A method and device for neighbor satellite adjustment based on satellite damage reconstruction

Abstract

The application provides a satellite damage reconstruction-based neighboring satellite adjustment method and device, and relates to the technical field of satellites. According to telemetry data of a target satellite, whether the target satellite is damaged is judged. If it is judged that the target satellite is damaged, according to a preset two-line element and an orbit model, and a two-line element of the target satellite and a two-line element of a neighboring satellite of the target satellite, real-time position data of the target satellite and real-time position data of the neighboring satellite of the target satellite are determined. According to the real-time position data of the target satellite and the real-time position data of the neighboring satellite, a mean anomaly change value required for the neighboring satellite to move from a current position to a target position is determined. According to the mean anomaly change value, the two-line element of the neighboring satellite is updated, and the orbit position of the neighboring satellite is adjusted based on the updated two-line element. The application can quickly and at low cost realize satellite damage reconstruction through neighboring satellite adjustment.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellites, in particular to a method and device for adjusting neighboring satellites based on satellite damage reconstruction. BACKGROUND

[0002] Satellites in space serve human needs for information transmission, position positioning, environmental monitoring and cosmic exploration through communication, navigation, remote sensing and scientific research functions. However, some satellites may malfunction or even be damaged due to various factors and cannot work normally. In order to ensure the normal work of the satellite constellation, the service capability of the satellite constellation needs to be recovered through rapid replenishment or function reorganization.

[0003] In related technologies, ground backup satellites are launched to replace damaged satellites, but there are problems of long response period and high cost. SUMMARY

[0004] The problem solved by the present application is how to quickly and low-cost realize satellite damage reconstruction.

[0005] To solve the above problems, the present application provides a method and device for adjusting neighboring satellites based on satellite damage reconstruction.

[0006] In a first aspect, the present application provides a method for adjusting neighboring satellites based on satellite damage reconstruction, comprising:

[0007] acquiring telemetry data of a target satellite;

[0008] judging whether the target satellite is damaged according to the telemetry data of the target satellite;

[0009] if it is judged that the target satellite is damaged, determining real-time position data of the target satellite and real-time position data of a neighboring satellite of the target satellite according to a pre-set two-line element and an orbit model, and a two-line element of the target satellite and a two-line element of the neighboring satellite of the target satellite;

[0010] determining a mean anomaly change value required for the neighboring satellite to move from a current position to a target position according to the real-time position data of the target satellite and the real-time position data of the neighboring satellite, the target position being an adjusted position of the neighboring satellite;

[0011] updating the two-line element of the neighboring satellite according to the mean anomaly change value, and adjusting the orbit position of the neighboring satellite based on the updated two-line element.

[0012] Optionally, the judging whether the target satellite is damaged according to the telemetry data of the target satellite comprises:

[0013] judging whether the target satellite is damaged according to a comparison result between the telemetry data of the target satellite and a corresponding preset threshold; and / or

[0014] analyzing a change trend of the telemetry data of the target satellite over time and / or analyzing a correlation between the telemetry data of the target satellite, to obtain an analysis result, and judging whether the target satellite is damaged according to the analysis result.

[0015] Optionally, the preset two-line element and orbit model is a model in which a two-body orbit model is taken as a basic model and a perturbation model is taken as a correction term.

[0016] Optionally, the two-line element includes at least an orbit inclination, an ascending node right ascension, a perigee amplitude, a mean anomaly, an orbit semi-major axis, an eccentricity and an average motion velocity.

[0017] The determining, according to the preset two-line element and orbit model and the two-line element of the target satellite and the two-line element of the adjacent satellite of the target satellite, of the real-time position data of the target satellite and the real-time position data of the adjacent satellite of the target satellite includes:

[0018] determining a real-time mean anomaly of the first satellite according to the average motion velocity of the first satellite and an initial mean anomaly of the first satellite; wherein the first satellite includes the target satellite or the adjacent satellite.

[0019] determining a real-time eccentric anomaly of the first satellite according to the real-time mean anomaly of the first satellite.

[0020] determining a real-time true anomaly of the first satellite according to the real-time eccentric anomaly of the first satellite.

[0021] determining real-time position data of the first satellite in an orbit plane according to the orbit semi-major axis, the eccentricity and the real-time true anomaly of the first satellite.

[0022] converting the real-time position data of the first satellite in the orbit plane into real-time three-dimensional position data in a preset geocentric inertial coordinate system, to obtain the real-time position data of the first satellite.

[0023] Optionally, the determining, according to the real-time position data of the target satellite and the real-time position data of the adjacent satellite, of a mean anomaly change value required for the adjacent satellite to move from a current position to a target position includes:

[0024] determining a target position to be adjusted of the adjacent satellite and an orbit parameter corresponding to the target position.

[0025] determine a target mean anomaly required for the proximate satellite to move to the target position according to the orbital parameters corresponding to the target position;

[0026] determine a mean anomaly change value required for the proximate satellite to move from the current position to the target position according to the target mean anomaly and a mean anomaly corresponding to the current position of the proximate satellite.

[0027] Optionally, the updating the two-line element of the proximate satellite according to the mean anomaly change value comprises:

[0028] determine a new mean anomaly for adjusting the orbit according to the mean anomaly change value;

[0029] replace the mean anomaly in the two-line element of the proximate satellite with the new mean anomaly to update the two-line element of the proximate satellite.

[0030] Optionally, the method further comprises:

[0031] obtain performance index data of the target satellite before the target satellite is damaged to obtain pre-damage performance index data;

[0032] obtain performance index data of the proximate satellite after the orbit position of the proximate satellite is adjusted to obtain post-reconstruction performance index data;

[0033] compare the pre-damage performance index data and the post-reconstruction performance index data to obtain and display a comparison result;

[0034] The performance index data comprises coverage performance index and communication performance index, the coverage performance index comprises coverage time percentage for a predetermined number of monitoring points in a target area, and the communication performance index comprises communication link availability of the target satellite or the proximate satellite.

[0035] In a second aspect, the present application provides a proximate satellite adjustment device based on satellite damage reconstruction, comprising:

[0036] a data acquisition module configured to acquire telemetry data of a target satellite;

[0037] a damage judgment module configured to judge whether the target satellite is damaged according to the telemetry data of the target satellite;

[0038] a position determination module configured to, if it is judged that the target satellite is damaged, determine real-time position data of the target satellite and real-time position data of a proximate satellite of the target satellite according to a preset two-line element and an orbit model, and a two-line element of the target satellite and a two-line element of the proximate satellite of the target satellite.

[0039] The flat near point angle change value determination module is configured to determine a flat near point angle change value required for the adjacent satellite to move from a current position to a target position according to the real-time position data of the target satellite and the real-time position data of the adjacent satellite, the target position being an adjusted position of the adjacent satellite.

[0040] The orbit adjustment module is configured to update the two-line element number of the adjacent satellite according to the flat near point angle change value, and adjust the orbit position of the adjacent satellite based on the updated two-line element number.

[0041] In a third aspect, the present application provides an electronic device comprising a memory and a processor.

[0042] The memory is configured to store a computer program.

[0043] The processor is configured to implement the satellite damage reconstruction-based adjacent satellite adjustment method according to the first aspect when executing the computer program.

[0044] In a fourth aspect, the present application provides a computer readable storage medium, wherein the storage medium stores a computer program, and when the computer program is executed by a processor, the satellite damage reconstruction-based adjacent satellite adjustment method according to the first aspect is implemented.

[0045] The satellite damage reconstruction-based adjacent satellite adjustment method and device have the following beneficial effects: telemetry data of a target satellite is acquired to provide data support for subsequent judgment of damage of the target satellite. Whether the target satellite is damaged is judged according to the telemetry data of the target satellite, and the damaged satellite can be accurately identified in a timely manner according to the telemetry data of the target satellite. If it is judged that the target satellite is damaged, the real-time position data of the target satellite and the real-time position data of the adjacent satellite of the target satellite are determined according to a preset two-line element number and an orbit model, and the two-line element number of the target satellite and the two-line element number of the adjacent satellite of the target satellite. After it is determined that the target satellite is damaged, the position of the target satellite and the position of the adjacent satellite can be determined by the preset two-line element number and the orbit model to provide data support for subsequent adjacent satellite adjustment. The flat near point angle change value required for the adjacent satellite to move from a current position to a target position is determined according to the real-time position data of the target satellite and the real-time position data of the adjacent satellite, wherein the target position is an adjusted position of the adjacent satellite. Since the orbit position of the adjacent satellite can be adjusted by changing the flat near point angle, the flat near point angle change value required for the adjacent satellite to move from the current position to the target position is accurately determined to provide adjustment data for subsequent orbit position adjustment of the adjacent satellite. The two-line element number of the adjacent satellite is updated according to the flat near point angle change value, and the orbit position of the adjacent satellite is adjusted based on the updated two-line element number. The orbit position of the adjacent satellite can be accurately adjusted by changing the flat near point angle of the adjacent satellite, thereby realizing rapid and low-cost satellite damage reconstruction. BRIEF DESCRIPTION OF DRAWINGS

[0046] Figure 1 A flow chart of a method for adjusting neighboring satellites based on satellite damage reconstruction according to an embodiment of the present application;

[0047] Figure 2 A flow chart of determining real-time position data of a target satellite and real-time position data of neighboring satellites of the target satellite according to an embodiment;

[0048] Figure 3 A flow chart of determining a mean motion change value required for a neighboring satellite to move from a current position to a target position according to an embodiment;

[0049] Figure 4 A flow chart of updating two-line element numbers of a neighboring satellite according to an embodiment;

[0050] Figure 5 A flow chart of comparing performance indicators before damage and after reconstruction according to an embodiment;

[0051] Figure 6 A schematic diagram of a comparison result of performance indicators according to an embodiment;

[0052] Figure 7 A structural schematic diagram of a device for adjusting neighboring satellites based on satellite damage reconstruction according to an embodiment of the present application;

[0053] Figure 8 A structural schematic diagram of an electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0054] In order to make the above objectives, features and advantages of the present application more clear and comprehensible, specific embodiments of the present application will be described in detail below with reference to the accompanying drawings. Although some embodiments of the present application are shown in the drawings, it should be understood that the present application can be implemented in various forms, and should not be interpreted as being limited to the embodiments set forth herein, but rather, these embodiments are provided to make the present application more thorough and complete. It should be understood that the drawings and embodiments of the present application are for exemplary purposes only, and are not intended to limit the scope of protection of the present application.

[0055] It should be understood that each step described in the method embodiments of the present application can be executed in different orders, and / or in parallel. In addition, the method embodiments can include additional steps and / or omit the execution of the steps shown. The scope of the present application is not limited in this respect.

[0056] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to"; the term "based on" means "at least partially based on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; and the term "optionally" means "optional embodiments". Definitions of other terms will be given in the following description. It should be noted that the concepts of "first," "second," etc., mentioned in this invention are used only to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0057] It should be noted that the terms "a" and "a plurality of" used in this invention are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0058] The names of the messages or information exchanged between the multiple devices in the embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of these messages or information.

[0059] In related technologies, for satellite damage reconstruction, there are many problems such as the inability to identify truly damaged and irreparable satellites in a timely and accurate manner, leading to misjudgment or omission of damaged satellites; and (2) the existing orbit adjustment methods based on the two-body orbit model have problems such as computational complexity, insufficient adjustment accuracy or response delay; and, there is a lack of scientific quantitative indicators to evaluate the satellite constellation performance after the orbit position of neighboring satellites is adjusted.

[0060] To address the problems existing in the aforementioned related technologies, this embodiment provides a method and apparatus for adjusting neighboring satellites based on satellite damage reconstruction.

[0061] like Figure 1 As shown in the figure, an embodiment of the present invention provides a method for adjusting neighboring satellites based on satellite damage reconstruction, which includes the following steps:

[0062] Step S100: Acquire telemetry data of the target satellite.

[0063] Specifically, the telemetry data of the target satellite may include: power system data, attitude control system data, and communication system data of the target satellite. Among them, the power system data may be the battery voltage data of the target satellite; the attitude control system data may be the attitude angle deviation and angular velocity of the target satellite; and the communication system data may be the communication signal strength and bit error rate of the target satellite.

[0064] Step S200: Determine whether the target satellite has been damaged based on the telemetry data of the target satellite.

[0065] Specifically, the telemetry data of the target satellite can be monitored, and when an anomaly is monitored, the target satellite can be determined as a faulty satellite. For the faulty satellite, further determination can be made to determine whether it is damaged. The monitoring of abnormal telemetry data can be achieved by a threshold-based detection method or a data analysis-based detection method, i.e., setting a normal threshold range of each parameter, and when a parameter of a satellite exceeds the range, it is determined that the satellite may be faulty; and a data analysis technique is used to analyze the telemetry data of the satellite to find potential signs of failure.

[0066] In some embodiments, according to the telemetry data of the target satellite, whether the target satellite is damaged is determined, including: according to a comparison result between the telemetry data of the target satellite and a corresponding preset threshold, whether the target satellite is damaged is determined.

[0067] Specifically, for the battery voltage in the power supply system data, when the real-time monitored battery voltage is lower than the battery voltage threshold, for example, 24V, the power supply system of the target satellite may have problems, such as battery aging, charging circuit failure, etc. Similarly, the working temperature of the battery also affects the performance and life of the satellite. Generally, the normal working temperature range of the satellite battery is between -20°C and 60°C. If the battery temperature exceeds this range, the battery performance will decrease or even be damaged, i.e., it can be determined as a faulty satellite.

[0068] Specifically, for the attitude angle deviation in the attitude control system data, a normal deviation threshold of the attitude angle is set to ±0.5, and when the actually measured attitude angle deviation exceeds the threshold, it indicates that the attitude control system of the target satellite has a fault, such as attitude control engine failure, sensor error, etc., i.e., it can be determined as a faulty satellite.

[0069] Specifically, for the angular velocity in the attitude control system data, under normal circumstances, the angular velocity of the satellite is within a reasonable range. For example, for a satellite in stable operation, a normal threshold of the angular velocity is set to ±0.01° / s, and if the monitored angular velocity exceeds the range, it may indicate that the satellite is disturbed by external interference or the attitude control system is abnormal.

[0070] Specifically, for the communication signal strength in the communication system data, the signal strength of the satellite communication system is an important indicator to measure the communication quality. A normal threshold range of the communication signal strength between the satellite and the ground station is set to -80dBm to -100dBm, and if the actually received signal strength is lower than -100dBm, it means that the communication antenna is faulty, the signal transmission link is damaged, etc., i.e., it can be determined as a faulty satellite.

[0071] Specifically, for the bit error rate in the data of the communication system, the bit error rate reflects the proportion of errors in the process of communication data transmission. Under normal circumstances, the bit error rate of satellite communication should be lower than a certain threshold, such as 10⁻ 6 When the bit error rate exceeds this threshold, it indicates that there are problems such as interference and equipment failure in the communication system, which affects the normal transmission of data, that is, the faulty satellite can be determined.

[0072] In other embodiments, according to the telemetry data of the target satellite, judging whether the target satellite is damaged can also include: analyzing the change trend of the telemetry data of the target satellite over time, and / or analyzing the correlation between the telemetry data of the target satellite, obtaining an analysis result, and determining whether the target satellite is damaged according to the analysis result.

[0073] Specifically, the trend analysis can be an analysis of the change trend of the satellite parameters over time. The change of the signal transmission delay in the satellite communication system over time is observed. Under normal circumstances, the signal transmission delay between the satellite and the ground station is relatively stable and maintained within a certain time interval. If it is found through long-term monitoring that the signal transmission delay has a continuous upward trend in the past period of time, even if the current delay value is still within the delay threshold allowed by the normal operation of the communication system, it is possible that some particle radiation in space gradually damages the electronic elements of the communication equipment, affecting the signal processing speed; Or the pointing of the communication antenna has a slight deviation during the on-orbit operation of the satellite, causing the signal transmission path to become longer, thereby causing the transmission delay to increase, that is, the faulty satellite can be determined.

[0074] Specifically, the correlation analysis is an analysis of the correlation between different parameters. There is a close relationship between the orbit height of the satellite and the orbit running speed of the satellite. According to Kepler's law, when the satellite runs on the orbit, if it is found that the orbit height of the satellite suddenly abnormally decreases, and the orbit running speed also significantly accelerates, it is very likely that the satellite is affected by unexpected atmospheric resistance, causing the orbit to decay. Because according to the principle of celestial mechanics, when the orbit height decreases, the satellite is subjected to increased earth's gravity, and in order to maintain the conservation of angular momentum, its running speed must be correspondingly accelerated. Similar correlation analysis can accurately locate the possible failure cause of the satellite from the coordinated changes of multiple parameters, and then determine the faulty satellite.

[0075] Specifically, after being determined as a failed satellite, the detected failed satellite is further screened to determine a satellite that is truly damaged and cannot resume normal operation. Specifically, the screening process can comprehensively evaluate the severity of the current detected failure, and focus on the actual impact of the failure on the key functions of the satellite. Once the failure causes the key functions of the satellite to malfunction, and it is impossible to restore the key functions to normal by simple adjustment or repair measures with existing technical means and resources, the satellite can be determined as a damaged satellite. For example, a satellite that bears the heavy responsibility of communication relay has a serious failure of its core communication repeater, resulting in complete interruption of communication signals. After detection and analysis, it is found that the failure is caused by permanent damage to the internal core chip of the repeater. With the existing space repair capability, it is impossible to complete the repair work in a short period of time. In this case, the satellite should be determined as a damaged satellite due to the loss of key communication functions.

[0076] Step S300: If it is determined that the target satellite is damaged, the real-time position data of the target satellite and the real-time position data of the neighboring satellite of the target satellite are determined according to the preset two-line element and the orbit model, and the two-line element of the target satellite and the two-line element of the neighboring satellite of the target satellite.

[0077] Specifically, the preset two-line element and orbit model is a model taking the two-body orbit model as the basic model and the J2 perturbation model as the correction term.

[0078] The two-body orbit model is selected as the basic model. This model is based on the ideal situation where the satellite is only subjected to the gravitational force of the Earth's center of mass. The motion of the satellite follows Kepler's law. Kepler's law describes the motion of the satellite in an elliptical orbit, including the shape of the orbit (determined by the eccentricity e), the size of the orbit (determined by the semi-major axis a), and the relationship between the position and velocity of the satellite in the orbit. Therefore, the two-body orbit model is suitable for preliminary orbit analysis and position calculation, and can quickly obtain the approximate position of the satellite.

[0079] In the actual space environment, the forces acting on the satellite are not only the gravitational force of the Earth's center of mass. The Earth is not a perfect sphere, and its mass distribution is not uniform. This non-uniformity causes the satellite to be subjected to additional gravitational perturbations. In order to perform more accurate orbit calculations, perturbation models such as the J2 perturbation model need to be introduced. The J2 perturbation model mainly considers the influence of the second-order zonal harmonic term (J2 term) of the Earth on the satellite orbit, and can more accurately describe the motion of the satellite in the non-spherical gravitational field of the Earth. Therefore, the J2 perturbation model is suitable for situations that require high-precision orbit calculation, such as precise orbit control and long-term orbit prediction of satellites.

[0080] The embodiment can accurately calculate and determine the position data of the damaged target satellite and the adjacent satellite at each moment based on the preset two-line element and the combined orbit model.

[0081] Step S400: determining the mean motion change value required for the adjacent satellite to move from the current position to the target position according to the real-time position data of the target satellite and the real-time position data of the adjacent satellite; wherein the target position is the adjusted position of the adjacent satellite.

[0082] Specifically, since the orbit position of the adjacent satellite is adjusted by adjusting the mean motion of the adjacent satellite, the mean motion change value required for the adjacent satellite to move from the current position to the target position needs to be determined to adjust the orbit position of the adjacent satellite.

[0083] Step S500: updating the two-line element of the adjacent satellite according to the mean motion change value, and adjusting the orbit position of the adjacent satellite based on the updated two-line element.

[0084] Specifically, according to the two-line element of the adjacent satellite, the current mean motion of the adjacent satellite can be determined, and then based on the mean motion change value, a new mean motion is determined. The new mean motion replaces the current mean motion in the two-line element of the adjacent satellite, and other parameters in the two-line element remain unchanged. Since the main purpose of this adjustment based on the mean motion change is to adjust the orbit position of the adjacent satellite by changing the mean motion, and other parameters are usually not changed at this stage, only the mean motion in the two-line element is updated.

[0085] Specifically, after the orbit system of the adjacent satellite loads the updated two-line element, the orbit state of the satellite is recalculated according to the updated two-line element. According to the new mean motion and other orbit parameters, the orbit mechanics algorithm and model are used to calculate the position, velocity and other information of the adjacent satellite on the new orbit. Based on these calculation results, the control system of the adjacent satellite automatically adjusts the running state of the satellite, so that it gradually changes to the orbit position corresponding to the new two-line element. When the position and orbit parameters of the adjacent satellite reach the expected target, it is judged that the orbit adjustment is completed, and the judgment condition can be set according to the error range of the orbit parameters.

[0086] In this embodiment, the telemetry data of the target satellite is acquired to provide data support for subsequent judgment of damage of the target satellite. According to the telemetry data of the target satellite, whether the target satellite is damaged is judged, and the damaged satellite can be identified in time and accurately according to the telemetry data of the target satellite. If it is judged that the target satellite is damaged, the real-time position data of the target satellite and the real-time position data of the adjacent satellite of the target satellite are determined according to the preset two-line element and the orbit model, the two-line element of the target satellite and the two-line element of the adjacent satellite of the target satellite. After it is determined that the target satellite is damaged, the position of the target satellite and the position of the adjacent satellite can be determined by the preset two-line element and the orbit model to provide data support for subsequent adjacent satellite adjustment. According to the real-time position data of the target satellite and the real-time position data of the adjacent satellite, the mean motion change value required for the adjacent satellite to move from the current position to the target position is determined, wherein the target position is the adjusted position of the adjacent satellite. Since the orbit position of the adjacent satellite can be adjusted by changing the mean motion, accurate determination of the mean motion change value required for the adjacent satellite to move from the current position to the target position provides adjustment data for subsequent orbit position adjustment of the adjacent satellite. According to the mean motion change value, the two-line element of the adjacent satellite is updated, and the orbit position of the adjacent satellite is adjusted based on the updated two-line element. The orbit position of the adjacent satellite can be accurately adjusted by changing the mean motion of the adjacent satellite, thereby realizing rapid and low-cost satellite damage reconstruction.

[0087] Optionally, the two-line element of the satellite at least includes an orbital inclination, an ascending node right ascension, an argument of perigee, a mean motion, an orbit semi-major axis, an eccentricity and an average motion speed. The latest two-line element of all satellites in the satellite constellation can be obtained from a satellite monitoring system or a ground control center.

[0088] Optionally, as shown in Figure 2 According to the preset two-line element and the orbit model, and the two-line element of the target satellite and the two-line element of the adjacent satellite of the target satellite, the real-time position data of the target satellite and the real-time position data of the adjacent satellite of the target satellite are determined, including the following steps:

[0089] Step S210: determining the real-time mean motion of the first satellite according to the average motion speed of the first satellite and the initial mean motion of the first satellite; wherein the first satellite includes the target satellite or the adjacent satellite.

[0090] Specifically, since the target satellite and the adjacent satellite have the same method of determining the real-time position data, the first satellite is taken as the general term of the target satellite or the adjacent satellite in this embodiment for overall description.

[0091] Specifically, the mean motion M is a parameter for describing the position of the first satellite on the orbit, which is related to time.

[0092] According to the average motion speed n and the initial mean anomaly M_0, the mean anomaly M(t) at time t can be calculated according to the following expression:

[0093] M(t) = M_0 + n(t - t_0);

[0094] where t_0 is the initial time. The average motion speed n reflects the average speed of the first satellite in the orbit, which is related to the semi-major axis a of the orbit and can be calculated by the formula where μ is the Earth's gravitational constant. The mean anomaly can be updated in real time according to the change of time, so as to track the position change of the first satellite in the orbit.

[0095] Step S220: determining the real-time eccentric anomaly of the first satellite according to the real-time mean anomaly of the first satellite.

[0096] Specifically, the relationship between the mean anomaly M and the eccentric anomaly E can be described by the Kepler equation, which is as follows:

[0097]

[0098] where e is the eccentricity.

[0099] Since the above Kepler equation cannot be solved directly, an iterative method (such as Newton-Raphson method) is needed to solve the eccentric anomaly E. The iterative formula of the Newton-Raphson method is as follows:

[0100]

[0101] where k is the iteration number, and the initial value E0 can be taken as M. In the iteration process, the value of is calculated and compared with When is less than a set convergence threshold (such as radians), the iteration ends, and the obtained is the approximate value of the eccentric anomaly E.

[0102] Step S230: determining the real-time true anomaly of the first satellite according to the real-time eccentric anomaly of the first satellite.

[0103] Specifically, after obtaining the eccentric anomaly E, the true anomaly f is calculated according to the following expression:

[0104]

[0105] where is the true anomaly. The true anomaly f directly describes the position of the first satellite in the orbit relative to the perigee, and is a key parameter for calculating the position of the first satellite in the orbital plane.​​​

[0106] Step S240: determining real-time position data of the first satellite in the orbital plane according to the orbit semi-major axis, eccentricity and real-time true anomaly of the first satellite.

[0107] Specifically, according to the orbit semi-major axis a, eccentricity e and true anomaly , the distance r of the satellite to the center of the earth in the position (r, ) of the first satellite in the orbital plane is calculated according to the following expression:

[0108] .

[0109] After determining the distance r of the satellite to the center of the earth, since the true anomaly is calculated in the above step S230, the position (r, ) of the first satellite in the orbital plane can be obtained.

[0110] Step S250: converting the real-time position data of the first satellite in the orbital plane into real-time three-dimensional position data in a preset geocentric inertial coordinate system to obtain real-time position data of the first satellite.

[0111] Specifically, the origin of the preset geocentric inertial coordinate system is located at the center of the earth, the Z axis points to the north pole, the X axis points to the vernal equinox, and the Y axis forms a right-handed rectangular coordinate system with the X and Z axes.

[0112] Specifically, the position (r, ) in the orbital plane is converted into a three-dimensional position (x, x, y, z ) in the preset geocentric inertial coordinate system, and a rotation matrix is used for coordinate transformation, and the expression is as follows:

[0113] ;

[0114] wherein, and are rotation matrices around the X and Z axes respectively, and the expressions are as follows: ; is the ascending node right ascension, i is the orbit inclination, is the argument of perigee.

[0115] In this optional embodiment, the position of the satellite in the orbital plane is converted into a three-dimensional position in the geocentric inertial coordinate system through a rotation operation, so that the actual position data of the satellite in space can be accurately calculated.

[0116] Optionally, as Figure 3As shown, according to the real-time position data of the target satellite and the real-time position data of the neighboring satellite, the value of the change in the mean anomaly required for the neighboring satellite to move from the current position to the target position is determined, including the following steps:

[0117] Step S310: Determine the target position to be adjusted of the neighboring satellite, and the orbit parameters corresponding to the target position.

[0118] Specifically, the target position to be adjusted of the neighboring satellite can be determined according to the functional requirement analysis of the target satellite. Different types of satellites have different functions, for example:

[0119] For a communication satellite, if the damaged target satellite is used for communication coverage, its task is to ensure that users in a certain area can receive stable communication signals. At this time, it is necessary to analyze information such as the communication coverage range of the target satellite, the signal strength distribution, and the distribution of users. Through these analyses, the communication blind area caused by the satellite damage is found. Then, according to the performance parameters of the neighboring satellite (such as the pointing range of the communication antenna, the transmission power, etc.), it is determined that the neighboring satellite moves to which position can fill these communication blind areas, so as to ensure that the communication service of the area is not greatly affected, that is, the target position can be determined.

[0120] For a remote sensing satellite, if the damaged target satellite is used for remote sensing monitoring, its function is to collect images and acquire data for a specific geographic area. In this case, factors such as the observation angle, resolution, and geographic features of the monitoring area of the target satellite need to be considered. According to these factors, the target position to which the neighboring satellite needs to move is determined, so as to be able to cover the area originally monitored by the damaged satellite and meet the accuracy and time requirements of image collection.

[0121] The above method of determining the target position according to the functional requirement analysis of the target satellite can input the three-dimensional position data corresponding to the target position by manually performing functional requirement analysis, or can automatically analyze and output by the system, wherein the automatic analysis and output can be realized by deep learning and the like.

[0122] Specifically, after the target position is determined, the orbit parameters of the target position, such as the semi-major axis, eccentricity, inclination, right ascension of the ascending node, and argument of perigee, can be determined. These orbit parameters need to be adjusted and determined according to the three-dimensional position data of the target position and the orbit characteristics of the neighboring satellite.

[0123] Step S320: According to the orbit parameters corresponding to the target position, determine the target mean anomaly required for the neighboring satellite to move to the target position.

[0124] Specifically, the target mean anomaly required for the neighboring satellite to move to the target position can be calculated according to the orbit parameters corresponding to the target position. The method for calculating the mean anomaly can refer to step 210, which will not be described here.

[0125] Step S330: determining a mean anomaly change value required for the neighboring satellite to move from the current position to the target position according to the target mean anomaly required for the neighboring satellite to move to the target position and the mean anomaly corresponding to the current position of the neighboring satellite.

[0126] Specifically, after obtaining the target mean anomaly, the target mean anomaly is subtracted from the current mean anomaly of the neighboring satellite to obtain the required mean anomaly change value.

[0127] In the optional embodiment, the neighboring satellite can effectively replace the damaged target satellite by determining the mean anomaly change value required for the neighboring satellite.

[0128] Optionally, as shown in Figure 4 According to the mean anomaly change value, the two-line element set of the neighboring satellite is updated, including:

[0129] Step S410: determining a new mean anomaly for adjusting the orbit according to the mean anomaly change value.

[0130] Specifically, the current mean anomaly of the neighboring satellite is added to the mean anomaly change value to obtain the new mean anomaly for adjusting the orbit.

[0131] Step S420: replacing the mean anomaly in the two-line element set of the neighboring satellite with the new mean anomaly to update the two-line element set of the neighboring satellite.

[0132] Specifically, after obtaining the new mean anomaly, the new mean anomaly is replaced with the mean anomaly in the two-line element set of the neighboring satellite, while other parameters in the two-line element set remain unchanged. Because the purpose of this adjustment based on the mean anomaly change is to adjust the orbit position of the neighboring satellite by changing the mean anomaly, other parameters are generally not changed at the current stage.

[0133] In the optional embodiment, the orbit position of the neighboring satellite is adjusted by changing the mean anomaly, which has small calculation amount and can accurately adjust the orbit of the neighboring satellite.

[0134] Optionally, as shown in Figure 5 The satellite damage reconstruction-based neighboring satellite adjustment method of the embodiment of the application further includes the following steps:

[0135] S510: obtaining performance index data of the target satellite before the target satellite is damaged to obtain the performance index data before the damage.

[0136] Specifically, the performance indicator data includes coverage performance indicators and communication performance indicators of the target satellite, the coverage performance indicators include coverage time percentages for a predetermined number of monitoring points in the target area, and the communication performance indicators include communication link availability of the target satellite.

[0137] First, the calculation of the coverage time percentage will be described below.

[0138] Specifically, for the target area, if the satellite is used for meteorological monitoring, the target area can be a certain specific geographic area; if the satellite is used for communication services, the target area can be a densely populated urban area or a specific communication service coverage area.

[0139] Specifically, for the monitoring points, a predetermined number of monitoring points are uniformly or targetedly set in the target area according to actual needs. The density and distribution of the monitoring points will affect the accuracy of the coverage performance calculation. For a large area and relatively uniform geographic environment, the monitoring points can be set in a uniform distribution; for areas with complex geographic environment or special needs, such as mountainous areas, city centers, etc., the density of the monitoring points can be appropriately increased.

[0140] In some embodiments, the coverage time percentage of the predetermined number of monitoring points in the target area is calculated by the following method:

[0141] Calculate the coverage time of each monitoring point, specifically: judge the coverage of the target satellite: for each monitoring point, according to the position of the target satellite and the position of the monitoring point, judge whether the target satellite can cover the monitoring point. Generally, the conditions for judging the coverage of the target satellite can be based on factors such as the line-of-sight blocking situation and signal strength between the target satellite and the monitoring point. For example, when there is no obstacle between the target satellite and the monitoring point, and the signal strength of the target satellite reaches a certain threshold, it is considered that the target satellite can cover the monitoring point. Record the coverage time: every fixed time step Δt, judge whether the target satellite covers the monitoring point, if it covers, record the coverage time in the time step Δt. For each monitoring point, all the time steps covered by the target satellite within a predetermined time range are accumulated to obtain the total time covered by the target satellite for each monitoring point.

[0142] The coverage time percentage is calculated according to the following expression:

[0143] ;

[0144] Where T is the predetermined time range, N is the number of monitoring points, is the coverage time percentage, is the coverage time of the i-th monitoring point. Wherein the coverage time percentage i ​The higher, the better the coverage performance of the target satellite to the target area is represented.

[0145] The calculation of the coverage time percentage is described again.

[0146] Specifically, the communication link can be a link between the target satellite and the ground station, an inter-satellite link between the target satellite and other satellites, etc. The number of communication links participating in the evaluation can be determined according to specific application scenarios and research needs.

[0147] Specifically, for each communication link, its normal working conditions and parameters are set. For example, for the communication link between the target satellite and the ground station, the normal working conditions can include parameters such as signal strength, signal quality, bit error rate, etc. within a certain threshold range.

[0148] In some embodiments, the normal working time of each communication link of the target satellite can be determined by the following way:

[0149] Monitoring the state of the communication link: The state of each communication link is monitored in real time. According to the pre-set normal working conditions, it is judged whether each communication link is normally working in each time step Δt. If the communication link meets the normal working conditions in a certain time step Δt, the normal working time in that time step Δt is recorded as Δt.

[0150] Accumulate the normal working time: for the jth communication link, all the time steps of its normal working in the predetermined time range are accumulated to obtain the total time of the normal working of the communication link .

[0151] The availability of each communication link is calculated according to the following expression:

[0152] ;

[0153] Wherein, is the availability of the communication link, M is the number of communication links, and T is the predetermined time range.

[0154] S520: Obtain the performance index data of the adjacent satellite after adjusting the orbital position of the adjacent satellite, and obtain the reconstructed performance index data.

[0155] Specifically, the performance index data of the adjacent satellite can be calculated in the same way as the performance index data of the target satellite. For details, please refer to the above related description, which will not be repeated here.

[0156] S530: Compare the performance index data before damage and the performance index data after reconstruction, and obtain and display the comparison result.

[0157] Specifically, the comparison result can be displayed in the form of a table, such asFigure 6 As shown, where, This represents the percentage of coverage time before the damage. This represents the percentage of coverage time after reconstruction. To determine the availability of the communication link before the damage, To ensure the availability of the reconstructed communication link.

[0158] In this optional embodiment, an evaluation system for coverage time percentage and communication link availability is established. By comparing the performance indicators before and after the damage through monitoring data, the performance of the constellation after the adjustment of neighboring satellites can be scientifically quantified.

[0159] It should be noted that the neighboring satellite adjustment method based on satellite damage reconstruction provided in this embodiment of the invention can be implemented in a simulation platform or in a satellite control system.

[0160] The following section explains the simulation parameter settings during implementation on the simulation platform.

[0161] In the simulation platform, it is necessary to clearly define the simulation time range and time step.

[0162] The choice of time range can be determined based on specific research needs and target satellite missions. For short-term adjustments to neighboring satellites of the target satellite, a shorter time range should be selected.

[0163] Time step: The time step Δt determines the temporal resolution of the simulation. In one embodiment, the time step Δt can be set to 60 seconds. A smaller time step can improve the accuracy of the simulation and more accurately capture the details of changes in the satellite orbit.

[0164] Furthermore, for the simulation platform, the acquired double-row roots need to be converted to a format that the simulation platform can process. The data needs to be verified to ensure that all parameters are within reasonable ranges. This includes the track inclination angle. i Should be in arrive Between these values, the eccentricity e should be greater than or equal to 0 and less than 1. If data anomalies are detected, they should be verified against the data source or alternative data should be used.

[0165] like Figure 7 As shown, an embodiment of the present invention provides a neighboring satellite adjustment device 700 based on satellite damage reconstruction, comprising:

[0166] The data acquisition module 710 is used to acquire telemetry data from the target satellite;

[0167] The damage assessment module 720 is used to determine whether the target satellite has been damaged based on the telemetry data of the target satellite;

[0168] The position determining module 730 is configured to, if it is determined that the target satellite is damaged, determine real-time position data of the target satellite and real-time position data of the neighboring satellite of the target satellite according to a preset two-line element and orbit model and the two-line element of the target satellite and the two-line element of the neighboring satellite of the target satellite.

[0169] The mean anomaly change value determining module 740 is configured to determine a mean anomaly change value required for the neighboring satellite to move from a current position to a target position according to the real-time position data of the target satellite and the real-time position data of the neighboring satellite, the target position being an adjusted position of the neighboring satellite.

[0170] The orbit adjusting module 750 is configured to update the two-line element of the neighboring satellite according to the mean anomaly change value, and adjust the orbit position of the neighboring satellite based on the updated two-line element.

[0171] Optionally, the determining whether the target satellite is damaged according to the telemetry data of the target satellite comprises:

[0172] determining whether the target satellite is damaged according to a comparison result between the telemetry data of the target satellite and a corresponding preset threshold value; and / or,

[0173] analyzing a change trend of the telemetry data of the target satellite over time and / or analyzing a correlation between the telemetry data of the target satellite, obtaining an analysis result, and determining whether the target satellite is damaged according to the analysis result.

[0174] Optionally, the preset two-line element and orbit model is a model in which a two-body orbit model is taken as a basic model and a perturbation model is taken as a correction term.

[0175] Optionally, the two-line element at least includes an orbit inclination, an ascending node right ascension, a perigee amplitude, a mean anomaly, an orbit semi-major axis, an eccentricity and an average motion velocity.

[0176] The determining the real-time position data of the target satellite and the real-time position data of the neighboring satellite of the target satellite according to the preset two-line element and orbit model and the two-line element of the target satellite and the two-line element of the neighboring satellite of the target satellite comprises:

[0177] determining real-time mean anomaly of the first satellite according to the average motion velocity of the first satellite and an initial mean anomaly of the first satellite, wherein the first satellite includes the target satellite or the neighboring satellite;

[0178] determining real-time eccentric anomaly of the first satellite according to the real-time mean anomaly of the first satellite.

[0179] determining real-time true anomaly of the first satellite according to real-time anomaly of the first satellite;

[0180] determining real-time position data of the first satellite in the orbital plane according to semi-major axis, eccentricity and real-time true anomaly of the first satellite;

[0181] converting the real-time position data of the first satellite in the orbital plane into real-time three-dimensional position data in a preset geocentric inertial coordinate system to obtain real-time position data of the first satellite.

[0182] Optionally, the determining of the change value of the mean anomaly required for the adjacent satellite to move from the current position to the target position according to the real-time position data of the target satellite and the real-time position data of the adjacent satellite comprises:

[0183] determining the target position to be adjusted of the adjacent satellite and the orbital parameter corresponding to the target position;

[0184] determining the target mean anomaly required for the adjacent satellite to move to the target position according to the orbital parameter corresponding to the target position;

[0185] determining the change value of the mean anomaly required for the adjacent satellite to move from the current position to the target position according to the target mean anomaly and the mean anomaly corresponding to the current position of the adjacent satellite.

[0186] Optionally, the updating of the two-line element of the adjacent satellite according to the change value of the mean anomaly comprises:

[0187] determining a new mean anomaly for adjusting the orbit according to the change value of the mean anomaly;

[0188] replacing the mean anomaly in the two-line element of the adjacent satellite with the new mean anomaly to update the two-line element of the adjacent satellite.

[0189] Optionally, the method further comprises:

[0190] obtaining performance index data of the target satellite before the target satellite is damaged to obtain pre-damage performance index data;

[0191] obtaining performance index data of the adjacent satellite after the orbit position of the adjacent satellite is adjusted to obtain post-reconstruction performance index data;

[0192] comparing the pre-damage performance index data and the post-reconstruction performance index data to obtain and display a comparison result;

[0193] The performance index data includes a coverage performance index and a communication performance index, the coverage performance index includes a coverage time percentage of a predetermined number of monitoring points in a target area, and the communication performance index includes a communication link availability of the target satellite or a neighboring satellite.

[0194] As shown in Figure 8 The electronic device 800 includes a memory 810 and a processor 820. The memory 810 is configured to store a computer program. The processor 820 is configured to execute the computer program to implement the method for adjusting a neighboring satellite based on satellite damage reconstruction.

[0195] Alternatively, the electronic device 800 includes a memory 810 and a processor 820 coupled to the memory 810. The memory 810 is configured to store a computer program. The processor 820 is configured to execute the computer program to perform the following operations:

[0196] Obtain telemetry data of a target satellite;

[0197] Determine, according to the telemetry data of the target satellite, whether the target satellite is damaged;

[0198] If it is determined that the target satellite is damaged, determine real-time position data of the target satellite and real-time position data of a neighboring satellite of the target satellite according to a pre-set two-line element and an orbit model, a two-line element of the target satellite, and a two-line element of the neighboring satellite of the target satellite;

[0199] Determine, according to the real-time position data of the target satellite and the real-time position data of the neighboring satellite, a mean anomaly change value required for the neighboring satellite to move from a current position to a target position, the target position being an adjusted position of the neighboring satellite;

[0200] Update the two-line element of the neighboring satellite according to the mean anomaly change value, and adjust an orbit position of the neighboring satellite based on the updated two-line element.

[0201] The electronic device 800 includes a memory 810 and a processor 820. The memory 810 is configured to store a computer program. The processor 820 is configured to execute the computer program to implement the method for adjusting a neighboring satellite based on satellite damage reconstruction.

[0202] Alternatively, a non-volatile computer readable storage medium stores a computer program. When the computer program is executed by a processor, the processor performs the following operations:

[0203] Obtain telemetry data of a target satellite;

[0204] judging whether the target satellite is damaged according to telemetry data of the target satellite;

[0205] if it is judged that the target satellite is damaged, determining real-time position data of the target satellite and real-time position data of a neighboring satellite of the target satellite according to a pre-set two-line element and an orbit model, and a two-line element of the target satellite and a two-line element of the neighboring satellite of the target satellite;

[0206] determining a mean anomaly change value required for the neighboring satellite to move from a current position to a target position according to the real-time position data of the target satellite and the real-time position data of the neighboring satellite, the target position being an adjusted position of the neighboring satellite;

[0207] updating the two-line element of the neighboring satellite according to the mean anomaly change value, and adjusting an orbit position of the neighboring satellite based on the updated two-line element.

[0208] An electronic device 800 that can be a server or a client of the present application will now be described, which is an example of a hardware device that can be applied to aspects of the present application. The electronic device 800 is intended to represent various forms of digital electronic computing devices, such as laptops, desktops, workstations, personal digital assistants, servers, blade servers, mainframes, and other appropriate computing devices. The electronic device 800 can also represent various forms of mobile devices, such as personal digital assistants, cellular telephones, smart phones, wearable devices, and other similar computing devices. The components shown here, their connections and relationships, and their functions, are meant to be examples only, and are not meant to limit implementations of the present application described and / or claimed in this document.

[0209] The electronic device 800 includes a computing unit that can perform various appropriate actions and processes according to a computer program stored in a read-only memory (ROM) or a computer program loaded into a random access memory (RAM) from a storage unit. Various programs and data required for device operation can also be stored in the RAM. The computing unit, the ROM, and the RAM are connected to each other through a bus. An input / output (I / O) interface is also connected to the bus.

[0210] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by a computer program instructing relevant hardware, and the program can be stored in a computer readable storage medium. When the program is executed, the program can include the processes of the above-mentioned embodiment methods. The storage medium can be a magnetic disc, an optical disc, a read-only memory (ROM), a random access memory (RAM), or the like. In this application, the units described as separate components can or can not be physically separated, and the components shown as units can or can not be physical units, that is, they can be located in one place, or they can be distributed on multiple network units. Part or all of the units can be selected according to actual needs to achieve the purpose of the embodiment of the present application. In addition, the functional units in each embodiment of the present application can be integrated in one processing unit, or each unit can exist physically independently, or two or more units can be integrated in one unit. The integrated unit can be realized in the form of hardware or in the form of a software functional unit.

[0211] Although the present application is disclosed as above, the protection scope of the present application is not limited to this. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present application, and these changes and modifications will fall within the protection scope of the present application.

Claims

1. A method for neighbor satellite adjustment based on satellite damage reconstruction, characterized in that, The method comprises: acquiring telemetry data of a target satellite; judging whether the target satellite is damaged according to the telemetry data of the target satellite; if it is judged that the target satellite is damaged, determining real-time position data of the target satellite and real-time position data of a neighboring satellite of the target satellite according to a preset two-line element and orbit model and two-line elements of the target satellite and two-line elements of the neighboring satellite of the target satellite; determining a mean motion of the first satellite and an initial mean anomaly of the first satellite, wherein the first satellite comprises the target satellite or the neighboring satellite; determining a real-time mean anomaly of the first satellite according to the real-time mean motion of the first satellite and the initial mean anomaly of the first satellite; 2. The method of claim 1, wherein, determining a real-time eccentric anomaly of the first satellite according to the real-time mean anomaly of the first satellite; determining real-time position data of the first satellite in an orbit plane according to an orbit semi-major axis, an eccentricity and the real-time eccentric anomaly of the first satellite; converting the real-time position data of the first satellite in the orbit plane into real-time three-dimensional position data in a preset geocentric inertial coordinate system to obtain real-time position data of the first satellite.

3. The method of claim 1, wherein the method further comprises: determining a mean motion of the first satellite and an initial mean anomaly of the first satellite, wherein the first satellite comprises the target satellite or the neighboring satellite; 4. The method of claim 3, wherein, determining a real-time mean anomaly of the first satellite according to the real-time mean motion of the first satellite and the initial mean anomaly of the first satellite; determining a real-time eccentric anomaly of the first satellite according to the real-time mean anomaly of the first satellite; determining real-time position data of the first satellite in an orbit plane according to an orbit semi-major axis, an eccentricity and the real-time eccentric anomaly of the first satellite; converting the real-time position data of the first satellite in the orbit plane into real-time three-dimensional position data in a preset geocentric inertial coordinate system to obtain real-time position data of the first satellite. determining a mean motion of the first satellite and an initial mean anomaly of the first satellite, wherein the first satellite comprises the target satellite or the neighboring satellite; determining a real-time mean anomaly of the first satellite according to the real-time mean motion of the first satellite and the initial mean anomaly of the first satellite; determining a real-time eccentric anomaly of the first satellite according to the real-time mean anomaly of the first satellite; 5. The method of claim 1, wherein the method further comprises: determining real-time position data of the first satellite in an orbit plane according to an orbit semi-major axis, an eccentricity and the real-time eccentric anomaly of the first satellite; converting the real-time position data of the first satellite in the orbit plane into real-time three-dimensional position data in a preset geocentric inertial coordinate system to obtain real-time position data of the first satellite. determining a mean motion of the first satellite and an initial mean anomaly of the first satellite, wherein the first satellite comprises the target satellite or the neighboring satellite; determining a real-time mean anomaly of the first satellite according to the real-time mean motion of the first satellite and the initial mean anomaly of the first satellite; determining a real-time eccentric anomaly of the first satellite according to the real-time mean anomaly of the first satellite; determining real-time position data of the first satellite in an orbit plane according to an orbit semi-major axis, an eccentricity and the real-time eccentric anomaly of the first satellite; converting the real-time position data of the first satellite in the orbit plane into real-time three-dimensional position data in a preset geocentric inertial coordinate system to obtain real-time position data of the first satellite. According to the target mean anomaly and the mean anomaly corresponding to the current position of the adjacent satellite, a mean anomaly change value required for the adjacent satellite to move from the current position to a target position is determined.

6. The method of claim 1, wherein the method further comprises: The updating of the two-line element set of the adjacent satellite according to the mean anomaly change value comprises: According to the mean anomaly change value, a new mean anomaly for adjusting the orbit is determined; The mean anomaly in the two-line element set of the adjacent satellite is replaced by the new mean anomaly to update the two-line element set of the adjacent satellite.

7. The method of claim 1 to 6, wherein, Further comprising: Obtaining performance index data of the target satellite before damage, to obtain pre-damage performance index data; Obtaining performance index data of the adjacent satellite after adjusting the orbit position, to obtain post-reconstruction performance index data; Comparing the pre-damage performance index data and the post-reconstruction performance index data to obtain and display the comparison result; The performance index data comprises coverage performance index and communication performance index, the coverage performance index comprises coverage time percentage for a predetermined number of monitoring points in a target area, and the communication performance index comprises communication link availability of the target satellite or the adjacent satellite.

8. A neighboring satellite adjustment device based on satellite damage reconstruction, characterized in that, Comprising: A data acquisition module for acquiring telemetry data of a target satellite; A damage judgment module for judging whether the target satellite is damaged according to the telemetry data of the target satellite; A position determination module for determining real-time position data of the target satellite and real-time position data of an adjacent satellite of the target satellite according to a preset two-line element set and an orbit model, and a two-line element set of the target satellite and a two-line element set of the adjacent satellite of the target satellite if it is judged that the target satellite is damaged; A mean anomaly change value determination module for determining a mean anomaly change value required for the adjacent satellite to move from a current position to a target position according to the real-time position data of the target satellite and the real-time position data of the adjacent satellite, the target position being an adjusted position of the adjacent satellite; An orbit adjustment module for updating the two-line element set of the adjacent satellite according to the mean anomaly change value, and adjusting the orbit position of the adjacent satellite based on the updated two-line element set.

9. An electronic device, comprising: Comprising a memory and a processor; The memory is configured to store a computer program; The processor is configured to implement the satellite damage reconstruction-based adjacent satellite adjustment method according to any one of claims 1 to 7 when executing the computer program.

10. A computer-readable storage medium, characterized in that, The storage medium has a computer program stored thereon, and the computer program, when executed by a processor, implements the satellite damage reconstruction-based adjacent satellite adjustment method according to any one of claims 1 to 7.

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