CN-117382921-B - Transfer track design method and system for circular moon large ellipse freezing track

Abstract

The invention discloses a transfer track design method and system of a circular moon large ellipse freezing track based on eccentricity vector targeting, which determines the lifting type of the transfer track in advance in the earth-moon transfer stage, the earth-moon transfer track is selected as track-descending emission and track-descending arrival, the method is characterized in that the ring moon orbit is ensured to be a large ellipse freezing orbit with a distant moon point above a southern hemisphere of a moon, an earth-moon transfer orbit meeting task constraint is generated by utilizing eccentricity vector targeting, after the moon is captured, a near-moon point amplitude angle is adjusted near the distant moon point, and the ring moon large ellipse freezing orbit is ensured to be generated efficiently. Finally, pulse transfer is applied to the large ellipse frozen orbit of the required period at the near month according to the task requirement.

Inventors

• LI HAIYANG
• ZHAO YINGJIE
• CHEN XIAO
• ZHANG WEI
• XIA YAN
• WANG HAIPENG
• CHU YINGZHI
• SHI WEIGANG

Assignees

• 深空探测实验室(天都实验室)
• 上海卫星工程研究所

Dates

Publication Date

20260512

Application Date

20231010

Claims (12)

1. 1. The method for designing the transfer orbit of the circular moon large ellipse freezing orbit based on the eccentricity vector targeting is used for designing the ground moon transfer orbit from a near place and running to the circular moon large ellipse freezing orbit and is characterized by comprising the following steps of: Defining a geocentric inertial coordinate system and a lunar white road surface coordinate system, setting the near-place moment of a geolunar transfer orbit, the transfer time, the near-place radius, the geocentric inertial system inclination angle, the near-moon radius, the lunar white road surface coordinate system inclination angle, and selecting the geolunar transfer orbit as a derailment emission and a derailment arrival; Reading ephemeris under a geocentric inertial system to obtain the position and the right ascent declination of a moon at a near moon point, calculating the right ascent and the near-site amplitude angles of a rising intersection point of a geolunar transfer orbit, and targeting to calculate the semi-long axis, the eccentricity and the true near-point angle at the near moon point of the geolunar transfer orbit, so as to determine orbit parameters of a geocentric departure orbit, obtain a vector initial value of the eccentricity of a geocentric segment, calculate the position and the speed of the geolunar transfer orbit when moving to a moon influence sphere, and transfer the position and the speed to a lunar white road surface coordinate system to obtain the vector initial value of the eccentricity of the geolunar segment; Calculating time, position and speed from a place departure orbit to a moon influence sphere according to a place segment eccentricity vector under a place center inertial system, calculating the position and speed of a moon arrival orbit for a certain time according to the place segment eccentricity vector under a moon white track surface coordinate system, transferring the state to the place center inertial system, calculating position and speed tolerance, targeting iteration place segment eccentricity vector and moon segment eccentricity vector, and solving by using a high-precision model with a targeting solving result as an initial value to obtain a complete place-month transfer orbit meeting task constraint; Fixing the height and the inclination angle of a near moon of a moon capturing orbit, calculating a capturing orbit period, and entering the moon capturing orbit; And fifthly, fixing the amplitude angle and the dip angle of the near moon of the target track and the height of the near moon, adjusting the amplitude angle of the near moon at the far moon to obtain a circular moon large ellipse freezing track, and finally applying pulse to the near moon according to the task requirement to transfer to the large ellipse freezing track of the required period.
2. 2. The method for designing a transfer orbit of a circular moon large ellipse frozen orbit based on eccentricity vector targeting according to claim 1, wherein in the first step, the following steps are performed: Step 1.1, defining a geocentric inertial coordinate system and a lunar white road surface coordinate system; in the geocentric inertial system, the X axis is the connecting line direction from the earth to the moon when the detector enters the moon, the Z axis is the normal line direction along the moon running track, and the Y axis is determined by a right hand rule; Step 1.2, calculating the moment of a near moon point and determining the type of the lifting rail; Calculating the near-point time of the earth-month transfer orbit according to the near-point time of the earth-month transfer orbit and the transfer time; The method comprises the steps of selecting a falling track launching track according to the launching field position, simultaneously considering that a detection target is a moon south pole, designing a ring moon track as a large oval freezing track with a distant moon point over a moon south hemisphere, selecting a falling track arrival track, and selecting the launching track and the arrival track of a ground moon transfer track as falling track launching and falling track arrival.
3. 3. The method for designing a transfer orbit of a circular moon large ellipse frozen orbit based on eccentricity vector targeting according to claim 2, wherein in the second step, the following steps are performed: Step 2.1, defining a double-body model; The double-body model takes a moon impact ball as a boundary, and only takes the action of the central gravity of the moon into consideration when the detector affects the movement in the moon, and only receives the action of the central gravity of the earth after the impact ball is taken out; Step 2.2, calculating an initial value of the eccentricity vector of the earth center section; the calculation formula of the eccentricity vector e is as follows (1) Wherein mu is an attractive force parameter, r and v are position vectors and speed vectors of the detector at any moment, an eccentricity vector of the orbit can be obtained by solving r and v at any point on the orbit, and a state vector can be solved by the orbit parameter; Reading ephemeris to obtain the position of moon at the moment of near moon under the geocentric inertial system, obtaining the right ascent and declination of the position of moon, using spherical triangle to obtain the right ascent and declination of transfer orbit, using targeting method to solve the other orbit parameters of earth-moon transfer orbit, according to the near-place radius r pE , transfer time t Trans and near-moon radius r pM of earth-moon transfer orbit, assuming that the near moon is on the extension line of moon position vector, the orbit far-place radius initial value is given as (2) Wherein r aE is the remote point radius; the radius of the far-place of the transfer track is obtained by targeting, and the targeting equation is that (3) (4) (5) (6) (7) Wherein, the true near point angle f f can be calculated by the close point angle M f , r f represents the orbit radius at the near point time, the target is fvec minimum, after the far point radius r aE is calculated, the semilong axis a E , the eccentricity e E and the true near point angle f f at the near point time of the earth-moon transfer orbit can be calculated according to the above formula, a group of orbit parameters are obtained and converted into a position vector and a speed vector, and the initial value e E0 of the earth-center section eccentricity vector can be calculated; Step 2.3, calculating an initial value of the eccentricity vector of the lunar section; The calculation is carried out under a geocentric inertial system, the state vector is transferred to a lunar white road surface coordinate system, and a lunar section eccentricity vector initial value e M0 is obtained through calculation.
4. 4. The method for designing a transfer orbit of a circular moon large ellipse frozen orbit based on eccentricity vector targeting according to claim 3, wherein in the third step, the following steps are performed: Step 3.1, calculating the time and position speed from the operation to the position of the moon to influence the ball according to the eccentricity vector of the earth center section; calculating a near-heart-point orbit parameter according to the eccentricity vector: Firstly, calculating the right-angle longitude and latitude of a near-heart point as (8) (9) Wherein e x ,e y ,e z is a direction component of e, and the right ascent point and the right ascent point angle of the track can be obtained according to right ascent and declination; The magnitude of the eccentricity vector is equal to the eccentricity, and a long half shaft is calculated according to the near-place radius and the eccentricity of the earth center section track; After obtaining the track parameters of the earth center section according to the eccentricity vector of the earth center section, the time t P and the position and speed vector from the track running to the moon impact ball can be calculated; Step 3.2, calculating the position speed of the backward pushing operation for a certain time according to the eccentricity vector of the lunar section; Obtaining a lunar section track parameter according to the lunar section eccentricity ratio vector, performing backward pushing operation for a period of time t M =t trans －t P to obtain a position and speed vector at a track splicing point, and converting a state vector under a lunar white road surface coordinate system into a state vector under a geocentric inertial system; step 3.3, targeting solving the ground-moon transfer orbit spliced by the conic curve, and solving by using a high-precision model with the targeting solving result as an initial value; And (3) calculating the difference between the position and the speed vector in the step (3.1) and the step (3.2) according to the initial value e E0 of the eccentricity vector of the land center section and the initial value e M0 of the eccentricity vector of the moon center section obtained in the step (2.2) and the step (2.3) as initial values of target practice guesses, iterating the position and the speed vector until the position and the speed tolerance are met by the vector of the eccentricity vector of the land center section and the vector of the eccentricity vector of the moon center section, solving by using a high-precision model with the target practice result as the initial values, and finally obtaining the complete land-moon transfer orbit meeting the task constraint.
5. 5. The method for designing a transfer orbit of a circular moon large ellipse frozen orbit based on eccentricity vector targeting according to claim 4, wherein in the fourth step, the following steps are performed: step 4.1, determining a capture orbit period T; in order to ensure the stability of the capturing orbit, the capturing orbit needs to be positioned in the moon to influence the ball, and the period of the capturing orbit is 6 days at most; after the capturing is successful, in order to enable the detector to run on the track for a period of time without collision with the month under the condition that the subsequent track change cannot be operated after the failure, the capturing track period is 4 days at most under the condition that 60 days are required to not collision with the month; The larger the capturing track period, the smaller the distance moon speed, the smaller the speed increment required by the distance moon track adjustment, so the capturing track period is as large as possible; The moon braking capture needs to consider the speed increment deviation of the actual orbit control, and a certain margin is reserved for capturing the speed increment, so that the moon braking capture can be ensured to be captured on a stable orbit; the capture orbit period was chosen to be 3 days by comprehensive consideration; step 4.2, calculating moon capturing orbit parameters; the half long axis a c of the capturing track is (10) The eccentricity is calculated according to the semilong axis of the capturing orbit and the radius of the near moon, the right ascent and intersection point is 0, the influence is avoided, and the amplitude angle of the near moon is obtained according to time; The near moon height and inclination of the moon capturing orbit are determined by the earth-moon transfer orbit.
6. 6. The method for designing a transfer orbit of a circular moon large ellipse frozen orbit based on eccentricity vector targeting according to claim 5, wherein in the fifth step, the following steps are performed: Step 5.1, maneuver adjustment of the amplitude angle of the near month in the distant month; The remote moon maneuver is to adjust the meniscus amplitude angle of the moon capturing orbit and adjust the orbit inclination angle to the required inclination angle, so as to obtain the large elliptic frozen orbit of the target; Due to the earth-moon space dynamics, the peri-moon amplitude angle when the earth-moon transfer orbit reaches the peri-moon varies from 120 degrees to 150 degrees, and the peri-moon amplitude angle which cannot directly reach the requirement of the large elliptical freezing orbit is 90 degrees; in the process of transferring the earth and moon, a midway maneuver is applied to adjust the amplitude angle of the near moon, a larger speed increment is needed, and feasibility is not provided; The perigee amplitude angle belongs to an in-plane orbit parameter, analysis is carried out based on a Gaussian perturbation equation, orbit transformation is carried out at different true perigee angles of the orbit under unit perturbation acceleration on a ring moon orbit formed after capturing, and the adjustment of the perigee amplitude angle is most efficient near a distant moon; Step 5.2, calculating a large ellipse frozen track; Performing orbit adjustment near the distant moon to generate a large elliptical freezing orbit with a period of 12 hours, wherein the adjustment targets are a near moon amplitude angle omega F , an inclination angle i F and a near moon height h pF ; under the two bodies, the track change is carried out at a certain point on the captured track, under the condition that the target tracks omega F 、i F and h pF are known, the track number of the target track can be determined through the space geometrical relationship, the track change position and track change speed increment under the two bodies are analyzed and calculated, and the calculation process is as follows: The position and speed vector of the orbit transferring point on the captured orbit can be obtained, the radius and the right ascent and descent of the position are calculated, whether the orbit transferring point is in the range of the target inclination angle or not is judged, the right ascent and descent point of the target orbit omega F and the true and near point angle f F can be obtained, and the orbit transferring point is obtained according to the following steps (11) (12) The eccentricity e F and the semimajor axis a F of the target frozen orbit can be obtained (13) (14) Obtaining a group of track parameters of a frozen track, calculating a speed vector of the track at the track change point, and obtaining a track change speed increment by making a difference with the speed vector at the track change point of the captured track; finally, in order to obtain the large ellipse frozen orbit of a given period, pulse is applied at a near moon point, and the large ellipse frozen orbit of a target period is obtained through a targeting method.
7. 7. A transfer orbit design system for designing a ground month transfer orbit from a near place and running to a circular month large ellipse freezing orbit based on eccentricity vector targeting, characterized by comprising: the earth-moon transfer orbit input module is used for defining an earth-center inertial coordinate system and a lunar-center white road surface coordinate system, setting the near-place moment, the transfer time, the near-place radius, the earth-center inertial system dip angle, the near-moon radius and the lunar-center white road surface coordinate system dip angle of the earth-moon transfer orbit, and selecting the earth-moon transfer orbit as the derailment emission and derailment arrival; The eccentricity vector initial value calculation module is used for reading ephemeris under a geocentric inertial system to obtain the position and the right ascent and the declination of a moon at a near moon point, calculating the right ascent and the near-site amplitude angles of an ascent point of a moon transfer orbit, and targeting to calculate the semi-long axis, the eccentricity and the true near-point angle at the near moon point of the moon transfer orbit so as to determine orbit parameters of a geocentric departure orbit, obtain a geocentric section eccentricity vector initial value, calculate the position and the speed of the moon transfer orbit when running to a moon influence sphere, and transfer the position and the speed to a lunar white road surface coordinate system to obtain a lunar section eccentricity vector initial value; the earth-moon transfer orbit calculation module is used for calculating the time, the position and the speed from the earth center departure orbit to the position of the moon influence sphere according to the earth center section eccentricity vector under the earth center inertial system, calculating the position and the speed from the moon center arrival orbit back-pushing operation for a certain time according to the moon center section eccentricity vector under the moon center white road surface coordinate system, transferring the state to the earth center inertial system, calculating the position and the speed tolerance, targeting iteration earth center section eccentricity vector and moon center section eccentricity vector, and solving by using a high-precision model with a targeting solving result as an initial value to obtain the complete earth-moon transfer orbit meeting the task constraint; The moon capturing orbit calculation module is used for fixing the height and the inclination angle of a near moon of the moon capturing orbit, calculating the capturing orbit period and entering the moon capturing orbit; The large ellipse freezing orbit calculation module is used for fixing the meniscus amplitude angle, the inclination angle and the meniscus height of the target orbit, adjusting the meniscus amplitude angle at the distant moon to obtain a circular moon large ellipse freezing orbit, and finally applying pulse to the near moon according to the task requirement to transfer to the large ellipse freezing orbit of the required period.
8. 8. The eccentricity vector targeting-based transfer trajectory design system of a ring moon large ellipse frozen trajectory according to claim 7, wherein in the earth moon transfer trajectory input module is performed: Step 1.1, defining a geocentric inertial coordinate system and a lunar white road surface coordinate system; In the geocentric inertial system, the X axis is the connecting line direction from the earth to the moon when the detector enters the moon, the Z axis is the normal line direction along the moon running track, and the Y axis is determined by a right hand rule; Step 1.2, calculating the moment of a near moon point and determining the type of the lifting rail; Calculating the near-point time of the earth-month transfer orbit according to the near-point time of the earth-month transfer orbit and the transfer time; The method comprises the steps of selecting a falling track launching track according to the launching field position, simultaneously considering that a detection target is a moon south pole, designing a ring moon track as a large oval freezing track with a distant moon point over a moon south hemisphere, selecting a falling track arrival track, and selecting the launching track and the arrival track of a ground moon transfer track as falling track launching and falling track arrival.
9. 9. The eccentricity vector targeting-based transfer trajectory design system of a large lunar oval frozen trajectory of claim 8, wherein the eccentricity vector initial value calculation module performs: Step 2.1, defining a double-body model; The double-body model takes a moon impact ball as a boundary, and only takes the action of the central gravity of the moon into consideration when the detector affects the movement in the moon, and only receives the action of the central gravity of the earth after the impact ball is taken out; Step 2.2, calculating an initial value of the eccentricity vector of the earth center section; the calculation formula of the eccentricity vector e is as follows (1) Wherein mu is an attractive force parameter, r and v are position vectors and speed vectors of the detector at any moment, an eccentricity vector of the orbit can be obtained by solving r and v at any point on the orbit, and a state vector can be solved by the orbit parameter; Reading ephemeris to obtain the position of moon at the moment of near moon under the geocentric inertial system, obtaining the right ascent and declination of the position of moon, using spherical triangle to obtain the right ascent and declination of transfer orbit, using targeting method to solve the other orbit parameters of earth-moon transfer orbit, according to the near-place radius r pE , transfer time t Trans and near-moon radius r pM of earth-moon transfer orbit, assuming that the near moon is on the extension line of moon position vector, the orbit far-place radius initial value is given as (2) Wherein r aE is the remote point radius; the radius of the far-place of the transfer track is obtained by targeting, and the targeting equation is that (3) (4) (5) (6) (7) Wherein, the true near point angle f f can be calculated by the close point angle M f , r f represents the orbit radius at the near point time, the target is fvec minimum, after the far point radius r aE is calculated, the semilong axis a E , the eccentricity e E and the true near point angle f f at the near point time of the earth-moon transfer orbit can be calculated according to the above formula, a group of orbit parameters are obtained and converted into a position vector and a speed vector, and the initial value e E0 of the earth-center section eccentricity vector can be calculated; Step 2.3, calculating an initial value of the eccentricity vector of the lunar section; The calculation is carried out under a geocentric inertial system, the state vector is transferred to a lunar white road surface coordinate system, and a lunar section eccentricity vector initial value e M0 is obtained through calculation.
10. 10. The eccentricity vector targeting-based transfer trajectory design system of a ring moon large ellipse frozen trajectory according to claim 9, wherein in the earth moon transfer trajectory calculation module: Step 3.1, calculating the time and position speed from the operation to the position of the moon to influence the ball according to the eccentricity vector of the earth center section; calculating a near-heart-point orbit parameter according to the eccentricity vector: Firstly, calculating the right-angle longitude and latitude of a near-heart point as (8) (9) Wherein e x ,e y ,e z is a direction component of e, and the right ascent point and the right ascent point angle of the track can be obtained according to right ascent and declination; The magnitude of the eccentricity vector is equal to the eccentricity, and a long half shaft is calculated according to the near-place radius and the eccentricity of the earth center section track; After obtaining the track parameters of the earth center section according to the eccentricity vector of the earth center section, the time t P and the position and speed vector from the track running to the moon impact ball can be calculated; Step 3.2, calculating the position speed of the backward pushing operation for a certain time according to the eccentricity vector of the lunar section; Obtaining a lunar section track parameter according to the lunar section eccentricity ratio vector, performing backward pushing operation for a period of time t M =t trans －t P to obtain a position and speed vector at a track splicing point, and converting a state vector under a lunar white road surface coordinate system into a state vector under a geocentric inertial system; step 3.3, targeting solving the ground-moon transfer orbit spliced by the conic curve, and solving by using a high-precision model with the targeting solving result as an initial value; And (3) calculating the difference between the position and the speed vector in the step (3.1) and the step (3.2) according to the initial value e E0 of the eccentricity vector of the land center section and the initial value e M0 of the eccentricity vector of the moon center section obtained in the step (2.2) and the step (2.3) as initial values of target practice guesses, iterating the position and the speed vector until the position and the speed tolerance are met by the vector of the eccentricity vector of the land center section and the vector of the eccentricity vector of the moon center section, solving by using a high-precision model with the target practice result as the initial values, and finally obtaining the complete land-moon transfer orbit meeting the task constraint.
11. 11. The eccentricity vector targeting-based transfer trajectory design system of a circular moon large ellipse freezing trajectory according to claim 10, wherein in the moon capture trajectory calculation module: step 4.1, determining a capture orbit period T; in order to ensure the stability of the capturing orbit, the capturing orbit needs to be positioned in the moon to influence the ball, and the period of the capturing orbit is 6 days at most; after the capturing is successful, in order to enable the detector to run on the track for a period of time without collision with the month under the condition that the subsequent track change cannot be operated after the failure, the capturing track period is 4 days at most under the condition that 60 days are required to not collision with the month; The larger the capturing track period, the smaller the distance moon speed, the smaller the speed increment required by the distance moon track adjustment, so the capturing track period is as large as possible; The moon braking capture needs to consider the speed increment deviation of the actual orbit control, and a certain margin is reserved for capturing the speed increment, so that the moon braking capture can be ensured to be captured on a stable orbit; the capture orbit period was chosen to be 3 days by comprehensive consideration; step 4.2, calculating moon capturing orbit parameters; the half long axis a c of the capturing track is (10) The eccentricity is calculated according to the semilong axis of the capturing orbit and the radius of the near moon, the right ascent and intersection point is 0, the influence is avoided, and the amplitude angle of the near moon is obtained according to time; The near moon height and inclination of the moon capturing orbit are determined by the earth-moon transfer orbit.
12. 12. The eccentricity vector targeting-based transfer trajectory design system of a circular moon macroellipse frozen trajectory of claim 11, wherein in the macroellipse frozen trajectory calculation module: Step 5.1, maneuver adjustment of the amplitude angle of the near month in the distant month; The remote moon maneuver is to adjust the meniscus amplitude angle of the moon capturing orbit and adjust the orbit inclination angle to the required inclination angle, so as to obtain the large elliptic frozen orbit of the target; Due to the earth-moon space dynamics, the peri-moon amplitude angle when the earth-moon transfer orbit reaches the peri-moon varies from 120 degrees to 150 degrees, and the peri-moon amplitude angle which cannot directly reach the requirement of the large elliptical freezing orbit is 90 degrees; in the process of transferring the earth and moon, a midway maneuver is applied to adjust the amplitude angle of the near moon, a larger speed increment is needed, and feasibility is not provided; The perigee amplitude angle belongs to an in-plane orbit parameter, analysis is carried out based on a Gaussian perturbation equation, orbit transformation is carried out at different true perigee angles of the orbit under unit perturbation acceleration on a ring moon orbit formed after capturing, and the adjustment of the perigee amplitude angle is most efficient near a distant moon; Step 5.2, calculating a large ellipse frozen track; Performing orbit adjustment near the distant moon to generate a large elliptical freezing orbit with a period of 12 hours, wherein the adjustment targets are a near moon amplitude angle omega F , an inclination angle i F and a near moon height h pF ; under the two bodies, the track change is carried out at a certain point on the captured track, under the condition that the target tracks omega F 、i F and h pF are known, the track number of the target track can be determined through the space geometrical relationship, the track change position and track change speed increment under the two bodies are analyzed and calculated, and the calculation process is as follows: The position and speed vector of the orbit transferring point on the captured orbit can be obtained, the radius and the right ascent and descent of the position are calculated, whether the orbit transferring point is in the range of the target inclination angle or not is judged, the right ascent and descent point of the target orbit omega F and the true and near point angle f F can be obtained, and the orbit transferring point is obtained according to the following steps (11) (12) The eccentricity e F and the semimajor axis a F of the target frozen orbit can be obtained (13) (14) Obtaining a group of track parameters of a frozen track, calculating a speed vector of the track at the track change point, and obtaining a track change speed increment by making a difference with the speed vector at the track change point of the captured track; finally, in order to obtain the large ellipse frozen orbit of a given period, pulse is applied at a near moon point, and the large ellipse frozen orbit of a target period is obtained through a targeting method.

Description

Transfer track design method and system for circular moon large ellipse freezing track Technical Field The invention relates to the technical field of transfer track design of a circular moon large ellipse freezing track, in particular to a transfer track design method for designing a ground moon transfer track from a near place and running to the circular moon large ellipse freezing track. Background The communication conditions between the ground and the back and polar regions of the moon are poor, and the complex requirements of future lunar exploration cannot be met only by relying on measurement and control stations built on the earth. Therefore, a lunar navigation system needs to be established to provide relay communication, navigation and remote sensing services for lunar and lunar surrounding users. The circular moon large ellipse freezing orbit has become the core of the current lunar polar detection and establishment of lunar scientific research stations. However, no study is currently made to establish a track scheme for designing a month transfer track from a near place and running to a large oval frozen track of the ring month. In addition, the design of the current earth-moon transfer track is four lifting track types, analysis is needed, and a proper one is selected, and the earth-moon transfer track can be designed into a track descending emission and track descending arrival in advance by adopting an eccentricity vector targeting method. Disclosure of Invention The technical problem to be solved by the invention is how to efficiently generate a large elliptical frozen orbit. The invention solves the technical problems by the following technical means: A transfer orbit design method of a circular moon large ellipse freezing orbit based on eccentricity vector targeting is used for designing a ground month transfer orbit from a near place and running to the circular moon large ellipse freezing orbit, and comprises the following steps of: Defining a geocentric inertial coordinate system and a lunar white road surface coordinate system, setting a near-place moment of a geolunar transfer orbit, transferring time, a near-place radius, a geocentric inertial system inclination angle, a near-moon radius, a lunar white road surface coordinate system inclination angle, and selecting lifting rail types of an earth departure section and a lunar arrival section; Reading ephemeris under a geocentric inertial system to obtain the position and the right ascent declination of a moon at a near moon point, calculating the right ascent and the near-site amplitude angles of a rising intersection point of a geolunar transfer orbit, and targeting to calculate the semi-long axis, the eccentricity and the true near-point angle at the near moon point of the geolunar transfer orbit, so as to determine orbit parameters of a geocentric departure orbit, obtain a vector initial value of the eccentricity of a geocentric segment, calculate the position and the speed of the geolunar transfer orbit when moving to a moon influence sphere, and transfer the position and the speed to a lunar white road surface coordinate system to obtain the vector initial value of the eccentricity of the geolunar segment; Calculating time, position and speed from a place departure orbit to a moon influence sphere according to a place segment eccentricity vector under a place center inertial system, calculating the position and speed of a moon arrival orbit for a certain time according to the place segment eccentricity vector under a moon white track surface coordinate system, transferring the state to the place center inertial system, calculating position and speed tolerance, targeting iteration place segment eccentricity vector and moon segment eccentricity vector, and solving by using a high-precision model with a targeting solving result as an initial value to obtain a complete place-month transfer orbit meeting task constraint; Fixing the height and the inclination angle of a near moon of a moon capturing orbit, calculating a capturing orbit period, and entering the moon capturing orbit; And fifthly, fixing the amplitude angle and the dip angle of the near moon of the target track and the height of the near moon, adjusting the amplitude angle of the near moon at the far moon to obtain a circular moon large ellipse freezing track, and finally applying pulse to the near moon according to the task requirement to transfer to the large ellipse freezing track of the required period. Further, in the first step, performing: Step 1.1, defining a geocentric inertial coordinate system and a lunar white road surface coordinate system; in the geocentric inertial system, the X axis is the connecting line direction from the earth to the moon when the detector enters the moon, the Z axis is the normal line direction along the moon running track, and the Y axis is determined by a right hand rule; Step 1.2, calculating the moment of a near moon point and dete