Method, system and device for controlling satellite through multi-party operation

Abstract

The invention provides a method for controlling satellites through multi-party operation, and the method comprises the steps: a main satellite task control system receives a satellite control instruction, collects the telemetering data of a to-be-controlled satellite according to the satellite control instruction, and transmits the satellite control instruction and the telemetering data to an auxiliary satellite task control system; the auxiliary satellite task control system simulates the state of a to-be-controlled satellite according to the telemetry data, determines a task planning result of the satellite control instruction based on the state of the to-be-controlled satellite and the satellite control instruction, and sends the task planning result to the main satellite task control system; the main satellite task control system generates a control instruction according to the task planning result and issues the control instruction to the to-be-controlled satellite, and simultaneous operation control of the main satellite task control system and the auxiliary satellite task control system on the same satellite is achieved. Meanwhile, the number of auxiliary satellite task control systems can be increased from one to multiple. According to the scheme, the satellite can be operated and controlled by multiple parties simultaneously and efficiently.

Description

Technical Field

[0001] One or more embodiments of this specification relate to the field of aerospace measurement, transportation, and control technology, and particularly to a method, system, and device for multi-party operation and control of satellites. Background Art

[0002] The satellite mission control system in the aerospace measurement, transportation, and control system is unique to a certain satellite. A satellite can only be controlled by a unique satellite mission control system. Traditionally, to solve the satellite mission requirements of multiple users, multiple users send satellite mission requirements to the satellite mission control system. The satellite mission control system completes the mission planning uniformly, and feedbacks whether the satellite mission requirements of the users are met. If the satellite mission requirements cannot be met, the users need to adjust the satellite mission requirements and then apply to the satellite mission control system again. This traditional method has low overall operating efficiency and low satisfaction of mission planning with user requirements, and it is difficult to meet the efficient and real-time planning requirements of multiple users. How to achieve multi-party simultaneous operation and control of satellites is one of the difficult problems faced by the aerospace measurement, transportation, and control system.

[0003] Application Content

[0004] This application describes a method, system, and device for multi-party operation and control of satellites, which can solve the above technical problems.

[0005] According to the first aspect, a method for multi-party operation and control of satellites is provided, including:

[0006] The main satellite mission control system receives a satellite control instruction, collects telemetry data of the satellite to be controlled according to the satellite control instruction, and sends the satellite control instruction and the telemetry data to the secondary satellite mission control system;

[0007] The secondary satellite mission control system simulates the state of the satellite to be controlled according to the telemetry data, determines the mission planning result of the satellite control instruction based on the state of the satellite to be controlled and the satellite control instruction, and sends the mission planning result to the main satellite mission control system;

[0008] The main satellite mission control system generates a control instruction according to the mission planning result and issues it to the satellite to be controlled.

[0009] Based on the above embodiment, further, the secondary satellite mission control system includes a satellite on-orbit state simulation module, a satellite usage rule library, a satellite mission feasibility analysis module, and a first mission planning module;

[0010] The sub-satellite mission control system simulates the state of the satellite to be controlled according to the telemetry data, determines the mission planning result of the satellite control instruction based on the state of the satellite to be controlled and the satellite control instruction, and sends the mission planning result to the main satellite mission control system, specifically including:

[0011] The first mission planning module receives the satellite control instruction and the telemetry data, and sends the satellite control instruction and the telemetry data to the satellite on-orbit state simulation module;

[0012] The satellite on-orbit state simulation module simulates the resource consumption state of the satellite to be controlled according to the telemetry data, obtains the on-orbit charge and discharge information of the satellite to be controlled according to the satellite orbit of the satellite to be controlled, and determines the resources required for the satellite to be controlled to execute the instruction according to the satellite control instruction;

[0013] The satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instruction according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resources required to execute the instruction, and the satellite usage rule library;

[0014] The first mission planning module sends the mission feasibility of the satellite to be controlled to execute the satellite control instruction to the main satellite mission control system.

[0015] Based on the above embodiments, further, the satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instruction according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resources required to execute the instruction, and the satellite usage rule library, specifically including:

[0016] The satellite mission feasibility analysis module determines the imaging mission feasibility, TT&C mission feasibility, and data transmission mission feasibility of the satellite to be controlled to execute the satellite control instruction according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resources required to execute the instruction, and the satellite usage rule library;

[0017] Among them, the imaging mission feasibility includes whether the orbit maneuver is feasible, whether the on-board storage margin is sufficient, and whether the satellite energy can support imaging;

[0018] The TT&C mission feasibility includes judging whether the command can be uploaded before the mission according to the satellite-ground visibility;

[0019] The data transmission mission feasibility includes whether the satellite energy can support the data transmission to the ground and judging whether the data can be transmitted back in time according to the satellite-ground visibility.

[0020] Based on the above embodiments, further, the main satellite mission control system includes a telemetry processing module, a satellite control module, and a mission planning module;

[0021] The main satellite mission control system receives satellite control instructions, collects telemetry data of the satellite to be controlled according to the satellite control instructions, and sends the satellite control instructions and the telemetry data to the secondary satellite mission control system, specifically including:

[0022] The mission planning module issues a telemetry command to the telemetry processing module according to the satellite control instructions;

[0023] The telemetry processing module collects the telemetry data of the satellite to be controlled according to the telemetry command, and sends the telemetry data to the mission planning module;

[0024] The mission planning module sends the satellite control instructions and the telemetry data to the secondary satellite mission control system, and receives the mission planning results sent by the secondary satellite mission control system.

[0025] Based on the above embodiments, further, the main satellite mission control system generates control instructions according to the mission planning results and issues them to the satellite to be controlled, specifically including:

[0026] The satellite control module generates control instructions according to the mission planning results and issues the control instructions to the satellite to be controlled.

[0027] Based on the above embodiments, further, the satellite usage rule library includes an imaging condition constraint library, an orbit maneuver constraint library, an attitude maneuver constraint library, an on-board storage constraint library, and a satellite energy constraint library;

[0028] The satellite mission feasibility analysis module determines the imaging mission feasibility, TT&C mission feasibility, and data transmission mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption status of the satellite to be controlled, the on-orbit charge and discharge information, the resources required to execute the instructions, and the satellite usage rule library, specifically including:

[0029] The satellite mission feasibility analysis module analyzes whether the satellite maneuver is feasible, whether the on-board storage margin is sufficient, and whether the on-board energy can support satellite imaging according to the satellite on-orbit status and the satellite usage rule library, and judges the feasibility of the imaging mission;

[0030] Judge the TT&C mission feasibility according to the space-ground visibility window;

[0031] Judge the data transmission mission feasibility according to the space-ground visibility window and whether the on-board energy can support space-ground data transmission.

[0032] According to a second aspect, there is provided a system for controlling a satellite through multi-party operations, including:

[0033] A main satellite mission control system, configured to receive satellite control instructions, collect telemetry data of a satellite to be controlled according to the satellite control instructions, and send the satellite control instructions and the telemetry data to a secondary satellite mission control system;

[0034] The secondary satellite mission control system is configured to simulate the state of the satellite to be controlled according to the telemetry data, determine a mission planning result of the satellite control instructions based on the state of the satellite to be controlled and the satellite control instructions, and send the mission planning result to the main satellite mission control system;

[0035] The main satellite mission control system is configured to generate control instructions according to the mission planning result and send them to the satellite to be controlled.

[0036] Based on the above embodiments, further, the secondary satellite mission control system includes a satellite on-orbit state simulation module, a satellite usage rule library, a satellite mission feasibility analysis module, and a first mission planning module;

[0037] The first mission planning module receives the satellite control instructions and the telemetry data, and sends the satellite control instructions and the telemetry data to the satellite on-orbit state simulation module;

[0038] The satellite on-orbit state simulation module simulates the resource consumption state of the satellite to be controlled according to the telemetry data, obtains the on-orbit charge and discharge information of the satellite to be controlled according to the satellite orbit of the satellite to be controlled, and determines the resources required for the satellite to be controlled to execute the instructions according to the satellite control instructions;

[0039] The satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resources required for executing the instructions, and the satellite usage rule library;

[0040] The first mission planning module sends the mission feasibility of the satellite to be controlled to execute the satellite control instructions to the main satellite mission control system.

[0041] Based on the above embodiments, further, the satellite mission feasibility analysis module determines the imaging mission feasibility, the TT&C mission feasibility, and the data transmission mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resources required for executing the instructions, and the satellite usage rule library;

[0042] Among them, the feasibility of the imaging task includes whether the orbital maneuver is feasible, whether the on-board storage margin is sufficient, and whether the satellite energy can support imaging;

[0043] The feasibility of the TT&C task includes judging whether commands can be uploaded before the mission according to the satellite-ground visibility;

[0044] The feasibility of the data transmission task includes whether the satellite energy can support the data transmission to the ground and judging whether the data can be transmitted back in time according to the satellite-ground visibility.

[0045] Based on the above embodiments, further, the main satellite mission control system includes a telemetry processing module, a satellite control module, and a mission planning module;

[0046] The mission planning module issues a telemetry command to the telemetry processing module according to the satellite control instruction;

[0047] The telemetry processing module collects the telemetry data of the satellite to be controlled according to the telemetry command, and sends the telemetry data to the mission planning module;

[0048] The mission planning module sends the satellite control instruction and the telemetry data to the secondary satellite mission control system, and receives the mission planning result sent by the secondary satellite mission control system.

[0049] Based on the above embodiments, further, the satellite control module generates a control instruction according to the mission planning result, and issues the control instruction to the satellite to be controlled.

[0050] Based on the above embodiments, further, the satellite usage rule library includes an imaging condition constraint library, an orbital maneuver constraint library, an attitude maneuver constraint library, an on-board storage constraint library, and a satellite energy constraint library;

[0051] The satellite mission feasibility analysis module analyzes whether the satellite maneuver is feasible, whether the on-board storage margin is sufficient, and whether the on-board energy can support satellite imaging according to the satellite's on-orbit state and the satellite usage rule library, and judges the feasibility of the imaging task;

[0052] Judge the feasibility of the TT&C task according to the satellite-ground visibility window;

[0053] Judge the feasibility of the data transmission task according to the satellite-ground visibility window and whether the on-board energy can support the satellite-ground data transmission.

[0054] According to a third aspect, there is provided a device for controlling a satellite by multiple parties, including;

[0055] The first processing module is used for the main satellite mission control system to receive satellite control instructions, collect the telemetry data of the satellite to be controlled according to the satellite control instructions, and send the satellite control instructions and the telemetry data to the secondary satellite mission control system;

[0056] The second processing module is used for the secondary satellite mission control system to simulate the state of the satellite to be controlled according to the telemetry data, determine the mission planning result of the satellite control instructions based on the state of the satellite to be controlled and the satellite control instructions, and send the mission planning result to the main satellite mission control system;

[0057] The third processing module is used for the main satellite mission control system to generate control instructions according to the mission planning result and send them to the satellite to be controlled.

[0058] Based on the above embodiments, further, the secondary satellite mission control system includes a satellite on-orbit state simulation module, a satellite usage rule library, a satellite mission feasibility analysis module, and a first mission planning module;

[0059] The first mission planning module receives the satellite control instructions and the telemetry data, and sends the satellite control instructions and the telemetry data to the satellite on-orbit state simulation module;

[0060] The satellite on-orbit state simulation module simulates the resource consumption state of the satellite to be controlled according to the telemetry data, obtains the on-orbit charge and discharge information of the satellite to be controlled according to the satellite orbit of the satellite to be controlled, and determines the resource consumption required for the satellite to be controlled to execute the instructions according to the satellite control instructions;

[0061] The satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resource consumption required for executing the instructions, and the satellite usage rule library;

[0062] The first mission planning module sends the mission feasibility of the satellite to be controlled to execute the satellite control instructions to the main satellite mission control system.

[0063] Based on the above embodiments, further, the satellite mission feasibility analysis module determines the imaging mission feasibility, the TT&C mission feasibility, and the data transmission mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resource consumption required for executing the instructions, and the satellite usage rule library;

[0064] Among them, the feasibility of the imaging task includes whether the orbital maneuver is feasible, whether the on-board storage margin is sufficient, and whether the satellite energy can support imaging;

[0065] The feasibility of the TT&C task includes judging whether commands can be uploaded before the mission according to the satellite-ground visibility;

[0066] The feasibility of the data transmission task includes whether the satellite energy can support the data transmission to the ground and judging whether the data can be transmitted back in time according to the satellite-ground visibility.

[0067] Based on the above embodiments, further, the main satellite mission control system includes a telemetry processing module, a satellite control module, and a mission planning module;

[0068] The mission planning module issues a telemetry command to the telemetry processing module according to the satellite control instruction;

[0069] The telemetry processing module collects the telemetry data of the satellite to be controlled according to the telemetry command and sends the telemetry data to the mission planning module;

[0070] The mission planning module sends the satellite control instruction and the telemetry data to the sub-satellite mission control system and receives the mission planning result sent by the sub-satellite mission control system.

[0071] Based on the above embodiments, further, the satellite control module generates a control instruction according to the mission planning result and issues the control instruction to the satellite to be controlled.

[0072] Based on the above embodiments, further, the satellite usage rule library includes an imaging condition constraint library, an orbital maneuver constraint library, an attitude maneuver constraint library, an on-board storage constraint library, and a satellite energy constraint library;

[0073] The satellite mission feasibility analysis module analyzes whether the satellite maneuver is feasible, whether the on-board storage margin is sufficient, and whether the on-board energy can support satellite imaging according to the satellite's on-orbit state and the satellite usage rule library, and judges the feasibility of the imaging task;

[0074] Judge the feasibility of the TT&C task according to the satellite-ground visibility window;

[0075] Judge the feasibility of the data transmission task according to the satellite-ground visibility window and whether the on-board energy can support the satellite-ground data transmission.

[0076] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, it implements a method for controlling a satellite with multi-party operations as described in the above technical solution.

[0077] The present invention also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, a method for controlling a satellite by multiple parties as described in the above technical solution is implemented.

[0078] In the above system and method provided by the embodiments of this specification, since the secondary satellite mission control system adds a satellite mission feasibility analysis module, a satellite on-orbit state simulation module, and a satellite usage rule library, it can accurately analyze the feasibility of satellite mission execution based on the satellite state and satellite usage rules, thereby realizing the simultaneous operation and control of the same satellite by the primary and secondary satellite mission control systems. At the same time, the secondary satellite mission control system can be extended from one to multiple. Using the solution of the present invention, multiple parties can simultaneously and efficiently operate and control the satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0079] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0080] Figure 1 A schematic diagram showing a method for controlling a satellite by multiple parties simultaneously provided by the embodiments of this specification;

[0081] Figure 2 A flowchart showing the basic process of accurate analysis of satellite mission feasibility provided by the embodiments of this specification;

[0082] Figure 3 A flowchart showing a method for controlling a satellite by multiple parties provided by the embodiments of this specification;

[0083] Figure 4 A schematic diagram showing a system for controlling a satellite by multiple parties simultaneously provided by the embodiments of this specification;

[0084] Figure 5 A schematic diagram showing a device for controlling a satellite by multiple parties provided by the embodiments of this specification. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0085] The following describes the solution provided by this specification in conjunction with the drawings.

[0086] In order to make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described below in conjunction with the drawings.

[0087] In the description of the embodiments of this application, words such as "exemplary", "for example", or "for illustration purposes" are used to represent examples, illustrations, or explanations. Any embodiment or design solution described as "exemplary", "for example", or "for illustration purposes" in the embodiments of this application should not be construed as being more preferred or having more advantages than other embodiments or design solutions. Rather, the use of words such as "exemplary", "for example", or "for illustration purposes" is intended to present relevant concepts in a specific manner.

[0088] In the description of the embodiments of this application, the term "and / or" is merely a description of the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, B exists alone, and both A and B exist simultaneously. Additionally, unless otherwise specified, the meaning of the term "plural" refers to two or more.

[0089] Furthermore, the terms "first" and "second" are only used for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly specifying the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. The terms "include", "comprise", "have" and their variants all mean "including but not limited to", unless otherwise specifically emphasized in other ways.

[0090] To achieve efficient and real-time operation and control of a satellite by multiple parties, the original satellite mission control system is defined as the primary satellite mission control system, and the user's new satellite mission control system is defined as the secondary satellite mission control system. The primary satellite mission control system sends the telemetry data processing results and satellite control instructions to the secondary satellite mission control system. To achieve precise mission planning for the satellite by the secondary satellite mission control system, a satellite mission feasibility analysis module, a satellite on-orbit state simulation module, and a satellite usage rule library are added to the secondary satellite mission control system. The satellite on-orbit state simulation module predicts the satellite fuel consumption, on-board storage consumption, and on-board energy consumption at the mission requirement moment based on the current satellite state and the upcoming satellite control instructions. The satellite usage rule library establishes constraint rule libraries for aspects such as satellite imaging, measurement and control, data transmission, storage, attitude, and energy. The satellite mission feasibility analysis module analyzes the feasibility of satellite imaging, measurement and control, data transmission, etc. tasks based on the satellite fuel consumption, on-board storage consumption, and on-board energy consumption at the mission requirement moment, as well as the satellite usage rule library. After the secondary satellite mission control system completes the satellite mission planning, it sends the mission planning results to the primary satellite mission control system, and the primary satellite mission control system generates control instructions to send to the satellite for execution.

[0091] The present invention provides a method for multiple parties to simultaneously operate and control a satellite. The method includes: the main satellite mission control system collects satellite control instructions generated by the system itself and the mission control subsystem, and processes the obtained on-orbit telemetry data; the secondary satellite mission control system simulates the on-orbit state of the satellite using the satellite control instructions to be executed and the current on-orbit telemetry data; the secondary satellite mission control system analyzes the feasibility of satellite mission execution based on the satellite usage rule library and the on-orbit state of the satellite; the secondary satellite mission control system generates a mission planning result according to the feasibility of satellite mission execution and mission requirements; the main satellite mission control system generates satellite control instructions according to the mission planning result.

[0092] Since the secondary satellite mission control system adds a satellite mission feasibility analysis module, a satellite on-orbit state simulation module, and a satellite usage rule library, it can accurately analyze the feasibility of satellite mission execution based on the satellite state and satellite usage rules, thus realizing the simultaneous operation and control of the same satellite by the main and secondary satellite mission control systems. At the same time, the secondary satellite mission control system can be extended from one to multiple. Using the solution of the present invention, multiple parties (one main and multiple secondary) can simultaneously and efficiently operate and control the satellite.

[0093] As Figure 1 Shown in the schematic diagram of multiple parties simultaneously operating and controlling a satellite, the main satellite mission control system processes the obtained on-orbit telemetry data, generates a telemetry processing result, obtains the satellite control instructions sent to the satellite, calculates the satellite orbit, and sends the telemetry data processing result, the remote control instruction, and the satellite orbit to the secondary satellite mission control system. The satellite on-orbit state simulation module of the secondary satellite mission control system predicts the on-orbit state of the satellite at the mission requirement moment according to the current satellite state and the satellite control instructions to be executed. The satellite usage rule library establishes constraint rule libraries in aspects such as satellite imaging, measurement and control, data transmission, storage, attitude, and energy. The satellite mission feasibility analysis module analyzes the feasibility of tasks such as satellite imaging, measurement and control, and data transmission according to the on-orbit state of the satellite and the satellite usage rule library.

[0094] As Figure 2The flow chart of the precise analysis of the satellite mission feasibility is shown. The satellite on-orbit state simulation module analyzes the satellite fuel margin, energy margin, and on-orbit storage margin according to the satellite telemetry processing results. The satellite on-orbit state simulation module predicts the satellite charge and discharge situation based on the satellite orbit analysis of the satellite illumination. The satellite on-orbit state simulation module predicts the satellite on-orbit state at the mission requirement moment according to the upcoming satellite remote control instructions. The satellite usage rule library establishes the constraint rule libraries for aspects such as satellite imaging, measurement and control, data transmission, storage, attitude, and energy. The satellite mission feasibility analysis module analyzes whether the satellite maneuver is feasible, whether the on-board storage margin is sufficient, and whether the on-board energy can support satellite imaging based on the satellite on-orbit state and the satellite usage rule library, and determines the feasibility of satellite imaging; analyzes the satellite-ground visible window to determine whether the satellite control instructions can be uploaded before the mission; analyzes the satellite-ground visible window and whether the on-board energy can support satellite-ground data transmission to determine the feasibility of the satellite data transmission mission.

[0095] Since the deputy satellite mission control system uses methods such as satellite on-orbit state simulation, satellite usage rule library, and satellite mission feasibility analysis to precisely analyze the satellite mission feasibility, it avoids the inaccurate mission planning results, resulting in frequent and inefficient interactions between the deputy satellite mission control system and the main satellite mission control system. Therefore, this method realizes the real-time and efficient operation control of the main satellite mission control and the deputy satellite mission control for the satellite at a relatively small cost.

[0096] As Figure 3 shown, this embodiment provides a method for multi-party operation control of a satellite, which specifically includes the following steps:

[0097] 110. The main satellite mission control system receives the satellite control instructions, collects the telemetry data of the satellite to be controlled according to the satellite control instructions, and sends the satellite control instructions and the telemetry data to the deputy satellite mission control system;

[0098] 120. The deputy satellite mission control system simulates the state of the satellite to be controlled according to the telemetry data, determines the mission planning result of the satellite control instructions based on the state of the satellite to be controlled and the satellite control instructions, and sends the mission planning result to the main satellite mission control system;

[0099] 130. The main satellite mission control system generates control instructions according to the mission planning result and sends them to the satellite to be controlled.

[0100] Based on the above embodiment, further, the deputy satellite mission control system includes a satellite on-orbit state simulation module, a satellite usage rule library, a satellite mission feasibility analysis module, and a first mission planning module;

[0101] Specifically included in step 120:

[0102] The first task planning module receives the satellite control instruction and the telemetry data, and sends the satellite control instruction and the telemetry data to the satellite on-orbit state simulation module;

[0103] The satellite on-orbit state simulation module simulates the resource consumption state of the satellite to be controlled according to the telemetry data, obtains the on-orbit charge-discharge information of the satellite to be controlled according to the satellite orbit of the satellite to be controlled, and determines the resources required for the satellite to be controlled to execute the instruction according to the satellite control instruction;

[0104] The satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instruction according to the resource consumption state of the satellite to be controlled, the on-orbit charge-discharge information, the resources required to execute the instruction, and the satellite usage rule library;

[0105] The first task planning module sends the mission feasibility of the satellite to be controlled to execute the satellite control instruction to the main satellite mission control system.

[0106] Based on the above embodiments, further, the satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instruction according to the resource consumption state of the satellite to be controlled, the on-orbit charge-discharge information, the resources required to execute the instruction, and the satellite usage rule library, specifically including:

[0107] The satellite mission feasibility analysis module determines the imaging mission feasibility, the TT&C mission feasibility, and the data transmission mission feasibility of the satellite to be controlled to execute the satellite control instruction according to the resource consumption state of the satellite to be controlled, the on-orbit charge-discharge information, the resources required to execute the instruction, and the satellite usage rule library;

[0108] Among them, the imaging mission feasibility includes whether the orbit maneuver is feasible, whether the on-board storage margin is sufficient, and whether the satellite energy can support imaging;

[0109] The TT&C mission feasibility includes determining whether an instruction can be uploaded before the mission according to the satellite-ground visibility;

[0110] The data transmission mission feasibility includes whether the satellite energy can support the ground data transmission and determining whether the data can be transmitted back in time according to the satellite-ground visibility.

[0111] Based on the above embodiments, further, the main satellite mission control system includes a telemetry processing module, a satellite control module, and a task planning module;

[0112] The main satellite mission control system receives satellite control instructions, collects telemetry data of the satellite to be controlled according to the satellite control instructions, and sends the satellite control instructions and the telemetry data to the secondary satellite mission control system, specifically including:

[0113] The mission planning module issues a telemetry command to the telemetry processing module according to the satellite control instructions;

[0114] The telemetry processing module collects the telemetry data of the satellite to be controlled according to the telemetry command, and sends the telemetry data to the mission planning module;

[0115] The mission planning module sends the satellite control instructions and the telemetry data to the secondary satellite mission control system, and receives the mission planning results sent by the secondary satellite mission control system.

[0116] Based on the above embodiments, further, the main satellite mission control system generates control instructions according to the mission planning results and issues them to the satellite to be controlled, specifically including:

[0117] The satellite control module generates control instructions according to the mission planning results and issues the control instructions to the satellite to be controlled.

[0118] Based on the above embodiments, further, the satellite usage rule library includes an imaging condition constraint library, an orbit maneuver constraint library, an attitude maneuver constraint library, an on-board storage constraint library, and a satellite energy constraint library;

[0119] The satellite mission feasibility analysis module determines the imaging mission feasibility, TT&C mission feasibility, and data transmission mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption status of the satellite to be controlled, the on-orbit charge and discharge information, the resources required to execute the instructions, and the satellite usage rule library, specifically including:

[0120] The satellite mission feasibility analysis module analyzes whether the satellite maneuver is feasible, whether the on-board storage margin is sufficient, and whether the on-board energy can support satellite imaging according to the on-orbit state of the satellite and the satellite usage rule library, and judges the feasibility of the imaging mission;

[0121] Judge the TT&C mission feasibility according to the satellite-ground visibility window;

[0122] Judge the data transmission mission feasibility according to the satellite-ground visibility window and whether the on-board energy can support satellite-ground data transmission.

[0123] In the above method provided by the embodiments of this specification, since the secondary satellite mission control system adds a satellite mission feasibility analysis module, a satellite on-orbit state simulation module, and a satellite usage rule library, it can accurately analyze the feasibility of satellite mission execution based on the satellite state and satellite usage rules, thereby realizing the simultaneous operation and control of the same satellite by the primary and secondary satellite mission control systems. At the same time, the secondary satellite mission control system can be extended from one to multiple. Using the solution of the present invention, multi-party simultaneous and efficient operation and control of the satellite can be achieved.

[0124] As Figure 4 shown, the present invention provides a system for multi-party operation and control of a satellite, and the system includes a primary satellite mission control system and a secondary satellite mission control system.

[0125] The primary satellite mission control system is used to receive satellite control instructions, collect telemetry data of the satellite to be controlled according to the satellite control instructions, and send the satellite control instructions and the telemetry data to the secondary satellite mission control system;

[0126] The secondary satellite mission control system is used to simulate the state of the satellite to be controlled according to the telemetry data, determine the mission planning result of the satellite control instructions based on the state of the satellite to be controlled and the satellite control instructions, and send the mission planning result to the primary satellite mission control system;

[0127] The primary satellite mission control system is used to generate control instructions according to the mission planning result and send them to the satellite to be controlled.

[0128] Based on the above embodiments, further, the secondary satellite mission control system includes a satellite on-orbit state simulation module, a satellite usage rule library, a satellite mission feasibility analysis module, and a first mission planning module;

[0129] The first mission planning module receives the satellite control instructions and the telemetry data, and sends the satellite control instructions and the telemetry data to the satellite on-orbit state simulation module;

[0130] The satellite on-orbit state simulation module simulates the resource consumption state of the satellite to be controlled according to the telemetry data, obtains the on-orbit charge and discharge information of the satellite to be controlled according to the satellite orbit of the satellite to be controlled, and determines the resource consumption required for the satellite to be controlled to execute the instructions according to the satellite control instructions;

[0131] The satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption state, on-orbit charge and discharge information, resource consumption required for executing the instructions of the satellite to be controlled, and the satellite usage rule library;

[0132] The first task planning module sends the task feasibility of the satellite to be controlled to execute the satellite control instruction to the main satellite task control system.

[0133] Based on the above embodiments, further, the satellite task feasibility analysis module determines the imaging task feasibility, TT&C task feasibility, and data transmission task feasibility of the satellite to be controlled to execute the satellite control instruction according to the resource consumption status of the satellite to be controlled, on-orbit charge and discharge information, resources required to execute the instruction, and the satellite usage rule library.

[0134] Among them, the imaging task feasibility includes whether the orbit maneuver is feasible, whether the on-board storage margin is sufficient, and whether the satellite energy can support imaging.

[0135] The TT&C task feasibility includes determining whether an instruction can be uplinked before the mission according to the satellite-ground visibility.

[0136] The data transmission task feasibility includes whether the satellite energy can support ground data transmission and determining whether data can be transmitted back in time according to the satellite-ground visibility.

[0137] Based on the above embodiments, further, the main satellite task control system includes a telemetry processing module, a satellite control module, and a task planning module.

[0138] The task planning module issues a telemetry command to the telemetry processing module according to the satellite control instruction.

[0139] The telemetry processing module collects the telemetry data of the satellite to be controlled according to the telemetry command and sends the telemetry data to the task planning module.

[0140] The task planning module sends the satellite control instruction and the telemetry data to the secondary satellite task control system and receives the task planning result sent by the secondary satellite task control system.

[0141] Based on the above embodiments, further, the satellite control module generates a control instruction according to the task planning result and issues the control instruction to the satellite to be controlled.

[0142] Based on the above embodiments, further, the satellite usage rule library includes an imaging condition constraint library, an orbit maneuver constraint library, an attitude maneuver constraint library, an on-board storage constraint library, and a satellite energy constraint library.

[0143] The satellite task feasibility analysis module analyzes whether the satellite maneuver is feasible, whether the on-board storage margin is sufficient, and whether the on-board energy can support satellite imaging according to the satellite on-orbit state and the satellite usage rule library, and determines the feasibility of the imaging task.

[0144] Judge the feasibility of TT&C missions according to the satellite-ground visibility window;

[0145] Judge the feasibility of data transmission missions according to the satellite-ground visibility window and whether the on-board energy can support satellite-ground data transmission.

[0146] In the above system provided by the embodiments of this specification, since the deputy satellite mission control system has added a satellite mission feasibility analysis module, a satellite on-orbit state simulation module, and a satellite usage rule library, it can accurately analyze the feasibility of satellite mission execution based on satellite states and satellite usage rules, thereby realizing the simultaneous operation and control of the same satellite by the main and deputy satellite mission control systems. At the same time, the deputy satellite mission control system can be extended from one to multiple. Using the solution of the present invention, multi-party simultaneous and efficient operation and control of satellites can be achieved.

[0147] As Figure 5 shown, the present invention provides a device for multi-party operation and control of satellites, including;

[0148] A first processing module, configured to receive a satellite control instruction by the main satellite mission control system, collect telemetry data of the satellite to be controlled according to the satellite control instruction, and send the satellite control instruction and the telemetry data to the deputy satellite mission control system;

[0149] A second processing module, configured to simulate the state of the satellite to be controlled by the deputy satellite mission control system according to the telemetry data, determine the mission planning result of the satellite control instruction based on the state of the satellite to be controlled and the satellite control instruction, and send the mission planning result to the main satellite mission control system;

[0150] A third processing module, configured to generate a control instruction according to the mission planning result by the main satellite mission control system and send it to the satellite to be controlled.

[0151] Based on the above embodiments, further, the deputy satellite mission control system includes a satellite on-orbit state simulation module, a satellite usage rule library, a satellite mission feasibility analysis module, and a first mission planning module;

[0152] The first mission planning module receives the satellite control instruction and the telemetry data, and sends the satellite control instruction and the telemetry data to the satellite on-orbit state simulation module;

[0153] The satellite on-orbit state simulation module simulates the resource consumption state of the satellite to be controlled according to the telemetry data, obtains the on-orbit charge and discharge information of the satellite to be controlled according to the satellite orbit of the satellite to be controlled, and determines the resource consumption required for the satellite to be controlled to execute the instruction according to the satellite control instruction;

[0154] The satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled for executing the satellite control instruction according to the resource consumption status of the satellite to be controlled, the on-orbit charge and discharge information, the resources required for executing the instruction, and the satellite usage rule library;

[0155] The first mission planning module sends the mission feasibility of the satellite to be controlled for executing the satellite control instruction to the main satellite mission control system.

[0156] Based on the above embodiments, further, the satellite mission feasibility analysis module determines the imaging mission feasibility, TT&C mission feasibility, and data transmission mission feasibility of the satellite to be controlled for executing the satellite control instruction according to the resource consumption status of the satellite to be controlled, the on-orbit charge and discharge information, the resources required for executing the instruction, and the satellite usage rule library;

[0157] Among them, the imaging mission feasibility includes whether the orbit maneuver is feasible, whether the on-board storage margin is sufficient, and whether the satellite energy can support imaging;

[0158] The TT&C mission feasibility includes judging whether instructions can be uploaded before the mission according to the satellite-ground visibility;

[0159] The data transmission mission feasibility includes whether the satellite energy can support data transmission to the ground and judging whether data can be transmitted back in time according to the satellite-ground visibility.

[0160] Based on the above embodiments, further, the main satellite mission control system includes a telemetry processing module, a satellite control module, and a mission planning module;

[0161] The mission planning module issues a telemetry command to the telemetry processing module according to the satellite control instruction;

[0162] The telemetry processing module collects the telemetry data of the satellite to be controlled according to the telemetry command and sends the telemetry data to the mission planning module;

[0163] The mission planning module sends the satellite control instruction and the telemetry data to the secondary satellite mission control system and receives the mission planning result sent by the secondary satellite mission control system.

[0164] Based on the above embodiments, further, the satellite control module generates a control instruction according to the mission planning result and issues the control instruction to the satellite to be controlled.

[0165] Based on the above embodiments, further, the satellite usage rule library includes an imaging condition constraint library, an orbit maneuver constraint library, an attitude maneuver constraint library, an on-board storage constraint library, and a satellite energy constraint library;

[0166] The satellite mission feasibility analysis module analyzes whether the satellite maneuver is feasible, whether the on-board storage margin is sufficient, and whether the on-board energy can support satellite imaging according to the on-orbit state of the satellite and the satellite usage rule library, and determines the feasibility of the imaging mission;

[0167] Judge the feasibility of the TT&C mission according to the satellite-ground visibility window;

[0168] Judge the feasibility of the data transmission mission according to the satellite-ground visibility window and whether the on-board energy can support satellite-ground data transmission.

[0169] In the above device provided by the embodiment of the present specification, since the sub-satellite mission control system adds a satellite mission feasibility analysis module, a satellite on-orbit state simulation module and a satellite usage rule library, it can accurately analyze the feasibility of satellite mission execution based on the satellite state and satellite usage rules, thereby realizing the simultaneous operation and control of the main and sub-satellite mission control systems for the same satellite. At the same time, the sub-satellite mission control system can be expanded from one to multiple. Using the solution of the present invention, multi-party simultaneous and efficient operation and control of the satellite can be realized.

[0170] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, it implements a method for multi-party operation and control of a satellite as in the above technical solution.

[0171] The present invention also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it implements a method for multi-party operation and control of a satellite as in the above technical solution.

[0172] Those skilled in the art should be able to realize that in one or more of the above examples, the functions described in this application can be implemented by hardware, software, firmware, or any combination thereof. When implemented using software, these functions can be stored in a computer-readable medium or transmitted as one or more instructions or codes on a computer-readable medium.

[0173] The specific embodiments described above further elaborate on the purpose, technical solution, and beneficial effects of this application. It should be understood that the above description is only the specific embodiments of this application and is not used to limit the protection scope of this application. Any modifications, equivalent replacements, improvements, etc. made on the basis of the technical solution of this application should be included in the protection scope of this application.

Claims

1. A method for controlling a satellite through multi-party operations, characterized in that, including; The main satellite mission control system receives satellite control instructions, collects the telemetry data of the satellite to be controlled according to the satellite control instructions, and sends the satellite control instructions and the telemetry data to the secondary satellite mission control system; The secondary satellite mission control system simulates the state of the satellite to be controlled according to the telemetry data, determines the mission planning result of the satellite control instructions based on the state of the satellite to be controlled and the satellite control instructions, and sends the mission planning result to the main satellite mission control system; The main satellite mission control system generates control instructions according to the mission planning result and issues them to the satellite to be controlled.

2. The method according to claim 1, wherein The secondary satellite mission control system includes a satellite on-orbit state simulation module, a satellite usage rule library, a satellite mission feasibility analysis module, and a first mission planning module; The secondary satellite mission control system simulates the state of the satellite to be controlled according to the telemetry data, determines the mission planning result of the satellite control instructions based on the state of the satellite to be controlled and the satellite control instructions, and sends the mission planning result to the main satellite mission control system, specifically including: The first mission planning module receives the satellite control instructions and the telemetry data, and sends the satellite control instructions and the telemetry data to the satellite on-orbit state simulation module; The satellite on-orbit state simulation module simulates the resource consumption state of the satellite to be controlled according to the telemetry data, obtains the on-orbit charge and discharge information of the satellite to be controlled according to the satellite orbit of the satellite to be controlled, and determines the resources required for the satellite to be controlled to execute the instructions according to the satellite control instructions; The satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resources required for executing the instructions, and the satellite usage rule library; The first mission planning module sends the mission feasibility of the satellite to be controlled to execute the satellite control instructions to the main satellite mission control system.

3. The method according to claim 2, wherein The satellite mission feasibility analysis module determines the mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resources required for executing the instructions, and the satellite usage rule library, specifically including: The satellite mission feasibility analysis module determines the imaging mission feasibility, the TT&C mission feasibility, and the data transmission mission feasibility of the satellite to be controlled to execute the satellite control instructions according to the resource consumption state of the satellite to be controlled, the on-orbit charge and discharge information, the resources required for executing the instructions, and the satellite usage rule library; Among them, the imaging mission feasibility includes whether the orbit maneuver is feasible, whether the on-board storage margin is sufficient, and whether the satellite energy can support imaging; The TT&C mission feasibility includes judging whether instructions can be uploaded before the mission according to the satellite-ground visibility; The data transmission mission feasibility includes whether the satellite energy can support ground data transmission and judging whether data can be transmitted back in time according to the satellite-ground visibility.

4. The method according to claim 1, characterized in that, The main satellite mission control system includes a telemetry processing module, a satellite control module, and a mission planning module; The main satellite mission control system receives satellite control instructions, collects the telemetry data of the satellite to be controlled according to the satellite control instructions, and sends the satellite control instructions and the telemetry data to the secondary satellite mission control system, specifically including: The mission planning module issues a telemetry command to the telemetry processing module according to the satellite control instructions; The telemetry processing module collects the telemetry data of the satellite to be controlled according to the telemetry command, and sends the telemetry data to the mission planning module; The mission planning module sends the satellite control instructions and the telemetry data to the secondary satellite mission control system, and receives the mission planning result sent by the secondary satellite mission control system.

5. The method according to claim 4, wherein The main satellite mission control system generates a control instruction according to the mission planning result, and issues it to the satellite to be controlled, specifically including: The satellite control module generates a control instruction according to the mission planning result, and issues the control instruction to the satellite to be controlled.

6. The method according to claim 3, wherein The satellite usage rule library includes an imaging condition constraint library, an orbital maneuver constraint library, an attitude maneuver constraint library, an on-board storage constraint library, and a satellite energy constraint library; The satellite mission feasibility analysis module determines the imaging mission feasibility, TT&C mission feasibility, and data transmission mission feasibility of the satellite to be controlled to execute the satellite control instruction according to the resource consumption status of the satellite to be controlled, the on-orbit charging and discharging information, the resources required to execute the instruction, and the satellite usage rule library, specifically including: The satellite mission feasibility analysis module analyzes whether the satellite maneuver is feasible, whether the on-board storage margin is sufficient, and whether the on-board energy can support satellite imaging according to the satellite on-orbit state and the satellite usage rule library, and judges the feasibility of the imaging mission; Judge the TT&C mission feasibility according to the satellite-ground visibility window; Judge the data transmission mission feasibility according to the satellite-ground visibility window and whether the on-board energy can support satellite-ground data transmission.

7. A system for controlling a satellite by multi-party operations, characterized in that Include; The main satellite mission control system is used to receive satellite control instructions, collect the telemetry data of the satellite to be controlled according to the satellite control instructions, and send the satellite control instructions and the telemetry data to the secondary satellite mission control system; The secondary satellite mission control system is used to simulate the state of the satellite to be controlled according to the telemetry data, determine the mission planning result of the satellite control instruction based on the state of the satellite to be controlled and the satellite control instruction, and send the mission planning result to the main satellite mission control system; The main satellite mission control system is used to generate a control instruction according to the mission planning result, and issue it to the satellite to be controlled.

8. A device for controlling a satellite by multi-party operation, characterized in that, Include; The first processing module is used for the main satellite mission control system to receive satellite control instructions, collect the telemetry data of the satellite to be controlled according to the satellite control instructions, and send the satellite control instructions and the telemetry data to the secondary satellite mission control system; The second processing module is used for the deputy satellite mission control system to simulate the state of the satellite to be controlled according to the telemetry data, determine the mission planning result of the satellite control instruction based on the state of the satellite to be controlled and the satellite control instruction, and send the mission planning result to the main satellite mission control system; The third processing module is used for the main satellite mission control system to generate a control instruction according to the mission planning result and send it to the satellite to be controlled.

9. An electronic device, characterized in that, It includes a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, it implements the method for controlling a satellite with multi-party operations according to any one of claims 1 to 6.

10. A computer-readable storage medium, characterized in that, A computer program is stored thereon, and when the computer program is executed by a processor, it implements the method for controlling a satellite with multi-party operations according to any one of claims 1 to 6.

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