A method for programming and launching a satellite payload command chain

Abstract

The application discloses a kind of satellite payload instruction chain's compilation and launch control method, solve how to flexibly compile and adjust load instruction, improve the technical problem of launch control efficiency;The method comprises setting satellite payload instruction as general instruction and special instruction;General instruction is combined with special instruction generated in real time according to time sequence, and satellite payload instruction chain is formed.The application controls satellite load by real-time instruction, satellite does not prestore instruction, when task adjustment is needed, real-time adjustment instruction can be sent according to demand, without adjusting all instructions, improve the flexibility of satellite control;In the process of instruction chain launch control, the telemetry data related to satellite instruction is transmitted to the instruction launch control software by the software, and the telemetry data reflecting the sending situation of the satellite instruction is transmitted to the instruction launch control software, and the instruction launch control software automatically discriminates the sending situation of the instruction to complete the large loop comparison, improve the comparison efficiency, save the labor cost, reduce the instruction launch control time.

Description

Technical Field

[0001] This invention relates to a method for compiling and controlling a satellite payload command chain, belonging to the field of satellite control. Background Technology

[0002] Satellite payloads conduct on-orbit operations typically by transmitting payload control commands to ground control stations and uploading them to the satellite via command transmission and control software on the satellite ground system. These commands are generated by command compilation software on the ground system, following the satellite command format and operational requirements. They are generally categorized into delayed commands and real-time commands. Delayed commands are generated by the command compilation software and transmitted to the satellite before the mission begins. The satellite data management subsystem parses the commands and stores them in the payload queue. Each command has an execution timecode added during compilation, and the satellite subsystems execute the commands according to the timecode at the corresponding time. Real-time commands only include the satellite's execution content, excluding the execution time. Operators transmit commands one by one to the satellite via command transmission and control software according to the satellite mission time requirements, and the satellite executes the commands immediately upon receipt. During satellite command transmission and control, operators need to manually compare telemetry information to ensure successful transmission of commands to the satellite.

[0003] When controlling a satellite payload, multiple commands must be sent for each mission. The disadvantage of delayed commands is that they include all satellite commands for a single mission and are executed strictly according to timecodes. When adjusting mission modes or configuration parameters, all commands stored in the satellite payload queue must be cleared, making it impossible to precisely change payload configuration parameters in real-time based on operational needs, resulting in poor flexibility. The disadvantage of real-time commands is that they require manual intervention throughout the entire transmission and control process. Commands must be sent manually one by one, and the transmission status of each command must be verified by interpreting telemetry information. Due to the slow speed of manual interpretation, the interval between sending a single command is generally 15 to 20 seconds. Especially for missions with multiple payloads operating simultaneously, with more than 100 control commands, the command transmission and control alone can last at least 30 minutes in a single mission, severely restricting the timeliness of satellite mission execution. Summary of the Invention

[0004] This invention addresses the aforementioned satellite payload control problem by providing a method for compiling and controlling satellite payload command chains. This method discloses a real-time command chain compilation and control approach. The command chain and command control system generated by this method can achieve the goals of minimal human intervention, short control time, and rapid and flexible transmission and adjustment of payload commands during control.

[0005] This invention discloses a method for compiling a satellite payload command chain, comprising:

[0006] Set the satellite payload commands into general commands and special commands;

[0007] The general instructions are pre-stored in the instruction database and are used to start and stop the satellite unit used each time the satellite operates. The content of the general instructions does not change with the actual service requirements in the payload mission plan.

[0008] The dedicated instructions are generated in real time according to business needs and are used to configure the parameters of a satellite unit by modifying its data storage area. These instructions change according to the changes in business needs in the payload mission plan.

[0009] Based on the operational requirements in the payload mission plan, the corresponding general instructions in the instruction database are read and combined with the special instructions generated in real time in sequence to generate a satellite payload instruction chain based on this payload mission plan, and then stored in the instruction database.

[0010] Furthermore, the method for compiling and generating the satellite payload instruction chain based on this mission specifically includes the following steps:

[0011] Step 1: Generate payload mission plan: Based on the satellite orbital elements, calculate the overlap between the satellite's effective payload coverage area and the mission target area during the mission time by extrapolating changes in the satellite's orbit, generate the payload mission plan, and store the payload mission plan in the database; where the satellite orbital elements represent the satellite's position in its orbit at a certain moment, and can be used to extrapolate the satellite's future orbital situation;

[0012] Step 2: Generate a load task plan: The load task scheme and load task plan conversion template in the planning software will convert the received load task scheme into a load task plan represented by an XML file.

[0013] Step 3: Generate Satellite Payload Command Chain: The command compilation software reads the XML file of the payload mission plan, calls the general command template and the special command template, reads the general commands corresponding to the business requirements of the payload mission plan from the command database, and combines them with the special commands corresponding to the business requirements of the payload mission plan generated in real time in a chronological order to compile and generate the satellite payload command chain based on the current mission plan, and stores it in the command database.

[0014] The payload mission plan in step one describes the main state of the satellite within a specified time period, and includes: payload operation sequence, data transmission operation sequence, satellite attitude parameters, and mission target area; wherein...

[0015] The specific content of the load working sequence includes the load working time period, load working mode, and load parameter configuration; the specific content of the data transmission working sequence includes the data transmission working time period, data transmission working mode, and data transmission parameter configuration; the load working sequence is displayed in the software interface showing the parameter configuration and working time period of the effective load; the data transmission working sequence is displayed in the software interface showing the parameter configuration and working time period of the data transmission subsystem; the specific content of the load working sequence and the data transmission working sequence are expressed in the form of XML files, and the parameter configuration types and value ranges are all specified according to the XSD file specification; XML files are Extensible Markup Language (XML), which is widely used for data information exchange between computer systems or software, and is used to describe the characteristics of the exchanged data.

[0016] The satellite attitude parameters refer to the spatial pointing state of the satellite in its orbit, calculated based on the latest orbital elements, the mission target area, and the effective payload coverage. Among them, the satellite orbital elements are parameters describing the satellite's orbital status. They are provided by the relevant satellite platform telemetry and control unit, and are obtained by measuring the satellite using ground telemetry and control equipment. They are expressed as six orbital elements or double-row orbital elements (TLE).

[0017] The target area of ​​the mission is selected according to its business requirements, and is represented as a certain area on the ground selected by a quadrilateral, which is described by the latitude and longitude coordinates of the four vertices of the quadrilateral on the earth; the business requirements are the task requirements in XML file format submitted by the business requirements submission software to the requirements processing software, which describe the requirements for the satellite's working status during the mission time period, and consist of the mission execution time period, mission type, mission objectives, the single-machine parameter configuration of the payload used, and data transmission time.

[0018] In step two, the conversion template between the load task scheme and the load task plan in the planning software is pre-set to the format of the load task plan XML file, and a correspondence is established between the XML file and the various contents of the load task scheme. When generating the load task plan, the planning software reads the data table of the load task scheme from the database, fills in the contents of the load task scheme according to the XML file format, and generates the load task plan.

[0019] The payload task plan, represented by an XML file, specifies the format and content through the interface control file between the planning software and the instruction planning software; the content includes, but is not limited to, task type, single machine used, single machine parameters, and working time period;

[0020] After receiving the payload task plan, the planning software reads the parameters from each work sequence in the payload task plan and generates an XML file of the payload task plan according to the XML file format of the interface control file specification.

[0021] In step three, the general instruction template pre-sets the correspondence between each task type in the payload mission plan and the satellite unit to be used. When the instruction compilation software receives the XML file of the payload mission plan, it first reads the task type described in the file, obtains the satellite unit corresponding to the task type according to the mapping relationship in the general instruction template, and reads the general instructions for starting and stopping the corresponding satellite unit from the instruction database to form the general instruction chain of this payload mission plan.

[0022] The dedicated instruction template sets the instruction code format and parameter configuration rules for dedicated instructions based on the interface control file between the satellite and the ground system. During instruction compilation, the instruction compilation software reads the individual parameters from the payload mission plan, calls the dedicated instruction template, and searches for the corresponding instruction code in the dedicated instruction template according to the individual name and parameter value to complete the compilation of the dedicated instruction. This is then combined with the general instruction chain to form the satellite payload instruction chain based on the current payload mission plan and stored in the instruction database. The interface control file describes the specific content, format, size, scope, protocol, and transmission method of information interaction between software or systems.

[0023] In step three, the satellite payload command chain is a hexadecimal code developed based on the satellite-ground system interface control file to control each individual unit of the satellite.

[0024] The interface control file specifies the instruction data format and parameter value range used for each control action of all individual units of the satellite.

[0025] The present invention also provides a method for controlling the launch of a satellite payload command chain, comprising: reading the satellite payload command chain based on the current payload mission plan from the command database;

[0026] The satellite payload command chain data is framed and its content is inverted. The inversion results are then constrained and verified. Once verified, the data is forwarded to the command control software. Framed data is the process of combining command data into data frames, which are the carriers of information transmitted over the network.

[0027] Operators send satellite payload command data to the satellite via command transmission and control software;

[0028] The command transmission and control software receives satellite telemetry data to check the correctness of each satellite payload command. It compares the data with the telemetry data; if they match, the command is considered correctly transmitted and the next command is automatically sent. If they don't match, an error is considered, or the transmission process is interrupted if no satellite telemetry data is received within a certain time. Telemetry data reflects the operational status of various satellite components. It is transmitted from the satellite to the ground control station via an information transmission channel, and then from the ground control station to the satellite ground system via the operational network.

[0029] Furthermore, the command issuing and control software and the ground telemetry and control station command data receiving software follow the interface control document agreement, which specifies the command data transmission format, transmission protocol and transmission method;

[0030] The command transmission and control uses the UDP protocol. After clicking the command transmission and control button, the software automatically sends each command data in the command chain three times. After receiving the command data, the ground control station command data receiving software performs a consistency check by comparing the CRC information to verify whether three frames of data have been received. Only when at least two completely identical frames of command data are received will a command confirmation message be returned to the command transmission and control software. After receiving the command confirmation message, the next frame of data will be sent. Otherwise, the software will wait for the command confirmation message from the ground control station command data receiving software until the command timeout period expires, at which point a command transmission failure message will be displayed.

[0031] The ground control station receives command data in real time, determines its correctness, and then transmits the command data to the satellite. Simultaneously, it monitors the transmission status of the command data, generates command comparison data (small-loop comparison), and sends the small-loop comparison result to the command transmission and control software. At the same time, the ground control station receives satellite telemetry data and transmits it to the satellite ground system in real time. The satellite ground system receives the satellite telemetry data, processes it in real time, and transmits the telemetry values ​​of selected points in the system's internal network. The command transmission and control software determines the command data comparison result based on the telemetry values ​​and completes the satellite command comparison (large-loop comparison). Only after the satellite command large-loop comparison is correct does it begin transmitting the next frame of command data.

[0032] Furthermore, the framing of satellite payload command chain data is based on the interface control file between the satellite and the ground system;

[0033] All satellite commands are represented in hexadecimal code. The second-to-last byte of each command contains a Cyclic Redundancy Check (CRC) code, which serves as the basis for consistency judgment between the command transmission and control software and the ground control station's data receiving software. The third-to-last byte of each command in the command chain contains a checksum, which serves as the basis for comparison between the command transmission and control software and the telemetry data. The checksum is calculated as follows: starting from the remote control packet header, each command data packet is paired and XORed with odd-numbered bytes and even-numbered bytes. The result is converted to hexadecimal and placed in the third-to-last and fourth-to-last bytes. When the command transmission and control software compares the received telemetry data and checksum with the checksum in the command data, if they match, the command data is considered correctly transmitted; otherwise, it is considered incorrectly transmitted. The mechanism of the logical XOR operation is that if the two values ​​are different, the result is 1; if the two values ​​are the same, the result is 0.

[0034] Inversion refers to translating the hexadecimal command data used to control the satellite into content about the satellite's operation that operators can understand, based on the satellite-to-ground system interface control documents.

[0035] Furthermore, the telemetry point selection is completed through telemetry inversion software, which is one of the software programs of the ground system;

[0036] The satellite ground control station receives satellite telemetry signals, transmits them to the ground system through the service network, and converts them into data frame format; the telemetry inversion software receives the telemetry data and converts it into user-oriented satellite telemetry data names;

[0037] Selecting key satellite telemetry data refers to selecting the most important satellite telemetry data from all satellite telemetry data, manually configuring the selection process, and then transmitting the data to the command and control software via the ground system's internal network.

[0038] This invention provides a method for compiling and controlling satellite payload command chains, solving the technical problem of how to flexibly compile and adjust payload commands to improve control efficiency. It provides control and mission adjustment support for satellite operation and control personnel. During command compilation, a distinction is made between general and dedicated command chains. During command chain control, telemetry data reflecting the correct execution of satellite commands is transmitted to the command control software via software. The software automatically performs a large-scale comparison to determine the command transmission status, eliminating reliance on manual comparison, saving labor costs, avoiding errors caused by manual comparison, and improving the efficiency of command control and control status determination. During command control, the next command is automatically sent only if the command control software automatically determines it is correct; if the determination is incorrect, the control process is automatically stopped, prompting the operator to check the system operation. In the dedicated command chain compilation process, commands are generated and composed of command chains by calling pre-set command templates. CRC checksums and SUM checks are used in the command data to ensure the correctness of command transmission between various systems, such as ground and satellite-to-ground communication. Attached Figure Description

[0039] Figure 1 This is a flowchart illustrating a method for compiling and controlling a satellite payload command chain, as provided by the present invention.

[0040] Figure 2 This is a schematic diagram of the instruction issuance and control processing flow. Detailed Implementation

[0041] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0042] Example 1

[0043] The basic concept of this invention is to improve the ground system by dividing satellite commands into two categories. One category consists of general commands used in all missions, whose command codes are fixed and therefore pre-stored in a command database. The other category comprises dedicated commands tailored to the specific requirements of the satellite payload's missions, generated using command generation software before each mission. These two types of commands are combined as needed to form command chains, supporting batch command issuance and control to control the satellite's mission execution. The command issuance and control software can automatically compare command telemetry information, eliminating the need for manual comparison of each command and reducing command issuance and control time.

[0044] As a technical solution for realizing the basic concept of this invention, such as Figure 1-2 As shown, Embodiment 1 of the present invention discloses a method for compiling a satellite payload command chain, including:

[0045] Set the satellite payload commands into general commands and special commands;

[0046] The general instructions are pre-stored in the instruction database and are used to turn on and off the satellite units used each time the satellite operates its services; for example, power on / off instruction chains, payload on / off instruction chains, and data transmission subsystem on / off instruction chains. The content of the general instructions does not change with the actual service requirements in the payload mission plan.

[0047] The dedicated instructions are generated in real time according to business needs and are used to configure the parameters of a satellite unit by modifying its data storage area. The instruction code of each instruction is a fixed hexadecimal code that conforms to the instruction composition rules of this type of satellite and changes according to the changes in business needs in the payload mission plan.

[0048] Based on the operational requirements in the payload mission plan, the corresponding general instructions in the instruction database are read and combined with the special instructions generated in real time in sequence to generate a satellite payload instruction chain based on this payload mission plan, and then stored in the instruction database.

[0049] Furthermore, the method for compiling and generating the satellite payload instruction chain based on this mission specifically includes the following steps:

[0050] Step 1: Generate payload mission plan: Based on the satellite orbital elements, calculate the overlap between the satellite's effective payload coverage area and the mission target area during the mission time by extrapolating changes in the satellite's orbit, generate the payload mission plan, and store the payload mission plan in the database; where the satellite orbital elements represent the satellite's position in its orbit at a certain moment, and can be used to extrapolate the satellite's future orbital situation;

[0051] Step 2: Generate a load task plan: The load task scheme and load task plan conversion template in the planning software will convert the received load task scheme into a load task plan represented by an XML file.

[0052] Step 3: Generate Satellite Payload Command Chain: The command compilation software reads the XML file of the payload mission plan, calls the general command template and the special command template, reads the general commands corresponding to the business requirements of the payload mission plan from the command database, and combines them with the special commands corresponding to the business requirements of the payload mission plan generated in real time in a chronological order to compile and generate the satellite payload command chain based on the current mission plan, and stores it in the command database.

[0053] The payload mission plan in step one describes the main state of the satellite within a specified time period, and includes: payload operation sequence, data transmission operation sequence, satellite attitude parameters, and mission target area; wherein...

[0054] The specific content of the load working sequence includes the load working time period, load working mode, and load parameter configuration; the specific content of the data transmission working sequence includes the data transmission working time period, data transmission working mode, and data transmission parameter configuration; the load working sequence is displayed in the software interface showing the parameter configuration and working time period of the effective load; the data transmission working sequence is displayed in the software interface showing the parameter configuration and working time period of the data transmission subsystem; the specific content of the load working sequence and the data transmission working sequence are expressed in the form of XML files, and the parameter configuration types and value ranges are all specified according to the XSD file specification; XML files are Extensible Markup Language (XML), which is widely used for data information exchange between computer systems or software, and is used to describe the characteristics of the exchanged data.

[0055] The satellite attitude parameters are the spatial pointing state of the satellite body in its orbit. They are calculated based on the latest orbital elements, the mission target area, and the coverage area of ​​the payload. The satellite orbital elements are provided by the relevant satellite platform telemetry and control unit. They are parameters describing the satellite's orbit obtained by measuring the satellite using ground telemetry and control equipment. They are expressed as six orbital elements or double-row orbital elements (TLE).

[0056] The target area of ​​the mission is selected according to its business requirements, and is represented as a certain area on the ground selected by a quadrilateral. Specifically, it is described by the latitude and longitude coordinates of the four vertices of the quadrilateral on the earth. The business requirements are the task requirements in XML file format submitted by the business requirements submission software to the requirements processing software. They describe the requirements for the satellite's working status during the mission time period and consist of the mission execution time period, mission type, mission objectives, the single-machine parameter configuration of the payload used, and data transmission time.

[0057] In step two, the conversion template between the load task scheme and the load task plan in the planning software is pre-set to the format of the load task plan XML file, and a correspondence is established between the XML file and the various contents of the load task scheme. When generating the load task plan, the planning software reads the data table of the load task scheme from the database, fills in the contents of the load task scheme according to the XML file format, and generates the load task plan.

[0058] The payload task plan, represented by an XML file, specifies the format and content through the interface control file between the planning software and the instruction planning software; the content includes, but is not limited to, task type, single machine used, single machine parameters, and working time period;

[0059] After receiving the payload task plan, the planning software reads the parameters from each work sequence in the payload task plan and generates an XML file of the payload task plan according to the XML file format of the interface control file specification.

[0060] In step three, the general instruction template pre-sets the correspondence between each task type in the payload mission plan and the satellite unit to be used. When the instruction compilation software receives the XML file of the payload mission plan, it first reads the task type described in the file, obtains the satellite unit corresponding to the task type according to the mapping relationship in the general instruction template, and reads the general instructions for starting and stopping the corresponding satellite unit from the instruction database to form the general instruction chain of this payload mission plan.

[0061] In the dedicated instruction template, the instruction code format and parameter configuration rules of the dedicated instructions are set according to the interface control file between the satellite and the ground system. During the instruction compilation process, the instruction compilation software reads the single-machine parameters in the payload mission plan, calls the dedicated instruction template, and finds the corresponding instruction code in the dedicated instruction template according to the single-machine name and parameter value to complete the compilation of the dedicated instructions. It then combines the dedicated instructions with the general instruction chain to form the satellite payload instruction chain based on the current payload mission plan and stores it in the instruction database.

[0062] In step three, the satellite payload command chain is a hexadecimal code developed based on the satellite-ground system interface control file to control each individual unit of the satellite.

[0063] Interface control files describe the specific content, format, size, range, protocol, and transmission method of information exchange between software or systems. They specify the instruction data format and parameter value range used by each control action of all individual units of the satellite.

[0064] In Example 1, a method for compiling a real-time command chain for satellite payloads was developed. This real-time command chain solves the problems of delayed commands not being able to be adjusted in a timely manner according to changes in mission requirements, and the complexity of the real-time command issuance and control process. Using delayed commands to control the satellite, when service requirements change during mission execution, it is necessary to first clear the satellite's pre-stored delayed commands, and then send the new mission commands to the satellite to start the next mission. This process is complex and time-consuming. Using real-time commands to control the satellite, commands cannot be sent to the satellite in batches, resulting in long processing times. The command chain approach supports batch issuance and control of satellite commands, simplifying the issuance and control process and improving the flexibility of satellite control. For example, when the satellite is carrying out a mission, the following operations on the satellite need to be completed through commands:

[0065] ① Service load power on: This is used to turn on the service load power switch and supply power to the load.

[0066] ② Heater control, used to maintain a suitable temperature for the satellite during operation;

[0067] ③ Service payload unit activation: This is used to activate the service payload unit, allowing the satellite to carry out its missions.

[0068] ④ Service payload stand-alone configuration, used to configure the service payload stand-alone parameters to meet task requirements;

[0069] ⑤ Data transmission unit startup: This is used to turn on the data transmission unit. The satellite transmits mission-related data to the ground system through the operation of the data transmission unit.

[0070] ⑥ Data transmission stand-alone configuration, used to configure the parameters of the data transmission stand-alone unit to meet the needs of the task;

[0071] ⑦ Mission execution begins, used to initiate the satellite mission and control the mission execution time as needed;

[0072] ⑧ Data transfer machine shutdown: Used to turn off the data transfer machine after the task is completed;

[0073] ⑨ Service payload standby shutdown: Used to shut down the service payload standby after the task is completed;

[0074] ⑩ Service payload power off: Used to turn off the service payload power after the task is completed.

[0075] Based on the above operations, the real-time command chain composed of satellite general commands includes: the service payload power-on command chain, the heater control command chain, the service payload stand-alone power-on command chain, the data transmission stand-alone power-on command chain, the data transmission stand-alone power-off command chain, the service payload stand-alone power-off command chain, and the service payload power-off command chain. Satellite-specific commands include: service payload stand-alone configuration commands, data transmission stand-alone configuration commands, and mission start commands. These two categories constitute the payload command chain.

[0076] Example 2

[0077] The present invention also provides a method for controlling the launch of a satellite payload command chain, comprising: reading the satellite payload command chain based on the current payload mission plan from the command database;

[0078] The satellite payload command chain data is framed and its content is inverted. The inversion results are then constrained and verified. Once verified, the data is forwarded to the command control software. Framed data is the process of combining command data into data frames, which are the carriers of information transmitted over the network.

[0079] Operators send satellite payload command data to the satellite via command transmission and control software;

[0080] The command transmission and control software receives satellite telemetry data to check the correctness of each satellite payload command. It compares the data with the telemetry data; if they match, the command is considered correctly transmitted and the next command is automatically sent. If they don't match, an error is considered, or the transmission process is interrupted if no satellite telemetry data is received within a certain time. Telemetry data reflects the operational status of various satellite components. It is transmitted from the satellite to the ground control station via an information transmission channel, and then from the ground control station to the satellite ground system via the operational network.

[0081] Furthermore, the command issuing and control software and the ground telemetry and control station command data receiving software follow the interface control document agreement, which specifies the command data transmission format, transmission protocol and transmission method;

[0082] The command transmission and control uses the UDP protocol. After clicking the command transmission and control button, the software automatically sends each command data in the command chain three times. After receiving the command data, the ground control station command data receiving software performs a consistency check by comparing the CRC information to verify whether three frames of data have been received. Only when at least two completely identical frames of command data are received will a command confirmation message be returned to the command transmission and control software. After receiving the command confirmation message, the next frame of data will be sent. Otherwise, the software will wait for the command confirmation message from the ground control station command data receiving software until the command timeout period expires, at which point a command transmission failure message will be displayed.

[0083] The ground control station receives command data in real time, verifies its correctness, and then transmits the command data to the satellite. Simultaneously, it monitors the transmission status of the command data, generates small-loop comparison data, and sends the small-loop comparison results to the command transmission and control software. At the same time, the ground control station receives satellite telemetry data and transmits it to the satellite ground system in real time. The satellite ground system receives the satellite telemetry data, processes it in real time, and transmits the selected telemetry values ​​in its internal network. The command transmission and control software determines the command data comparison result based on the telemetry values ​​and completes the large-loop comparison of the satellite command data. Only after the large-loop comparison of the satellite command data is correct does it begin transmitting the next frame of command data.

[0084] Furthermore, the framing of satellite payload command chain data is based on the interface control file between the satellite and the ground system;

[0085] All satellite commands are represented in hexadecimal code. The second-to-last byte of each command contains a Cyclic Redundancy Check (CRC) code, which serves as the basis for consistency judgment between the command transmission and control software and the ground control station's data receiving software. The third-to-last byte of each command in the command chain contains a checksum, which serves as the basis for comparison between the command transmission and control software and the telemetry data. The checksum is calculated as follows: starting from the remote control packet header, each command data packet is paired and XORed with odd-numbered bytes and even-numbered bytes. The result is converted to hexadecimal and placed in the third-to-last and fourth-to-last bytes. When the command transmission and control software compares the received telemetry data and checksum with the checksum in the command data, if they match, the command data is considered correctly transmitted; otherwise, it is considered incorrectly transmitted. The mechanism of the logical XOR operation is that if the two values ​​are different, the result is 1; if the two values ​​are the same, the result is 0.

[0086] Inversion refers to translating the hexadecimal command data used to control the satellite into content about the satellite's operation that operators can understand, based on the satellite-to-ground system interface control documents.

[0087] Furthermore, the telemetry point selection is completed through telemetry inversion software, which is one of the software programs of the ground system;

[0088] The satellite ground control station receives satellite telemetry signals, transmits them to the ground system through the service network, and converts them into data frame format; the telemetry inversion software receives the telemetry data and converts it into user-oriented satellite telemetry data names;

[0089] Selecting key satellite telemetry data refers to selecting the most important satellite telemetry data from all satellite telemetry data, manually configuring the selection process, and then transmitting the data to the command and control software via the ground system's internal network.

[0090] In Example 2, software-based control software determines the command issuance status and automatically issues control commands based on the determination, replacing manual judgment and manual command issuance. This improves command issuance efficiency and reduces the risk of errors during the issuance process. In use, operators initiate the command issuance process through the command issuance software:

[0091] ① During the power-on command chain of the transmission and control service payload, following the above process, after the first command in the command chain is sent to the ground telemetry and control station for three consecutive frames;

[0092] ② After receiving the command data, the ground control station command data receiving software compares the CRC information to determine the consistency and verify whether three frames of data have been received. Only when at least two completely identical frames of command data are received will the command confirmation information be returned to the command sending and control software.

[0093] ③ The ground control station receives command data in real time, and after determining that the command data is correct, it sends the command data to the satellite. At the same time, it detects the command data transmission status, generates command small-loop comparison data, and sends the small-loop comparison results to the command transmission and control software. The satellite receives the command, processes it, and enables the payload power supply to respond. Meanwhile, the ground control station receives satellite telemetry data and sends it to the satellite ground system in real time.

[0094] ④ The satellite ground system receives satellite telemetry data, processes it in real time, and transmits the telemetry values ​​of selected points in the system's internal network; the command transmission and control software determines the command data comparison results based on the telemetry values ​​and completes the large-scale comparison of satellite commands.

[0095] ⑤ After the instruction control software determines that the large-loop comparison is correct, it sends the next instruction until all instructions have been issued and controlled.

[0096] To verify the overall effectiveness of this invention, a scenario with the same payload on a satellite was set up, and the old real-time / delayed command method was compared with the method of this invention. Because the method of this invention uses software to compare the verification information (CRC code and checksum) of the satellite's transmission control, instead of the manual method of "selecting a command to send – manually comparing verification information – selecting the next command to send," the transmission interval of a single command is approximately equal to the satellite's set command interval for data transmission between satellite and ground, shortening the command transmission time for a single mission. Specifically, according to the old command mode, sending 100 command data takes approximately 30 minutes; using the method of this invention, the software automatically sends control commands and determines the command transmission status, controlling the command transmission interval to 8 to 10 seconds. Executing the same command transmission for the same mission takes only about 18 minutes, and the operator only needs to monitor whether the command transmission process is completed, without needing to participate in determining the transmission status. Furthermore, because real-time command control of the satellite payload is adopted, the satellite does not pre-store commands. When mission adjustments are needed, adjustment commands can be sent in real time as required, without having to adjust all commands, thus improving the flexibility of satellite control. In terms of ground system command issuance and control, telemetry values ​​that can reflect the commonalities of command issuance are selected from a large amount of telemetry data as comparison criteria, which balances comparison effectiveness and efficiency, saves manpower costs, and reduces command issuance and control time.

[0097] This invention provides a method for compiling and controlling the transmission of satellite payload command chains, solving the technical problem of how to flexibly compile and adjust payload commands to improve transmission efficiency. It provides control and mission adjustment support for satellite operation and control personnel. During command compilation, a distinction is made between general command chains and dedicated command chains. During command chain transmission, telemetry data reflecting the correct execution of satellite commands is transmitted to the command transmission software via software. The software automatically performs a large-scale comparison to determine the command transmission status, eliminating reliance on manual comparison, saving labor costs, avoiding errors caused by manual comparison, and improving the efficiency of command transmission and control status determination. During command transmission, the next command is automatically sent only if the command transmission software automatically determines it is correct; if the determination is incorrect, the transmission process is automatically stopped, prompting the operator to check the system operation. In the dedicated command chain compilation process, commands are generated and composed of command chains by calling pre-set command templates. CRC checksums and SUM checks are used in the command data to ensure the correctness of command transmission between systems.

[0098] The sequence numbers of the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0099] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that the present invention is not limited to the described order of actions, because according to the present invention, some steps can be performed in other orders or simultaneously. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to the present invention.

[0100] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A method for compiling a satellite payload command chain, characterized in that, include: Set the satellite payload commands into general commands and special commands; The general instructions are pre-stored in the instruction database and are used to turn on and off the satellite unit used each time the satellite operates a service. The dedicated instructions are generated in real time according to business needs and are used to configure the parameters of a satellite unit by modifying its data storage area. Based on the business requirements in the payload mission plan, read the corresponding general instructions from the instruction database and combine them with the special instructions generated in real time in sequence to generate a satellite payload instruction chain based on this payload mission plan, and store it in the instruction database; The method for developing and generating the satellite payload command chain based on this mission specifically includes the following steps: Step 1: Generate payload mission plan: Based on the satellite orbit elements, calculate the overlap between the satellite's effective payload coverage area and the mission target area during the mission time by extrapolating changes in the satellite orbit, generate the payload mission plan, and store the payload mission plan in the database; Step 2: Generate a load task plan: The load task scheme and load task plan conversion template in the planning software will convert the received load task scheme into a load task plan represented by an XML file. Step 3: Generate satellite payload instruction chain: The instruction compilation software reads the XML file of the payload mission plan, calls the general instruction template and the special instruction template, reads the general instructions corresponding to the business requirements of the payload mission plan from the instruction database, and combines them with the special instructions corresponding to the business requirements of the payload mission plan generated in real time in a time sequence to compile and generate the satellite payload instruction chain based on the current mission plan, and stores it in the instruction database. In step three, the general instruction template pre-sets the correspondence between each mission type in the payload mission plan and the satellite units required. When the instruction compilation software receives the XML file of the payload mission plan, it first reads the mission type described in the file, obtains the corresponding satellite unit according to the mapping relationship in the general instruction template, and reads the general instructions for starting and stopping the corresponding satellite unit from the instruction database to form the general instruction chain for this payload mission plan. In the dedicated instruction template, the instruction code format and parameter configuration rules of the dedicated instructions are set according to the interface control file between the satellite and the ground system. During the instruction compilation process, the instruction compilation software reads the unit parameters in the payload mission plan, calls the dedicated instruction template, finds the corresponding instruction code in the dedicated instruction template according to the unit name and parameter value, completes the compilation of the dedicated instructions, combines them with the general instruction chain to form the satellite payload instruction chain based on this payload mission plan, and stores it in the instruction database.

2. The method as described in claim 1, characterized in that, The payload mission plan in step one describes the main state of the satellite within a specified time period, and its contents include: payload working sequence, data transmission working sequence, satellite attitude parameters, and mission target area; wherein... The specific content of the load working sequence includes the load working time period, load working mode, and load parameter configuration; the specific content of the data transmission working sequence includes the data transmission working time period, data transmission working mode, and data transmission parameter configuration; the load working sequence is displayed in the software interface as the parameter configuration and working time period of the effective load; the data transmission working sequence is displayed in the software interface as the parameter configuration and working time period of the data transmission subsystem; at the same time, the specific content of the load working sequence and the data transmission working sequence are expressed in the form of XML files, and the parameter configuration types and value ranges are all specified through XSD files; The satellite attitude parameters refer to the spatial pointing state of the satellite in its orbit. They are calculated based on the latest orbital elements, the mission target area, and the coverage area of ​​the payload. Among them, the satellite orbital elements are parameters describing the satellite's orbital status. They are provided by the relevant satellite platform telemetry and control unit and are obtained by measuring the satellite using ground telemetry and control equipment. They are expressed using six orbital elements or double orbital elements. The target area of ​​the mission is selected according to its business requirements, and is represented as a certain area on the ground selected by a quadrilateral, which is described by the latitude and longitude coordinates of the four vertices of the quadrilateral on the earth; the business requirements are the task requirements in XML file format submitted by the business requirements submission software to the requirements processing software, which describe the requirements for the satellite's working status during the mission time period, and consist of the mission execution time period, mission type, mission objectives, the single-machine parameter configuration of the payload used, and data transmission time.

3. The method as described in claim 1, characterized in that, In step two, the conversion template between the load task scheme and the load task plan in the planning software is pre-set to the format of the load task plan XML file, and a correspondence is established between the XML file and the various contents of the load task scheme. When generating the load task plan, the planning software reads the data table of the load task scheme from the database, fills in the contents of the load task scheme according to the XML file format, and generates the load task plan. The payload task plan, represented by an XML file, specifies the format and content through the interface control file between the planning software and the instruction planning software; the content includes, but is not limited to, task type, single machine used, single machine parameters, and working time period; After receiving the payload task plan, the planning software reads the parameters from each work sequence in the payload task plan and generates an XML file of the payload task plan according to the XML file format of the interface control file specification.

4. The method as described in claim 1, characterized in that, In step three, the satellite payload command chain is a hexadecimal code developed based on the satellite-ground system interface control file to control each individual unit of the satellite. Interface control files describe the specific content, format, size, range, protocol, and transmission method of information exchange between software or systems. They specify the instruction data format and parameter value range used by each control action of all individual units of the satellite.

5. A method for controlling the transmission of a satellite payload command chain, characterized in that, include: Read the satellite payload instruction chain generated from the instruction database using the satellite payload instruction chain compilation method as described in any one of claims 1-4, based on the current payload mission plan; The satellite payload command chain data is framed and its content is inverted. The inversion results are then constrained and verified. Once the verification is successful, the data is forwarded to the command control software. Operators send satellite payload command data to the satellite via command transmission and control software; The command transmission and control software receives the satellite telemetry data sent by the point of origin to check whether the command is correct. It compares each satellite payload command with the satellite telemetry data to see if they are consistent. If they are consistent, the command data is determined to be sent correctly, and the next command data is sent automatically. If they are inconsistent, the transmission is determined to be incorrect. If no satellite telemetry data is received within a certain period of time, the transmission process is interrupted.

6. The method as described in claim 5, characterized in that, The command transmission and control software and the ground telemetry and control station command data receiving software follow the interface control document agreement, which specifies the transmission format, transmission protocol and transmission method of command data; The command transmission and control uses the UDP protocol. After clicking the command transmission and control button, the software automatically sends each command data in the command chain three times. After receiving the command data, the ground control station command data receiving software performs a consistency check by comparing the CRC information to verify whether three frames of data have been received. Only when at least two completely identical frames of command data are received will a command confirmation message be returned to the command transmission and control software. After receiving the command confirmation message, the next frame of data will be sent. Otherwise, the software will wait for the command confirmation message from the ground control station command data receiving software until the command timeout period expires, at which point a command transmission failure message will be displayed. The ground control station receives command data in real time, verifies its correctness, and then transmits the command data to the satellite. Simultaneously, it monitors the transmission status of the command data, generates small-loop comparison data, and sends the small-loop comparison results to the command transmission and control software. At the same time, the ground control station receives satellite telemetry data and transmits it to the satellite ground system in real time. The satellite ground system receives the satellite telemetry data, processes it in real time, and transmits the selected telemetry values ​​in its internal network. The command transmission and control software determines the command data comparison result based on the telemetry values ​​and completes the large-loop comparison of the satellite command data. Only after the large-loop comparison of the satellite command data is correct does it begin transmitting the next frame of command data.

7. The method as described in claim 5 or 6, characterized in that, The framing of satellite payload command chain data is based on the interface control file between the satellite and the ground system. All satellite commands are represented in hexadecimal code: the second to last byte of each command is a cyclic redundancy check (CRC) code, which serves as the basis for consistency judgment between the command transmission and control software and the ground control station data receiving software; the third to last byte of each command in the command chain is a checksum, which serves as the basis for comparison between the command transmission and control software and the telemetry data; the checksum is calculated as follows: starting from the remote control packet header, each command data is paired and a logical XOR operation is performed between odd-numbered bytes and between even-numbered bytes, and the result is converted into a hexadecimal number and placed in the third to last byte; when the command transmission and control software compares the received telemetry data and checksum with the checksum in the command data, if they match, the command data is considered correctly transmitted; if they do not match, the command data is considered incorrectly transmitted; the mechanism of the logical XOR operation is that if the two values ​​are not the same, the result is 1; if the two values ​​are the same, the result is 0. Inversion refers to translating the hexadecimal command data used to control the satellite into information about the satellite's operational status, based on the satellite-ground system interface control documents.

8. The method as described in claim 5, characterized in that, The selection of telemetry points is accomplished using telemetry inversion software, which is one of the software programs of the ground system. The satellite ground control station receives satellite telemetry signals, transmits them to the ground system through the service network, and converts them into data frame format; the telemetry inversion software receives the telemetry data and converts it into user-oriented satellite telemetry data names; Selecting key satellite telemetry data refers to selecting the most important satellite telemetry data from all satellite telemetry data, manually configuring the selection process, and then transmitting the data to the command and control software via the ground system's internal network.

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