Earth-moon space double-satellite link establishment planning system and method

Abstract

The invention provides an earth-moon space double-star link establishment planning system and method, relates to the technical field of satellite task planning, and can be used for establishing a multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target multi-target The calculation process is visually deduced through layer-by-layer association, dimension perspective and multi-time-sequence link table layer-by-layer association, process and result query and analysis are facilitated, the method is suitable for various link application scenes from the angle of benefit maximization of application links, and optimal and alternative link time sequence schemes are provided for reasonable application of links by related 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, the exploration of the cis-lunar space has been very popular. With more and more cis-lunar activities, the demand for instant communication in the cis-lunar space has also increased. With the limited resources of the ground-based measurement and control network and the limited breadth and depth of communication coverage, a new form of space-based intersatellite link has emerged, that is, to establish a link architecture between distant retrograde orbit (DRO) satellites and low earth orbit (LEO) satellites. The establishment of links between cis-lunar space satellites is of great significance for communication, measurement, autonomous orbit determination, navigation and other directions. The link planning is a reasonable and executable link execution plan arrangement given after considering the comprehensive constraints such as space flight scenarios, application mission requirements, satellite working modes, payload planning, energy balance, etc.

[0003] According to the different link building application mission requirements in the Earth-Moon space, the feasibility of the link between the DRO satellite and space-based resources (LEO satellites) and ground-based resources (stations) needs to be comprehensively considered. Compared with the planning of single-satellite links in low-Earth orbit, the planning of dual-satellite links in the Earth-Moon space is more complicated: first, for link visibility, it is necessary to face the inter-satellite (DRO satellite and LEO satellite) and satellite-Earth visible arcs with staggered timing; second, the energy of the dual-satellites must meet the needs synchronously, and the satellite energy is closely related to the dual-satellite orbits, lighting conditions (Earth-Moon shadows), and satellite working modes; in the background of the Earth-Moon space, the dual-satellite flights are different, and these factors are coupled with each other when building the link. Therefore, how to establish a dual-satellite link plan in the Earth-Moon space is an urgent problem 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 applicable to various link application scenarios from the perspective of maximizing the benefits of the application link, and provide optimal and alternative link timing solutions for the reasonable application of the link by relevant personnel.

[0005] The technical solution of the present invention to solve the above technical problems is as follows: In one aspect, the present invention provides a system for planning a link establishment of a dual-satellite link in an earth-moon space, comprising: 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.

[0006] The satellite illumination period calculation module is used to obtain the spatial geometric relationship between the satellite, the sun, the moon and the earth corresponding to the target link according to the positions of the satellite, the sun, the moon and the earth corresponding to the target link, and to eliminate the influence of the earth shadow and the moon shadow in the obtained spatial geometric relationship to obtain the illumination period of the satellite corresponding to the target link.

[0007] The module for constructing a weight factor link timing table is used to determine the application task link calculation timing table TA based on the 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 the visible start time and visible end time of the target link under any second visible timing; the visible start time of the target link under one of the second visible timing corresponds to the visible start time of the target link under one of the first visible timing; the duration from the visible start time to the visible end time of the target link under any second visible timing is the preset visible duration. It is also used to determine the comprehensive factor weight of the target link under any second visible timing based on the link effective visible period factor weight of the target link under any second visible timing and the illumination factor weight of the 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; 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 link effective visible period factor weight, 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.

[0008] Energy balance estimation module: used to determine the power generation, load power consumption and remaining power of the battery array included in the satellite corresponding to the target link at any third visible time sequence based on the energy analysis start time and energy analysis end time at any third visible time sequence. Based on the power generation, load power consumption and remaining power of the battery array at any third visible time sequence meeting the preset conditions, determine the energy balance of the target link at any third visible time sequence.

[0009] 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 timings; the link establishment application task timing table TC includes the third visible timing of the energy balance corresponding to the target link.

[0010] 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.

[0011] Based on the above technical solution, the present invention can also be improved as follows.

[0012] Further, 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. When the target link is the star link, the target link visibility calculation module is used to determine the visible time Tsat as the visible time of the star link. When the target link is the star station link, the target link visibility calculation module is used to determine the visible time Tsta as the visible time of the star station link. When the target link is the integrated link, the target link visibility calculation module is used to determine the union of the visible time Tsat and the visible time Tsta as the visible time of the integrated link.

[0013] 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, the earth and the moon.

[0014] Further, 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 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 station, and the radius of the earth.

[0015] Further, the module for constructing a weight factor link timing table is also used to determine the period from the visible start time to the visible end time included in any second visible timing as the first period. The period from the visible start time to the visible end time included in any first visible timing is determined as the second period. The period in which the first period overlaps with each of the second period is determined as the 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. The period in which the first period overlaps with the illumination period of the satellite corresponding to the target link is determined as the 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.

[0016] 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 at 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 working time sequence of each mission system in the at least one mission system and the working time sequence of each load 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 state of the simulated battery.

[0017] Further, the satellite corresponding to the target link includes a solar sail panel drive mechanism and a solar sail panel. The solar sail panel drive mechanism is used to drive the solar sail panel activity, and the system also includes a link building task demand injection module and a battery array solar incidence angle calculation module. The link building task demand injection module is used to determine the control mode of the solar sail panel drive mechanism, the working sequence of each task system in the at least one task system, and the working sequence of each load in the at least one load. 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 under 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 in the energy analysis period, the 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 sail panel drive mechanism in the energy analysis period, the normal vector of the battery array is determined. Based on the sunlight vector and the normal vector, the incident angle of the sun on the battery array in the energy analysis period is calculated.

[0018] Further, the control mode of the solar sail panel driving mechanism includes a normal mode and an angle holding mode. When the control mode of the solar sail panel driving mechanism is the normal mode, the solar sail panel driving mechanism automatically controls the solar sail 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 sail panel in the solar sail panel driving mechanism, and determine the normal vector of the battery array based on the attitude information of the solar sail panel. When the control mode of the solar sail panel driving mechanism is the angle holding mode, the solar incident angle calculation module of the battery array is used to determine the angle to be rotated of the solar sail 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 sail panel to the solar sail panel driving mechanism. The solar incident angle calculation module of the battery array is also used to read the attitude information of the solar sail panel in the solar sail panel driving mechanism after the solar sail panel rotates the angle to be rotated, and determine the normal vector of the battery array based on the attitude information of the solar sail panel.

[0019] Furthermore, the visualization display module is also used to 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 under each of the third visible timings. And / or, display a setting interface for at least one of the preset visible duration, the preset link establishment recovery time, and the preset conditions.

[0020] On the other hand, the present invention provides a method for planning the establishment of a dual-satellite link in the earth-moon space, in which the visible time of the target link is obtained, and the target visible link timing table T0 is determined based on the visible time of the target link. 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 the earth used to establish a link and communicate 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. According to the positions of the satellite, the sun, the moon, and the earth corresponding to the target link, the spatial geometric relationship between the satellite, the sun, the moon, and the earth corresponding to the target link is obtained, and the influence of the earth shadow and the moon shadow is eliminated in the obtained spatial geometric relationship to obtain the illumination period of the satellite corresponding to the target link. Based on the preset visible duration and the target visible link timing table T0, determine the application task link calculation timing table TA; 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 under any second visible timing; the visible start time of the target link under one of the second visible timing corresponds to the visible start time of the target link under one of the first visible timing; the duration from the visible start time to the visible end time of the target link under any second visible timing is the preset visible duration. Based on the link effective visible period factor weight of the target link under any second visible timing and the illumination factor weight of the satellite corresponding to the target link, determine the comprehensive factor weight of the target link under any second visible timing; 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; 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 time sequence, the at least one second visible time sequence is sorted 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; a third visible time sequence corresponding to the target link corresponds to a second visible time sequence corresponding to the target link; any third visible time sequence corresponding to the target link includes the energy analysis start time, energy analysis end time, the link effective visible period factor weight, the illumination factor weight of the satellite corresponding to the target link, and the comprehensive factor weight under any third visible time sequence; the energy analysis start time under any third visible time sequence is the visible start time of the target link included in the second visible time sequence corresponding to any third visible time sequence; the energy analysis end time under any third visible time sequence is determined based on the visible end time of the target link included in the second visible time sequence corresponding to any third visible time sequence and the preset link establishment recovery time. Based on the energy analysis start time and energy analysis end time under 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 under any third visible time sequence are determined. Based on the fact that the power generation, load power consumption and remaining power of the battery array in any third visible time sequence meet the preset conditions, the energy balance of the target link in any third visible time sequence is determined. Based on the energy balance results of the target link in each third visible time sequence, a link building application task timing table TC is obtained; the link building application task timing table TC includes the third visible time sequence of the energy balance corresponding to the target link. The link building application task timing table TC is displayed to prompt the application of the target link based on the link building application task timing table TC.

[0021] The beneficial effect of the present invention is that the present invention will integrate the intricately coupled orbits between multiple targets of dual-satellite links such as star links and star-station links, link visibility, satellite platform working sequence, lighting conditions, energy constraints and other influencing factors through multi-timing link surface layer association and dimensional perspective, intuitively deduce the calculation process, facilitate the query and analysis of the process and results, and from the perspective of maximizing the benefits of application links, it is suitable for various link application scenarios, and provides optimal and alternative link timing solutions for the reasonable application of links by relevant personnel. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A schematic diagram of the structure of a system for planning a link establishment of a dual-satellite link in Earth-Moon space provided by the present invention; Figure 2 A schematic diagram of the target visible link timing table T0, the application task link calculation timing table TA and the energy balance calculation timing table TB provided by the present invention; Figure 3A schematic diagram of the flow of a method for planning a link establishment for a dual-satellite link in Earth-Moon space provided by the present invention. DETAILED DESCRIPTION

[0023] 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, which 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. And, 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 items 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, the words "first", "second" and the like are used to distinguish between the same items or similar items with substantially the same functions and effects. Those skilled in the art will understand that the words "first", "second" and the like do not limit the quantity and execution order, and the words "first", "second" and the like do not necessarily limit the differences. At the same time, in the embodiments of the present application, the words "exemplary" or "for example" are used to indicate examples, illustrations or descriptions. 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.

[0024] In recent years, the exploration of the Earth-Moon space has been very popular. With more and more Earth-Moon activities, the demand for instant communication in the Earth-Moon space has also increased. With the limited resources of the ground-based measurement and control network and the limited breadth and depth of communication coverage, a new form of space-based intersatellite link has emerged, that is, the establishment of a link architecture between DRO satellites and LEO satellites. The establishment of links between Earth-Moon space satellites is of great significance for communication, measurement, autonomous orbit determination, navigation and other directions. Link establishment planning is a reasonable and executable link execution (or application) plan arrangement given after considering comprehensive constraints such as space flight scenarios, application mission requirements, satellite working modes, payload planning, and energy balance.

[0025] According to the different requirements of the Earth-Moon space link application mission, the feasibility of the links of DRO satellites, LEO satellites and ground-based resources needs to be considered in a coordinated manner. Compared with the planning of single-satellite links in low-Earth orbit, the planning of dual-satellite links in Earth-Moon space is more complicated: first, for link visibility, we have to face the inter-satellite (DRO satellite and LEO satellite) and satellite-Earth visible arcs with staggered timing; second, the energy of the dual-satellite must meet the needs synchronously, and the satellite energy is closely related to the dual-satellite orbit, lighting conditions (Earth-Moon shadow), and satellite working mode. In the background of Earth-Moon space, the two satellites fly differently, and these factors are coupled with each other during link building. How to arrange a link building execution sequence can not only ensure the feasibility of implementation, but also improve the efficiency of application tasks, that is, to have more effective link building time during the long link building mission cycle of the satellite platform. Based on this, at this stage, there is no publicly available link building planning scheme for the Earth-Moon space dual-satellite link. Therefore, how to establish the Earth-Moon space dual-satellite link planning is an urgent problem to be solved.

[0026] In view of the above problems, the present invention provides a system and method for planning the establishment of a dual-satellite link in the Earth-Moon space. Through the perspective of multiple timing link tables, the calculation process can be intuitively deduced, and the query and analysis of the process and results are convenient. In addition, from the perspective of maximizing the benefits of application links, it can be applicable to various link application scenarios, and provide optimal and alternative link timing solutions for the reasonable application of links by relevant personnel.

[0027] Figure 1 The present invention provides a system for planning the establishment of a dual-satellite link in Earth-Moon space. Figure 1 The Earth-Moon space dual-satellite link establishment planning system provided by the present invention includes a target link visibility calculation module, a satellite illumination period calculation module, a weight factor link timing table construction module, an energy balance estimation module, a link establishment planning result output module and a visualization display module.

[0028] The target link visibility calculation module is 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.

[0029] 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 a first satellite and a station. The station is an observation station on the earth that establishes a link communication with the first satellite. The comprehensive link includes a star link and a star-station link.

[0030] See also Figure 2, the target visible link timing table T0 may include multiple visible time period (also referred to as the first visible timing in the embodiment of the present application) records. The time period information may be recorded in strips. That is, the target visible link timing table T0 may include 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.

[0031] 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.

[0032] In some embodiments, 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. When the target link is a star link, the target link visibility calculation module is used to determine the visible time Tsat as the visible time of the star link. When the target link is a star station link, the target link visibility calculation module is used to determine the visible time Tsta as the visible time of the star station link. When the target link is a comprehensive link, the target link visibility calculation module is used to determine the union of the visible time Tsat and the visible time Tsta as the visible time of the comprehensive link.

[0033] 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-moon transfer orbit. In this cis-moon space, the visible link arc between the DRO satellite, the LEO satellite and the measuring station can be fully utilized to perform communication measurements and related experiments.

[0034] The visible 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 visible time Tsta is determined based on the position of the first satellite, the position of the station and the radius of the earth.

[0035] The satellite illumination period calculation module is used to obtain the spatial geometric relationship between the satellite, the sun, the moon and the earth corresponding to the target link according to the positions of the satellite, the sun, the moon and the earth corresponding to the target link. In addition, the influence of the earth shadow and the moon shadow is eliminated from the obtained spatial geometric relationship to obtain the illumination period of the satellite corresponding to the target link.

[0036] In some embodiments, see Figure 1The earth-moon space dual-satellite link establishment planning system provided by the present invention also includes an orbit simulator module. The orbit simulator module can be used to simulate the orbit of the satellite corresponding to the target link according to the link establishment application mission scenario and the time range Ts~Te. And, based on the simulated orbit of the satellite corresponding to the target link, determine the position of the satellite corresponding to the target link. And, calculate the positions of the sun, the earth and the moon.

[0037] The module for constructing a weight factor link timing table is used to determine an application task link calculation timing table TA based on a preset visible duration and a target visible link timing table T0.

[0038] Among them, 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 under any second visible timing. The visible start time of the target link under a second visible timing corresponds to the visible start time of the target link under a first visible timing. The duration from the visible start time to the visible end time of the target link under any second visible timing is the preset visible duration (which may also be referred to as the expected link establishment duration in the embodiment of the present application).

[0039] In some embodiments, the module for constructing the weight factor link timing table can determine the application task link calculation timing table TA based on the application requirement calculation method, the expected link establishment time and the weight factor configuration parameters. Each timing in the application task link calculation timing table TA may include the link start time, the link end time, the sequence number of the link start time in the timing table T0, and the sequence number of the link end time in the timing table T0.

[0040] In some embodiments, the application requirement calculation method may include ergodic calculation and fast calculation.

[0041] If the application demand 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. And so on, we can get Figure 2 All records in the application task link calculation timing table TA are shown. Among them, TP is the expected link establishment time determined according to the link establishment application task planning or analysis requirements.

[0042] 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 link end time in the timing table T0 as i. The link start time of the second record is TA21=T0i1, record the link start time in the timing table T0 as i, and the end time is TA22=T0i1+TP, determine the position j of the link end time TA22 in the timing table T0, and record it. And so on, get Figure 2 The application task link shown calculates all records in the timing table TA.

[0043] 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.

[0044] The effective visible period factor weight of the link is determined based on at least one first visible time sequence and at least one second visible 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.

[0045] In some embodiments, the module for constructing a weight factor link timing table is further used to determine the period from the visible start time to the visible end time included in any second visible timing as the first period. The period from the visible start time to the visible end time included in any first visible timing is determined as the second period. The period in which the first period overlaps with each second period is determined as the third period. The ratio of the third period to the first period is determined as the link effective visible period factor weight under any second visible timing.

[0046] In some embodiments, the module for constructing the weight factor link timing table is further used to determine the period of overlap between the first period and the illumination period of the satellite corresponding to the target link as the fourth period, and determine the ratio of the fourth period to the first period as the illumination factor weight of the satellite corresponding to the target link.

[0047] The module for constructing the weight factor link timing table is further used 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 the energy balance calculation timing table TB.

[0048] Among them, 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, link effective visible period factor weight, satellite illumination factor weight corresponding to the target link, and 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.

[0049] In some embodiments, the comprehensive factor weight can select a single factor or multiple factors according to the weight factor configuration and combine them at 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), and the following can be obtained: Figure 2 The energy balance calculation timing chart TB is shown.

[0050] The energy balance estimation module is used to determine the power generation, load power consumption and remaining power of the battery array included in the satellite corresponding to the target link at any third visible time sequence based on the energy analysis start time and energy analysis end time at any third visible time sequence. Based on the power generation, load power consumption and remaining power of the battery array at any third visible time sequence meeting the preset conditions, the energy balance of the target link at any third visible time sequence is determined.

[0051] 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 incident angle of the sun on the battery array. The load power consumption of the battery array is determined based on the working time sequence of each mission system in the at least one mission system and the working time sequence of each load 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 state of the simulated battery.

[0052] In some embodiments, the Calculate the power generation of the battery array. Among them, 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 in the stage, T n Represents the time interval for sampling the solar incidence angle data.

[0053] 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 load m.

[0054] In some embodiments, the Calculate the amount of power change within the stage. Based on the initial variables of the battery array and the amount of power change within the stage, the remaining power of the battery array can be obtained.

[0055] In some embodiments, the residual current in phase i is: When in the light area, flag1=1, and in the shadow area, flag=0; Q delta When greater than 0, flag2=1; Q delta When less than 0, flag2=0; 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, in Ah.

[0056] 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 task demand injection module and a battery array solar incidence angle calculation module.

[0057] Among them, the link-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.

[0058] Furthermore, the solar incident angle calculation module of the battery array is used to determine the period between the energy analysis start time and the energy analysis end time under any third visible time sequence as the energy analysis period. Based on the position of the satellite corresponding to the target link in the energy analysis period and the position of the sun, the 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 sail driving mechanism in the energy analysis period, the normal vector of the battery array is determined. Based on the sunlight vector and the normal vector, the incident angle of the sun on the battery array in the energy analysis period is calculated.

[0059] Exemplarily, when the target link is a star link, the solar incidence angle calculation module of the battery array can obtain the positions of the DRO satellite, the LEO satellite and the sun. Afterwards, the position of the DRO satellite can be subtracted from the position of the sun to obtain the solar vector of the DRO satellite in the orbital coordinate system. The position of the LEO satellite can be subtracted from the position of the sun to obtain the solar vector of the LEO satellite in the orbital coordinate system. The sunlight vector of the DRO satellite system and the sunlight vector of the LEO satellite system can be calculated through coordinate system conversion. And, according to the position and attitude of the DRO satellite and the working timing of the DRO satellite mission system, the attitude information of the DRO satellite in the corresponding mode during the link establishment period is calculated for each timing in the energy balance calculation timing table TB. Similarly, the above method is performed on the LEO satellite to obtain the attitude information of the LEO satellite in the corresponding mode during the link establishment period.

[0060] Furthermore, 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.

[0061] The incident angle of the sun on the battery array included in the DRO satellite can be calculated from the sunlight vector under the DRO satellite system and the normal vector of the battery array included in the DRO satellite. Also, the incident angle of the sun on the battery array included in the LEO satellite can be calculated from the sunlight vector under the LEO satellite system and the normal vector of the battery array included in the LEO satellite.

[0062] In some embodiments, the working sequence of the mission system included in the satellite includes the attitude modes before, during and after link establishment. The working sequence of the payload included in the satellite includes the timing combination of each single machine of the payload used during the link establishment period.

[0063] In some embodiments, the energy balance estimation module can divide the energy assessment stage according to the start and end time sequence of each energy period in the energy balance calculation time sequence table TB, and calculate the battery array power generation, load power consumption, and battery power of each stage in turn according to the stage battery power estimation method, and estimate whether the energy of the time sequence is balanced.

[0064] In some embodiments, the energy assessment stage is to divide each link building cycle into a link building start-up segment, a link building stabilization segment, and a link building end segment according to the link building process. Among them, the link building start-up segment mainly completes the switching of the satellite platform working mode, and is a load power consumption segment with low power generation. The link building stabilization segment is a load power consumption segment with stable power generation. The link building end segment preferably takes the satellite platform recovery time t period, and mainly completes the switching from link building to the normal mode of the satellite platform, which is a load power consumption segment with low power generation. According to the shadow situation, it is identified whether the assessment stage is in the shadow area or the sun-illuminated area. If the assessed stage spans the shadow area and the sun-illuminated area, the stage is further divided according to the changes in the shadow and illumination areas to ensure that each stage is in an independent shadow or illumination.

[0065] In some embodiments, the control mode of the solar panel driving mechanism includes a normal mode and an angle holding mode. The normal mode means that the solar panel driving mechanism can normally control the solar panel to track the sun. The angle holding mode means that the rotation angles corresponding to the positive and negative Y axes of the solar panel need to be set separately based on application requirements.

[0066] Wherein, when the control mode of the solar sail panel driving mechanism is the normal mode, the solar sail panel driving mechanism automatically controls the solar sail 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 sail panel in the solar sail panel driving mechanism, and determine the normal vector of the battery array based on the attitude information of the solar sail panel. When the control mode of the solar sail panel driving mechanism is the angle holding mode, the solar incident angle calculation module of the battery array is used to determine the angle to be rotated of the solar sail 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 sail panel to the solar sail panel driving mechanism. The solar incident angle calculation module of the battery array is also used to read the attitude information of the solar sail panel in the solar sail panel driving mechanism after the solar sail panel rotates the angle to be rotated, and determine the normal vector of the battery array based on the attitude information of the solar sail panel.

[0067] 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 result of the target link under each third visible time sequence.

[0068] The link building application task timing table TC includes the third visible timing of the energy balance corresponding to the target link.

[0069] That is to say, the link establishment planning result can be based on the energy balance result of the energy balance calculation timing table TB, taking each time period in the energy balance calculation timing table TB as a reference, eliminating the energy imbalance of the satellite in each time period, and statistically summarizing to obtain the energy-balanced link establishment application task timing table TC.

[0070] 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.

[0071] In some embodiments, the visualization display module is further used to 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 under each third visible timing. And / or, display a setting interface for at least one of the preset visible time, the preset link establishment and recovery time, and the preset conditions.

[0072] 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, load working timing, and interfaces for querying and displaying timing table processes such as T0, TA, TB, TC, etc., to meet the different needs of users.

[0073] Figure 3 The present invention provides a method for planning the establishment of a dual-satellite link in Earth-Moon space. Figure 3 The method for planning the link establishment of a dual-satellite link in the Earth-Moon space provided by the present invention comprises the following steps S310-S380: 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.

[0074] 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 a first satellite and a measuring station. The measuring station is an observation station on the earth for observing the first satellite and the second satellite. The comprehensive link includes a star link and a 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.

[0075] S320: According to the positions of the satellite, the sun, the moon and the earth corresponding to the target link, a spatial geometric relationship between the satellite, the sun, the moon and the earth corresponding to the target link is obtained, and the influence of the earth shadow and the moon shadow is eliminated from the obtained spatial geometric relationship to obtain the illumination period of the satellite corresponding to the target link.

[0076] S330: Determine an application task link calculation schedule TA based on the preset visible duration and the target visible link schedule T0.

[0077] Among them, 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.

[0078] S340: Determine a 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.

[0079] The effective visible period factor weight of the link is determined based on at least one first visible time sequence and at least one second visible 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.

[0080] 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.

[0081] Among them, 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, link effective visible period factor weight, satellite illumination factor weight corresponding to the target link, and 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.

[0082] 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. Based on the power generation, load power consumption and remaining power of the battery array in any third visible time sequence meeting the preset conditions, determine the energy balance of the target link in any third visible time sequence.

[0083] S370: Based on the energy balance results of the target link in each third visible time sequence, obtain a link building application task time sequence table TC.

[0084] The link building application task timing table TC includes the third visible timing of the energy balance corresponding to the target link.

[0085] S380: Displaying the link building application task sequence table TC to prompt application of the target link based on the link building application task sequence table TC.

[0086] The above embodiments are described by taking 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 also applicable.

[0087] 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 restriction 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. A person of ordinary skill in the art will think of a variety of 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.

[0088] In addition, some steps in the method embodiment may be equivalently replaced by other possible steps. Alternatively, some steps in the method embodiment may be optional and may be deleted in certain usage scenarios. Alternatively, other possible steps may be added to the method embodiment. Furthermore, the method embodiments may be implemented separately or in combination.

[0089] 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.

[0090] In the several embodiments provided in the present application, it should be understood that the disclosed systems and methods can be implemented in other ways. For example, the system embodiments described above are only schematic. For example, the division of the modules or units is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of systems or units, which can be electrical, mechanical or other forms.

[0091] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0092] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a readable storage medium. Based on this understanding, the technical solution of the embodiment of the present application is essentially or the part that contributes or all or part of the technical solution can be embodied in the form of a software product, which is stored in a storage medium, including several instructions to enable a device (which can be a single-chip microcomputer, chip, etc.) or a processor (processor) to perform all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read only memory (ROM), random access memory (RAM), disk or optical disk and other media that can store program code.

[0093] The above contents are only specific implementation methods of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present application shall be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A system for planning the establishment of a dual-satellite link in Earth-Moon space, characterized in that: include: A 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 that establishes 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; A satellite illumination period calculation module is used to obtain the spatial geometric relationship between the satellite, the sun, the moon and the earth corresponding to the target link according to the positions of the satellite, the sun, the moon and the earth corresponding to the target link, and to eliminate the influence of the earth shadow and the moon shadow in 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 under any second visible timing; the visible start time of the target link under one of the second visible timings corresponds to the visible start time of the target link under one of the first visible timings; the duration from the visible start time to the visible end time of the target link under any second visible timing is the preset visible duration; It 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; 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; 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 link effective visible period factor weight, 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; Energy balance estimation module: used to determine the power generation, load power consumption and remaining power of the battery array included in the satellite corresponding to the target link under any third visible time sequence based on the energy analysis start time and energy analysis end time under any third visible time sequence; Determine the energy balance of the target link at any third visible time sequence based on that the power generation, load power consumption and remaining power of the battery array at 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 timings; the link establishment application task timing table TC includes the third visible timing of the energy balance corresponding to the target link; 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.

2. The system according to claim 1, characterized in that 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 the case where the target link is the star link, the target link visibility calculation module is used to determine the visible time Tsat as the visible time of the star link; In the case where the target link is the satellite station link, the target link visibility calculation module is used to determine the visible time Tsta as the visible time of the satellite station link; In the case where the target link is the integrated link, the target link visibility calculation module is used 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 used to: determine the period from the visible start time to the visible end time included in any second visible timing as the first period; Determine a time period from a visible start time to a visible end time included in any first visible time sequence as a second time period; Determine 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 visible time period factor weight of the link under any second visible timing; Determine a period in 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 at 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 working time sequence of each task system in the at least one task system and the working time sequence of each load in the at least one load; The remaining power of the battery array is determined based on the initial power of the battery array and the charge and discharge state of the simulated storage battery.

7. The system according to claim 6, characterized in that 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 activities, and the system also includes a link building task demand injection module and a battery array solar incident angle calculation module; The link building task requirement injection module is used to: Determining a control mode of the solar panel driving mechanism, a working sequence of each task system in the at least one task system, and a working 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 under 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 in the energy analysis period, calculating the sunlight vector of the sun at the position of the satellite corresponding to the target link; determining a normal vector of the battery array based on a control mode of the solar panel driving mechanism during the energy analysis period; Based on the sunlight vector and the normal vector, an incident angle of the sun on the battery array in the energy analysis period is calculated.

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 sail panel driving mechanism is the normal mode, the solar sail panel driving mechanism automatically controls the solar sail 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 sail panel in the solar sail panel driving mechanism, and determine the normal vector of the battery array based on the attitude information of the solar sail panel; When the control mode of the solar sail panel driving mechanism is the angle holding mode, the battery array solar incident angle calculation module is used to determine the angle to be rotated of the solar sail 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 sail panel to the solar sail panel driving mechanism; The battery array solar incident angle calculation module is also used 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 of a dual-satellite link in Earth-Moon space, characterized in that: include: 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 station; the station is an observation station on the earth that establishes 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; According to the positions of the satellite, the sun, the moon and the earth corresponding to the target link, a spatial geometric relationship between the satellite, the sun, the moon and the earth corresponding to the target link is obtained, and the influence of the earth shadow and the moon shadow is eliminated from the obtained spatial geometric relationship to obtain the 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 under any second visible timing; the visible start time of the target link under one of the second visible timings corresponds to the visible start time of the target link under one of the first visible timings; the duration from the visible start time to the visible end time of the target link under any second visible timing is the preset visible duration; 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; 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; 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 of the second visible timings, 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; 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 link effective visible period factor weight, 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; Based on the energy analysis start time and the energy analysis end time under 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 under any third visible time sequence; Determine the energy balance of the target link at any third visible time sequence based on that the power generation, load power consumption and remaining power of the battery array at any third visible time sequence meet preset conditions; Based on the energy balance result of the target link under each of the third visible time sequences, a link building application task time sequence table TC is obtained; the link building application task time sequence table TC includes the third visible time sequence of the energy balance corresponding to the target link; The link building application task schedule table TC is displayed to prompt the application of the target link based on the link building application task schedule table TC.

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