A Design Method for Transfer Orbit from DRO Orbit to Low-Lunar-Orbit Circular Orbit

Abstract

The present application relates to a method for designing a transfer orbit from a DRO orbit to a low lunar circular orbit. The method includes: establishing a mapping data table and a three-dimensional data pair of the delta-v of orbit transfer according to the preset DRO orbit size parameters and the phase angle of the DRO vehicle at the initial moment; dividing the three-dimensional data pair of the delta-v of orbit transfer into two groups according to the positive and negative conditions of the high and low angles of the delta-v of orbit transfer, obtaining the right ascension of the ascending node and the transfer flight time corresponding to the data pair with the minimum delta-v during the transfer process in each group to calculate the orbit transfer moment, and selecting the minimum value of the two orbit transfer moments as the selected orbit transfer moment; correcting the phase of the selected orbit transfer moment, and calculating the projection of the delta-v of orbit transfer according to the corrected phase; using the Newton iteration method to perform iterative solution with the selected orbit transfer moment and the projection of the delta-v of orbit transfer as the initial iteration values to obtain the transfer orbit transfer moment and the transfer delta-v of orbit transfer. Using this method can improve the design accuracy of the transfer orbit.

Description

Technical Field

[0001] This application relates to the technical field of data processing, and particularly to a method for designing a transfer orbit from a DRO orbit to a low lunar circular orbit. Background Art

[0002] The DRO (Distant Retrograde Orbit) is a periodic orbit proposed under the assumption of a circular restricted three-body model. In practical problems, although the force on a DRO orbit spacecraft is much more complex than the force model of the circular restricted three-body problem, its periodicity and stability can still be maintained to a certain extent. Therefore, it has unique application value in the exploration applications in the Earth-Moon space and deep space beyond the Moon. Transferring from a DRO orbit to a low lunar circular orbit is an important mode of DRO orbit application and has important value in lunar exploration and applications of leveraging the Moon for transfer.

[0003] Generally, the problem of designing an Earth-Moon space transfer orbit is based on a circular restricted three-body model, an elliptical restricted three-body model, or a restricted four-body model. Although such analysis and design can obtain relatively simple theoretical results and can also conduct qualitative characteristic analysis, due to the large difference between the force model and the actual force situation, and the sensitivity of the spacecraft orbit itself to the initial value in a multi-body system, in actual engineering calculations, the error of the calculation result often cannot meet the accuracy requirements of the iterative initial value. Using a numerical integration method based on a high-precision force model can effectively improve the calculation accuracy. By performing search iterations through intelligent algorithms, high-precision calculation results within the global range can be obtained. However, due to the sensitivity of the spacecraft orbit itself to the initial value, such intelligent search algorithms often have a slow convergence speed, and it is difficult to guarantee the solution time and convergence reliability. From the currently available public information, there is still a lack of a design method with high calculation accuracy, fast and reliable convergence for the problem of designing an orbit for transferring from a DRO orbit to a low lunar circular orbit. Summary of the Invention

[0004] Based on this, in view of the above technical problems, it is necessary to provide a method for designing a transfer orbit from a DRO orbit to a low lunar circular orbit with high precision and fast convergence speed.

[0005] A method for designing a transfer orbit from a DRO orbit to a low lunar circular orbit, the method comprising:

[0006] Obtaining the DRO orbit-related parameters and target orbit-related parameters at the moment of spacecraft orbit transfer; the DRO orbit-related parameters include DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment; the target orbit-related parameters include the lunar surface altitude of the target orbit, the inclination angle of the target orbit, and the longitude of the ascending node of the target orbit at the initial moment;

[0007] Establish a mapping data table based on the pre-set DRO orbit size parameters and the phase angle of the DRO vehicle at the initial moment; select the mapping data table corresponding to the value with the closest numerical value among the pre-set DRO orbit size parameters according to the DRO orbit size parameters at the vehicle's orbit transfer moment; screen out the three-dimensional data pairs of the velocity increment at the perigee orbit height and the orbital plane inclination angle that satisfy the pre-set dispersion range according to the target orbit lunar surface height and the target orbit inclination angle;

[0008] Divide the three-dimensional data pairs of the velocity increment at the orbit transfer that satisfy the pre-set dispersion range into two groups according to the positive and negative conditions of the high and low angles of the velocity increment at the orbit transfer, corresponding to two transfer orbits of ascending orbit and descending orbit transfers, obtain the right ascension of the ascending node and the transfer flight time corresponding to the data pair with the minimum velocity increment during each group's transfer process to calculate the orbit transfer moment, and select the minimum value among the two orbit transfer moments as the selected orbit transfer moment;

[0009] Correct the phase of the selected orbit transfer moment to obtain the corrected phase; calculate the projection of the velocity increment at the orbit transfer according to the corrected phase; use the Newton iteration method to perform iterative solution with the selected orbit transfer moment and the projection of the velocity increment at the orbit transfer as the initial iteration values to obtain the transfer orbit transfer moment and the transfer velocity increment at the orbit transfer.

[0010] The above-mentioned method for designing a transfer orbit from a DRO orbit to a low lunar orbit circular orbit. In the above-mentioned method for designing a transfer orbit from a DRO orbit to a low lunar orbit circular orbit, in this application, by accurately obtaining orbit parameters, establishing an efficient mapping data table, finely screening orbit data pairs, reasonably determining the orbit transfer moment, and using scientific phase correction and iterative solution methods, the accuracy and convergence problems faced in the design of the transfer from a DRO orbit to a low lunar orbit circular orbit are comprehensively and systematically solved. This method is closely adapted to a high-precision force model, provides a reliable and efficient solution for orbit design in space engineering, and has important practical application value. Description of the Drawings

[0011] Figure 1 It is a schematic flowchart of a method for designing a transfer orbit from a DRO orbit to a low lunar orbit circular orbit in an embodiment;

[0012] Figure 2 It is an internal structure diagram of a computer device in an embodiment. Detailed Embodiment

[0013] In order to make the purpose, technical solution and advantages of this application clearer, the following further details this application in combination with the drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain this application and are not used to limit this application.

[0014] In an embodiment, as Figure 1As shown in the figure, a method for designing a transfer orbit from a DRO orbit to a low circular orbit around the moon is provided, including the following steps:

[0015] Step 102, obtain the DRO orbit-related parameters and target orbit-related parameters at the time of the spacecraft's orbit transfer; the DRO orbit-related parameters include the DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment; the target orbit-related parameters include the lunar surface altitude of the target orbit, the inclination angle of the target orbit, and the longitude of the ascending node at the initial moment of the target orbit.

[0016] The DRO orbit-related parameters cover the DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment, which accurately describe the state of the spacecraft on the initial orbit. The target orbit-related parameters, including the lunar surface altitude of the target orbit, the inclination angle of the target orbit, and the longitude of the ascending node at the initial moment of the target orbit, clearly define the characteristics of the target orbit that the spacecraft finally reaches. By accurately grasping these parameters, subsequent calculations can closely focus on the actual operating state and target state of the spacecraft, avoiding calculation deviations caused by inaccurate parameters, and providing reliable data support for accurate calculations based on high-precision force models.

[0017] Step 104, establish a mapping data table according to the preset DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment; select the mapping data table corresponding to the value with the closest numerical value among the preset DRO orbit size parameters according to the DRO orbit size parameters at the time of the spacecraft's orbit transfer; screen out the three-dimensional data pairs of the velocity increment at the orbit transfer point whose perigee orbit altitude and orbital plane inclination angle meet the preset dispersion range according to the lunar surface altitude of the target orbit and the inclination angle of the target orbit.

[0018] Establishing a mapping data table according to the preset DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment greatly optimizes the calculation process. In practical applications, when facing the DRO orbit size parameters at the time of the spacecraft's orbit transfer, the mapping data table corresponding to the value with the closest numerical value can be quickly selected among the preset DRO orbit size parameters. This method avoids blind searches in a large amount of data, greatly improving the speed and accuracy of data matching. Through efficient data screening, unnecessary calculation amounts are reduced, providing strong guarantee for quickly and accurately determining the orbit transfer plan subsequently, and playing a positive role in improving the convergence speed.

[0019] Screen out three-dimensional data pairs of the velocity increment for orbit transfer whose perigee altitude and orbital plane inclination satisfy the preset dispersion range according to the lunar surface altitude and orbital inclination of the target orbit, ensuring the orbital accuracy. In a complex multi-body system, the spacecraft orbit is extremely sensitive to the initial values, and a tiny deviation may lead to a large difference between the orbital calculation result and the actual requirements. By strictly limiting the screening of data pairs within the preset dispersion range, orbit schemes that do not meet the accuracy requirements can be effectively excluded, enabling subsequent calculations to be based on orbital parameters closer to the actual requirements. This refined screening of orbital parameters ensures that the entire orbit design process is compatible with the high-precision force model, thereby significantly improving the calculation accuracy and overcoming the problem of low accuracy of traditional simplified force models.

[0020] Step 106: Divide the three-dimensional data pairs of the velocity increment for orbit transfer that meet the preset dispersion range into two groups according to the positive and negative conditions of the high and low angles of the velocity increment for orbit transfer, corresponding to two transfer orbits for ascending and descending orbit transfers. Obtain the right ascension of the ascending node and the transfer flight time corresponding to the data pair with the minimum velocity increment during the transfer process in each group to calculate the orbit transfer moment, and select the minimum value of the two orbit transfer moments as the selected orbit transfer moment.

[0021] Divide the three-dimensional data pairs of the velocity increment for orbit transfer that meet the preset dispersion range into two groups according to the positive and negative conditions of the high and low angles of the velocity increment for orbit transfer, corresponding to two transfer orbits for ascending and descending orbit transfers. Then obtain the right ascension of the ascending node and the transfer flight time corresponding to the data pair with the minimum velocity increment during the transfer process in each group to calculate the orbit transfer moment, and select the minimum value of the two orbit transfer moments as the selected orbit transfer moment, fully considering various actual situations during the orbit transfer process. By carefully analyzing different transfer orbits, the optimal orbit transfer moment is found. Selecting the minimum orbit transfer moment can, on the premise of meeting the orbital accuracy requirements, minimize the energy consumption and time cost of the aircraft during the orbit transfer process, and at the same time further improve the convergence stability of the entire orbit design scheme, avoiding orbit deviation and convergence problems caused by unreasonable selection of the orbit transfer moment. The convergence speed of the present application is fast.

[0022] Step 108: Correct the phase of the selected orbit transfer moment to obtain the corrected phase; calculate the projection of the velocity increment for orbit transfer according to the corrected phase; use the Newton iteration method to perform iterative solution with the selected orbit transfer moment and the projection of the velocity increment for orbit transfer as the initial iteration values to obtain the transfer orbit transfer moment and the transfer velocity increment for orbit transfer.

[0023] Modify the phase at the selected orbit transfer moment to obtain the modified phase, and calculate the projection of the orbit transfer velocity increment based on the modified phase. Use the Newton iteration method to perform iterative solution with the selected orbit transfer moment and the projection of the orbit transfer velocity increment as the initial iteration values. Finally, obtain the transfer orbit transfer moment and the transfer orbit transfer velocity increment. The phase modification further optimizes the initial conditions of orbit calculation, enabling the iterative process to converge more accurately to the true orbit transfer parameters, featuring a fast convergence speed and high precision. Combining the carefully determined initial iteration values with the Newton iteration method can quickly and accurately search for orbit transfer parameters that meet the high-precision force model globally, thereby obtaining high-precision calculation results, effectively solving the problems of slow convergence speed, difficult-to-guarantee solution duration, and convergence reliability of traditional intelligent search algorithms.

[0024] In the above method for designing the transfer orbit from the DRO orbit to the low lunar circular orbit, the present application comprehensively and systematically solves the accuracy and convergence problems faced in the design of the transfer from the DRO orbit to the low lunar circular orbit by accurately obtaining orbit parameters, establishing an efficient mapping data table, carefully screening orbit data pairs, reasonably determining the orbit transfer moment, and using scientific phase modification and iterative solution methods. This method is closely adapted to the high-precision force model, providing a reliable and efficient solution for orbit design in space engineering and having important practical application value.

[0025] In one embodiment, establish a mapping data table according to the pre-set DRO orbit size parameters and the phase angle of the DRO vehicle at the initial moment, including:

[0026] Perform interval sampling within the pre-set range of orbit transfer velocity increments according to the pre-set DRO orbit size parameters and the phase angle of the DRO vehicle at the initial moment. Calculate the lunar surface altitude, inclination angle, longitude of the ascending node, and transfer flight time at the moment of flying to the perigee through numerical integration of the high-precision force model, and establish a mapping data table between the three-dimensional data pairs of the orbit transfer velocity increment and the lunar surface altitude, inclination angle, longitude of the ascending node, and transfer flight time at the moment of the perigee.

[0027] In a specific embodiment, the DRO orbit phase at the moment of the vehicle's orbit transfer and in the cases where the DRO orbit size parameters are 60000 km, 65000 km, 70000 km, 75000 km, and 80000 km respectively, sampling is performed at 1 m / s intervals within the range of [200 m / s, 350 m / s] for the magnitude of the orbit transfer velocity increment, at 0.5° intervals within the range of [100°, 130°] for the azimuth angle of the orbit transfer velocity increment, and at 0.5° intervals within the range of [-15°, 15°] for the elevation angle of the orbit transfer velocity increment. Through numerical integration based on a high-precision force model, the lunar surface altitude, inclination, longitude of the ascending node, and transfer flight time at the moment of flying to the perilune are calculated, thereby establishing a three-dimensional data pair of the orbit transfer velocity increment , and the lunar surface altitude at the perilune , inclination , longitude of the ascending node and transfer flight time mapping data tables.

[0028] In one embodiment, the lunar surface altitude, inclination, longitude of the ascending node, and transfer flight time at the moment of flying to the perilune are calculated through numerical integration of a high-precision force model, and a mapping data table of the three-dimensional data pair of the orbit transfer velocity increment and the lunar surface altitude, inclination, longitude of the ascending node, and transfer flight time at the moment of the perilune is established, including:

[0029] Calculating the lunar surface altitude, inclination, longitude of the ascending node, and transfer flight time at the moment of flying to the perilune through numerical integration of a high-precision force model, and establishing the mapping data table of the three-dimensional data pair of the orbit transfer velocity increment and the lunar surface altitude, inclination, longitude of the ascending node, and transfer flight time at the moment of the perilune as

[0030] ;

[0031] ;

[0032] ;

[0033] ;

[0034] Among them, represents the three-dimensional data pair of the orbit transfer velocity increment, represents the lunar surface altitude at the moment of the perilune, represents the inclination at the moment of the perilune, represents the longitude of the ascending node at the moment of the perilune, represents the transfer flight time at the moment of the perilune, represents the orbit transfer velocity increment parameter - lunar surface altitude, represents the orbit transfer velocity increment parameter - inclination, represents the orbit transfer velocity increment parameter - longitude of the ascending node, Indicates the orbital transfer velocity increment parameter - transfer flight time, Indicates the magnitude of the velocity increment during the transfer, Indicates the azimuth angle of the orbital transfer velocity increment, Indicates the elevation angle of the orbital transfer velocity increment.

[0035] In one embodiment, the preset DRO orbit size parameters include 60000km, 65000km, 70000km, 75000km, 80000km.

[0036] In a specific embodiment, according to the given DRO orbit size parameter , among 60000km, 65000km, 70000km, 75000km, 80000km, select the mapping data table corresponding to the value with the closest numerical value.

[0037] In one embodiment, according to the target orbit lunar surface altitude and the target orbit inclination angle, three-dimensional data pairs of the orbital transfer velocity increment are screened out where the perigee orbit altitude and the orbital plane inclination angle satisfy a preset dispersion range, including:

[0038] The three-dimensional data pairs of the orbital transfer velocity increment screened out according to the target orbit lunar surface altitude and the target orbit inclination angle where the perigee orbit altitude and the orbital plane inclination angle satisfy a preset dispersion range are

[0039] ;

[0040] Among them, and , Indicates the target orbit lunar surface altitude, Indicates the target orbit inclination angle, Indicates the perigee orbit altitude, Indicates the orbital plane inclination angle, Indicates the allowable deviation range of the perigee orbit altitude relative to the target orbit lunar surface altitude, Indicates the allowable deviation range of the orbital plane inclination angle relative to the target orbit inclination angle.

[0041] In a specific embodiment, according to the given target orbit altitude and the orbital plane inclination angle , the perigee orbit altitude and the orbital plane inclination angle satisfying a certain dispersion range are screened out, that is, in the mapping data table, find and and simultaneously satisfying the following conditions data pairs. Among the obtained data pairs, according to The cases of positive and negative are divided into two groups, corresponding to two transfer orbits of the ascending and descending orbits. For each group, select the smallest data pair, denoted as ( , , ). At the same time, the right ascension of the ascending node and the transfer flight time corresponding to this data pair can be obtained, denoted as , .

[0042] In one embodiment, obtaining the right ascension of the ascending node and the transfer flight time corresponding to the data pair with the smallest velocity increment during the transfer process in each group to calculate the orbit change time includes:

[0043] Obtaining the right ascension of the ascending node and the transfer flight time corresponding to the data pair with the smallest velocity increment during the transfer process in each group to calculate the orbit change time as

[0044] ;

[0045] Among them, is the angular velocity of the lunar revolution, is the average orbital angular velocity of the DRO vehicle in the L2 coordinate system, represents the transfer flight time corresponding to the data pair with the smallest velocity increment during the transfer process in each group, represents the right ascension of the ascending node, represents the right ascension of the ascending node at the initial moment of the target orbit, represents the phase angle of the DRO vehicle at the initial moment, represents the initial moment.

[0046] In a specific embodiment, is the average orbital angular velocity of the DRO vehicle (in the L2 coordinate system), which can be obtained by interpolation according to the given DRO size parameters in Table 1.

[0047] Table 1

[0048]

[0049] The positive and negative two groups and are respectively calculated to obtain two orbit change times, and the smaller value is taken as the selected orbit change time.

[0050] In one embodiment, correcting the phase of the selected orbit change time to obtain the corrected phase includes:

[0051] Calculating the phase of the selected orbit change time as

[0052] ;

[0053] Among them, Represents the phase angle of the DRO vehicle at the initial moment, In the L2 coordinate system, it is the average orbital angular velocity of the DRO vehicle, Represents the selected orbital transfer moment, Represents the initial moment.

[0054] In one of the embodiments, the phase at the selected orbital transfer moment includes the azimuth angle and the elevation angle , and the corrected results are denoted as , , and there is

[0055]

[0056] Among them, the correction coefficients and are obtained according to the interpolation table obtained from the pre-simulation experiment.

[0057] In a specific embodiment, The interpolation table is shown in Table 2, The interpolation table is shown in Table 3.

[0058] Table 2

[0059]

[0060] Table 3

[0061]

[0062] In one of the embodiments, calculating the projection of the orbital transfer velocity increment according to the corrected phase includes:

[0063] Calculating the projection of the orbital transfer velocity increment according to the corrected phase as

[0064] ;

[0065] Among them, Represents the corrected azimuth angle, Represents the corrected elevation angle, Represents the phase at the selected orbital transfer moment, Represents the minimum orbital transfer velocity increment, Represents the coordinate transformation matrix.

[0066] It should be understood that although Figure 1 The steps in the flowchart of Figure 1At least some of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed and completed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed alternately or in turn with at least some of the sub-steps or stages of other steps or other steps.

[0067] In one embodiment, a computer device is provided. The computer device may be a terminal, and its internal structure diagram may be as Figure 2 shown. The computer device includes a processor, a memory, a network interface, a display screen, and an input device connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, it realizes a method for designing a transfer orbit from a DRO orbit to a low lunar circular orbit. The display screen of the computer device may be a liquid crystal display screen or an electronic ink display screen. The input device of the computer device may be a touch layer covering the display screen, or may be a button, a trackball, or a touchpad provided on the housing of the computer device, or may also be an external keyboard, a touchpad, or a mouse, etc.

[0068] Those skilled in the art can understand that Figure 2 the structure shown in

[0069] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods. Among them, any reference to a memory, storage, database, or other medium used in the embodiments provided in the present application can include non-volatile and / or volatile memories. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and Rambus dynamic RAM (RDRAM), etc.

[0070] The technical features of the above embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope described in this specification.

[0071] The above-described embodiments merely represent several implementation manners of the present application. The description is relatively specific and detailed, but it should not be construed as a limitation on the scope of the invention. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present application, several modifications and improvements can still be made, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the appended claims.

Claims

1. A method for designing a transfer orbit from a DRO orbit to a low lunar circular orbit, characterized in that, The method includes: Obtaining the DRO orbit - related parameters and target - orbit - related parameters at the moment of the spacecraft's orbit transfer; the DRO orbit - related parameters include the DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment; the target - orbit - related parameters include the lunar surface altitude of the target orbit, the inclination angle of the target orbit, and the longitude of the ascending node at the initial moment of the target orbit; Establishing a mapping data table according to the preset DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment; selecting the mapping data table corresponding to the value with the closest numerical value among the preset DRO orbit size parameters according to the DRO orbit size parameters at the moment of the spacecraft's orbit transfer; screening out the three - dimensional data pairs of the orbit - transfer velocity increment whose lunar surface altitude and inclination angle at the perigee moment satisfy the preset dispersion range according to the lunar surface altitude of the target orbit and the inclination angle of the target orbit; Dividing the three - dimensional data pairs of the orbit - transfer velocity increment that satisfy the preset dispersion range into two groups according to the positive and negative conditions of the high - low angle of the orbit - transfer velocity increment, corresponding to two transfer orbits of ascending - orbit transfer and descending - orbit transfer, obtaining the longitude of the ascending node and the transfer flight time corresponding to the data pair with the minimum velocity increment during the transfer process in each group to calculate the moment of orbit transfer, and selecting the minimum value of the two moments of orbit transfer as the selected moment of orbit transfer; Correcting the phase of the selected moment of orbit transfer to obtain the corrected phase; calculating the projection of the orbit - transfer velocity increment according to the corrected phase; using the Newton iteration method to perform iterative solution with the selected moment of orbit transfer and the projection of the orbit - transfer velocity increment as the initial iteration values to obtain the moment of transfer orbit transfer and the orbit - transfer velocity increment; Establishing a mapping data table according to the preset DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment, including: Performing interval sampling within the preset range of the orbit - transfer velocity increment according to the preset DRO orbit size parameters and the phase angle of the DRO spacecraft at the initial moment, calculating the lunar surface altitude, inclination angle, longitude of the ascending node, and transfer flight time at the perigee moment through numerical integration of the high - precision force model, and establishing a mapping data table between the three - dimensional data pairs of the orbit - transfer velocity increment and the lunar surface altitude, inclination angle, longitude of the ascending node, and transfer flight time at the perigee moment.

2. The method according to claim 1, wherein Calculating the lunar surface altitude, inclination angle, longitude of the ascending node, and transfer flight time at the perigee moment through numerical integration of the high - precision force model, and establishing a mapping data table between the three - dimensional data pairs of the orbit - transfer velocity increment and the lunar surface altitude, inclination angle, longitude of the ascending node, and transfer flight time at the perigee moment, including: Calculating the lunar surface altitude, inclination angle, longitude of the ascending node, and transfer flight time at the perigee moment through numerical integration of the high - precision force model, and the mapping data table established between the three - dimensional data pairs of the orbit - transfer velocity increment and the lunar surface altitude, inclination angle, longitude of the ascending node, and transfer flight time at the perigee moment is: Among them, represents the three-dimensional data pair of the orbit transfer velocity increment, represents the lunar surface altitude at the periselene time, represents the inclination angle at the periselene time, represents the longitude of the ascending node at the periselene time, represents the transfer flight time at the periselene time, represents the orbit transfer velocity increment parameter - lunar surface altitude, represents the orbit transfer velocity increment parameter - inclination angle, represents the orbit transfer velocity increment parameter - longitude of the ascending node, represents the orbit transfer velocity increment parameter - transfer flight time, represents the magnitude of the velocity increment during the transfer process, represents the azimuth angle of the orbit transfer velocity increment, represents the elevation angle of the orbit transfer velocity increment.

3. The method according to claim 1, characterized in that, The preset DRO orbit size parameters include 60000 km, 65000 km, 70000 km, 75000 km, and 80000 km.

4. The method according to any one of claims 1 to 3, characterized in that, Screening out the three - dimensional data pairs of the orbit - transfer velocity increment whose lunar surface altitude and inclination angle at the perigee moment satisfy the preset dispersion range according to the lunar surface altitude of the target orbit and the inclination angle of the target orbit, including: The three-dimensional data pairs of the velocity increment for orbit transfer whose lunar surface altitude at the perilune moment and inclination angle at the perilune moment satisfy the preset dispersion range are screened out according to the lunar surface altitude of the target orbit and the inclination angle of the target orbit: Among them, and , represents the lunar surface altitude of the target orbit, represents the inclination angle of the target orbit, represents the lunar surface altitude at the periselene time, represents the inclination angle at the periselene time, represents the allowable deviation range of the lunar surface altitude at the periselene time relative to the lunar surface altitude of the target orbit, represents the allowable deviation range of the inclination angle at the periselene time relative to the inclination angle of the target orbit.

5. The method according to claim 1, wherein Obtaining the longitude of the ascending node and the transfer flight time corresponding to the data pair with the minimum velocity increment during each transfer process to calculate the orbit transfer moment, including: Obtaining the longitude of the ascending node and the transfer flight time corresponding to the data pair with the minimum velocity increment during each transfer process to calculate the orbit transfer moment as: Among them, is the angular velocity of the lunar revolution, is the average orbital angular velocity of the DRO vehicle in the L2 coordinate system, represents the transfer flight time corresponding to the data pair of the velocity increment in each minimum transfer process, represents the longitude of the ascending node, represents the longitude of the ascending node at the initial moment of the target orbit, represents the phase angle of the DRO vehicle at the initial moment, represents the initial moment.

6. The method according to claim 1, wherein Correcting the phase at the selected orbit transfer moment to obtain the corrected phase, including: Calculating the phase at the selected orbit transfer moment as: Among them, represents the phase angle of the DRO vehicle at the initial moment, is the average orbital angular velocity of the DRO vehicle in the L2 coordinate system, represents the selected orbit transfer moment, represents the initial moment.

7. The method according to claim 5, wherein The method further includes: The phase of the selected orbit transfer moment includes the azimuth angle and the elevation angle , and the corrected results are denoted as , , there is: Among them, the correction coefficients and are obtained according to the interpolation table acquired from pre-simulation experiments.

8. The method according to claim 1, characterized in that Calculating the projection of the velocity increment for orbit transfer according to the corrected phase, including: Calculating the projection of the velocity increment for orbit transfer according to the corrected phase as: Among them, represents the corrected azimuth angle, represents the corrected elevation angle, represents the phase at the selected orbit transfer moment, represents the minimum orbit transfer velocity increment, represents the coordinate transformation matrix.

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