Method and system for autonomously generating satellite orbit control instruction and orbit control activity supervision table

Abstract

The invention relates to the technical field of spaceflight orbit control, and provides a method and system for autonomously generating a satellite orbit control instruction and orbit control activity supervision table in order to solve the problems that a traditional satellite orbit control process depends on manual operation and is low in efficiency and prone to errors. According to the method, non-orbit-control-period orbit data are obtained, an apogee moment sequence is automatically calculated according to set parameters such as task time, thruster working duration and an orbit transfer mode, intelligent grouping is carried out according to a continuous or intermittent orbit transfer strategy, and the orbital transfer efficiency is improved. A complete orbit control plan including a specific ignition time sequence, an orbit lifting instruction, a hexadecimal source code capable of being directly injected and related physical parameters is generated, finally, a reported ephemeris file and an orbit control activity supervision record table which meet the specification are output in a one-key mode, and automation and standardization of the whole process from task planning to instruction generation and document compiling are achieved. The method is especially suitable for a task scene in which a low-orbit satellite climbs an orbit by using a thruster after satellite-rocket separation.

Description

Technical Field

[0001] This invention belongs to the field of aerospace orbit control technology, specifically relating to a method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables. Background Technology

[0002] The higher the separation altitude of the satellite from the launch vehicle, the greater the cost for the satellite operator. Therefore, thruster-based orbit climbing is more cost-effective. The altitude difference between the separation orbit and the operational orbit results in a longer orbit deployment cycle and increased personnel investment. Traditional satellite orbit maneuvering procedures generally rely on orbit data transmitted via ground transit, generating orbit change commands through ground calculations, and uploading commands from ground stations. Since each orbit control command has many input parameters, long-term multi-track orbit control operations are quite cumbersome. In addition, an orbit control plan form needs to be filled out before each orbit control operation to report the orbit change plan. The submitted orbit control plan form has a prescribed data filling format, so long-term continuous orbit changes also incur manpower costs for filling out the orbit plan form. Therefore, generating orbit control commands autonomously and directly generating orbit control plan forms based on the commands can save manpower and avoid errors in command uploading caused by human factors each time. Summary of the Invention

[0003] This invention addresses the shortcomings of traditional satellite orbit control, which requires manual processing of command generation, injection, and plan table entry, resulting in time-consuming, labor-intensive, and error-prone processes. It proposes a method for the autonomous generation of satellite orbit control commands and orbit control activity monitoring tables. This method automatically generates orbit control commands, ephemeris files, and satellite orbit control activity monitoring records, supporting both continuous and intermittent orbit changes. The orbit control commands include physical parameters and hexadecimal code annotation files. The number of ephemeris days generated and the time interval between the orbit date and the orbit control mission start date are dynamically adjusted according to different orbit control plans. A satellite orbit control plan is generated based on the previously generated orbit control plan.

[0004] To achieve the above objectives, the present invention provides the following technical solution: In a first aspect, the present invention provides a method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables, the method comprising the following steps: Step 1: Acquire track data during non-track control periods; Step 2: Confirm the start and end times of the orbit control mission, as well as the thruster operating time, and select the number of days for ephemeris recursion after the orbit control ends. Confirm whether the orbit change is continuous or intermittent. If it is intermittent, confirm how many orbits to push and how many orbits to stop. Step 3: Generate the apogee time sequence using an algorithm for calculating apogee time; Step 4: Filter the generated apogee time series according to the mission start and end times; based on the filtered apogee times, group the time series according to continuous orbit change / intermittent orbit change to achieve a cycle of the thruster working continuously for a certain number of orbits and then stopping for a certain number of orbits. Step 5: Generate the track control time series based on Step 4, and generate the track lifting command based on the track control time series, as well as output 16 for track control source code and physical parameters; Step 6: Generate satellite ephemeris files and satellite orbit control activity monitoring record forms.

[0005] Furthermore, the above orbital data includes the six orbital data and the cumulative UTC seconds of the orbit in the downlink telemetry; including: semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, mean perigee, cumulative UTC seconds of the orbit, start and end time of orbit control mission, orbit control duration in min, number of orbits per group, number of orbits pushed in a group, input propulsion specific impulse and thrust, and satellite dry weight.

[0006] Furthermore, the specific calculation of the apogee time is as follows:

[0007] in, It is the angle of approach and is linearly related to time. , It is the average angular velocity. It is the moment when the satellite passes through its closest point to Earth. For the near point angle, The orbital eccentricity; At the apogee, the angle is closer to the perigee. According to Kepler's equations:

[0008] Obtain the angle of approach. Time corresponding to apogee time: The time of apogee is:

[0009]

[0010]

[0011] The apogee time is obtained by adding half an orbital period to the perigee time.

[0012] Furthermore, step 4 above specifically includes: Step 4.1: Preserve the apogee time series between the task start and end times; Step 4.2: Based on the apogee time series filtered in Step 4.1, the total number is recorded as count_orbit. If intermittent track control is required, all apogee time series are grouped into X tracks. Within each X track, the first k tracks are continuously changed, and track control stops on track Xk.

[0013] Furthermore, step 5 above specifically involves: generating the track control time series, splicing it into hexadecimal source code according to the track control instruction content, generating the track elevation instruction, and outputting hexadecimal source code and physical parameters.

[0014] Furthermore, step 6 above specifically includes: Step 6.1: Generate the ephemeris, which contains the satellite's position, velocity, and time; calculate the six elements based on the formula for the influence of small impulses on each element; calculate the satellite's position and velocity using Kepler elements; Step 6.2: Generate a satellite orbit control activity monitoring record table, read the time series from step 4.1, where duration is the orbit control duration, orbit_time-duration / 2 is the ignition time, and orbit_time+duration / 2 is the ignition end time.

[0015] Secondly, the method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables described in this invention can be entirely implemented using computer software. Therefore, correspondingly, this invention also provides a system for autonomously generating satellite orbit control commands and orbit control activity monitoring tables, the system comprising: Storage device used to acquire track data during non-track control periods; Used to confirm the start and end times of the orbit control mission, as well as the thruster operating time, and to select the number of days for ephemeris recursion after the orbit control ends, and to confirm whether the orbit change is continuous or intermittent. If it is intermittent, it is necessary to confirm the storage device for how many orbits to push and how many orbits to stop. Storage device for generating apogee time sequences using an algorithm for calculating apogee time; This device is used to filter the generated apogee time series based on the mission start and end times; and to group the time series according to continuous or intermittent orbit changes based on the filtered apogee times, thus realizing a cyclical storage device that allows the thruster to work continuously for a certain number of orbits before stopping for a certain number of orbits. A storage device for generating track control time series, generating track lifting commands based on track control time series, and outputting 16 track control source code and physical parameters; Storage device used to generate satellite ephemeris files and satellite orbit control activity monitoring records.

[0016] Thirdly, the present invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, performs a method for autonomously generating satellite orbit control instructions and orbit control activity monitoring tables as described in any of the preceding claims.

[0017] Fourthly, the present invention also provides a computer device, which includes a memory and a processor. The memory stores a computer program. When the processor runs the computer program stored in the memory, the processor executes the method for autonomously generating satellite orbit control instructions and orbit control activity monitoring tables as described in any one of the above claims.

[0018] The method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables provided by this invention has the following beneficial effects: (1) Supports the generation of consecutive instructions and indirect instructions; (2) Provide track control command parameters; (3) Provide the hexadecimal code annotation value for track control commands; (4) Provide the submitted ephemeris documents; (5) Provide a satellite orbit control activity monitoring record form for reporting, matching the standardized template for orbit control reporting materials; Specifically, this method employs a highly integrated automated process to first acquire orbital data during non-orbit control periods and confirm mission parameters (such as mission start and end times, thruster operating duration, and orbit change modes). Then, it uses algorithms to generate and filter apogee time sequences, intelligently grouping them to adapt to continuous or intermittent orbit change strategies. Based on this, it automatically generates orbit control time sequences, orbit increase commands, directly uploading hexadecimal source code, and related physical parameters. Finally, it outputs compliant reporting materials—namely, satellite ephemeris files and orbit control activity monitoring records—in a single step, thus achieving full automation and standardization from mission planning to command generation and document preparation.

[0019] This invention is particularly applicable to satellites that separate from rockets in low Earth orbit and use thrusters to climb to higher orbits. Attached Figure Description

[0020] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1This is a flowchart illustrating a method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables, as described in this embodiment of the invention. Figure 2 This is a flowchart illustrating how time series are grouped according to continuous or intermittent orbit changes based on the selected far-away locations as described in this embodiment of the invention. Figure 3 The track control commands described in the embodiments of this invention; Figure 4 The above-annotated source code for the track control commands described in this embodiment of the invention is shown in hexadecimal. Figure 5 The ephemeris described in the embodiments of the present invention; Figure 6 This refers to the satellite orbit control activity monitoring record form described in this embodiment of the invention. Figure 7 The apogee time as described in the embodiments of the present invention; Figure 8 The track control commands used in actual operation as described in the embodiments of the present invention; Figure 9 This is the hexadecimal source code of the track control commands used in actual operation as described in this embodiment of the invention. Detailed Implementation

[0022] The specific implementation details (such as experimental apparatus, operation procedures, data processing steps, and example parameters) of "a method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables" provided in this specification are primarily intended for illustrative purposes rather than limiting definitions, aiming to help those skilled in the art thoroughly understand the principles and implementation of the invention. However, those skilled in the art should understand that these details represent only one feasible embodiment, and the core concept of the invention can be fully realized through other technical means or alternative solutions not described in detail, without departing from its spirit and essence. Furthermore, the omission of details of conventional experimental methods and apparatus known in the art in the specification is to avoid redundant information interfering with the understanding of the innovation points. This does not mean that these known technologies are not required during implementation, and those skilled in the art should be able to supplement and apply them based on their professional knowledge.

[0023] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention.

[0024] Example 1, Combination Figure 1This embodiment addresses the shortcomings of traditional satellite orbit control, which requires manual processing of command generation, injection, and plan table entry, resulting in time-consuming, labor-intensive, and error-prone processes. It proposes a method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables. This method automatically generates orbit control commands, ephemeris files, and satellite orbit control activity monitoring records, supporting both continuous and intermittent orbit changes. The orbit control commands include physical parameters and hexadecimal code annotation files. The method dynamically adjusts the number of ephemeris days generated and the time interval between the orbit date and the orbit control mission start date based on different orbit control plans. A satellite orbit control plan is generated based on the previously generated orbit control plan.

[0025] The method flow is as follows: Figure 1 As shown, it includes the following steps: Step 1: Obtain track data during non-track control periods, i.e., the number of six track members and the cumulative UTC seconds of the track in the downlink telemetry data; Step 2: Confirm the start and end times of the orbit control mission, as well as the thruster operating time, and select the number of days for ephemeris recursion after the orbit control ends. Confirm whether the orbit change is continuous or intermittent. If it is intermittent, confirm how many orbits to push and how many orbits to stop. Step 3: Generate the apogee time sequence using an algorithm for calculating apogee time; Step 4: Filter the generated apogee time series according to the mission start and end times; based on the filtered apogee times, group the time series according to continuous orbit change / intermittent orbit change to achieve a cycle of the thruster working continuously for a certain number of orbits and then stopping for a certain number of orbits. Step 5: Generate the track control time series based on Step 4, and generate the track lifting command based on the track control time series, as well as output 16 for track control source code and physical parameters; Step 6: Generate satellite ephemeris files and satellite orbit control activity monitoring record forms.

[0026] The method proposed in this embodiment first acquires orbital data during the non-orbit control period and confirms mission parameters (such as mission start and end times, thruster operating duration, and orbit change mode) through a highly integrated automated process. Then, it uses algorithms to generate and filter apogee time sequences and intelligently groups them to adapt to continuous or intermittent orbit change strategies. Subsequently, it automatically generates orbit control time sequences, orbit increase commands, hexadecimal source code that can be directly uploaded, and related physical parameters based on these. Finally, it outputs compliant reporting materials in one stop—namely, satellite ephemeris files and orbit control activity monitoring records—thus achieving full automation and standardization from mission planning to command generation and even document preparation.

[0027] Example 2, Combination Figures 2 to 6This embodiment is a detailed explanation of the method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables as described in Embodiment 1 above. Steps 1 and 2: Confirm the input parameters: semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, mean perigee, cumulative UTC seconds of the orbit, start and end time of the orbit control mission, orbit control duration in min, number of orbits per group, number of orbits pushed in a group, input propulsion specific impulse and thrust, and satellite dry weight; Step 3.1: Calculate the time of apogee passage:

[0028] in, It is the angle of approach and is linearly related to time. , It is the average angular velocity. It is the moment when the satellite passes through its closest point to Earth. For the near point angle, The orbital eccentricity; At the apogee, the angle is closer to the perigee. Substituting into Kepler's equation:

[0029] Obtain the angle of approach. Time corresponding to apogee time: The time of apogee is:

[0030]

[0031]

[0032] That is, the apogee time is the perigee time plus half an orbital period.

[0033] The formula for calculating the apogee time for the entire 24 hours based on the time and mean anomaly angle corresponding to the initial orbit is:

[0034]

[0035] Step 4.1: Retain the apogee time sequence between the task start and end times; otherwise, delete it; represented by orbit_time; Step 4.2: As Figure 2 As shown, the total number of apogee time series selected in step 4.1 is counted as count_orbit. If intermittent track control is required, all apogee time series are grouped into X tracks. The first k tracks in the X track are continuously changed, and track control stops on track Xk. Step 5.1: Generate the track control time series, concatenate it into hexadecimal source code according to the track control command content, generate the track upgrade command, and output the hexadecimal source code and physical parameters; where the track control command is as follows: Figure 3 As shown, the hexadecimal source code of the track control command is as follows: Figure 4 As shown; Step 6.1: Generate the ephemeris, which contains the satellite's position, velocity, and time of motion. Calculate the six roots based on the formula for the influence of small impulses on each root number. The ephemeris is as follows: Figure 5 As shown,

[0036] Calculating satellite position and velocity using Kepler elements: The vectors in the orbital plane need to be transformed to the J2000 inertial frame through three rotations. The rotation matrix is:

[0037] in,

[0038]

[0039]

[0040] radial velocity component

[0041] Lateral velocity component

[0042] Polar coordinate orbit equations

[0043]

[0044]

[0045]

[0046]

[0047] Step 6.2: Generate as follows Figure 6 The satellite orbit control activity monitoring record table is shown. Read the time series from step 4.1, where `duration` is the orbit control duration, `orbit_time - duration / 2` is the ignition time, and `orbit_time + duration / 2` is the ignition end time.

[0048] Example 3, Combination Figures 5 to 9 This embodiment will be described in detail below with reference to specific implementation methods. This invention is a method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables.

[0049] like Figure 1 As shown, a flowchart of a method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables is provided, including the following steps: Steps 1 and 2: Confirm the input parameters: {7066873.50000,0.001368,0.96141000,0.64578,0.014429,0.339941,270687695,'2025-8-1 3:00:00','2025-8-1 08:00:00',20,2,1,1200,0.013,100} represents the semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, mean perigee, accumulated UTC seconds of the orbit, start and end time of the orbital control mission, orbital control duration in minutes, number of orbits per group, number of orbits pushed in a group, input propulsion specific impulse and thrust, and satellite dry weight; Step 3.1: Calculate the apogee time, such as Figure 7 As shown; Step 4.1: Filter the apogee time series between the task start and end times; Step 4.2: Based on the apogee time series selected in Step 4.1, the total number is recorded as 8. If intermittent track control is required, all apogee time series are grouped into groups of 4 tracks each. The first 3 tracks in the 4 tracks are continuously track-changed, track control is stopped on the 4th track, track control is continuously changed on the 5th, 6th, and 7th tracks, and track control is stopped on the 8th track. Step 5.1: Generate the track control time series, concatenate it into hexadecimal source code according to the track control command content, generate the track upgrade command, and output the hexadecimal source code and physical parameters. The track control command content is as follows: Figure 8 As shown, the hexadecimal source code is as follows: Figure 9 As shown.

[0050] Step 6.1: Calculate the satellite's position and velocity using Kepler elements, and output the result. Figure 5 The ephemeris shown Figure 6 The table shown is a record of monitoring satellite orbit control activities.

[0051] Example 4: The method for autonomously generating satellite orbit control commands and orbit control activity monitoring tables described in any of the above embodiments can be entirely implemented using computer software. Therefore, correspondingly, this embodiment provides a system for autonomously generating satellite orbit control commands and orbit control activity monitoring tables, the system comprising: Storage device used to acquire track data during non-track control periods; Used to confirm the start and end times of the orbit control mission, as well as the thruster operating time, and to select the number of days for ephemeris recursion after the orbit control ends, and to confirm whether the orbit change is continuous or intermittent. If it is intermittent, it is necessary to confirm the storage device for how many orbits to push and how many orbits to stop. Storage device for generating apogee time sequences using an algorithm for calculating apogee time; This device is used to filter the generated apogee time series based on the mission start and end times; and to group the time series according to continuous or intermittent orbit changes based on the filtered apogee times, thus realizing a cyclical storage device that allows the thruster to work continuously for a certain number of orbits before stopping for a certain number of orbits. A storage device for generating track control time series, generating track lifting commands based on track control time series, and outputting 16 track control source code and physical parameters; Storage device used to generate satellite ephemeris files and satellite orbit control activity monitoring records.

[0052] Example 5: This example provides a computer-readable storage medium storing a computer program. When the computer program is run by a processor, it executes a method for autonomously generating satellite orbit control instructions and orbit control activity monitoring tables as described in any of the above examples.

[0053] Those skilled in the art will understand that implementing all or part of the processes in the above embodiments can be accomplished by a computer program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. The storage medium can be a magnetic disk, optical disk, read-only memory (ROM), random access memory (RAM), flash memory, hard disk drive (HDD), or solid-state drive (SSD), etc.; the storage medium can also include combinations of the above types of memory.

[0054] Example 6: This example provides a computer device, which includes a memory and a processor. The memory stores a computer program. When the processor runs the computer program stored in the memory, the processor executes a method for autonomously generating satellite orbit control instructions and orbit control activity monitoring tables as described in any of the above examples.

[0055] This embodiment provides a computer device. This part of the hardware device is a general model and is not shown in the figure. The system includes a processor and a memory. The processor and the memory can be connected by a bus or other means. The memory, as a non-transitory computer-readable storage medium, can be used to store non-transitory software programs, non-transitory computer-executable programs and modules, as well as corresponding program instructions / modules. The processor executes various functional applications and data processing by running the non-transitory software programs, instructions and modules stored in the memory, so as to realize the method and steps of autonomously generating satellite orbit control instructions and orbit control activity monitoring tables in the above method embodiment.

[0056] The memory may include a program storage area and a data storage area, wherein the program storage area may store the operating system and applications required for at least one function; the data storage area may store data created by the processor, etc. Furthermore, the memory may include high-speed random access memory and may also include non-transitory memory, such as at least one disk storage device, flash memory device, or other non-transitory solid-state storage device. In some embodiments, the memory may optionally include memory remotely located relative to the processor, which can be connected to the processor via a network. Examples of such networks include, but are not limited to, the Internet, corporate intranets, mobile communication networks, and combinations thereof.

[0057] One or more modules are stored in the memory. When the processor executes, it performs the method steps in the embodiments. In this way, the invention objective can be achieved through the method, apparatus and process of the present invention. The specific details of the computer device described above can be understood by referring to the relevant descriptions and effects in the embodiments, and will not be repeated here.

[0058] The above description of the technical solution provided by the present invention through several specific embodiments is intended to highlight the advantages and benefits of the technical solution provided by the present invention. However, the above-described specific embodiments are not intended to limit the present invention. Any reasonable modifications and improvements to the present invention, reasonable combinations of implementation methods and equivalent substitutions based on the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for autonomous generation of satellite orbit control command and orbit control activity supervision table, characterized in that, The method is: Step 1: Obtain the orbit data during the non-orbit control period; Step 2: Confirm the start time and end time of the orbit control task, and confirm the working time of the thruster, and select the ephemeris prediction days after the end of the orbit control, confirm whether the continuous orbit change or the intermittent orbit change, if the intermittent orbit change, confirm the number of orbits after the thrust and the number of orbits after the stop; Step 3: Generate the apogee time sequence by using the apogee time calculation algorithm; Step 4: Screen the generated apogee time sequence according to the task start time and end time; according to the screened apogee time, group the time sequence according to the continuous orbit change / intermittent orbit change, realize the cycle of the continuous working of the thruster after the thrust and the stop after the thrust; Step 5: Generate the orbit control time sequence according to step 4, and generate the orbit-raising instruction according to the orbit control time sequence, and output the 16 orbit control source code and physical parameters; Step 6: Generate the satellite ephemeris file and the satellite orbit control activity supervision record table.

2. The method for autonomous generation of a satellite orbit control command and orbit control activity monitoring table according to claim 1, characterized in that, The orbit data is the orbit six numbers and the orbit UTC cumulative seconds in the downlink telemetry.

3. The method for autonomous generation of a satellite orbit control command and orbit control activity monitoring table according to claim 2, characterized in that, The orbit data includes semi-major axis, eccentricity, orbit inclination, ascending node right ascension, perigee amplitude, mean anomaly, orbit UTC cumulative seconds, orbit control task start and end time, orbit control time length min, several orbits in a group, several orbits in a group, input specific impulse and thrust, satellite dry weight.

4. The method for autonomous generation of a satellite orbit control command and orbit control activity monitoring table according to claim 1, characterized in that, The specific calculation of the apogee time is: wherein is the mean anomaly and linearly related to time , is the average angular velocity of the motion, is the time of the satellite's passage through the perigee, is the eccentric anomaly, is the orbital eccentricity; At apogee, the eccentric anomaly , by Kepler's equation: The mean anomaly at the time of the perigee is obtained The time of the apogee corresponds to the time of the perigee: The time of the apogee is then: The apogee time is obtained by adding half of the orbit period to the perigee time.

5. The method for autonomous generation of a satellite orbit control command and orbit control activity monitoring table according to claim 1, characterized in that, Step 4 is specifically: Step 4.1: Keep the apogee time sequence between the task start time and the end time; Step 4.2: According to the apogee time sequence screened in step 4.1, the total number is count_orbit, if intermittent orbit control, group all the apogee time sequences, X orbits in each group, the first k orbits in X orbits are continuously changed, and X-k orbits stop orbit control.

6. The method for autonomous generation of a satellite orbit control command and orbit control activity monitoring table according to claim 5, characterized in that, Step 5 is specifically: generate the orbit control time sequence, splice it into 16 hexadecimal source code according to the orbit control instruction content, generate the orbit-raising instruction, output the 16 orbit control source code and physical parameters.

7. The method for autonomous generation of a satellite orbit control command and orbit control activity monitoring table according to claim 6, characterized in that, Step 6 is specifically: Step 6.1: Generate ephemeris, the ephemeris content is the position, velocity and time of satellite motion; calculate the six numbers according to the influence formula of small impulse on each number; calculate the satellite position and velocity by using Kepler's elements; Step 6.2: Generate the satellite orbit control activity supervision record table, read the time sequence of step 4.1, duration is the orbit control time, orbit_time-duration / 2 is the ignition time, and orbit_time+duration / 2 is the ignition end time.

8. A system for autonomous generation of satellite orbit control command and orbit control activity monitoring table, characterized in that, The method is realized by the method for autonomously generating a satellite orbit control instruction and an orbit control activity supervision table according to any one of claims 1-7.

9. A computer-readable storage medium, characterized in that, The computer readable storage medium stores a computer program, which is run by the processor to execute the method for autonomously generating a satellite orbit control instruction and an orbit control activity supervision table according to any one of claims 1-7.

10. A computer device, comprising: The device comprises a memory and a processor, the memory stores a computer program, when the processor runs the computer program stored in the memory, the processor executes the method for autonomously generating a satellite orbit control instruction and an orbit control activity monitoring table according to any one of claims 1-7.

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