A method and system for orbit maintenance maneuver of a distant retrograde orbit spacecraft

Abstract

The application provides a long-distance retro-orbit spacecraft orbit maintenance maneuver method and system. The method generates a candidate maneuver period based on the current orbit state of the spacecraft, and removes the maneuver period that does not meet the requirements through engineering constraints. Next, a first maneuver parameter combination set is constructed for preliminary first parameter screening. Then, based on the first parameter screening result, a second maneuver parameter combination set is constructed for detailed second parameter screening to determine the second screening parameter combination. Further, based on the second screening parameter combination, the above steps are repeated to determine the third screening parameter combination of the next maintenance maneuver. The maneuver interval time between the current maintenance maneuver and the next maintenance maneuver is determined. Finally, based on the maneuver interval time, the final target maneuver parameter combination is determined to be used for orbit maintenance maneuver of the spacecraft. The method effectively improves the efficiency and accuracy of the long-distance retro-orbit spacecraft orbit maintenance maneuver.

Description

Technical Field

[0001] This invention relates to the field of spacecraft orbit control technology, specifically to an orbit maintenance maneuvering method and system for a long-distance retrograde orbit spacecraft. Background Technology

[0002] With the continuous development of aerospace technology, lunar space exploration has gradually become a research hotspot in the global aerospace field. Among them, distant retrograde orbits (DROs), as a unique type of three-body dynamic orbit in lunar space, have the characteristics of orbiting the Earth progradely and orbiting the Moon retrogradely, and possess significant advantages such as low-energy orbit insertion, stable parking, and accessibility across the entire lunar orbital region. Therefore, lunar DROs can provide highly stable parking orbits and are extremely important test sites and transit stations in the development of lunar space and deep space exploration.

[0003] Currently, orbit maintenance technology primarily focuses on low Earth orbit (LEO), emphasizing maneuver design to address spacecraft orbital stability issues. However, the lunar orbit environment where the DRO operates differs significantly from that of LEO. Spacecraft operating on the DRO face a more severe threat of solar eclipses, with frequent prolonged eclipses. For solar-powered spacecraft, this could lead to prolonged power outages, severely impacting their normal operation. Furthermore, perturbations in lunar space and routine unloading activities can cause spacecraft to deviate from their planned orbits, affecting their stability and eclipse performance, necessitating orbit maintenance maneuvers.

[0004] Therefore, there is an urgent need for an orbit maintenance maneuver method suitable for long-distance retrograde orbit spacecraft to effectively address the impact of long solar eclipses on spacecraft on DRO and achieve long-term stable orbit maintenance to meet practical engineering needs. Summary of the Invention

[0005] The technical problem to be solved by this invention is the inability to efficiently and accurately perform orbit maintenance maneuvers on spacecraft in retrograde orbits at long distances.

[0006] To address the aforementioned technical problems, this invention provides a method and system for orbit maintenance maneuvering of a long-distance retrograde orbit spacecraft, specifically employing the following technical solution:

[0007] In a first aspect, the present invention provides an orbit maintenance maneuver method for a spacecraft in a long-distance retrograde orbit, applicable to a target spacecraft in a long-distance retrograde orbit. The method includes: First, determining a first candidate maneuver period based on the target spacecraft's current orbital state information and a high-fidelity ephemeris model; wherein the first candidate maneuver period is before a long eclipse, and the long eclipse is the time of an eclipse with an equivalent shadow duration greater than a preset duration. Then, filtering the first candidate maneuver period based on preset engineering constraints to determine a second candidate maneuver period. Next, constructing a first set of maneuver parameter combinations based on the second candidate maneuver period, a preset maneuver size range, and a first preset maneuver size interval. The first set of maneuver parameter combinations includes multiple first candidate parameter combinations, each including a first maneuver time and a first maneuver size. The first maneuver time is within the second candidate maneuver period, and the first maneuver size is determined based on the preset maneuver size range and the first preset maneuver size interval. Second, based on the first set of maneuver parameter combinations, filtering the first parameters using a high-fidelity ephemeris model and a first maintenance effect evaluation threshold to determine a first filtered parameter combination. Furthermore, based on the first selection parameter combination and the second preset maneuver size interval, a second maneuver parameter combination set is constructed. This set includes multiple second candidate parameter combinations, each comprising a second maneuver time and a second maneuver size. The second maneuver time is determined based on the first maneuver time in the first selection parameter combination, and the second maneuver size is determined based on the first maneuver size and the second preset maneuver size interval in the first selection parameter combination; wherein the second preset maneuver size interval is smaller than the first preset maneuver size interval. Then, based on the second maneuver parameter combination set, second parameter selection is performed using a high-fidelity ephemeris model and a second maintenance effect evaluation threshold to determine the second selection parameter combination. Next, the updated orbital state information of the target spacecraft after maneuvering is determined based on the second selection parameter combination. Using this updated orbital state information as the current orbital state information, the first candidate maneuver time period is determined again to obtain the third selection parameter combination. Based on the second and third selection parameter combinations, the maneuver interval time corresponding to the second selection parameter combination is determined. Finally, the target maneuver parameter combination is determined based on the maneuver interval time, and the target spacecraft is maneuvered based on this target maneuver parameter combination. The target maneuver parameter combination is the second selection parameter combination corresponding to the longest maneuver interval time.

[0008] This method uses the timing and magnitude of the maintenance maneuver as design parameters. Based on the spacecraft's current orbital state, candidate maneuver periods are generated, and unsuitable maneuver times are eliminated through engineering constraints. Next, a first set of maneuver parameter combinations is constructed for preliminary first-parameter screening. Then, based on the first-parameter screening results, a second set of maneuver parameter combinations is constructed for more detailed second-parameter screening to determine the precise selected parameter combinations, i.e., the second-screened parameter combinations. Further, based on the second-screened parameter combinations, the above steps are repeated to determine the third-screened parameter combinations for the next maintenance maneuver. Then, based on the second and third-screened parameters, the maneuver interval between the current and next maintenance maneuver is determined. Finally, based on the maneuver interval, the final target maneuver parameter combination is obtained for orbit maintenance maneuvers of the spacecraft. This method, considering the characteristics of long-distance retrograde orbits, engineering application requirements, and the impact of solar eclipses, employs a two-stage progressive screening to determine the target maneuver parameter combination, i.e., the target maneuver timing and the target maneuver magnitude. In this way, while ensuring screening efficiency, all effective combinations of maneuver parameters can be fully covered to find the optimal combination of target maneuver parameters, thereby meeting the need to avoid long-term eclipses and maintain long-term stability, thus improving the efficiency and accuracy of orbit maintenance maneuvers for long-distance retrograde orbit spacecraft.

[0009] In conjunction with the first aspect, in one alternative implementation, the determination of the first candidate maneuver period based on the target spacecraft's current orbital state information and a high-fidelity ephemeris model includes: First, determining the target spacecraft's predicted orbital state information within a first preset period using a high-fidelity ephemeris model, based on the current orbital state information. Then, determining the equivalent shadow duration of the solar eclipse based on the predicted orbital state information and the sun's position information. Second, determining the moment when the first equivalent shadow duration of the solar eclipse exceeds the preset duration as the long eclipse moment. Finally, determining the period from the current moment to the long eclipse moment as the first candidate maneuver period; wherein, the current moment corresponds to the moment of the current orbital state information.

[0010] In conjunction with the first aspect, in one alternative implementation, the aforementioned preset engineering constraints include one or more of the following: the elevation angle of the target spacecraft relative to the ground observation station is greater than a first preset angle, the angle between the antenna pointing of the target spacecraft and the direction of the line connecting the target spacecraft and the Earth is less than a second preset angle, and the observation time of the target spacecraft is greater than a time threshold.

[0011] In conjunction with the first aspect, in one alternative implementation, the above-mentioned method of determining the first selected parameter combination based on the first set of maneuver parameter combinations through a high-fidelity ephemeris model and a first maintenance effect evaluation threshold includes: First, based on the high-fidelity ephemeris model, determining the first maintenance effect evaluation parameter for each first candidate parameter combination in the first set of maneuver parameter combinations; the first maintenance effect evaluation parameter is used to characterize the orbital maintenance effect of the target spacecraft after maneuvering based on the first candidate parameter combination. Then, based on the first maintenance effect evaluation parameter and the first maintenance effect evaluation threshold, determining the first selected parameter combination, which is the first candidate parameter combination whose first maintenance effect evaluation parameter satisfies the first maintenance effect evaluation threshold.

[0012] In conjunction with the first aspect, in one alternative implementation, the aforementioned first maintenance effect evaluation parameters include one or more of the following: the bounded distance range between the target spacecraft and the moon during a second preset time period, and the time from when the target spacecraft performs its maneuver to when the first long solar eclipse occurs.

[0013] In conjunction with the first aspect, in one alternative implementation, the above-mentioned second parameter selection based on the second set of maneuver parameter combinations, using a high-fidelity ephemeris model and a second maintenance effect evaluation threshold, to determine the second selection parameter combination includes: First, based on the high-fidelity ephemeris model, determining the second maintenance effect evaluation parameter for each second candidate parameter combination in the second set of maneuver parameter combinations; the second maintenance effect evaluation parameter is used to characterize the orbital maintenance effect of the target spacecraft after maneuvering based on the second candidate parameter combination. Then, based on the second maintenance effect evaluation parameter and the second maintenance effect evaluation threshold, determining the second selection parameter combination, which is the second candidate parameter combination whose second maintenance effect evaluation parameter satisfies the second maintenance effect evaluation threshold.

[0014] In conjunction with the first aspect, in one alternative implementation, the aforementioned first set of maneuver parameter combinations is represented by a first parameter grid. The horizontal axis of the first parameter grid represents the first maneuver time, the vertical axis represents the first maneuver magnitude, and each grid point of the first parameter grid represents a first candidate parameter combination. The second set of maneuver parameter combinations is represented by a second parameter grid. The horizontal axis of the second parameter grid represents the second maneuver time, the vertical axis represents the second maneuver magnitude, and each grid point of the second parameter grid represents a second candidate parameter combination.

[0015] In conjunction with the first aspect, in one alternative implementation, the aforementioned first maneuver time is: the lunar perihelion time of the target spacecraft during the second candidate maneuver period.

[0016] In conjunction with the first aspect, in one alternative implementation, the aforementioned preset maneuver size range is [-10, 10] m / s, the first preset maneuver size interval is 0.5 m / s, and the second preset maneuver size interval is 0.1 m / s.

[0017] Secondly, this invention provides an orbit maintenance maneuvering system for a long-distance retrograde orbit spacecraft, applicable to target spacecraft in a long-distance retrograde orbit. Specifically, the system includes: a candidate maneuvering time period determination module, a time period filtering module, a first construction module, a first parameter filtering module, a second construction module, a second parameter filtering module, an orbital state update module, a third parameter filtering module, and a maneuvering parameter determination module. The candidate maneuvering time period determination module is used to determine a first candidate maneuvering time period based on the target spacecraft's current orbital state information and a high-fidelity ephemeris model; wherein the first candidate maneuvering time period is before a long solar eclipse, and the long solar eclipse time period is the time when an eclipse occurs with an equivalent shadow duration greater than a preset duration. The time period filtering module is used to filter the first candidate maneuvering time period based on preset engineering constraints to determine a second candidate maneuvering time period after the time period filtering. The first construction module can be used to construct a first set of maneuver parameter combinations based on a second candidate maneuver time period, a preset maneuver size range, and a first preset maneuver size interval. The first set of maneuver parameter combinations includes multiple first candidate parameter combinations, each including a first maneuver time and a first maneuver size. The first maneuver time falls within the second candidate maneuver time period, and the first maneuver size is determined based on the preset maneuver size range and the first preset maneuver size interval. The first parameter filtering module can be used to filter the first parameters based on the first set of maneuver parameter combinations using a high-fidelity ephemeris model and a first maintenance effect evaluation threshold, thus determining the first filtered parameter combinations. The second construction module can be used to construct a second set of maneuver parameter combinations based on the first filtered parameter combinations and a second preset maneuver size interval. The second set of maneuver parameter combinations includes multiple second candidate parameter combinations, each including a second maneuver time and a second maneuver size. The second maneuver time is determined based on the first maneuver time in the first filtered parameter combinations, and the second maneuver size is determined based on the first maneuver size and the second preset maneuver size interval in the first filtered parameter combinations; wherein the second preset maneuver size interval is smaller than the first preset maneuver size interval. The second parameter filtering module can be used to filter the second set of maneuver parameter combinations using a high-fidelity ephemeris model and a second maintenance effect evaluation threshold to determine the second selected parameter combinations. The orbital state update module can be used to determine the updated orbital state information of the target spacecraft after maneuvering, based on the second selected parameter combinations. The third parameter filtering module can be used to use the updated orbital state information as the current orbital state information to re-determine the first candidate maneuver period, thereby obtaining the third selected parameter combination. The maneuver parameter determination module can be used to determine the maneuver interval time corresponding to the second selected parameter combination based on the second and third selected parameter combinations.The maneuver parameter determination module can also be used to determine the target maneuver parameter combination based on the maneuver interval time, so as to apply maneuver to the target spacecraft based on the target maneuver parameter combination, which is the second screening parameter combination corresponding to the longest maneuver interval time.

[0018] Thirdly, the present invention provides an electronic device, comprising: a memory and one or more processors; the memory being coupled to the processors; wherein the memory stores computer program code, the computer program code including computer instructions, which, when executed by the processor, cause the electronic device to perform the method provided by the first aspect and any of its alternative implementations.

[0019] Fourthly, the present invention provides a computer-readable storage medium including computer instructions that, when executed on an electronic device, cause the electronic device to perform the method provided by the first aspect and any alternative implementation thereof.

[0020] Understandably, the beneficial effects of the orbit maintenance maneuvering system for the long-distance retrograde orbit spacecraft provided in the second aspect, the electronic equipment in the third aspect, and the computer-readable storage medium in the fourth aspect can be referenced to the beneficial effects of the first aspect and any of its possible design embodiments, which will not be elaborated here. Attached Figure Description

[0021] Figure 1 A schematic flowchart illustrating the orbit maintenance maneuver method for a long-distance retrograde orbit spacecraft provided in this application embodiment;

[0022] Figure 2 A schematic diagram of the track segment corresponding to the second candidate maneuvering time period provided in the embodiments of this application;

[0023] Figure 3 A schematic diagram of the first combination of screening parameters provided in an embodiment of this application;

[0024] Figure 4 A schematic diagram of the second combination of screening parameters provided in an embodiment of this application;

[0025] Figure 5 A schematic diagram of the orbit maintenance maneuvering system for a long-distance retrograde orbit spacecraft provided in this application embodiment. Detailed Implementation

[0026] The embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described below do not represent all embodiments consistent with this application. They are merely examples of systems and methods consistent with some aspects of this application as detailed in the claims.

[0027] With the continuous development of aerospace technology, lunar space exploration has gradually become a research hotspot in the global aerospace field. Among them, long-distance retrograde orbits, as a unique type of three-body dynamic orbit in lunar space, have the characteristics of orbiting the Earth progradely and orbiting the Moon retrogradely, and possess significant advantages such as low-energy orbit insertion, stable parking, and accessibility across the entire lunar orbit. Therefore, the lunar-Earth space DRO can provide highly stable parking orbits and is an extremely important test field and transit station in the development of lunar space and deep space exploration.

[0028] Currently, orbit maintenance technology primarily focuses on low Earth orbit (LEO), emphasizing maneuver design to address spacecraft orbital stability issues. However, the lunar orbit environment where the DRO operates differs significantly from that of LEO. Spacecraft operating on the DRO face a more severe threat of solar eclipses, with frequent prolonged eclipses. For solar-powered spacecraft, this could lead to prolonged power outages, severely impacting their normal operation. Furthermore, perturbations in lunar space and routine unloading activities can cause spacecraft to deviate from their planned orbits, affecting their stability and eclipse performance, necessitating orbit maintenance maneuvers.

[0029] Therefore, there is an urgent need for an orbit maintenance maneuver method suitable for long-distance retrograde orbit spacecraft to effectively address the impact of long solar eclipses on spacecraft on DRO and achieve long-term stable orbit maintenance to meet practical engineering needs.

[0030] To address the aforementioned issues, this application provides a method and system for orbit maintenance maneuvering of a spacecraft in a long-distance retrograde orbit. This method uses the timing and magnitude of the maintenance maneuver as design parameters. Based on the spacecraft's current orbital state, candidate maneuver time periods are generated, and unsuitable maneuver times are eliminated through engineering constraints. Next, a first set of maneuver parameter combinations (e.g., a sparse parameter grid) is constructed for preliminary screening. Then, based on the preliminary screening, a second set of maneuver parameter combinations (e.g., a dense parameter grid) is constructed for detailed screening to determine the precise parameter combinations. Further, the above steps are repeated based on the selected parameter combinations to determine the time interval between the current maintenance maneuver and the next. Finally, based on the time interval of the maintenance maneuver, the final target maneuver parameter combination is determined for orbit maintenance maneuvering of the spacecraft. This method, considering the characteristics of long-distance retrograde orbits, engineering application requirements, and the impact of solar eclipses, employs a two-stage progressive screening to determine the target maneuver parameter combination, namely, the target maneuver timing and the target maneuver magnitude. In this way, while ensuring screening efficiency, all effective combinations of maneuver parameters can be fully covered to find the optimal combination of target maneuver parameters, thereby meeting the need to avoid long-term eclipses and maintain long-term stability, thus improving the efficiency and accuracy of orbit maintenance maneuvers for long-distance retrograde orbit spacecraft.

[0031] The solutions provided in the embodiments of this application will be described below with reference to the accompanying drawings.

[0032] Specifically, Figure 1 A flowchart illustrating the orbit maintenance maneuvering method for a long-distance retrograde orbit spacecraft provided in this application embodiment is shown below. Figure 1 As shown, the orbit maintenance maneuver method for a long-distance retrograde orbit spacecraft provided in this application includes the following steps S101-S110:

[0033] S101. Based on the current orbital status information of the target spacecraft and the high-fidelity ephemeris model, determine the first candidate maneuvering period.

[0034] In this embodiment, the current orbital state information of the target spacecraft in a long-distance retrograde orbit can first be obtained. This current orbital state information can be used to characterize the target spacecraft's position and velocity at the current moment. For example, the current orbital state information may include: position parameters along the x-axis, y-axis, and z-axis, velocity parameters along the x-axis, y-axis, and z-axis, and the current time parameter.

[0035] Then, based on the current orbital state information and a high-fidelity ephemeris model, a first candidate maneuver period can be determined. This first candidate maneuver period is the candidate interval for maneuvering times to maintain the orbit. Specifically, the first candidate maneuver period must fall before the longest solar eclipse, which is the time when an eclipse occurs with an equivalent shadow duration greater than a preset length. This ensures that the target spacecraft performs maneuvers before the longest solar eclipse, thus reducing the impact of the eclipse on the target spacecraft.

[0036] In some embodiments, S101 may specifically include the following steps S1011-S1014:

[0037] S1011. Based on the current orbital status information, determine the predicted orbital status information of the target spacecraft within the first preset time period using a high-fidelity ephemeris model.

[0038] Specifically, based on the current orbital state information, the orbital state can be integrated using a high-fidelity ephemeris model to obtain the predicted orbital state information of the target spacecraft within the first preset time period.

[0039] The first preset time period can be preset based on prior knowledge and actual application needs; for example, the first preset time period can be 10 years. This ensures the stability of the target spacecraft over a relatively long period.

[0040] S1012. Based on the predicted orbital state information and the position information of the sun, determine the equivalent shadow duration of the solar eclipse.

[0041] Then, based on the predicted orbital state information and the sun's position information, the positional relationship between the target spacecraft and the sun can be determined, so as to further determine the equivalent shadow duration of the solar eclipse.

[0042] The equivalent shadow duration can be expressed as follows:

[0043] ;

[0044] in, Indicates the duration of the equivalent shadow. This represents the occlusion rate of a celestial body when the target spacecraft is in the total shadow. =1; Indicates the start time of the penumbra. Indicates the end time of the penumbra.

[0045] S1013. The moment when the first equivalent shadow duration is longer than the preset duration of a solar eclipse is determined as the moment of a long solar eclipse.

[0046] In this embodiment, a prolonged solar eclipse is defined as a solar eclipse exceeding the requirements for a target spacecraft to undergo a solar or lunar eclipse. For example, the preset duration can be 1 hour; that is, the moment when the first equivalent shadow duration of a solar eclipse exceeds 1 hour can be determined as the moment of a prolonged solar eclipse. The preset duration can be set according to the needs of actual applications, and this application does not impose specific limitations on it.

[0047] S1014. The period from the current time to the time of the long solar eclipse is determined as the first candidate maneuvering period.

[0048] The current time refers to the time corresponding to the current orbital state information.

[0049] In this way, the first candidate maneuver time period can be effectively and accurately determined through the above S1011-S1014.

[0050] S102. Based on preset engineering constraints, the first candidate maneuver time period is screened to determine the second candidate maneuver time period after the time period screening.

[0051] Then, the first candidate maneuver period is screened using preset engineering constraints to ensure that the target spacecraft can meet the engineering application requirements of observation, communication, and command operations with the ground observation station within the second candidate maneuver period. The second candidate maneuver period facilitates the further determination of the maneuver timing.

[0052] In some embodiments, the above-mentioned preset engineering constraints may include one or more of the following: the elevation angle of the target spacecraft relative to the ground observation station is greater than a first preset angle, the angle between the antenna pointing of the target spacecraft and the direction of the line connecting the target spacecraft and the Earth is less than a second preset angle, and the observation time of the target spacecraft is greater than a time threshold.

[0053] It should be noted that the first preset angle, the second preset angle, and the time threshold can be preset based on prior knowledge and actual application requirements, and this application does not impose specific limitations on them. For example, the first preset angle can be 0°, and the second preset angle can be 70°.

[0054] For example, Figure 2 A schematic diagram of the track segment corresponding to the second candidate maneuver time period provided in the embodiments of this application, as shown below. Figure 2 As shown, track segment 201 is the track segment corresponding to the second candidate maneuver time period after time period filtering.

[0055] S103. Based on the second candidate maneuver time period, the preset maneuver size range and the first preset maneuver size interval, construct a first maneuver parameter combination set.

[0056] Furthermore, by constructing a first set of maneuver parameter combinations, it is easier to filter (or search) maneuver parameter combinations, so as to quickly determine the timing and magnitude of the maneuver.

[0057] The first set of maneuver parameter combinations includes multiple first candidate parameter combinations. Each first candidate parameter combination includes a first maneuver time and a first maneuver size. The first maneuver time is within the second candidate maneuver time period, and the first maneuver size is determined based on a preset maneuver size range and a first preset maneuver size interval.

[0058] In some embodiments, the first set of maneuver parameter combinations can be represented by a first parameter grid; wherein the horizontal axis of the first parameter grid represents the first maneuver time, the vertical axis of the first parameter grid represents the first maneuver magnitude, and each grid point of the first parameter grid represents a first candidate parameter combination. This first parameter grid, as a sparse parameter grid, facilitates rapid preliminary screening of maneuver parameter combinations, thereby improving the efficiency of maneuver parameter screening.

[0059] In some embodiments, the first maneuver time is the lunar perihelion time of the target spacecraft during the second candidate maneuver period.

[0060] Specifically, the candidate maneuver times can be further discretized from the second candidate maneuver period into perilune times. For example, the orbit of the target spacecraft can be divided into multiple orbital segments by using the apogee, with the perilune as the representative of each orbital segment, and the perilune as the candidate maneuver time.

[0061] For example, taking the target spacecraft's orbital period of approximately 14 days as an example, the orbital segment that can be divided by the apogee is approximately 7 days. That is, the perigee moment replaces 24×7=168 moments (taking each hour as a candidate moment as an example), which greatly reduces the amount of calculation.

[0062] Typically, the perigee moment is when the target spacecraft is at a phase of 0 degrees or 180 degrees. Therefore, in the embodiments of this application, the perigee moment or the moment corresponding to the 0-degree or 180-degree phase can be selected as the first maneuver moment.

[0063] In some embodiments, the preset maneuver size range is [-10, 10] m / s, and the first preset maneuver size interval is 0.5 m / s, that is, within the range of -10 m / s to 10 m / s, a value is taken every 0.5 m / s to serve as the first maneuver size. This ensures the stability of the target spacecraft during DRO operation within the [-10, 10] m / s range. The first preset maneuver size interval of 0.5 m / s ensures the accuracy of determining the maneuver size.

[0064] The preset maneuver size and the first preset maneuver size interval can be preset based on ensuring the stability of DRO, combined with prior knowledge and the needs of actual application (e.g., using a smaller maneuver size).

[0065] S104. Based on the first set of maneuver parameter combinations, the first parameter is screened using a high-fidelity ephemeris model and a first maintenance effect evaluation threshold to determine the first screening parameter combination.

[0066] Next, using a high-fidelity ephemeris model and a first maintenance effect evaluation threshold, the first candidate parameter combinations in the first set of first maneuver parameter combinations constructed in S103 can be screened to determine the first screened parameter combinations. These first screened parameter combinations are the first candidate parameter combinations that satisfy the first maintenance effect evaluation threshold.

[0067] In some embodiments, S104 may specifically include:

[0068] First, based on a high-fidelity ephemeris model, the first maintenance effect evaluation parameter is determined for each first candidate parameter combination in the first maneuver parameter combination set.

[0069] Specifically, a high-fidelity ephemeris model can be used to determine the orbital state of the target spacecraft after maneuvering based on the first candidate parameter combination. Then, based on this defined state, the first maintenance effect evaluation parameter corresponding to the first candidate parameter combination can be determined. The first maintenance effect evaluation parameter characterizes the orbital maintenance effect of the target spacecraft after maneuvering based on the first candidate parameter combination.

[0070] Furthermore, based on the first maintenance effect evaluation parameter and the first maintenance effect evaluation threshold, a first screening parameter combination is determined. The first screening parameter combination is a first candidate parameter combination in which the first maintenance effect evaluation parameter satisfies the first maintenance effect evaluation threshold.

[0071] In some embodiments, the first maintenance effect evaluation parameters include one or more of the following: the bounded distance range between the target spacecraft and the Moon during a second preset time period, and the time from when the target spacecraft performs a maneuver to when the first long solar eclipse occurs.

[0072] Specifically, the first maintenance effect evaluation parameters may include: stability evaluation parameters, and / or, eclipse shadow evaluation parameters. The stability evaluation parameters may be: the bounded distance range between the target spacecraft and the Moon within a second preset time period, such as 10 years. The eclipse shadow evaluation parameters may be: the time from the first long eclipse after the target spacecraft performs a maneuver. Thus, the stability evaluation parameters can characterize the stability of the target spacecraft after maneuvering based on the first candidate parameter combination, and the eclipse shadow evaluation parameters can characterize the eclipse situation of the target spacecraft after maneuvering based on the first candidate parameter combination, thereby avoiding frequent maneuvers of the target spacecraft.

[0073] In one implementation, for the stability evaluation parameter, the first maintenance effect evaluation threshold may include: the bounded distance between the target spacecraft and the moon within a second preset time period is 40,000 to 140,000 kilometers. For the eclipse shadow evaluation parameter, the first maintenance effect evaluation threshold may further include: the time between the target spacecraft performing its maneuver and the first occurrence of the long eclipse is greater than six months.

[0074] It is understandable that the first maintenance effect evaluation threshold can be preset based on prior knowledge and the needs of actual application, and this application does not impose specific limitations on it.

[0075] For example, Figure 3 A schematic diagram of the first combination of screening parameters provided in the embodiments of this application is shown below. Figure 3 As shown, the set of first selection parameter combinations is represented by parameter grid 301. The horizontal axis of parameter grid 301 represents the moment of the first maneuver, the vertical axis represents the magnitude of the first maneuver, and each grid point in parameter grid 301 represents a first selection parameter combination. The color of the region corresponding to a grid point in parameter grid 301 represents the magnitude of the eclipse shadow evaluation parameter for that first selection parameter combination.

[0076] It should be noted that, Figure 3 The colors used to represent the magnitude of the eclipse shadow evaluation parameters are for illustrative purposes only and are not intended to be limiting.

[0077] In some embodiments, after obtaining the first set of screening parameters, feasible maneuvers and margins can be determined for each set of first screening parameters (using the first maneuver time as an example, which is the perigee time after screening). For example, at a perigee time, maneuver sizes of -3 m / s to -4 m / s and 1.53 m / s to 3 m / s both meet the above requirements (i.e., they pass the first parameter screening). Therefore, there are two candidate maneuver sizes at this perigee time: -3.5 m / s and 2.3 m / s, with margins of 0.5 m / s and 0.7 m / s, respectively. These two maneuver sizes and margins are recorded as two independent candidate results, and the candidate maneuver sizes and maneuver times at the perigee time are statistically analyzed as the initial screening result. It should be noted that each perigee (perigee time) can represent that orbital segment, and subsequent processing of the initial maneuvers on that orbital segment can refer to the maneuvers at the perigee.

[0078] S105. Based on the first combination of screening parameters and the second preset maneuver size interval, construct a second set of maneuver parameter combinations.

[0079] Next, based on the first set of parameters determined after the first parameter filtering in S104, a second set of maneuver parameter combinations can be constructed. Constructing this second set of maneuver parameter combinations facilitates further refined filtering of maneuver parameter combinations, enabling rapid determination of maneuver timing and magnitude.

[0080] The second set of maneuver parameter combinations includes multiple second candidate parameter combinations. Each second candidate parameter combination includes a second maneuver timing and a second maneuver magnitude. The second maneuver timing is determined based on the first maneuver timing in the first selection parameter combination, and the second maneuver magnitude is determined based on the first maneuver magnitude and the interval between a second preset maneuver magnitude in the first selection parameter combination. The interval between the second preset maneuver magnitudes is smaller than the interval between the first preset maneuver magnitudes. This allows for a higher density (i.e., higher precision) of second maneuver magnitudes for parameter selection.

[0081] In some embodiments, the second set of maneuver parameter combinations is represented by a second parameter grid; wherein the horizontal axis of the second parameter grid represents the second maneuver time, the vertical axis of the second parameter grid represents the second maneuver magnitude, and each grid point of the second parameter grid represents a second candidate parameter combination. This second parameter grid, as a dense parameter grid, facilitates rapid and accurate fine-tuning of maneuver parameter combinations, thereby improving the efficiency and accuracy of maneuver parameter selection.

[0082] In some embodiments, when the first preset maneuver size interval is 0.5 m / s, the second preset maneuver size interval can be 0.1 m / s. This not only allows for a more detailed determination of the second maneuver size but also improves the accuracy of maneuver size determination.

[0083] In some embodiments, the second maneuver time can be determined by further discretizing and refining the first maneuver time in the first combination of filtering parameters. For example, the second maneuver time can be an hour or a half-hour within the time period composed of the first maneuver times in the first combination of filtering parameters.

[0084] In some embodiments, to facilitate more accurate screening and determination of the maneuver size, the range of maneuver sizes can be expanded based on the first maneuver size in the first screening parameter combination, thereby expanding the screening range of maneuver sizes.

[0085] Specifically, after determining the feasible maneuvers and margins of the first combination of screening parameters, the range of the second maneuver size can also be determined by combining the feasible maneuvers and margins. For example, taking the feasible maneuver of the first combination of screening parameters as -3.5 m / s, based on this -3.5 m / s, a range threshold (e.g., 3 m / s) can be added to or subtracted to obtain the range of the second maneuver size as [-6.5, -0.5] m / s.

[0086] S106. Based on the second set of maneuver parameter combinations, the second parameters are screened using a high-fidelity ephemeris model and a second maintenance effect evaluation threshold to determine the second set of screened parameters.

[0087] Then, the second candidate parameter combinations in the second maneuver parameter combination set constructed in S105 are screened again using the high-fidelity ephemeris model and the second maintenance effect evaluation threshold, thus determining the second screened parameter combination. The second screened parameter combination is the second candidate parameter combination that satisfies the second maintenance effect evaluation threshold.

[0088] In some embodiments, S106 may specifically include:

[0089] First, based on a high-fidelity ephemeris model, the second maintenance effect evaluation parameter is determined for each second candidate parameter combination in the second maneuver parameter combination set.

[0090] Specifically, a high-fidelity ephemeris model can be used to determine the orbital state of the target spacecraft after maneuvering based on the second candidate parameter combination. Then, based on this defined state, the second maintenance effect evaluation parameter corresponding to the second candidate parameter combination can be determined. This second maintenance effect evaluation parameter characterizes the orbital maintenance effect of the target spacecraft after maneuvering based on the second candidate parameter combination.

[0091] Furthermore, based on the second maintenance effect evaluation parameter and the second maintenance effect evaluation threshold, a second selection parameter combination is determined. The second selection parameter combination is a second candidate parameter combination in which the second maintenance effect evaluation parameter satisfies the second maintenance effect evaluation threshold.

[0092] In some embodiments, the second maintenance effect evaluation parameter may be the same as the first maintenance effect evaluation parameter, or it may be different from the first maintenance effect evaluation parameter. For example, the second maintenance effect evaluation parameter may include one or more of the following: the bounded distance range between the target spacecraft and the Moon within a third preset time period, and the time from when the target spacecraft performs its maneuver to the first occurrence of the long solar eclipse.

[0093] It is understandable that the function and determination method of the second maintenance effect evaluation threshold are similar to those of the first maintenance effect evaluation threshold. For details, please refer to the function and determination method of the first maintenance effect evaluation threshold mentioned above, which will not be repeated here.

[0094] For example, Figure 4 This is a schematic diagram of the second combination of screening parameters provided in the embodiments of this application, as shown below. Figure 4 As shown, the set of second selection parameter combinations is represented by parameter grid 401. The horizontal axis of parameter grid 401 represents the second maneuver time, the vertical axis represents the second maneuver magnitude, and each grid point in parameter grid 401 represents a second selection parameter combination. The color of the region corresponding to a grid point in parameter grid 401 characterizes the magnitude of the eclipse shadow evaluation parameter for that second selection parameter combination.

[0095] It should be noted that, Figure 4 The colors used to represent the magnitude of the eclipse shadow evaluation parameters are for illustrative purposes only and are not intended to be limiting.

[0096] S107. Determine the updated orbital state information of the target spacecraft after it has performed a maneuver based on the second set of screening parameters.

[0097] Specifically, the updated orbital state information of the target spacecraft after maneuvering based on the second set of screening parameters can be determined using a high-fidelity ephemeris model, which can then be used to determine the maneuver parameters for the next maneuver.

[0098] S108. The updated orbital status information is used as the current orbital status information, and the first candidate maneuver time period is determined again to obtain the third selection parameter combination.

[0099] Specifically, the updated orbital state information determined in S107 is used as the current orbital state information, and the first candidate maneuver period is determined again. That is, the above steps S101-S106 are repeated to predict and determine the maneuver parameters for the next maneuver, i.e., the third selection parameter combination.

[0100] S109. Based on the second and third screening parameter combinations, determine the maneuver interval time corresponding to the second screening parameter combination.

[0101] Then, based on the maneuver parameters of the current sustained maneuver (i.e., the second selection parameter combination) and the maneuver parameters of the next sustained maneuver (i.e., the third selection parameter combination), the interval between the two sustained maneuvers is determined, serving as the maneuver interval corresponding to the second selection parameter combination. In this way, multiple second selection parameter combinations can be filtered based on the maneuver interval to determine the target maneuver parameter combination.

[0102] Specifically, the difference between the third maneuver time in the third selection parameter combination and the second maneuver time in the second selection parameter combination is the maneuver interval time.

[0103] S110. Based on the maneuver interval time, the target maneuver parameter combination is determined, and maneuvering is applied to the target spacecraft based on the target maneuver parameter combination.

[0104] Finally, in order to reduce the frequency of maintenance maneuvers on the target spacecraft, the second selection parameter combination with the longest maneuver interval can be selected as the target maneuver parameter combination, that is, the target maneuver parameter combination is the second selection parameter combination corresponding to the longest maneuver interval.

[0105] The target maneuver parameters include the target maneuver timing and the target maneuver magnitude. Specifically, the target maneuver timing is the second maneuver timing in the second selection parameter combination corresponding to the longest maneuver interval, and the target maneuver magnitude is the second maneuver magnitude in the second selection parameter combination corresponding to the longest maneuver interval. Based on these target maneuver timing and magnitude, (orbit maintenance) maneuvers can be applied to the target spacecraft to ensure its stability.

[0106] The orbit maintenance maneuvering method for a long-distance retrograde orbit spacecraft provided in the above embodiments of this application uses the timing and magnitude of the maintenance maneuver as design parameters. Candidate maneuvering periods are generated based on the spacecraft's current orbital state, and unsuitable maneuvering times are eliminated through engineering constraints. Next, a first set of maneuvering parameter combinations is constructed for preliminary first parameter screening. Then, a second set of maneuvering parameter combinations is constructed based on the first parameter screening for detailed second parameter screening to determine the precise screening parameter combination, i.e., the second screening parameter combination. Further, the above steps are repeated based on the second screening parameter combination to determine the third screening parameter combination for the next maintenance maneuver. Then, the maneuver interval between the current maintenance maneuver and the next maintenance maneuver is determined based on the second and third screening parameters. Finally, the final target maneuvering parameter combination is obtained based on the maneuver interval time for orbit maintenance maneuvering of the spacecraft.

[0107] This method employs a two-stage progressive parameter selection process. First, a preliminary parameter selection is performed using a first set of maneuver parameter combinations. Then, a more detailed second set of maneuver parameter combinations is used for further selection, enabling rapid selection of DRO maintenance maneuver parameters. Furthermore, this method considers both orbital stability and eclipse constraints, incorporating engineering constraints to ensure the target spacecraft meets practical engineering requirements during maintenance maneuvers. Simultaneously, the parameter selection process considers orbital tangency, significantly reducing the parameter selection space and improving efficiency while ensuring feasibility. This parameter selection method also guarantees maneuver margin requirements, improving maneuver reliability. While estimating the current maintenance maneuver, the method can also obtain the estimation result for the next maintenance maneuver through repeated operations to assess whether the frequency of maneuver application meets the expected requirements. This method can also efficiently and comprehensively determine maneuver parameters and their application effects while meeting engineering constraints, thereby effectively improving the efficiency and accuracy of orbit maintenance maneuvers for long-distance retrograde orbit spacecraft.

[0108] This application also provides an orbit maintenance maneuvering system for a long-distance retrograde orbit spacecraft, which can be applied to a target spacecraft in a long-distance retrograde orbit. Specifically, Figure 5 A schematic diagram of the orbit maintenance maneuvering system for a long-distance retrograde orbit spacecraft provided in this application embodiment is shown below. Figure 5 As shown, the orbit maintenance maneuvering system 500 of the long-distance retrograde orbit spacecraft includes: a candidate maneuvering time period determination module 501, a time period filtering module 502, a first construction module 503, a first parameter filtering module 504, a second construction module 505, a second parameter filtering module 506, an orbital status update module 507, a third parameter filtering module 508, and a maneuvering parameter determination module 509.

[0109] The candidate maneuvering time period determination module 501 can be used to determine the first candidate maneuvering time period based on the current orbital state information of the target spacecraft and the high-fidelity ephemeris model. The first candidate maneuvering time period is before the long eclipse moment, which is the moment when the equivalent shadow duration is greater than the preset duration.

[0110] The time period filtering module 502 can be used to filter the first candidate maneuver time period based on preset engineering constraints, and determine the second candidate maneuver time period after the time period filtering.

[0111] The first construction module 503 can be used to construct a first set of maneuver parameter combinations based on a second candidate maneuver time period, a preset maneuver size range, and a first preset maneuver size interval. The first set of maneuver parameter combinations includes multiple first candidate parameter combinations. Each first candidate parameter combination includes a first maneuver time and a first maneuver size. The first maneuver time is within the second candidate maneuver time period, and the first maneuver size is determined according to the preset maneuver size range and the first preset maneuver size interval.

[0112] The first parameter screening module 504 can be used to screen the first parameter combination based on the first set of maneuvering parameter combinations, through a high-fidelity ephemeris model and a first maintenance effect evaluation threshold, to determine the first screening parameter combination.

[0113] The second construction module 505 can be used to construct a second set of maneuver parameter combinations based on the first combination of screening parameters and the second preset maneuver size interval. The second set of maneuver parameter combinations includes multiple second candidate parameter combinations. Each second candidate parameter combination includes a second maneuver time and a second maneuver size. The second maneuver time is determined based on the first maneuver time in the first combination of screening parameters, and the second maneuver size is determined based on the first maneuver size and the second preset maneuver size interval in the first combination of screening parameters. The second preset maneuver size interval is smaller than the first preset maneuver size interval.

[0114] The second parameter filtering module 506 can be used to filter the second parameter combination based on the second set of maneuver parameters, through a high-fidelity ephemeris model and a second maintenance effect evaluation threshold, to determine the second filtering parameter combination.

[0115] The orbital state update module 507 can be used to determine the updated orbital state information of the target spacecraft after it has performed a maneuver, based on the second set of screening parameters.

[0116] The third parameter filtering module 508 can be used to take the updated orbital status information as the current orbital status information, and re-determine the first candidate maneuver period to obtain the third filtering parameter combination.

[0117] The maneuver parameter determination module 509 can be used to determine the maneuver interval time corresponding to the second screening parameter combination based on the second screening parameter combination and the third screening parameter combination.

[0118] The maneuver parameter determination module 509 can also be used to determine the target maneuver parameter combination based on the maneuver interval time, so as to apply maneuver to the target spacecraft based on the target maneuver parameter combination, where the target maneuver parameter combination is the second screening parameter combination corresponding to the longest maneuver interval time.

[0119] The orbit maintenance maneuvering system for a long-distance retrograde orbit spacecraft provided in the above embodiments of this application uses the timing and magnitude of the maintenance maneuver as design parameters. Based on the spacecraft's current orbital state, candidate maneuvering periods are generated, and unsuitable maneuvering times are eliminated through engineering constraints. Next, a first set of maneuvering parameter combinations is constructed for preliminary first parameter screening. Then, based on the first parameter screening, a second set of maneuvering parameter combinations is constructed for detailed second parameter screening to determine the precise screening parameter combinations, i.e., the second screening parameter combinations. Further, based on the second screening parameter combinations, the above steps are repeated to determine the third screening parameter combinations for the next maintenance maneuver. Then, based on the second and third screening parameters, the maneuver interval between the current and next maintenance maneuver is determined. Finally, based on the maneuver interval, the final target maneuvering parameter combination is obtained for orbit maintenance maneuvers of the spacecraft. This system, considering the characteristics of long-distance retrograde orbits, engineering application requirements, and the impact of solar eclipses, employs a two-stage progressive screening to determine the target maneuvering parameter combination, i.e., the target maneuver timing and the target maneuver magnitude. In this way, while ensuring screening efficiency, all effective combinations of maneuver parameters can be fully covered to find the optimal combination of target maneuver parameters, thereby meeting the need to avoid long-term eclipses and maintain long-term stability, thus improving the efficiency and accuracy of orbit maintenance maneuvers for long-distance retrograde orbit spacecraft.

[0120] This invention also provides an electronic device, which may include a display screen, a memory, and one or more processors. The display screen, memory, and processors are coupled. The memory stores computer program code, which includes computer instructions. When the processor executes the computer instructions, the electronic device can perform various methods or steps executed in the above-described embodiments of the orbit maintenance maneuvering method for a long-distance retrograde orbit spacecraft. Of course, this electronic device includes, but is not limited to, the aforementioned display screen, memory, and one or more processors.

[0121] This invention also provides a computer-readable storage medium for storing computer instructions for operating the orbit maintenance maneuvering method of the aforementioned long-distance retrograde orbit spacecraft.

[0122] Through the above description of the embodiments, those skilled in the art can clearly understand that, for the sake of convenience and brevity, only the division of the above functional modules is used as an example. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the device can be divided into different functional modules to complete all or part of the functions described above.

[0123] In the description of this invention, it should be understood that the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0124] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0125] Similar parts between the embodiments provided in this application can be referred to mutually. The specific implementation methods provided above are only a few examples under the overall concept of this application and do not constitute a limitation on the scope of protection of this application. For those skilled in the art, any other implementation methods extended from the solution of this application without creative effort shall fall within the scope of protection of this application.

Claims

1. A method for orbit maintenance maneuvering of a long-distance retrograde orbit spacecraft, characterized in that, The method, applied to a target spacecraft in a distant retrograde orbit, includes: Based on the current orbital state information of the target spacecraft and the high-fidelity ephemeris model, a first candidate maneuvering period is determined; wherein, the first candidate maneuvering period is before the long eclipse moment, and the long eclipse moment is the moment when the equivalent shadow duration is greater than a preset duration. Based on preset engineering constraints, the first candidate maneuver time period is filtered to determine the second candidate maneuver time period after the time period is filtered. Based on the second candidate maneuver time period, the preset maneuver size range, and the first preset maneuver size interval, a first maneuver parameter combination set is constructed; the first maneuver parameter combination set includes multiple first candidate parameter combinations, each of which includes a first maneuver time and a first maneuver size, wherein the first maneuver time is within the second candidate maneuver time period, and the first maneuver size is determined according to the preset maneuver size range and the first preset maneuver size interval; Based on the first set of maneuvering parameters, the first parameter combination is determined by screening the first parameters through the high-fidelity ephemeris model and the first maintenance effect evaluation threshold. Based on the first combination of filtering parameters and the second preset maneuver size interval, a second set of maneuver parameter combinations is constructed; the second set of maneuver parameter combinations includes multiple second candidate parameter combinations, each of which includes a second maneuver time and a second maneuver size. The second maneuver time is determined based on the first maneuver time in the first combination of filtering parameters, and the second maneuver size is determined based on the first maneuver size in the first combination of filtering parameters and the second preset maneuver size interval; wherein, the second preset maneuver size interval is smaller than the first preset maneuver size interval. Based on the second set of maneuver parameters, the second parameter combination is determined by screening the second parameters through the high-fidelity ephemeris model and the second maintenance effect evaluation threshold. The updated orbital state information of the target spacecraft after it has performed a maneuver is determined based on the second combination of screening parameters. The updated orbital state information is used as the current orbital state information to determine the first candidate maneuver time period again, so as to obtain the third combination of screening parameters. Based on the second combination of screening parameters and the third combination of screening parameters, the maneuver interval time corresponding to the second combination of screening parameters is determined; The target maneuver parameter combination is determined based on the maneuver interval time, and the target spacecraft is maneuvered based on the target maneuver parameter combination; the target maneuver parameter combination is the second screening parameter combination corresponding to the longest maneuver interval time.

2. The method according to claim 1, characterized in that, The determination of the first candidate maneuvering period based on the current orbital state information of the target spacecraft and a high-fidelity ephemeris model includes: Based on the current orbital state information, the predicted orbital state information of the target spacecraft within a first preset time period is determined using the high-fidelity ephemeris model. Based on the predicted orbital state information and the sun's position information, the equivalent shadow duration of the solar eclipse is determined; The moment when the equivalent shadow duration of the first solar eclipse is greater than the preset duration is determined as the moment of the long solar eclipse; The period from the current time to the time of the long solar eclipse is determined as the first candidate maneuvering period; wherein, the current time is the time corresponding to the current orbital state information.

3. The method according to claim 2, characterized in that, The preset engineering constraints include one or more of the following: The altitude angle of the target spacecraft relative to the ground observation station is greater than a first preset angle, the angle between the antenna pointing of the target spacecraft and the direction of the line connecting the target spacecraft and the Earth is less than a second preset angle, and the observation time of the target spacecraft is greater than a time threshold.

4. The method according to any one of claims 1-3, characterized in that, The first selection parameter combination is determined based on the first set of maneuver parameter combinations, using the high-fidelity ephemeris model and the first maintenance effect evaluation threshold. This includes: Based on the high-fidelity ephemeris model, a first maintenance effect evaluation parameter is determined for each first candidate parameter combination in the first set of maneuver parameter combinations; the first maintenance effect evaluation parameter is used to characterize the orbital maintenance effect of the target spacecraft after maneuvering based on the first candidate parameter combination. Based on the first maintenance effect evaluation parameter and the first maintenance effect evaluation threshold, the first screening parameter combination is determined. The first screening parameter combination is a first candidate parameter combination in which the first maintenance effect evaluation parameter satisfies the first maintenance effect evaluation threshold.

5. The method according to claim 4, characterized in that, The first maintenance effect evaluation parameter includes one or more of the following: The target spacecraft is within a bounded distance from the moon during a second preset time period, which is the time between the target spacecraft performing its maneuver and the first occurrence of a long solar eclipse.

6. The method according to claim 4, characterized in that, The second set of maneuvering parameters is used to screen the second parameters through the high-fidelity ephemeris model and the second maintenance effect evaluation threshold, to determine the second set of screened parameters, including: Based on the high-fidelity ephemeris model, a second maintenance effect evaluation parameter is determined for each second candidate parameter combination in the second maneuver parameter combination set; the second maintenance effect evaluation parameter is used to characterize the orbital maintenance effect of the target spacecraft after maneuvering based on the second candidate parameter combination. Based on the second maintenance effect evaluation parameter and the second maintenance effect evaluation threshold, the second screening parameter combination is determined. The second screening parameter combination is a second candidate parameter combination in which the second maintenance effect evaluation parameter satisfies the second maintenance effect evaluation threshold.

7. The method according to claim 1, characterized in that, The first set of maneuver parameter combinations is represented by a first parameter grid; wherein, the horizontal axis of the first parameter grid represents the first maneuver moment, the vertical axis of the first parameter grid represents the first maneuver magnitude, and each grid point of the first parameter grid represents a first candidate parameter combination; The second set of maneuver parameter combinations is represented by a second parameter grid; wherein the horizontal axis of the second parameter grid represents the second maneuver time, the vertical axis of the second parameter grid represents the second maneuver magnitude, and each grid point of the second parameter grid represents a second candidate parameter combination.

8. The method according to claim 1, characterized in that, The first maneuver time is the lunar perihelion time of the target spacecraft during the second candidate maneuver period.

9. The method according to claim 1, characterized in that, The preset maneuver size range is [-10, 10] m / s, the first preset maneuver size interval is 0.5 m / s, and the second preset maneuver size interval is 0.1 m / s.

10. An orbit maintenance maneuvering system for a long-distance retrograde orbit spacecraft, characterized in that, For target spacecraft in a long-distance retrograde orbit, the system includes: a candidate maneuver period determination module, a period filtering module, a first construction module, a first parameter filtering module, a second construction module, a second parameter filtering module, an orbital state update module, a third parameter filtering module, and a maneuver parameter determination module; wherein, The candidate maneuvering time period determination module is used to determine a first candidate maneuvering time period based on the current orbital state information of the target spacecraft and a high-fidelity ephemeris model; wherein the first candidate maneuvering time period is before the long solar eclipse moment, and the long solar eclipse moment is the moment when the equivalent shadow duration is greater than a preset duration of the solar eclipse; The time period filtering module is used to filter the first candidate maneuver time period based on preset engineering constraints, and determine the second candidate maneuver time period after the time period filtering. The first construction module is used to construct a first set of maneuver parameter combinations based on the second candidate maneuver time period, a preset maneuver size range, and a first preset maneuver size interval. The first set of maneuver parameter combinations includes multiple first candidate parameter combinations, each of which includes a first maneuver time and a first maneuver size. The first maneuver time is within the second candidate maneuver time period, and the first maneuver size is determined based on the preset maneuver size range and the first preset maneuver size interval. The first parameter filtering module is used to filter the first parameter combination based on the first set of maneuvering parameter combinations, through the high-fidelity ephemeris model and the first maintenance effect evaluation threshold. The second construction module is used to construct a second set of maneuver parameter combinations based on the first set of filtering parameters and the second preset maneuver size interval. The second set of maneuver parameter combinations includes multiple second candidate parameter combinations, each of which includes a second maneuver time and a second maneuver size. The second maneuver time is determined based on the first maneuver time in the first set of filtering parameters, and the second maneuver size is determined based on the first maneuver size in the first set of filtering parameters and the second preset maneuver size interval. The second preset maneuver size interval is smaller than the first preset maneuver size interval. The second parameter filtering module is used to filter the second parameters based on the second set of maneuvering parameters, through the high-fidelity ephemeris model and the second maintenance effect evaluation threshold, to determine the second filtering parameter combination. The orbital state update module is used to determine the updated orbital state information of the target spacecraft after it has performed a maneuver, based on the second combination of filtering parameters. The third parameter filtering module is used to take the updated orbital state information as the current orbital state information and determine the first candidate maneuver time period again to determine the third filtering parameter combination. The maneuver parameter determination module is used to determine the maneuver interval time corresponding to the second screening parameter combination based on the second screening parameter combination and the third screening parameter combination. The maneuver parameter determination module is further configured to determine a target maneuver parameter combination based on the maneuver interval time, and to apply maneuver to the target spacecraft based on the target maneuver parameter combination, wherein the target maneuver parameter combination is the second screening parameter combination corresponding to the longest maneuver interval time.

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