0075] Figure 1 This is the remote sensing satellite digital satellite system architecture of the present invention. Figure 2 The remote sensing satellite digital satellite system of the present invention is composed of system-level, application-level and engineering-level satellite digitization models.

[0076] The digital satellite system modeling method for remote sensing satellite mission constraint verification of the present invention is oriented to remote sensing satellite mission constraint verification, and simultaneously considers satellite-ground resource window constraints and satellite on-orbit constraints such as measurement and control, digital transmission arc, energy balance, data balance, and sunlight avoidance, and obtains task sequences and uplink instruction codewords that simultaneously meet the observation requirements of the command and dispatch system, the measurement and control arc resources of the measurement and control system, the digital transmission arc resources of the operation and control system, and the observation and transmission capabilities of the satellite itself, and can cover the entire ground control process such as the remote sensing satellite command and dispatch system issuing task requirements, the operation and control system completing task sequence compilation, and the measurement and control system preparing satellite mission instructions.

[0077] Some of the techniques not described in the present invention belong to the known techniques in the art.

Claims

1. A digital satellite system modeling method for remote sensing satellite mission constraint verification, characterized in that: include: (1) Establishing a basic support layer for the digital satellite system, which provides modular simulation support services, including providing storage and access services for various types of simulation data for data use, providing integrated operation and call services for all simulation models for simulation operation, and providing basic computing tools for the operation of the digital satellite system; (2) Establishing a model layer of the digital satellite system, the model layer provides componentized simulation models, including satellite digital models at the system level, application level, and engineering level. Under the integrated operation and scheduling of the basic support layer, the model layer implements simulation operation calculations of each simulation subsystem and generates simulation test data. The simulation subsystems include satellite systems, operation and control systems, application systems, observation objects, and observation environments. (3) Establishing 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 for interacting with the command and dispatch system, a measurement and control data transmission plan interface for interacting with the operation and control system, and a measurement and control command interface for interacting with the measurement and control system by calling various service interfaces and model interfaces. (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 to obtain a digital satellite system that can form measurement, control, data transmission and observation mission instruction sequences that meet the remote sensing satellite space-ground resource window constraints and on-orbit operation constraints.

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

3. The digital satellite system modeling method for remote sensing satellite mission constraint verification according to claim 1 is 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 measurement and control resource model and ground data transmission resource model; Among them, the remote sensing satellite model is responsible for the extrapolation and prediction of the orbital information of the simulated satellite; the observation target model is responsible for defining the geometric size, motion trajectory, geographical longitude and latitude, and observation priority of the target to be observed in the application scenario; the observation environment model is responsible for defining the sea conditions and cloud cover in the observation area in the application scenario; the space-based information link resource model is responsible for the extrapolation and prediction of the orbital information of the relay tracking and control satellite and the calculation of the relay arc; the ground tracking and control resource model is responsible for the geographical longitude and latitude position binding and tracking and control arc calculation of the ground tracking and control station; the ground data transmission resource model is responsible for the geographical longitude and latitude position binding and data transmission arc calculation of the ground data transmission station.

4. The digital satellite system modeling method for remote sensing satellite mission constraint verification according to claim 1 is characterized in that: The application-level satellite digital model includes observation time window constraint model, attitude maneuver constraint model, data transmission capability constraint model, measurement and control capability constraint model, data balance constraint model, energy balance constraint model, and sunlight avoidance constraint model; Among them, the observation time window constraint model is responsible for defining the constraints of the remote sensing satellite for the overlap of the maximum payload imaging observation time and the observation period, and checking whether the observation time windows of previous simulation tasks meet the requirements; the attitude maneuver constraint model is responsible for defining the constraints of the maximum angular velocity and angular acceleration of the remote sensing satellite, and checking whether the attitude maneuver sequences of previous simulation tasks meet the requirements; the data transmission capability constraint model is responsible for defining the data transmission channel rate gear and the maximum envelope range of the data transmission antenna beam of the remote sensing satellite, and checking whether the satellite-to-ground data transmission windows of previous simulation tasks meet the requirements; the measurement and control capability constraint model is responsible for defining the measurement and control channel rate gear of the remote sensing satellite and the maximum envelope range of the measurement and control antenna beam, and is responsible for checking whether the satellite-to-ground measurement and control windows specified on the ground in previous simulation missions meet the requirements; the data balance constraint model is responsible for defining the maximum storage capacity of on-board data of the remote sensing satellite, and is responsible for checking whether the observation data of previous simulation missions 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 is responsible for checking whether the power generation and electricity consumption of previous simulation missions meet the energy balance requirements; the sunlight avoidance constraint model is responsible for defining the constraints of the remote sensing satellite on sunlight shining on the satellite surface, and is responsible for checking whether the solar vector orientation from sunlight to the satellite in previous simulation missions meets the requirements.

5. The digital satellite system modeling method for remote sensing satellite mission constraint verification according to claim 1 is characterized in that: The engineering-level satellite digital model includes ground mission planning model, onboard mission management model, attitude control model, energy model, measurement and control model, imaging payload model, data storage model and data transmission model; Among them, the ground mission planning model is responsible for receiving observation mission requirements from users and generating macro instruction sequences according to the working mode of the remote sensing satellite; the on-board mission management model defines the process, events, logic and correlation of remote sensing satellite imaging, data transmission, measurement and control tasks, and is responsible for processing the macro instruction sequence generated by the ground mission planning model. After confirming the format legality and conflict resolution of the instructions, the attitude control model, imaging payload model, energy model, measurement and control model, data storage model and data transmission model are called in sequence according to the instruction content; the attitude control model is responsible for outputting the attitude angle, angular velocity and angular acceleration sequence of the roll, pitch and yaw directions of previous simulation tasks under the call of the on-board mission management model, and providing the angle sequence of the solar vector about the mechanical coordinate axis of the satellite roll, pitch and yaw directions; the imaging payload model is responsible for calculating the imaging window of the imaging task and generating the amount of observation data under the call of the on-board mission management model; the energy model is responsible for, according to the call of the mission management model, The simulation results of the attitude control model are used to output the simulated power generation by calculating the effective illumination area of ​​the satellite solar wing, and the simulated power consumption is output according to the rated power consumption of the satellite equipment in different working modes; the measurement and control model is responsible for calculating the uplink time of the measurement and control task and the theoretical available window of the satellite with respect to the ground measurement and control station and relay measurement and control satellite according to the simulation results of the attitude control model, the measurement and control channel rate gear of the remote sensing satellite and the maximum envelope range of the measurement and control antenna beam under the call of the on-board task management model; the data storage model is responsible for recording or erasing the amount of observation data of previous imaging simulation tasks output by the imaging payload model under the call of the on-board task management model, and passing the data volume of the corresponding task to the data transmission model as needed; the data transmission model is responsible for calculating the data downlink time of the data transmission task and the theoretical available window of the satellite with respect to the ground data transmission station according to the output results of the data transmission channel rate gear, the maximum envelope range of the data transmission antenna beam and the attitude control model and the data storage model under the call of the on-board task management model.

6. A digital satellite system modeling method for remote sensing satellite mission constraint verification according to claim 1, characterized in that: The command and control interface is responsible for accepting the user's measurement and control, data transmission and observation mission requirements as input to the system-level and engineering-level satellite digital models, and feeding back the mission simulation operation results, which include the satellite's theoretical on-orbit operation status of previous mission sequences, constraint conflict conditions, macro instruction sequences to be confirmed and mission contents after conflict resolution.

7. The digital satellite system modeling method for remote sensing satellite mission constraint verification according to claim 1 is characterized in that: The measurement and control data transmission planning interface is responsible for accepting the available windows specified by the operation and control system for receiving the ground data transmission station and the ground measurement and control station, as the input of the data transmission capability constraint model and the measurement and control capability constraint model in the application-level satellite digital model during the mission simulation process.

8. The digital satellite system modeling method for remote sensing satellite mission constraint verification according to claim 1 is characterized in that: The measurement and control command interface is responsible for transmitting the macro instruction sequence to be injected to the measurement and control system.

9. The digital satellite system modeling method for remote sensing satellite mission constraint verification according to claim 1, characterized in that: The digital satellite system mission constraint verification process includes seven steps: application scenario input, ground mission planning, satellite working mode strategy modeling, mission operation status simulation, mission constraint check, mission constraint conflict resolution, mission instruction generation and verification. The specific implementation is as follows: (4.1) Application scenario input phase: Based on the mission of the remote sensing satellite, a typical application scenario is designed. Through the command and control interface and the measurement, control and transmission planning interface of the digital satellite system service layer, the system-level satellite digital model is called to construct the scenario elements of the simulation scenario start and end time, the target object to be observed, the environment to be observed, and the space-based relay satellite and ground measurement, control and transmission station resources to be used; (4.2) The ground mission planning phase 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 measurement and control, data transmission, and observation mission requirements from the user, and obtains a preliminary planned 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) The satellite working mode strategy modeling phase uses the on-board task management model of the engineering-level satellite digital model 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 observation area, imaging mode, scanning path, and task timing usage strategy under different working modes of the remote sensing satellite, and then handed over to the task operation status simulation phase in step (4.4) for processing; (4.4) The task operation status simulation link calls the engineering-level satellite digital model according to the call sequence and content formed in step (4.3), obtains the attitude maneuver sequence, solar vector sequence, imaging window, imaging data volume, power generation, power consumption, measurement and control instruction injection time, imaging data transmission time, and actually available measurement and control, and data transmission windows within the simulation time of each measurement and control, data transmission and observation task, and hands it over to the task constraint check link in step (4.5) for processing; (4.5) Task constraint check phase Based on the application-level satellite digital model, the task operation status simulation results obtained in step (4.4) are checked for on-orbit constraints of the remote sensing satellite, and the macro instruction sequence initially planned in step (4.2) is judged in turn whether it satisfies the observation time window constraint, attitude maneuver constraint, data transmission capability constraint, measurement and control capability constraint, data balance constraint, energy balance constraint, and sunlight avoidance constraint used by the satellite on orbit; if there is a situation where the constraint conditions are not met, then enter step (4.6) task constraint conflict resolution phase to adjust the task, otherwise enter step (4.7); (4.6) Task constraint conflict resolution phase: for the constraint conflicts in observation, data transmission, and measurement and control tasks, a new macro instruction sequence is formed by adjusting the multi-task time window and task parameters, taking into account the satellite on-orbit constraints, ground measurement and control data transmission constraints, and the logical matching and timing conflicts between different tasks, and then returning to step (4.3); (4.7) The task instruction generation and verification phase calls the on-board task management model of the engineering-level satellite digital model to process the macro instruction sequence that has passed the task constraint check, checks the format validity of the instruction sequence, and feeds back the macro instruction sequence and task content 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 measurement and control system through the measurement and control instruction interface of the digital satellite system service layer.

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

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