Satellite autonomous Q / V feed link establishment method based on program control instruction group

Abstract

The invention discloses a satellite autonomous feed link establishment method based on a program control instruction group, which comprises the following steps of: autonomously performing power-on, configuration and power-off operations on a load single machine according to the program control instruction group and link establishment table information by taking satellite integrated electronics as a control center; meanwhile, the satellite integrated electronics broadcast the orbit and attitude information of the satellite to the load controller at a specific frequency, and the load controller calculates the rotation angle of the feed antenna mechanism, so that autonomous startup and shutdown and autonomous feed link establishment of the load are realized; and grouping the instructions according to task types, performing top injection, modification and deletion according to groups, and performing execution according to groups. Compared with a single delay instruction, the program control instruction group is more suitable for satellites with multiple load types, multiple task types and complex tasks, and has the advantages of being clear in classification, flexible in modification and reusable. The satellite autonomous feed link establishment method based on the program control instruction group can autonomously perform feed link establishment and link breaking actions according to the link establishment table, and has the advantages of autonomous operation and energy saving.

Description

Technical Field

[0001] The invention relates to the technical field of satellite autonomous operation, and in particular to a satellite autonomous Q / V feeding link building method based on a program-controlled instruction group. Background Art

[0002] The Q / V feeder link is a method of communicating between satellites and the ground using two electromagnetic wave segments, the Q band and the V band. Compared with the commonly used C, Ku and Ka bands, the use of the Q / V band for satellite communication has the advantages of high speed, wide bandwidth and large capacity. It is the preferred frequency band for high-throughput broadband communication systems and is of great significance for the construction of space-based broadband Internet constellations.

[0003] In November 2018, the plan for the second phase of Starlink's 7,518 satellites to use the Q / V band for constellation networking was approved by the Federal Communications Commission (FCC). In January 2020, Galaxy Aerospace successfully launched a low-orbit satellite constellation using the Q / V band for the first time, and successfully verified the communication rate, communication performance and other technologies and services in orbit. At present, domestic low-orbit satellite communication constellations widely use the Q / V band for high-speed, large-bandwidth satellite communications.

[0004] If the Q / V band is used for large-capacity, high-speed communications, the beam width needs to be designed into a narrow beam to achieve the effect of concentrated beam power. Therefore, the satellite Q / V antenna and the ground Q / V antenna need to be precisely aligned when in use. Similar to the commonly used measurement and control ephemeris in aerospace, the start time, end time, and target pointing position (latitude and longitude) of the satellite feed link establishment can be informed by filling in the feed link establishment table on the ground. However, due to onboard energy constraints and onboard unit heat dissipation constraints, some onboard units and boards are only turned on when working and should be turned off when not working. Therefore, it is necessary to complete the power-on and configuration of the unit / board before the start time of the link establishment, and to power off the unit / board after the end time of the link establishment; in addition, for the reflector feed antenna, the antenna pre-pointing work needs to be completed before accurately tracking the target ground station and conducting two-way communication. Such as Figure 1 As shown in the figure, the entire startup and configuration time of the relevant stand-alone / board and the antenna pre-pointing time are about X seconds. In order to maximize the use of the satellite visible time and achieve the maximum feed link establishment time T1-T0 (for a satellite at 1100 kilometers, the visible time is about 15 minutes), it is also necessary to use the delay command to complete a series of startup operations before the satellite enters the country and a series of shutdown operations after the satellite leaves the country, so that the feed can be visible. The arc segment can maintain the link establishment state.

[0005] For a low-orbit satellite at an altitude of 1,100 kilometers, it takes about 108 minutes to run one circle. There are about 6 visible periods in China every day, and each visible period is about 15 minutes. The feeding and link establishment task of each circle can be completed by injecting delay instructions one day in advance. However, due to the limited space for storing instructions on the satellite platform, it is necessary to inject delay instructions frequently (about once a day). For large-scale low-orbit satellite constellations, the number of injection delay instructions increases by orders of magnitude. Taking a satellite constellation composed of 108 low-orbit satellites as an example, assuming that there are L1 single-machine / board startup and configuration instructions related to one feeding and link establishment, and L2 shutdown instructions, and each satellite enters the country 6 times a day, the following Table 1 gives the number of feeding and link establishment of the constellation, and the number of injection startup and shutdown instructions. There are about 230,000 feeding and link establishment events each year. If the ground injection delay instruction method is continued for feeding and link establishment, it will bring a huge workload to the ground operation and control system, occupy a large amount of bandwidth resources for satellite-to-ground communication, and increase the cost of constellation system operation and maintenance.

[0006] Table 1

[0007] Summary of the invention

[0008] Regarding the conventional method of implementing satellite power feeding and link building through delay instructions, in large-scale low-orbit satellite constellation scenarios, due to the large number of times of power feeding and link building, frequent delay instructions occupy a large amount of satellite-ground measurement and control resources and satellite platform instruction storage space, while bringing a huge workload to the ground operation and control system, increasing the cost of constellation system operation and maintenance. Regarding the method of autonomously turning on and off payloads according to regions, in the power feeding and link building task scenario, there will be a problem that the power-on time is longer than the actual link building time, resulting in unnecessary energy consumption. The present invention makes full use of the satellite platform programmable instruction group function and provides a satellite autonomous Q / V power feeding and link building method based on the programmable instruction group.

[0009] The present invention provides a program-controlled instruction group mode, which groups instructions according to task types, and annotates, modifies, deletes, and executes them according to groups. Compared with a single delay instruction, the program-controlled instruction group is more suitable for satellites with multiple payload types, multiple task types, and complex tasks, and has the advantages of clear classification, flexible modification, and reusability. The satellite autonomous power feeding and link building method based on the program-controlled instruction group can autonomously perform power feeding, link building, and link breaking actions according to the link building table, and has the advantages of autonomous operation and energy saving.

[0010] The present invention provides a satellite autonomous power feeding and link building method based on a program-controlled instruction group. The satellite integrated electronics serves as a control center. According to the program-controlled instruction group and the link building table information, the satellite integrated electronics autonomously performs power-on, configuration and power-off operations on a single payload. At the same time, the satellite integrated electronics broadcasts the satellite orbit and attitude information to the payload controller at a specific frequency. The payload controller calculates the rotation angle of the feeding antenna mechanism to realize autonomous power on and off of the payload and autonomous power feeding and link building.

[0011] The specific implementation steps are as follows:

[0012] Step 1: The ground operation control records "Programmed Control Instruction Group 1" (task type: feed link start) and "Programmed Control Instruction Group 2" (task type: feed shutdown) and stores them in the satellite platform. This operation only needs to be performed once. If the instructions of the feed link task are changed, the programmed control instruction group can be modified by recording the remote control instructions;

[0013] Step 2: The ground operation control adds the "feed link table" to the satellite platform, which saves the link table and forwards it to the payload controller. The link table contains "link start time", "link end time", and "ground station latitude and longitude". A link table can contain the time information of N feed link establishments;

[0014] Step 3: The satellite platform calls the program control instruction group 1 according to the time information of the power supply link establishment table, and after reaching the power-on time (X seconds in advance of the "link establishment start time"), executes a series of power-on and configuration instructions to start the power supply link establishment. Generally, X is the number of seconds required for the power-on sequence to be executed, ensuring that the power-on action is completed at the "link establishment start time";

[0015] Step 4: The payload controller receives the feed link table forwarded by the satellite platform and saves it. It also calculates the rotation angle of the feed antenna mechanism based on the "ground station latitude and longitude" in the link table and the satellite orbit and attitude information broadcast by the satellite platform every second, and controls the feed antenna to pre-point and track the ground station.

[0016] Step 5: The satellite platform calls program-controlled instruction group 2 according to the time information of the feed chain table, and after the shutdown time ("chain end time" is delayed by Y seconds), executes a series of instructions to shut down the single machine / board related to the feed chain. Generally, Y is the time seconds reserved for the mechanism to return to the zero position after the feed chain is completed.

[0017] Preferably, step 1 comprises the following steps:

[0018] Step 1A: The ground operation control configures the command parameters of a series of commands (power-on commands, configuration commands, etc.) required for power feed link establishment, and configures the relative time interval for executing each command, and encapsulates them into the format of a program-controlled command group; configures the task type of the program-controlled command group to be "power feed link establishment start", as program-controlled command group 1;

[0019] Step 1B: The ground operation control configures the command parameters for a series of shutdown commands required for power supply disconnection, and configures the relative time interval for executing each command, encapsulates them into the format of a program-controlled command group, and configures the task type of the program-controlled command group to be "power supply shutdown", as program-controlled command group 2;

[0020] Step 1C: The ground operation control injects the program control instruction group 1 and the program control instruction group 2 to the satellite platform through the conventional measurement and control channel;

[0021] Step 1D: After receiving the program control instruction group, the satellite platform parses the task type of the program control instruction group, identifies whether it is a "feed link start" sequence or a "feed shutdown" sequence, and saves it in the non-volatile storage area of ​​the satellite platform;

[0022] Step 1E: If the instruction parameters or instruction quantity in the program-controlled instruction group need to be updated, the program-controlled instruction group is regenerated, the task type is configured, and the program-controlled instruction group is uploaded to the satellite platform to achieve the replacement of the program-controlled instruction group;

[0023] Preferably, step 2 comprises the following steps:

[0024] Step 2A: The ground operation and control simulates the satellite orbit parameters to predict the future visible time information of the satellite and the ground station, including "link establishment start time", "link establishment end time", and the corresponding "ground station latitude and longitude height" information;

[0025] Step 2B: The ground operation control encapsulates the satellite entry and exit time and ground station location information predicted in step 2A into the format of a feed link table;

[0026] Step 2C: The ground operation and control package the feed link table into the command format of satellite-to-ground communication and inject it into the satellite platform through the conventional measurement and control channel;

[0027] Step 2D: The satellite platform identifies and parses the feed link table as the time basis for autonomous operation, and forwards the feed link table to the payload controller.

[0028] Preferably, step 3 comprises the following steps:

[0029] Step 3A: The satellite platform compares the current on-board time with the time information in the feed link table to determine whether it is time to start up, that is, the "link start time" is advanced by X seconds. Generally, X is the number of seconds required to fully execute the boot sequence, ensuring that all boot and configuration actions have been completed after the "link start time" is reached, and the satellite-to-ground communication state is immediately entered;

[0030] Step 3B: If the onboard time reaches the power-on time, the satellite platform starts the program control instruction group 1 (task type: feed link start), and sets the start flag of the program control instruction group 1 to "valid".

[0031] Step 3C: The satellite platform iterates through all instructions in the program control instruction group 1, and executes the corresponding startup and configuration instructions in sequence according to the preset time intervals in the program control instruction group to complete the startup action.

[0032] Preferably, step 4 comprises the following steps:

[0033] Step 4A: The payload controller receives the feed link table forwarded by the satellite platform and saves it, and identifies the time information and ground station location information in the link table;

[0034] Step 4B: The payload controller receives the local satellite orbit and attitude information broadcast by the satellite platform every second;

[0035] Step 4C: The payload controller uses the local satellite's orbit and attitude information and the ground station position information in the link establishment table to calculate the angle that the feed antenna mechanism should rotate, control the feed antenna to perform pre-pointing, track the ground station, complete the link establishment action, and maintain the link establishment state;

[0036] Preferably, step 5 comprises the following steps:

[0037] Step 5A: The satellite platform compares the current on-board time with the time information in the feed link table to determine whether it is time to shut down, that is, the "link end time" is delayed by Y seconds. Generally, Y is the number of seconds reserved for the feed antenna mechanism to return to zero position, ensuring that the mechanism returns to zero position after the "link end time" is reached before shutting down the single machine / board;

[0038] Step 5B: If the onboard time reaches the shutdown time, the satellite platform starts the program control instruction group 2 (task type: power supply shutdown) and sets the start flag of the program control instruction group 2 to "valid".

[0039] Step 5C: The satellite platform iterates through all the instructions in the control instruction group 2, and executes the corresponding shutdown instructions in sequence according to the preset time intervals in the instruction group to complete the shutdown action.

[0040] The startup instruction sequence and shutdown instruction sequence are uploaded to the satellite platform in the form of a program-controlled instruction group. Each instruction in the program-controlled instruction group has a configuration parameter of relative execution time. The program-controlled instruction group has the advantage of one-time upload and repeated use.

[0041] The satellite platform identifies the power feed link table, and autonomously calls the corresponding program-controlled instruction group according to the "link start time" and "link end time" in the power feed link table to power on, configure or power off the payload unit;

[0042] The satellite platform broadcasts satellite orbit information to the payload controller at a frequency of 1 Hz. The payload controller has the ability to calculate the rotation angle of the feed antenna mechanism based on the orbit and attitude information and the ground station position information, and control the antenna for pre-pointing and tracking.

[0043] Compared with the prior art, the present invention has the following beneficial effects:

[0044] 1. The present invention solves the management problem of the ground operation and control system caused by the hundreds of thousands of power-on and power-off management of the satellite-to-ground feeder link of a large-scale constellation each year;

[0045] 2. The application of the present invention improves the autonomous operation capability of the constellation system, saves the satellite platform instruction storage space, reduces the workload of the ground operation and control system, and reduces the operation and maintenance cost of the constellation system;

[0046] 3. The application of the present invention only turns on the relevant single machine / board card during the time period when power feeding and link establishment are required, thereby completing the task of on-orbit power feeding and link establishment while saving on-board energy to the maximum extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0048] Figure 1 This is a timing diagram of the satellite single-track feeding and link establishment task in the background technology.

[0049] Figure 2 A linked list format is built for the feed used in the present invention.

[0050] Figure 3 The present invention is a block diagram of the satellite autonomous power feeding and link building system. DETAILED DESCRIPTION

[0051] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0052] The present invention discloses a satellite autonomous feeding link building method based on a program-controlled instruction group, which realizes the autonomous link building of high-speed communication between large-scale constellation satellites and ground feeding stations. The method implementation device and method include satellite integrated electronics, a payload controller, a feeding controller, a feeding antenna, a feeding baseband, a measurement and control antenna, a space router, a ground feeding station, a ground measurement and control station, and a ground operation and control center.

[0053] Table 2 gives the format definition of the program-controlled instruction group of the present invention. The elements included in the program-controlled instruction group are "program-controlled instruction group ID", "number of instructions", "instruction execution time", and "instruction remote control package". Among them, the "program-controlled instruction group ID" represents the group number of the group of instructions. If the satellite integrated electronic storage space is sufficient, multiple groups of program-controlled instruction groups can be stored; "number of instructions" represents the number of instructions included in the group of program-controlled instruction groups; "instruction execution time" represents the execution time of the instruction, which is a relative time, and is the time value in seconds relative to the time when the group of instructions is started; "instruction remote control package" is the codeword of the instruction. A program-controlled instruction group can contain M instructions for executing a specific task. When in use, the instructions required to execute the task are added to the program-controlled instruction group according to the format, and the relative time interval for the execution of the instructions is configured.

[0054] Table 2

[0055]

[0056] Figure 2 The format of the link table used in the present invention is given. Similar to the satellite measurement and control ephemeris table, a link table can contain N segments of link information. The elements involved in the link table include "link table segment number", "link start time", "link end time", and "ground station longitude and latitude". Among them, the "link table segment number" uniquely identifies this segment of the link table, and the satellite stores and updates the content of the link table according to the segment number; the "link start time" represents the start time of the link table for this segment, that is, the start time when the satellite and the feed station are visible; the "link end time" represents the end time of the link table for this segment, that is, the time when the satellite and the feed station change from visible to invisible; the "ground station longitude and latitude" represents the ground station information that is linked to the satellite, including the longitude, latitude, and altitude of the ground station. The payload controller solves the mechanism pointing based on the information and sends it to the feed controller, thereby controlling the feed antenna to pre-point and track the ground station.

[0057] Figure 3The block diagram of the composition of the satellite autonomous feeding link building of the present invention is given. First, the operation and control center notes the startup program control instruction group and the shutdown program control instruction group to the satellite integrated electronics through the measurement and control station, and the satellite integrated electronics identifies and saves them; at the same time, the operation and control center predicts the future visible time of the satellite and the ground station according to the satellite orbit data, generates a feeding link building table, notes it to the satellite integrated electronics, and the integrated electronics saves and forwards it to the payload controller after receiving the link building table. Secondly, the satellite integrated electronics parses the program control instruction group and the feeding link building table, and sends the control instruction to the payload controller at the startup time ("link building start time" in advance of X seconds) according to the time information in the feeding link building table and the instruction information in the program control instruction group, and executes the startup link building task; sends the control instruction to the payload controller at the shutdown time ("link building end time" delayed by Y seconds), and executes the shutdown link breaking task. In addition, the satellite integrated electronics broadcasts the orbit and attitude data of the satellite to the payload controller through the control bus every second, and the payload controller solves the feeding antenna pointing according to the orbit and attitude information and the ground station position information, and controls the antenna rotation tracking. Finally, after the satellite feed antenna and the ground gateway complete the link communication, large-capacity data transmission and distribution can be carried out through the feed baseband and space router. Among them, the power-on program control instruction group and the power-off program control instruction group only need to be entered once, and the operation and control center only needs to regularly update the feed link table and enter it to the satellite to complete the daily feed link task.

[0058] The startup instruction sequence and shutdown instruction sequence are uploaded to the satellite platform in the form of a program-controlled instruction group. Each instruction in the program-controlled instruction group has a configuration parameter of relative execution time. The program-controlled instruction group has the advantage of one-time upload and repeated use.

[0059] The satellite platform identifies the power feed link table, and autonomously calls the corresponding program-controlled instruction group according to the "link start time" and "link end time" in the power feed link table to power on, configure or power off the payload unit;

[0060] The satellite platform broadcasts satellite orbit and attitude information to the payload controller at a frequency of 1 Hz. The payload controller has the ability to calculate the rotation angle of the feed antenna mechanism based on the orbit and attitude information and the ground station position information, and control the antenna for pre-pointing and tracking.

[0061] The present invention provides a program-controlled instruction group mode, which groups instructions according to task types, and annotates, modifies, deletes, and executes them according to groups. Compared with a single delay instruction, the program-controlled instruction group is more suitable for satellites with multiple payload types, multiple task types, and complex tasks, and has the advantages of clear classification, flexible modification, and reusability. The satellite autonomous power feeding and link building method based on the program-controlled instruction group can autonomously perform power feeding, link building, and link breaking actions according to the link building table, and has the advantages of autonomous operation and energy saving.

[0062] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A satellite autonomous Q / V feed link establishment method based on a program-controlled instruction group, characterized in that: The satellite integrated electronics serves as the control center. According to the program-controlled instruction group and the link-building table information, it autonomously powers on, configures, and shuts down the payload. At the same time, the satellite integrated electronics broadcasts the satellite's orbit and attitude information to the payload controller at a specific frequency. The payload controller calculates the rotation angle of the feed antenna mechanism to achieve autonomous power on / off and autonomous feed link building for the payload. The specific implementation steps are as follows: Step 1: The ground operation control records the program control instruction group 1 and the program control instruction group 2 pre-stored on the satellite platform. The task type of the program control instruction group 1 is: feed link start, and the task type of the program control instruction group 2 is: feed shutdown. This operation only needs to be performed once. If the instructions of the feed link task are changed, the program control instruction group can be modified by recording the remote control instructions. Step 2: The ground operation control uploads the feed link table to the satellite platform, which saves the feed link table and forwards it to the payload controller; the feed link table contains the link start time, link end time and the longitude and latitude of the ground station. One feed link table can contain the time information of N feed link establishments; Step 3: The satellite platform calls the program-controlled instruction group 1 according to the time information of the power-feeding link-building table, and executes a series of power-on and configuration instructions for starting power-feeding link-building after the power-on time is reached. The power-on time is X seconds in advance of the link-building start time, and X is the number of seconds required for the power-on sequence to be executed, ensuring that the power-on action is completed at the link-building start time; Step 4: The payload controller receives the feed link table forwarded by the satellite platform and saves it. It also calculates the rotation angle of the feed antenna mechanism based on the latitude and longitude of the ground station in the link table and the satellite orbit and attitude information broadcast by the satellite platform every second, and controls the feed antenna to pre-point and track the ground station. Step 5: The satellite platform calls the program-controlled instruction group 2 according to the time information of the feed chain establishment table, and executes a series of instructions to shut down the single machine / board related to the feed chain establishment after the shutdown time. The shutdown time is Y seconds after the end of the chain establishment, and Y is the time seconds reserved for the mechanism to return to the zero position after the feed chain establishment is completed.

2. According to claim 1, a satellite autonomous Q / V feed link establishment method based on a program-controlled instruction group is characterized in that: The step 1 comprises the following steps: Step 1A: The ground operation control configures the instruction parameters for a series of instructions required for the feed link establishment, wherein the series of instructions required for the feed link establishment include a power-on instruction, a configuration instruction, and configures the relative time interval for executing each instruction, and encapsulates the instructions into the format of a program-controlled instruction group; the task type of the program-controlled instruction group is configured as the feed link establishment start, as the program-controlled instruction group 1; Step 1B: The ground operation control configures the command parameters for a series of shutdown commands required for power supply disconnection, and configures the relative time interval for executing each command, encapsulates them into the format of a program-controlled command group, and configures the task type of the program-controlled command group to power supply shutdown, as program-controlled command group 2; Step 1C: The ground operation control injects the program control instruction group 1 and the program control instruction group 2 to the satellite platform through the conventional measurement and control channel; Step 1D: After receiving the program control instruction group, the satellite platform parses the task type of the program control instruction group, identifies whether it is a power feed link establishment start sequence or a power feed shutdown sequence, and saves it in the non-volatile storage area of ​​the satellite platform; Step 1E: If you want to update the instruction parameters or instruction quantity in the program-controlled instruction group, regenerate the program-controlled instruction group, configure the task type, and upload it to the satellite platform to achieve the replacement of the program-controlled instruction group.

3. A satellite autonomous Q / V feed link establishment method based on a program-controlled instruction group according to claim 2, characterized in that: The step 2 comprises the following steps: Step 2A: The ground operation and control performs simulation based on the satellite orbit parameters to predict the future visible time information of the satellite and the ground station, including the link establishment start time, link establishment end time, and the corresponding ground station latitude and longitude information; Step 2B: The ground operation control encapsulates the satellite entry and exit time and ground station location information predicted in step 2A into the format of a feed link table; Step 2C: The ground operation and control package the feed link table into the command format of satellite-to-ground communication and inject it into the satellite platform through the conventional measurement and control channel; Step 2D: The satellite platform identifies and parses the feed link table as the time basis for autonomous operation, and forwards the feed link table to the payload controller.

4. The satellite autonomous Q / V feed link establishment method based on a program-controlled instruction group according to claim 3, characterized in that: The step 3 comprises the following steps: Step 3A: The satellite platform compares the current onboard time with the time information in the feed link table to determine whether it is time to start the system. That is, the link start time is advanced by X seconds, where X is the number of seconds required to fully execute the boot sequence. This ensures that all boot and configuration actions have been completed when the link start time is reached, and the satellite-to-ground communication state is immediately entered. Step 3B: If the onboard time reaches the power-on time, the satellite platform starts the program control instruction group 1, the task type of the program control instruction group 1 is: feed link establishment start, and the start flag of the program control instruction group 1 is set to valid; Step 3C: The satellite platform iterates through all the instructions in the program control instruction group 1, and executes the corresponding power-on and configuration instructions in sequence according to the preset time intervals in the program control instruction group to complete the power-on action.

5. The satellite autonomous Q / V feed link establishment method based on a program-controlled instruction group according to claim 4, characterized in that: The step 4 comprises the following steps: Step 4A: The payload controller receives the feed link table forwarded by the satellite platform and saves it, and identifies the time information and ground station location information in the link table; Step 4B: The payload controller receives the local satellite orbit and attitude information broadcast by the satellite platform every second; Step 4C: The payload controller uses the local satellite’s orbit and attitude information and the ground station position information in the link establishment table to calculate the angle that the feed antenna mechanism should rotate, control the feed antenna to pre-point and track the ground station, complete the link establishment action, and maintain the link establishment state.

6. A satellite autonomous Q / V feed link establishment method based on a program-controlled instruction set according to claim 5, characterized in that: The step 5 comprises the following steps: Step 5A: The satellite platform compares the current on-board time with the time information in the feed link table to determine whether it is time to shut down, that is, the link end time is delayed by Y seconds, where Y is the number of seconds reserved for the feed antenna mechanism to return to zero position, to ensure that the mechanism returns to zero position after the link end time is reached before shutting down the single machine / board; Step 5B: If the onboard time reaches the shutdown time, the satellite platform starts the program control instruction group 2, the task type of the program control instruction group 2 is: power supply shutdown, and the start flag of the program control instruction group 2 is set to be valid; Step 5C: The satellite platform iterates through all the instructions in the control instruction group 2, and executes the corresponding shutdown instructions in sequence according to the preset time intervals in the instruction group to complete the shutdown action.

7. The satellite autonomous Q / V feed link establishment method based on a program-controlled instruction group according to claim 1, characterized in that: The power-on instruction sequence and the power-off instruction sequence are uploaded to the satellite platform in the form of a program-controlled instruction group. Each instruction in the program-controlled instruction group has a configuration parameter of relative execution time. The program-controlled instruction group has the advantage of one-time upload and repeated use.

8. The satellite autonomous Q / V feed link establishment method based on a program-controlled instruction group according to claim 1, characterized in that: The satellite platform identifies the feed link table, and autonomously calls the corresponding program-controlled instruction group according to the link start time and link end time in the feed link table to power on, configure or power off the payload unit.

9. The satellite autonomous Q / V feed link establishment method based on a program-controlled instruction group according to claim 1, characterized in that: The satellite platform broadcasts satellite orbit and attitude information to the payload controller at a frequency of 1 Hz. The payload controller has the ability to calculate the rotation angle of the feed antenna mechanism based on the satellite's orbit and attitude information and the ground station position information, and control the antenna for pre-pointing and tracking.

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