Earth-moon space dual-satellite link chain establishment planning system and method

Abstract

The application provides a system and method for link planning of a geocentric-lunar space dual-satellite link, relates to the technical field of satellite task planning, and can consider the influence factors such as orbit, link visibility, working time sequence of a satellite task system, illumination condition, energy constraint and the like of a dual-satellite link multi-target complex coupling like a satellite-satellite link and a satellite-station link, through multi-time sequence link layer-by-layer association and dimension perspective, intuitively deduces a calculation process, facilitates query and analysis of the process and the result, and is suitable for various link application scenarios from the perspective of maximizing the benefit of an application link, so as to provide an optimal and alternative link time sequence scheme for reasonable application of the link by relevant personnel.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite mission planning, and in particular to a system and method for planning the establishment of a dual-satellite link in an Earth-Moon space. Background Art

[0002] In recent years, interest in cis-lunar space exploration has remained high. With increasing cis-lunar activities, the demand for instant communication in this space has also increased. Due to limited ground-based tracking and control network resources and limited communication coverage, a new form of space-based intersatellite link has emerged: a link architecture between distant retrograde orbit (DRO) satellites and low Earth orbit (LEO) satellites. Establishing links between cis-lunar satellites is of great significance for communication, measurement, autonomous orbit determination, and navigation. Link planning is a rational and executable link execution plan that considers comprehensive constraints such as space flight scenarios, application mission requirements, satellite operating modes, payload planning, and energy balance.

[0003] Based on the different link-building application mission requirements in the cis-lunar space, the feasibility of links between DRO satellites and space-based resources (LEO satellites) and ground-based resources (observation stations) must be comprehensively considered. Compared with planning for single-satellite links in low-Earth orbit, planning for dual-satellite links in the cis-lunar space is more complex. First, regarding link visibility, we must deal with the time-staggered inter-satellite (DRO satellite and LEO satellite) and satellite-to-Earth visibility arcs. Second, the energy requirements of the two satellites must be met simultaneously, and satellite energy is closely related to the two satellites' orbits, lighting conditions (Earth-Moon shadows), and satellite operating modes. In the context of cis-lunar space, the two satellites fly differently, and these factors are coupled when establishing the link. Therefore, how to establish a plan for a dual-satellite link in the cis-lunar space is an urgent problem that needs to be solved. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a system and method for planning the establishment of a dual-satellite link in Earth-Moon space, which can be applied from the perspective of maximizing the benefits of the link, is applicable to various link application scenarios, and provides optimal and alternative link timing solutions for the rational application of the link by relevant personnel.

[0005] The technical solution of the present invention to solve the above technical problems is as follows:

[0006] In one aspect, the present invention provides a system for planning a link establishment for a dual-satellite Earth-Moon space link, comprising:

[0007] Target link visibility calculation module: used to obtain the visible time of the target link, and determine the target visible link timing table T0 based on the visible time of the target link; wherein the target link includes any one of a star link, a star station link and a comprehensive link; the star link includes a link between a first satellite and a second satellite; the star station link includes a link between the first satellite and a measuring station; the measuring station is an observation station on the earth used to establish a link communication with the first satellite; the comprehensive link includes the star link and the star station link; the target visible link timing table T0 includes at least one first visible timing corresponding to the target link; any first visible timing corresponding to the target link includes the visible start time and visible end time of the target link under any first visible timing.

[0008] The satellite illumination period calculation module is used to obtain the spatial geometric relationship between the satellite, sun, moon and earth corresponding to the target link based on the positions of the satellite, sun, moon and earth corresponding to the target link, and to eliminate the influence of the earth shadow and the moon shadow from the obtained spatial geometric relationship to obtain the illumination period of the satellite corresponding to the target link.

[0009] The module for constructing a weighted factor link timing table is configured to determine an application task link calculation timing table TA based on a preset visibility duration and the target visible link timing table T0. The application task link calculation timing table TA includes at least one second visibility timing corresponding to the target link. Any second visibility timing corresponding to the target link includes a visibility start time and a visibility end time of the target link in any second visibility timing. The visibility start time of the target link in a second visibility timing corresponds to the visibility start time of the target link in a first visibility timing. The duration from the visibility start time to the visibility end time of the target link in any second visibility timing is the preset visibility duration. The module is further configured to determine a comprehensive factor weight of the target link in any second visibility timing based on a link effective visibility period factor weight of the target link in any second visibility timing and an illumination factor weight of the satellite corresponding to the target link. The link effective visibility period factor weight is determined based on the at least one first visibility timing and the at least one second visibility timing; and the illumination factor weight of the satellite corresponding to the target link is determined based on the at least one second timing and the illumination period of the satellite corresponding to the target link. It is also used to sort the at least one second visible timing based on the priority of the comprehensive factor weight of the target link in each second visible timing to obtain an energy balance calculation timing table TB; the energy balance calculation timing table TB includes at least one third visible timing corresponding to the target link; a third visible timing corresponding to the target link corresponds to a second visible timing corresponding to the target link; any third visible timing corresponding to the target link includes the energy analysis start time, energy analysis end time, the effective visible period factor weight of the link, the illumination factor weight of the satellite corresponding to the target link, and the comprehensive factor weight under any third visible timing; the energy analysis start time under any third visible timing is the visible start time of the target link included in the second visible timing corresponding to any third visible timing; the energy analysis end time under any third visible timing is determined based on the visible end time of the target link included in the second visible timing corresponding to any third visible timing and the preset link establishment recovery time.

[0010] An energy balance estimation module is configured to determine the power generation, load power consumption, and remaining power of a battery array included in a satellite corresponding to the target link in any third visible time sequence based on the energy analysis start time and energy analysis end time in the third visible time sequence. The energy balance of the target link in any third visible time sequence is determined based on whether the power generation, load power consumption, and remaining power of the battery array in the third visible time sequence meet preset conditions.

[0011] The link establishment planning result output module is used to obtain a link establishment application task timing table TC based on the energy balance result of the target link under each of the third visible time sequences; the link establishment application task timing table TC includes the third visible time sequence of the energy balance corresponding to the target link.

[0012] The visual display module is used to display the link establishment application task sequence table TC to prompt the application of the target link based on the link establishment application task sequence table TC.

[0013] On the basis of the above technical solution, the present invention can also be improved as follows.

[0014] Furthermore, the target link visibility calculation module stores the visibility time Tsat of the star link and the visibility time Tsta of the satellite station link. If the target link is the star link, the target link visibility calculation module is configured to determine the visibility time Tsat as the visibility time of the star link. If the target link is the satellite station link, the target link visibility calculation module is configured to determine the visibility time Tsta as the visibility time of the satellite station link. If the target link is the integrated link, the target link visibility calculation module is configured to determine the union of the visibility time Tsat and the visibility time Tsta as the visibility time of the integrated link.

[0015] Furthermore, the Earth-Moon space dual-satellite link establishment planning system provided by the present invention also includes an orbit simulator module. The orbit simulator module is used to determine the position of the satellite corresponding to the target link based on simulating the orbit of the satellite corresponding to the target link, and is used to calculate the positions of the sun, earth, and moon.

[0016] Furthermore, the first satellite is a long-range retrograde orbit satellite, and the second satellite is a low-Earth orbit satellite. The visibility time Tsat is determined based on the position of the first satellite, the position of the second satellite, the position of the station, and the radius of the Earth. The visibility time Tsta is determined based on the position of the first satellite, the position of the station, and the radius of the Earth.

[0017] Furthermore, the module for constructing a weight factor link timing table is further configured to determine the period from the visible start time to the visible end time included in any second visible timing sequence as a first period. The period from the visible start time to the visible end time included in any first visible timing sequence is determined as a second period. The period in which the first period overlaps with each of the second period is determined as a third period. The ratio of the third period to the first period is determined as the effective visible period factor weight of the link under any second visible timing sequence. The period in which the first period overlaps with the illumination period of the satellite corresponding to the target link is determined as a fourth period. The ratio of the fourth period to the first period is determined as the illumination factor weight of the satellite corresponding to the target link.

[0018] Furthermore, the satellite corresponding to the target link includes at least one mission system and at least one payload. The power generation of the battery array during any third visible time sequence is determined based on the solar incidence angle on the battery array. The load power consumption of the battery array is determined based on the operating time sequence of each mission system in the at least one mission system and the operating time sequence of each payload in the at least one payload. The remaining power of the battery array is determined based on the initial power of the battery array and the charge and discharge status of the simulated battery.

[0019] Furthermore, the satellite corresponding to the target link includes a solar panel drive mechanism and a solar panel. The solar panel drive mechanism is used to drive the solar panel. The system also includes a link establishment mission requirement injection module and a battery array solar incidence angle calculation module. The link establishment mission requirement injection module is used to determine a control mode for the solar panel drive mechanism, the operating sequence of each task system in the at least one mission system, and the operating sequence of each load in the at least one payload. The battery array solar incidence angle calculation module is used to determine the period between the energy analysis start time and the energy analysis end time in any third visible time sequence as an energy analysis period. Based on the position of the satellite corresponding to the target link and the position of the sun during the energy analysis period, a sunlight vector of the sun at the position of the satellite corresponding to the target link is calculated. Based on the control mode of the solar panel drive mechanism during the energy analysis period, a normal vector of the battery array is determined. Based on the sunlight vector and the normal vector, an angle of incidence of the sun on the battery array during the energy analysis period is calculated.

[0020] Furthermore, the control mode of the solar panel drive mechanism includes a normal mode and an angle-holding mode. When the control mode of the solar panel drive mechanism is the normal mode, the solar panel drive mechanism automatically controls the solar panel to track the sun, and the solar array solar incident angle calculation module is configured to read the attitude information of the solar panel in the solar panel drive mechanism and determine the normal vector of the solar array based on the attitude information of the solar panel. When the control mode of the solar panel drive mechanism is the angle-holding mode, the solar array solar incident angle calculation module is configured to determine the angle to be rotated of the solar panel based on the attitude information and orbit information of the satellite corresponding to the target link, and to send the angle to be rotated of the solar panel to the solar panel drive mechanism. The solar array solar incident angle calculation module is further configured to read the attitude information of the solar panel in the solar panel drive mechanism after the solar panel has rotated to the angle to be rotated, and determine the normal vector of the solar array based on the attitude information of the solar panel.

[0021] Furthermore, the visualization display module is further configured to display at least one of the following: the target link content, the target visible link time sequence table T0, the spatial geometric relationship, and the application task link calculation time sequence table TA. Furthermore, the visualization display module is configured to display at least one of the power generation, load power consumption, and remaining power of the battery array in each of the third visible time sequences. Furthermore, the visualization display module is configured to display a setting interface for at least one of the preset visible duration, the preset link establishment and recovery time, and the preset conditions.

[0022] In another aspect, the present invention provides a method for planning a dual-satellite link in Earth-Moon space. In this method, the visibility time of a target link is obtained, and based on the visibility time of the target link, a target visible link timing table T0 is determined. The target link includes any one of a star link, a star-station link, and a combined link. The star link includes a link between a first satellite and a second satellite. The star-station link includes a link between the first satellite and a station. The station is an observation station on Earth used to establish communication with the first satellite. The combined link includes the star link and the star-station link. The target visible link timing table T0 includes at least one first visible timing corresponding to the target link. Each first visible timing corresponding to the target link includes the visible start time and visible end time of the target link in each first visible timing. Based on the positions of the satellite, sun, moon, and earth corresponding to the target link, a spatial geometric relationship between the satellite, sun, moon, and earth corresponding to the target link is obtained. The effects of the earth's shadow and the moon's shadow are eliminated from the obtained spatial geometric relationship to obtain the illumination period of the satellite corresponding to the target link. Based on the preset visibility duration and the target visible link timing table T0, an application task link calculation timing table TA is determined; the application task link calculation timing table TA includes at least one second visible timing corresponding to the target link; any second visible timing corresponding to the target link includes the target link's visibility start time and visibility end time in any second visible timing; the target link's visibility start time in a second visible timing corresponds to the target link's visibility start time in a first visible timing; and the duration from the target link's visibility start time to its visibility end time in any second visible timing is the preset visibility duration. Based on the link effective visibility period factor weight of the target link in any second visible timing and the illumination factor weight of the satellite corresponding to the target link, a comprehensive factor weight of the target link in any second visible timing is determined; wherein the link effective visibility period factor weight is determined based on the at least one first visible timing and the at least one second visible timing; and the illumination factor weight of the satellite corresponding to the target link is determined based on the at least one second timing and the illumination period of the satellite corresponding to the target link.sequencing the at least one second visible time sequence based on the priority of the comprehensive factor weight of the target link at each second visible time sequence, to obtain an energy balance calculation time sequence table TB; the energy balance calculation time sequence table TB includes at least one third visible time sequence corresponding to the target link; one third visible time sequence corresponding to the target link corresponds to one second visible time sequence corresponding to the target link; any third visible time sequence corresponding to the target link includes an energy analysis start time, an energy analysis end time, a link effective visible period factor weight, an illumination factor weight of a satellite corresponding to the target link, and a comprehensive factor weight at the any third visible time sequence; the energy analysis start time at the any third visible time sequence is a visible start time of the target link included in the second visible time sequence corresponding to the any third visible time sequence; the energy analysis end time at the any third visible time sequence is determined based on a visible end time of the target link included in the second visible time sequence corresponding to the any third visible time sequence and a preset link establishment recovery time. Based on the energy analysis start time and the energy analysis end time at the any third visible time sequence, the power generation, the load power consumption and the residual power of a battery array included in a satellite corresponding to the target link at the any third visible time sequence are determined. Based on the power generation, the load power consumption and the residual power of the battery array at the any third visible time sequence satisfying a preset condition, the energy balance of the target link at the any third visible time sequence is determined. Based on the energy balance result of the target link at each third visible time sequence, a link application task time sequence table TC is obtained; the link application task time sequence table TC includes the third visible time sequence of the energy balance corresponding to the target link. The link application task time sequence table TC is displayed to prompt the application of the target link based on the link application task time sequence table TC.

[0023] The application has the advantages that: the application directly deduces the calculation process through multi-time sequence link layer association and dimension perspective, facilitates the query and analysis of the process and the result, and is suitable for various link application scenarios from the perspective of maximizing the benefit of the applied link, so as to provide an optimal and alternative link time sequence scheme for the reasonable application of the link by related personnel. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 A structural schematic diagram of a lunar-terrestrial space dual-satellite link establishment planning system provided by the application is shown in the figure.

[0025] Figure 2 A schematic diagram of a target visible link time sequence table T0, an application task link calculation time sequence table TA and an energy balance calculation time sequence table TB provided by the application is shown in the figure.

[0026] Figure 3 A flowchart of a method for planning a link establishment for a dual-satellite Earth-Moon space link provided by the present invention. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present application will be described below in conjunction with the drawings in the embodiments of the present application. Among them, in the description of the present application, unless otherwise specified, " / " indicates that the objects associated before and after are in an "or" relationship. For example, A / B can represent A or B; "and / or" in the present application is only a description of the association relationship of the associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone, where A and B can be singular or plural. In addition, in the description of the present application, unless otherwise specified, "multiple" refers to two or more than two. "At least one of the following" or similar expressions refers to any combination of these items, including any combination of single or plural items. For example, at least one of a, b, or c can represent: a, b, c, ab, ac, bc, or abc, where a, b, c can be single or multiple. In addition, in order to facilitate the clear description of the technical solutions of the embodiments of the present application, in the embodiments of the present application, words such as "first" and "second" are used to distinguish between identical or similar items with substantially the same functions and effects. Those skilled in the art will understand that words such as "first" and "second" do not limit the quantity and execution order, and words such as "first" and "second" do not necessarily limit differences. At the same time, in the embodiments of the present application, words such as "exemplary" or "for example" are used to indicate examples, illustrations or explanations. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or design.

[0028] In recent years, interest in cis-lunar space exploration has remained high. With increasing cis-lunar activities, the demand for real-time communication in this space has also increased. Due to limited ground-based tracking and control network resources and limited communication coverage, a new form of space-based intersatellite link has emerged: a link architecture between DRO satellites and LEO satellites. Establishing links between cis-lunar satellites is of great significance for communication, measurement, autonomous orbit determination, and navigation. Link planning is the process of formulating a reasonable and executable link execution (or application) plan based on comprehensive constraints such as space flight scenarios, application mission requirements, satellite operating modes, payload planning, and energy balance.

[0029] According to different lunar space link building application task requirements, the link feasibility of DRO satellite, LEO satellite and ground resources needs to be considered. Compared with the near-earth orbit single satellite link planning, the lunar space double satellite link planning is more complex: firstly, for the link visibility, the time staggered inter-satellite (DRO satellite and LEO satellite) and ground-satellite visible arc segments need to be faced; secondly, the double satellite energy needs to be synchronized to meet the demand, and the satellite energy is closely related to the double satellite orbit, illumination condition (lunar shadow), satellite working mode. In the lunar space background, the double satellites fly differently, and these factors are coupled with each other when building a link. How to arrange a link building execution time sequence can not only guarantee the feasibility of implementation, but also improve the application task benefit, that is, there is more effective link building time in the long time link building task cycle of the satellite platform. Based on this, the link building planning scheme of the lunar space double satellite link has not been publicly obtained at the current stage. Therefore, how to establish the lunar space double satellite link planning is a problem to be solved.

[0030] In order to solve the above problems, the application provides a lunar space double satellite link building planning system and method, which can intuitively deduce the calculation process through the multi-time sequence link table dimension perspective, facilitate the query and analysis of the process and results. And from the perspective of maximizing the benefit of the application link, it is suitable for various link application scenes, and provides the optimal and alternative link time sequence scheme for the reasonable application of the link by the relevant personnel.

[0031] Figure 1 The application provides a lunar space double satellite link building planning system. Referring to Figure 1 The lunar space double satellite link building planning system provided by the application includes a target link visibility calculation module, a satellite illumination period calculation module, a weight factor link time sequence table construction module, an energy balance estimation module, a link building planning result output module and a visual display module.

[0032] The target link visibility calculation module is used to obtain the visible time of the target link, and based on the visible time of the target link, a target visible link time sequence table T0 is determined.

[0033] The target link includes any one of a satellite-satellite link, a satellite-station link and a comprehensive link. The satellite-satellite link includes a link between a first satellite and a second satellite. The satellite-station link includes a link between the first satellite and a station. The station is an observation station on the earth for building a link with the first satellite. The comprehensive link includes the satellite-satellite link and the satellite-station link.

[0034] Referring to Figure 2The target visible link timing table T0 may include multiple visible time period records (also referred to as first visible time periods in this embodiment). The time period information may be recorded separately. That is, the target visible link timing table T0 may include at least one first visible time period corresponding to the target link. Any first visible time period corresponding to the target link includes the target link's visible start time and visible end time in any first visible time period.

[0035] For example, in the target visible link timing table T0, the visible start time of the first record is T011 and the visible end time is T012. The visible start time of the Nth record is T0N1 and the visible end time is T0N2, and so on.

[0036] In some embodiments, the target link visibility calculation module stores the visibility time Tsat of the star link and the visibility time Tsta of the satellite station link. If the target link is a star link, the target link visibility calculation module is configured to determine the visibility time Tsat as the visibility time of the star link. If the target link is a satellite station link, the target link visibility calculation module is configured to determine the visibility time Tsta as the visibility time of the satellite station link. If the target link is a comprehensive link, the target link visibility calculation module is configured to determine the union of the visibility time Tsat and the visibility time Tsta as the visibility time of the comprehensive link.

[0037] In some embodiments, the first satellite is a DRO satellite and the second satellite is a LEO satellite. The DRO satellite and the LEO satellite can fly in a cis-lunar transfer orbit. In this cis-lunar space, the visible link arc between the DRO satellite, the LEO satellite, and the observation station can be fully utilized to conduct communication measurements and related experiments.

[0038] The visibility time Tsat is determined based on the position of the first satellite, the position of the second satellite, the position of the station, and the radius of the earth. The visibility time Tsta is determined based on the position of the first satellite, the position of the station, and the radius of the earth.

[0039] The satellite illumination period calculation module is used to determine the spatial geometric relationship between the satellite, sun, moon, and Earth corresponding to the target link based on the positions of the satellite, sun, moon, and Earth. Furthermore, the influence of the Earth's and Moon's shadows is eliminated from this spatial geometric relationship to obtain the satellite illumination period corresponding to the target link.

[0040] In some embodiments, see Figure 1The earth-moon space dual-satellite link chain establishment planning system also includes an orbit simulator module. The orbit simulator module can be used to simulate the running orbit of a satellite corresponding to a target link according to a chain establishment application task scenario, a time range Ts~Te, and determine the position of the satellite corresponding to the target link based on the simulated running orbit of the satellite corresponding to the target link, and calculate the positions of the sun, the earth, and the moon.

[0041] The weight factor link timing table construction module is configured to determine an application task link calculation timing table TA based on the preset visible duration and the target visible link timing table T0.

[0042] The application task link calculation timing table TA includes at least one second visible timing corresponding to the target link. Any second visible timing corresponding to the target link includes a visible start time and a visible end time of the target link at the second visible timing. The visible start time of the target link at a second visible timing corresponds to the visible start time of the target link at a first visible timing. The duration from the visible start time to the visible end time of the target link at any second visible timing is the preset visible duration (which can also be referred to as the required chain establishment duration in the embodiments of the present application).

[0043] In some embodiments, the weight factor link timing table construction module can determine the application task link calculation timing table TA according to an application requirement calculation method, a required chain establishment duration, and weight factor configuration parameters. Each timing of the application task link calculation timing table TA can include a link start time, a link end time, a sequence number of the link start time in the timing table T0, and a sequence number of the link end time in the timing table T0.

[0044] In some embodiments, the application requirement calculation method can include traversal calculation and fast calculation.

[0045] If the application requirement calculation method is traversal calculation, the link start time of the first record of the application task link calculation timing table TA is TA11=T011, and the end time is TA12=T011+TP; the link start time of the second record is TA21=T021, and the end time is TA22=T021+TP. In this way, all records in the application task link calculation timing table TA are obtained as shown in Table 2. Figure 2 TP is the required chain establishment duration determined according to chain establishment application task planning or analysis requirements.

[0046] If the application requirement calculation method is fast calculation, then TA11 = T011, record the link start time in the timing table T0 as 1; the end time is TA12 = T011 + TP, determine the position of TA12 in the timing table T0, record it as i, and record the sequence number i of the link end time in the timing table T0. The link start time of the second record is TA21 = T0i 1, record the sequence number i of the link start time in the timing table T0, and the end time is TA22 = T0i 1 + TP, determine the position j of the link end time TA22 in the timing table T0 and record it. And so on, we can get the following Figure 2 The application task link shown calculates all records in the timing table TA.

[0047] The module for constructing a weight factor link timing table is also used to determine the comprehensive factor weight of the target link at any second visible timing based on the link effective visible period factor weight of the target link at any second visible timing and the illumination factor weight of the satellite corresponding to the target link.

[0048] The effective visibility period factor weight of the link is determined based on at least one first visibility time sequence and at least one second visibility time sequence. The illumination factor weight of the satellite corresponding to the target link is determined based on at least one second time sequence and the illumination period of the satellite corresponding to the target link.

[0049] In some embodiments, the module for constructing a weight factor link timing table is further configured to determine the period from the visible start time to the visible end time included in any second visible timing sequence as a first period, determine the period from the visible start time to the visible end time included in any first visible timing sequence as a second period, determine the period of overlap between the first period and each second period as a third period, and determine the ratio of the third period to the first period as the link effective visible period factor weight for any second visible timing sequence.

[0050] In some embodiments, the module for constructing the weight factor link timing table is further configured to determine a period of time in which the first period overlaps with an illumination period of the satellite corresponding to the target link as a fourth period of time, and to determine a ratio of the fourth period of time to the first period of time as the illumination factor weight of the satellite corresponding to the target link.

[0051] The weight factor link timing table construction module is further configured to sort at least one second visible timing based on the priority of the comprehensive factor weight of the target link in each second visible timing to obtain an energy balance calculation timing table TB.

[0052] The energy balance calculation timing table TB includes at least one third visible timing sequence corresponding to the target link. Each third visible timing sequence corresponding to the target link corresponds to a second visible timing sequence corresponding to the target link. Any third visible timing sequence corresponding to the target link includes the energy analysis start time, energy analysis end time, link effective visible period factor weight, satellite illumination factor weight corresponding to the target link, and comprehensive factor weight. The energy analysis start time for any third visible timing sequence is the visibility start time of the target link included in the second visible timing sequence corresponding to the third visible timing sequence. The energy analysis end time for any third visible timing sequence is determined based on the visibility end time of the target link included in the second visible timing sequence corresponding to the third visible timing sequence and a preset link establishment and recovery time.

[0053] In some embodiments, the comprehensive factor weight can be selected according to the weight factor configuration to select a single factor or multiple factors with different weight ratios. In the embodiment of the present application, the multi-factor weight setting can be selected by default, and the weight ratio of each factor is assigned to 1. Based on the comprehensive factor weight value, it can be sorted by priority (for example, sorted in descending order of weight value) to obtain the following: Figure 2 The energy balance calculation time table TB is shown.

[0054] The energy balance estimation module is configured to determine the power generation, load power consumption, and remaining power of the battery array included in the satellite corresponding to the target link in any third visible time sequence based on the energy analysis start time and energy analysis end time in any third visible time sequence. The energy balance of the target link in any third visible time sequence is determined based on the power generation, load power consumption, and remaining power of the battery array in any third visible time sequence meeting preset conditions.

[0055] In some embodiments, the satellite corresponding to the target link includes at least one mission system and at least one payload. The power generation of the battery array at any third visible time sequence is determined based on the solar incidence angle on the battery array. The load power consumption of the battery array is determined based on the operating time sequence of each mission system in the at least one mission system and the operating time sequence of each payload in the at least one payload. The remaining power of the battery array is determined based on the initial power of the battery array and the charge and discharge status of the simulated battery.

[0056] In some embodiments, the Calculate the power generation of the battery array. Where PS represents the maximum power generation of the satellite battery array, n represents the number of sampling points of the solar incident angle θ of the battery array during the stage, T n Represents the time interval for sampling solar incidence angle data.

[0057] In some embodiments, the Calculate the power consumption of the entire satellite load. mRepresents the power of a single load m, t m Indicates the startup time of a single machine with load m.

[0058] In some embodiments, the Calculate the change in power within the phase. Based on the initial variables of the battery array and the change in power within the phase, the remaining power of the battery array can be obtained.

[0059] In some embodiments, the residual current in phase i is:

[0060]

[0061] When in the light area, flag1=1, when in the shadow area, flag=0;

[0062] Q delta When greater than 0, flag2=1;

[0063] Q delta When less than 0, flag2=0;

[0064] Among them U c is the charging voltage, U f is the discharge voltage, η c is the charging efficiency, η BRD is the output efficiency of the discharge regulator, Q(0) is the initial charge, and the unit is Ah.

[0065] In some embodiments, the satellite corresponding to the target link includes a solar sail panel driving mechanism and a solar sail panel. The solar sail panel driving mechanism is used to drive the solar sail panel to move. Figure 1 The Earth-Moon space dual-satellite link establishment planning system provided by the present invention also includes a link establishment mission requirement injection module and a battery array solar incidence angle calculation module.

[0066] Among them, the chain-building task requirement injection module is used to determine the control mode of the solar panel drive mechanism, the working sequence of each task system, and the working sequence of each load.

[0067] Furthermore, the solar array solar incidence angle calculation module is configured to determine the period between the energy analysis start time and the energy analysis end time in any third visible time sequence as the energy analysis period. Based on the position of the satellite corresponding to the target link and the position of the sun during the energy analysis period, the solar light vector of the sun at the position of the satellite corresponding to the target link is calculated. Based on the control mode of the solar panel drive mechanism during the energy analysis period, the normal vector of the solar array is determined. Based on the solar light vector and the normal vector, the solar incidence angle on the solar array during the energy analysis period is calculated.

[0068] Exemplarily, in the case that the target link is a star link, the battery array solar incidence angle calculation module can obtain the positions of the DRO satellite, the LEO satellite and the sun. Then, the position of the sun can be subtracted from the position of the DRO satellite to obtain a solar vector of the DRO satellite in an orbit coordinate system. The position of the sun can be subtracted from the position of the LEO satellite to obtain a solar vector of the LEO satellite in the orbit coordinate system. The sunlight vector in the DRO satellite body system and the sunlight vector in the LEO satellite body system can be calculated through coordinate system conversion. In addition, according to the position and attitude of the DRO satellite and the working time sequence of the DRO satellite mission system, the attitude information of the DRO satellite in the corresponding mode during the link establishment is calculated for each time sequence in the energy balance calculation time sequence table TB. Similarly, the above method is calculated for the LEO satellite to obtain the attitude information of the LEO satellite in the corresponding mode during the link establishment.

[0069] In addition, according to the sailboard rotation mode corresponding to the control mode of the solar sailboard driving mechanism, the normal vector of the battery array included in the DRO satellite and the normal vector of the battery array included in the LEO satellite are calculated.

[0070] The incidence angle of the sun on the battery array included in the DRO satellite can be calculated from the sunlight vector in the DRO satellite body system and the normal vector of the battery array included in the DRO satellite. In addition, the incidence angle of the sun on the battery array included in the LEO satellite can be calculated from the sunlight vector in the LEO satellite body system and the normal vector of the battery array included in the LEO satellite.

[0071] In some embodiments, the working time sequence of the mission system included in the satellite contains the attitude modes before, during and after the link establishment. The working time sequence of the load included in the satellite contains the time sequence combination of each single machine of the load used in the link establishment period.

[0072] In some embodiments, the energy balance estimation module can divide the energy evaluation stage according to the satellite link establishment process according to each period time sequence in the energy balance calculation time sequence table TB, and calculate the battery array power generation, load power consumption and battery capacity in each stage according to the stage battery capacity estimation method, and estimate whether the energy of the period time sequence is balanced.

[0073] In some embodiments, the energy assessment phase divides each link establishment cycle into a link establishment startup phase, a link establishment stabilization phase, and a link establishment termination phase based on the link establishment process. The link establishment startup phase primarily completes the transition of the satellite platform's operating mode and is a period of low power generation and load power consumption. The link establishment stabilization phase is a period of stable power generation and load power consumption. The link establishment termination phase, preferably during the satellite platform recovery time t, primarily completes the transition from link establishment to the satellite platform's normal mode and is a period of low power generation and load power consumption. The shadow conditions are used to identify whether the assessment phase is in a shadowed or sunny area. If the assessed phase spans both shadowed and sunny areas, the phase is further segmented based on the changes in shadow and sun areas, ensuring that each phase is independently within shadow or sun.

[0074] In some embodiments, the control modes of the solar panel drive mechanism include a normal mode and an angle-holding mode. Normal mode allows the solar panel drive mechanism to normally control the solar panel to track the sun. Angle-holding mode allows the rotation angles corresponding to the solar panel's positive and negative Y axes to be set based on application requirements.

[0075] When the control mode of the solar panel drive mechanism is normal mode, the solar panel drive mechanism automatically controls the solar panel to track the sun, and the solar array solar incidence angle calculation module is used to read the attitude information of the solar panel in the solar panel drive mechanism and determine the normal vector of the solar array based on the attitude information of the solar panel. When the control mode of the solar panel drive mechanism is angle hold mode, the solar array solar incidence angle calculation module is used to determine the angle to which the solar panel is to rotate based on the attitude information and orbit information of the satellite corresponding to the target link, and to send the angle to which the solar panel is to rotate to the solar panel drive mechanism. The solar array solar incidence angle calculation module is also used to read the attitude information of the solar panel in the solar panel drive mechanism after the solar panel rotates to the desired angle, and determine the normal vector of the solar array based on the attitude information of the solar panel.

[0076] The link establishment planning result output module is used to obtain a link establishment application task time sequence table TC based on the energy balance results of the target link in each third visible time sequence.

[0077] The link establishment application task sequence table TC includes the third visible sequence of the energy balance corresponding to the target link.

[0078] In other words, the link establishment planning results can be based on the energy balance results of the energy balance calculation time sequence table TB. Taking each time period in the energy balance calculation time sequence table TB as a reference, the energy imbalance of the satellites in each time period is eliminated, and the energy-balanced link establishment application task time sequence table TC is obtained by statistical summary.

[0079] The visual display module is used to display the link building application task timing table TC to prompt the application of the target link based on the link building application task timing table TC.

[0080] In some embodiments, the visualization module is further configured to display at least one of the following: target link content, target visible link time sequence table T0, spatial geometric relationships, and application task link calculation time sequence table TA. Furthermore, the visualization module is configured to display at least one of the following: power generation, load power consumption, and remaining power of the battery array at each third visible time sequence. Furthermore, the visualization module is configured to display a setting interface for at least one of the following: a preset visible duration, a preset link establishment and recovery time, and preset conditions.

[0081] In other words, the visualization display module can be used to display parameter configuration interfaces such as target link configuration, calculation method configuration, weight factor configuration, solar panel SADA control configuration, platform working timing, and load working timing, as well as interfaces for querying and displaying timing table processes such as T0, TA, TB, and TC, to meet the different needs of users.

[0082] Figure 3 The present invention provides a method for planning a link between two satellites in Earth-Moon space. Figure 3 The method for planning a link establishment for a dual-satellite Earth-Moon space link provided by the present invention includes the following steps S310-S380:

[0083] S310: Obtain the visible time of the target link, and determine the target visible link timing table T0 based on the visible time of the target link.

[0084] The target link includes any of a star link, a star-station link, and a combined link. A star link includes a link between a first satellite and a second satellite. A star-station link includes a link between a first satellite and a station. A station is an observation station on Earth used to observe the first and second satellites. Combined links include star links and star-station links. The target visible link timing table T0 includes at least one first visible timing sequence corresponding to the target link. Any first visible timing sequence corresponding to the target link includes the visible start time and visible end time of the target link in any first visible timing sequence.

[0085] S320: Based on the positions of the satellite, sun, moon, and earth corresponding to the target link, a spatial geometric relationship between the satellite, sun, moon, and earth corresponding to the target link is obtained. Furthermore, the effects of the earth's shadow and the moon's shadow are eliminated from the obtained spatial geometric relationship to obtain the illumination period of the satellite corresponding to the target link.

[0086] S330: Determine an application task link calculation schedule TA based on the preset visible duration and the target visible link schedule T0.

[0087] The application task link calculation timing table TA includes at least one second visible timing corresponding to the target link. Any second visible timing corresponding to the target link includes the visible start time and visible end time of the target link in any second visible timing. The visible start time of the target link in a second visible timing corresponds to the visible start time of the target link in a first visible timing. The duration from the visible start time to the visible end time of the target link in any second visible timing is the preset visible duration.

[0088] S340: Determine a comprehensive factor weight of the target link in any second visible timing based on the link effective visible period factor weight of the target link in any second visible timing and the illumination factor weight of the satellite corresponding to the target link.

[0089] The effective visibility period factor weight of the link is determined based on at least one first visibility time sequence and at least one second visibility time sequence. The illumination factor weight of the satellite corresponding to the target link is determined based on at least one second time sequence and the illumination period of the satellite corresponding to the target link.

[0090] S350: Sort at least one second visible time sequence based on the priority of the comprehensive factor weight of the target link in each second visible time sequence to obtain an energy balance calculation time sequence table TB.

[0091] The energy balance calculation timing table TB includes at least one third visible timing sequence corresponding to the target link. Each third visible timing sequence corresponding to the target link corresponds to a second visible timing sequence corresponding to the target link. Any third visible timing sequence corresponding to the target link includes the energy analysis start time, energy analysis end time, link effective visible period factor weight, satellite illumination factor weight corresponding to the target link, and comprehensive factor weight. The energy analysis start time for any third visible timing sequence is the visibility start time of the target link included in the second visible timing sequence corresponding to the third visible timing sequence. The energy analysis end time for any third visible timing sequence is determined based on the visibility end time of the target link included in the second visible timing sequence corresponding to the third visible timing sequence and a preset link establishment and recovery time.

[0092] S360: Based on the energy analysis start time and energy analysis end time in any third visible time sequence, determine the power generation, load power consumption, and remaining power of the battery array included in the satellite corresponding to the target link in any third visible time sequence. If the power generation, load power consumption, and remaining power of the battery array in any third visible time sequence meet preset conditions, determine the energy balance of the target link in any third visible time sequence.

[0093] S370: Based on the energy balance results of the target link in each third visible time sequence, obtain a link establishment application task time sequence table TC.

[0094] The link establishment application task sequence table TC includes the third visible sequence of the energy balance corresponding to the target link.

[0095] S380: Displaying the link establishment application task sequence table TC to prompt the application of the target link based on the link establishment application task sequence table TC.

[0096] The above embodiments are described using DRO satellites and LEO satellites as examples. In actual applications, if a high-orbit satellite has the same link establishment application as a DRO satellite, the same is applicable.

[0097] In some schemes, multiple embodiments of the present application can be combined and the combined scheme can be implemented. Optionally, some operations in the process of each method embodiment are optionally combined, and / or the order of some operations is optionally changed. In addition, the execution order between the steps of each process is only exemplary and does not constitute a limitation on the execution order between the steps. There can also be other execution orders between the steps. It is not intended to indicate that the execution order is the only order in which these operations can be performed. Ordinary technicians in this field will think of many ways to reorder the operations described herein. In addition, it should be noted that the process details involved in a certain embodiment of this article are also applicable to other embodiments in a similar manner, or different embodiments can be used in combination.

[0098] Furthermore, some steps in the method embodiments may be equivalently replaced with other possible steps. Alternatively, some steps in the method embodiments may be optional and may be deleted in certain usage scenarios. Alternatively, other possible steps may be added to the method embodiments. Furthermore, the various method embodiments may be implemented separately or in combination.

[0099] Through the description of the above implementation methods, technical personnel in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional modules is used as an example. In actual applications, the above-mentioned functions can be assigned to different functional modules as needed, that is, the internal structure of the system can be divided into different functional modules to complete all or part of the functions described above.

[0100] In several embodiments provided in the present application, it should be understood that the disclosed system and method can be implemented in other manners. For example, the division of the system embodiments described above is merely a logical function division, and there can be another division manner for the actual implementation. For example, a plurality of units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the displayed or discussed mutual couplings or direct couplings or communication connections between different units, or the among different units, can be indirect couplings or communication connections through some interfaces, and electrical, mechanical or other forms.

[0101] In addition, each function unit in the embodiments of the present application can be integrated into a processing unit, or each unit can exist physically independently, or two or more units can be integrated into one unit. The integrated unit can be implemented in the form of hardware, or in the form of a software function unit.

[0102] When the integrated unit is implemented in the form of a software function unit and sold or used as an independent product, it can be stored in a readable storage medium. Based on such an understanding, the technical solutions of the embodiments of the present application essentially, or the part that contributes to the prior art, or all or a part of the technical solutions can be embodied in the form of a software product. The software product is stored in a storage medium, and includes several instructions for causing an apparatus (which can be a single chip, a chip, etc.) or a processor to perform all or part of the steps of the methods described in the embodiments of the present application. The foregoing storage medium includes: a U disk, a mobile hard disk, a read only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk, and various other media that can store program codes.

[0103] The above is merely specific embodiments of the present application, but the protection scope of the present application is not limited thereto. Any change or replacement within the technical scope disclosed in the present application should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A system for planning and establishing a link between two satellites in Earth-Moon space, characterized in that: include: A target link visibility calculation module is configured to obtain the visibility time of a target link and determine a target visible link timing table T0 based on the visibility time of the target link; wherein the target link includes any one of a star link, a star-station link, and a comprehensive link; the star link includes a link between a first satellite and a second satellite; the star-station link includes a link between the first satellite and a station; the station is an observation station on Earth that establishes a link and communicates with the first satellite; the comprehensive link includes the star link and the star-station link; the target visible link timing table T0 includes at least one first visible timing corresponding to the target link; any first visible timing corresponding to the target link includes a visible start time and a visible end time of the target link under any first visible timing; a satellite illumination period calculation module, configured to obtain a spatial geometric relationship between the satellite, the sun, the moon, and the earth corresponding to the target link based on the positions of the satellite, the sun, the moon, and the earth, and to eliminate the effects of the earth's shadow and the moon's shadow from the obtained spatial geometric relationship to obtain the illumination period of the satellite corresponding to the target link; Construct the weight factor link timing table module: Used to determine an application task link calculation timing table TA based on a preset visible duration and the target visible link timing table T0; the application task link calculation timing table TA includes at least one second visible timing corresponding to the target link; any second visible timing corresponding to the target link includes a visible start time and a visible end time of the target link in any second visible timing; the visible start time of the target link in one of the second visible timings corresponds to the visible start time of the target link in one of the first visible timings; the duration from the visible start time to the visible end time of the target link in any second visible timing is the preset visible duration; The method is further configured to determine a comprehensive factor weight of the target link at any second visible timing based on a link effective visible period factor weight of the target link at any second visible timing and an illumination factor weight of a satellite corresponding to the target link; wherein the link effective visible period factor weight is determined based on the at least one first visible timing and the at least one second visible timing; and the illumination factor weight of the satellite corresponding to the target link is determined based on the at least one second timing and the illumination period of the satellite corresponding to the target link. It is also used to sort the at least one second visible timing based on the priority of the comprehensive factor weight of the target link in each second visible timing to obtain an energy balance calculation timing table TB; the energy balance calculation timing table TB includes at least one third visible timing corresponding to the target link; one third visible timing corresponding to the target link corresponds to one second visible timing corresponding to the target link; any third visible timing corresponding to the target link includes the energy analysis start time, energy analysis end time, the effective visible period factor weight of the link, the illumination factor weight of the satellite corresponding to the target link, and the comprehensive factor weight in any third visible timing; the energy analysis start time in any third visible timing is the visible start time of the target link included in the second visible timing corresponding to any third visible timing; the energy analysis end time in any third visible timing is determined based on the visible end time of the target link included in the second visible timing corresponding to any third visible timing and a preset link establishment recovery time; An energy balance estimation module is configured to determine the power generation, load power consumption, and remaining power of a battery array included in the satellite corresponding to the target link in any third visible time sequence based on the energy analysis start time and the energy analysis end time in the any third visible time sequence; determining an energy balance of the target link in any third visible time sequence based on that the power generation, load power consumption, and remaining power of the battery array in any third visible time sequence meet preset conditions; a link establishment planning result output module, configured to obtain a link establishment application task timing table TC based on the energy balance result of the target link under each of the third visible time sequences; the link establishment application task timing table TC includes the third visible time sequence of the energy balance corresponding to the target link; The visual display module is used to display the link establishment application task sequence table TC to prompt the application of the target link based on the link establishment application task sequence table TC.

2. The system according to claim 1, wherein: The target link visibility calculation module stores the visible time Tsat of the star link and the visible time Tsta of the star station link; In a case where the target link is the star link, the target link visibility calculation module is configured to determine the visibility time Tsat as the visibility time of the star link; In a case where the target link is the satellite station link, the target link visibility calculation module is configured to determine the visibility time Tsta as the visibility time of the satellite station link; In the case that the target link is the integrated link, the target link visibility calculation module is configured to determine the union of the visible time Tsat and the visible time Tsta as the visible time of the integrated link.

3. The system according to claim 2, characterized in that It also includes an orbit simulator module; the orbit simulator module is used to determine the position of the satellite corresponding to the target link based on simulating the orbit of the satellite corresponding to the target link, and is used to calculate the positions of the sun, the earth and the moon.

4. The system according to claim 3, characterized in that The first satellite is a long-distance retrograde orbit satellite; the second satellite is a low-Earth orbit satellite; the visible time Tsat is determined based on the position of the first satellite, the position of the second satellite, the position of the survey station and the radius of the earth; the visible time Tsta is determined based on the position of the first satellite, the position of the survey station and the radius of the earth.

5. The system according to claim 4, characterized in that The module for constructing the weight factor link timing table is further configured to: determine a period from a visible start time to a visible end time included in any second visible timing as a first period; Determine a time period from a visible start time to a visible end time included in any one of the first visible time sequences as a second time period; determining a period of time in which the first period of time overlaps with each of the second period of time as a third period of time; Determine the ratio of the third time period to the first time period as the effective visibility period factor weight of the link under any second visibility timing; determining a period during which the first period overlaps with an illumination period of a satellite corresponding to the target link as a fourth period; The ratio of the fourth time period to the first time period is determined as the illumination factor weight of the satellite corresponding to the target link.

6. The system according to claim 5, characterized in that The satellite corresponding to the target link includes at least one mission system and at least one payload; The power generation of the battery array in any third visible time sequence is determined based on the incident angle of the sun on the battery array; the load power consumption of the battery array is determined based on the operating time sequence of each task system in the at least one task system and the operating time sequence of each load in the at least one load; The remaining capacity of the battery array is determined based on the initial capacity of the battery array and the charge and discharge status of the simulated battery.

7. The system according to claim 6, characterized in that The satellite corresponding to the target link includes a solar panel drive mechanism and a solar panel; the solar panel drive mechanism is used to drive the solar panel activity, and the system also includes a link establishment task demand injection module and a battery array solar incidence angle calculation module; The link building task requirement injection module is used to: Determining a control mode of the solar panel driving mechanism, an operating sequence of each task system in the at least one task system, and an operating sequence of each load in the at least one load; The solar incident angle calculation module of the battery array is used for: Determine the period between the energy analysis start time and the energy analysis end time in any third visible time series as the energy analysis period; Calculating a sunlight vector of the sun at the position of the satellite corresponding to the target link based on the position of the satellite corresponding to the target link and the position of the sun during the energy analysis period; determining a normal vector of the battery array based on a control mode of the solar panel driving mechanism during the energy analysis period; An incident angle of the sun on the solar array during the energy analysis period is calculated based on the sunlight vector and the normal vector.

8. The system according to claim 7, characterized in that The control modes of the solar sail panel driving mechanism include a normal mode and an angle holding mode; When the control mode of the solar panel driving mechanism is the normal mode, the solar panel driving mechanism automatically controls the solar panel to track the sun, and the solar incident angle calculation module of the battery array is used to read the attitude information of the solar panel in the solar panel driving mechanism and determine the normal vector of the battery array based on the attitude information of the solar panel; When the control mode of the solar panel driving mechanism is the angle holding mode, the solar array solar incident angle calculation module is used to determine the angle to be rotated of the solar panel based on the attitude information and orbit information of the satellite corresponding to the target link, and send the angle to be rotated of the solar panel to the solar panel driving mechanism; The solar incident angle calculation module for the battery array is further configured to read the attitude information of the solar panel in the solar panel driving mechanism after the solar panel rotates the angle to be rotated, and determine the normal vector of the battery array based on the attitude information of the solar panel.

9. The system according to claim 8, characterized in that The visual display module is also used for: Display at least one of the content of the target link, the target visible link timing table T0, the spatial geometric relationship, and the application task link calculation timing table TA; and / or, Display at least one of the power generation, load power consumption and remaining power of the battery array in each of the third visible time series; and / or, A setting interface for displaying at least one of the preset visible duration, the preset link establishment recovery time, and the preset condition.

10. A method for planning a link establishment for a dual-satellite Earth-Moon space link, characterized in that: include: Obtaining a visible time of a target link, and determining a target visible link timing table T0 based on the visible time of the target link; wherein the target link includes any one of a star link, a star-station link, and a comprehensive link; the star link includes a link between a first satellite and a second satellite; the star-station link includes a link between the first satellite and a station; the station is an observation station on Earth that establishes a link and communicates with the first satellite; the comprehensive link includes the star link and the star-station link; the target visible link timing table T0 includes at least one first visible timing corresponding to the target link; any first visible timing corresponding to the target link includes a visible start time and a visible end time of the target link under any first visible timing; Obtaining a spatial geometric relationship between the satellite, the sun, the moon, and the earth corresponding to the target link based on the positions of the satellite, the sun, the moon, and the earth, and eliminating the effects of the earth's shadow and the moon's shadow from the obtained spatial geometric relationship to obtain an illumination period of the satellite corresponding to the target link; Based on the preset visible duration and the target visible link timing table T0, an application task link calculation timing table TA is determined; the application task link calculation timing table TA includes at least one second visible timing corresponding to the target link; any second visible timing corresponding to the target link includes the visible start time and visible end time of the target link in any second visible timing; the visible start time of the target link in one of the second visible timings corresponds to the visible start time of the target link in one of the first visible timings; the duration from the visible start time to the visible end time of the target link in any second visible timing is the preset visible duration; Determine a comprehensive factor weight of the target link at any second visible timing based on a link effective visible period factor weight of the target link at any second visible timing and an illumination factor weight of a satellite corresponding to the target link; wherein the link effective visible period factor weight is determined based on the at least one first visible timing and the at least one second visible timing; and the illumination factor weight of the satellite corresponding to the target link is determined based on the at least one second timing and the illumination period of the satellite corresponding to the target link. Based on the priority of the comprehensive factor weight of the target link in each second visible timing, the at least one second visible timing is sorted to obtain an energy balance calculation timing table TB; the energy balance calculation timing table TB includes at least one third visible timing corresponding to the target link; one third visible timing corresponding to the target link corresponds to one second visible timing corresponding to the target link; any third visible timing corresponding to the target link includes the energy analysis start time, energy analysis end time, the effective visible period factor weight of the link, the illumination factor weight of the satellite corresponding to the target link, and the comprehensive factor weight in any third visible timing; the energy analysis start time in any third visible timing is the visible start time of the target link included in the second visible timing corresponding to any third visible timing; the energy analysis end time in any third visible timing is determined based on the visible end time of the target link included in the second visible timing corresponding to any third visible timing and a preset link establishment and recovery time; Determine, based on the energy analysis start time and the energy analysis end time in any third visible time sequence, the power generation, load power consumption, and remaining power of the battery array included in the satellite corresponding to the target link in any third visible time sequence; determining an energy balance of the target link in any third visible time sequence based on that the power generation, load power consumption, and remaining power of the battery array in any third visible time sequence meet preset conditions; Based on the energy balance results of the target link under each of the third visible time sequences, a link establishment application task timing table TC is obtained; the link establishment application task timing table TC includes the third visible time sequence of the energy balance corresponding to the target link; The link establishment application task sequence table TC is displayed to prompt the application of the target link based on the link establishment application task sequence table TC.

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