Satellite north-south control strategy optimization method, device and equipment

Abstract

The present invention provides a method, device and equipment for optimizing a satellite north-south control strategy, including: identifying the north-south exit time of a target satellite; calculating a differential inclination vector according to the instantaneous root of the true equatorial orbit system corresponding to the north-south exit time and a target inclination vector, and determining the control time, velocity increment and the post-control inclination vector corresponding to the velocity increment in the north-south control strategy according to the differential inclination vector; if the difference between the post-control inclination vector and the target inclination vector does not meet a preset condition, updating the target inclination vector based on the difference, iteratively optimizing the differential inclination vector, the control time, the velocity increment and the post-control inclination vector corresponding to the velocity increment based on the updated target inclination vector until the preset condition is met, and obtaining the target control time and target velocity increment in the north-south control strategy. The present invention effectively improves the problem of selecting the best of the north-south control strategy, thereby significantly improving the control effect of the north-south control strategy.

Description

Technical Field

[0001] The present invention relates to the field of satellite technology, and in particular to a method, device and equipment for optimizing a satellite north-south control strategy. Background Art

[0002] Traditional chemical propulsion north-south control is to select an appropriate moment and control the inclination vector in the opposite direction of the annual average perturbation when the inclination is about to exceed the required orbit. However, it does not involve issues related to the optimization of the north-south control strategy for chemical propulsion GEO (geosynchronous orbit) satellites, including the selection of control moment and optimization of control quantity when the target inclination is in any direction. Therefore, the north-south control effect is poor. Summary of the invention

[0003] In view of this, the purpose of the present invention is to provide a satellite north-south control strategy optimization method, device and equipment, which effectively improves the problem of optimizing the north-south control strategy, thereby significantly improving the control effect of the north-south control strategy.

[0004] In a first aspect, an embodiment of the present invention provides a method for optimizing a satellite north-south control strategy, including:

[0005] Identify the north and south exit times of the target satellite based on the current instantaneous root orbit, inclination holding range and predicted start and end times of the target satellite;

[0006] The differential inclination vector is calculated based on the instantaneous root of the true equatorial orbit system corresponding to the north and south exit times and the target inclination vector, and the control time, velocity increment and the post-control inclination vector corresponding to the velocity increment in the north-south control strategy are determined based on the differential inclination vector;

[0007] If the difference between the post-control tilt angle vector and the target tilt angle vector does not meet the preset conditions, the target tilt angle vector is updated based on the difference, and the differential tilt angle vector, control moment, speed increment and the post-control tilt angle vector corresponding to the speed increment are iteratively optimized based on the updated target tilt angle vector until the preset conditions are met, thereby obtaining the target control moment and target speed increment in the north-south control strategy.

[0008] In one embodiment, the north and south exit times of the target satellite are identified based on the current instantaneous root orbit, the inclination holding range, and the predicted start and end times of the target satellite, including:

[0009] Preprocessing the current instantaneous root orbit of the target satellite to generate a true equatorial orbit system position velocity set and a true equatorial orbit system instantaneous root set;

[0010] Extract the true equatorial orbit inclination angle sequence within the preset start and end time range from the true equatorial orbit instant root set;

[0011] The true equatorial orbit inclination sequence is traversed, and when the true equatorial orbit inclination value in the true equatorial orbit inclination sequence exceeds the inclination holding range, the north and south exit-loop times of the target satellite and the true equatorial orbit instantaneous roots corresponding to the north and south exit-loop times are obtained.

[0012] In one embodiment, the differential inclination vector is calculated based on the instantaneous root of the true equatorial orbit system corresponding to the north and south exit times and the target inclination vector, including:

[0013] Extract the inclination value of the loop point and the right ascension of the ascending node of the loop point from the instantaneous root of the true equatorial orbit system corresponding to the north and south loop exit times, and calculate the initial inclination vector based on the inclination value of the loop point and the right ascension of the ascending node of the loop exit time;

[0014] and, if the target inclination value and the target ascending node right ascension are configured, the target inclination vector is calculated based on the target inclination value and the target ascending node right ascension; if the target inclination value and the target ascending node right ascension are not configured, the target inclination value and the target ascending node right ascension are determined according to the loop-out point inclination value and the loop-out point ascending node right ascension, respectively, and the target inclination vector is calculated based on the target inclination value and the target ascending node right ascension;

[0015] Calculate the difference inclination vector between the initial inclination vector and the target inclination vector.

[0016] In one embodiment, determining the control time, speed increment, and the post-control tilt angle vector corresponding to the speed increment in the north-south control strategy according to the differential tilt angle vector includes:

[0017] Determine the corrected inclination value and the right ascension of the ascending node of the initial control point according to the differential inclination vector;

[0018] The position velocity set of the date of the north and south exit time is extracted from the true equatorial orbit system position velocity set, and based on the position velocity set of the date and the thruster direction, the right ascension of the ascending node of the initial control point is optimized to obtain the right ascension of the ascending node of the target control point;

[0019] Extracting a first true equatorial orbit system position velocity subset before the north-south exit-loop moment and a second true equatorial orbit system position velocity subset after the north-south exit-loop moment from the true equatorial orbit system position velocity set, and determining the control moment in the north-south control strategy and the J2000 position velocity corresponding to the control moment based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset;

[0020] According to the corrected tilt angle value and the J2000 position speed corresponding to the control time, the speed increment in the north-south control strategy and the post-control tilt angle vector corresponding to the speed increment are determined.

[0021] In one embodiment, based on the position velocity set and thruster direction of the date, the right ascension of the ascending node of the initial control point is optimized to obtain the right ascension of the ascending node of the target control point, including:

[0022] Based on the position and velocity set of that date, the right ascension of the ascending node on the day of looping and the right ascension of the descending node on the day of exiting the loop are calculated;

[0023] Determine the first absolute value of the difference between the right ascension of the ascending node of the initial control point and the right ascension of the ascending node on the day of exiting the loop, and determine the second absolute value of the difference between the right ascension of the ascending node of the initial control point and the descending node on the day of exiting the loop;

[0024] Based on the thruster direction, a first comparison result between the first difference absolute value and the second difference absolute value, and a second comparison result between the right ascension of the ascending node on the day of exiting the loop and a preset threshold, determining whether to optimize the right ascension of the ascending node of the initial control point;

[0025] If yes, the sum of the ascending node right ascension of the initial control point and 180° is used as the optimized ascending node right ascension of the target control point.

[0026] In one embodiment, based on the thruster direction, a first comparison result between the first difference absolute value and the second difference absolute value, and a second comparison result between the right ascension of the ascending node on the day of exiting the loop and a preset threshold, determining whether to optimize the right ascension of the ascending node of the initial control point includes:

[0027] When the thruster is facing south, if the first comparison result indicates that the control point is close to the ascending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is greater than the preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized;

[0028] Alternatively, when the thruster is facing south, if the first comparison result indicates that the control point is close to the descending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is less than the preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized;

[0029] Alternatively, when the thruster is facing north, if the first comparison result indicates that the control point is close to the descending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is greater than a preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized;

[0030] Alternatively, when the thruster is facing north, if the first comparison result indicates that the control point is close to the ascending node, and the second comparison result is that the right ascension of the ascending node on the day of leaving the loop is less than a preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized.

[0031] In one implementation, determining the control time in the north-south control strategy and the J2000 position velocity corresponding to the control time based on the first true equatorial orbital system position velocity subset or the second true equatorial orbital system position velocity subset includes:

[0032] Based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset, determining a first right ascension value and a second right ascension value located within a threshold interval corresponding to the right ascension of the ascending node of the target control point; wherein the time corresponding to the first right ascension value is less than the time corresponding to the second right ascension value, and the right ascension of the ascending node of the target control point is greater than the first right ascension value and less than the second right ascension value;

[0033] Generate a J2000 position velocity and a true equatorial orbit system position velocity set within a time period between a time corresponding to a first right ascension value and a time corresponding to a second right ascension value;

[0034] Based on the true equatorial orbit system position velocity set within the time period, determine a third right ascension value and a fourth right ascension value within a threshold interval corresponding to the right ascension of the ascending node of the target control point; wherein the time corresponding to the third right ascension value is less than the time corresponding to the fourth right ascension value, and the right ascension of the ascending node of the target control point is greater than the third right ascension value and less than the fourth right ascension value;

[0035] The time corresponding to the fourth right ascension value is taken as the control moment in the north-south control strategy, and the J2000 position velocity corresponding to the control moment is extracted from the J2000 position velocity within the time period.

[0036] In one implementation, before the difference between the post-control tilt angle vector and the target tilt angle vector does not satisfy a preset condition, the method further includes:

[0037] If the difference between the controlled back tilt angle value in the controlled back tilt angle vector and the target tilt angle value in the target tilt angle vector is greater than the first difference threshold, or the difference between the right ascension of the controlled back ascending node in the controlled back tilt angle vector and the right ascension of the target ascending node in the target tilt angle vector is greater than the second difference threshold, it is determined that the preset condition is not met.

[0038] In a second aspect, an embodiment of the present invention further provides a satellite north-south control strategy optimization device, comprising:

[0039] A data acquisition module is used to identify the north and south exit times of the target satellite based on the current instantaneous root orbit, the inclination holding range and the predicted start and end times of the target satellite;

[0040] A strategy determination module is used to calculate the differential inclination vector according to the instantaneous root of the true equatorial orbit system corresponding to the north and south exit times and the target inclination vector, and determine the control time, velocity increment and post-control inclination vector corresponding to the velocity increment in the north-south control strategy according to the differential inclination vector;

[0041] The strategy optimization module is used to update the target inclination vector based on the difference if the difference between the control rear inclination vector and the target inclination vector does not meet the preset conditions, so as to iteratively optimize the differential inclination vector, the control moment, the speed increment and the control rear inclination vector corresponding to the speed increment based on the updated target inclination vector until the preset conditions are met, thereby obtaining the target control moment and the target speed increment in the north-south control strategy.

[0042] In a third aspect, an embodiment of the present invention further provides an electronic device, comprising a processor and a memory, wherein the memory stores computer-executable instructions that can be executed by the processor, and the processor executes the computer-executable instructions to implement any one of the methods provided in the first aspect.

[0043] The satellite north-south control strategy optimization method, device and equipment provided by the embodiment of the present invention first identify the north-south exit time of the target satellite based on the current instantaneous root orbit, inclination holding range and predicted start and end time of the target satellite; then calculate the differential inclination vector according to the instantaneous root of the true equatorial orbit system corresponding to the north-south exit time and the target inclination vector, so as to determine the control time, speed increment and the post-control inclination vector corresponding to the speed increment in the north-south control strategy according to the differential inclination vector; if the difference between the post-control inclination vector and the target inclination vector does not meet the preset conditions, then update the target inclination vector based on the difference, so as to iteratively optimize the differential inclination vector, the control time, the speed increment and the post-control inclination vector corresponding to the speed increment based on the updated target inclination vector until the preset conditions are met, and obtain the target control time and target speed increment in the north-south control strategy. After identifying the north-south exit moment when the inclination of the target satellite is about to exceed the inclination holding range, the above method uses the instantaneous root of the true equatorial orbit system at this moment and the target inclination vector to calculate the differential inclination vector, so as to select the control moment and the speed increment based on the differential inclination vector, and continue to iteratively optimize the control moment and the speed increment according to the post-control inclination vector and the target inclination vector, and finally generate the optimal north-south control strategy for the target satellite. The embodiment of the present invention effectively improves the problem of optimizing the north-south control strategy, including realizing the selection of the control moment based on any target inclination vector, optimizing the iterative step size of the speed increment, etc., thereby significantly improving the control effect of the north-south control strategy.

[0044] Other features and advantages of the present invention will be described in the following description, and partly become apparent from the description, or understood by practicing the present invention. The purpose and other advantages of the present invention are realized and obtained by the structures particularly pointed out in the description, claims and drawings.

[0045] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0047] Figure 1 A schematic flow chart of a method for optimizing a satellite north-south control strategy provided by an embodiment of the present invention;

[0048] Figure 2 A schematic diagram of the overall process of a satellite north-south control strategy optimization method provided by an embodiment of the present invention;

[0049] Figure 3 A schematic diagram of the structure of a satellite north-south control strategy optimization device provided by an embodiment of the present invention;

[0050] Figure 4 A schematic diagram of the structure of an electronic device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0051] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution of the present invention will be clearly and completely described in combination with the embodiments below. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0052] At present, the relevant technology does not involve the issues related to the optimization of the North-South control strategy of chemical propulsion GEO satellites, including the selection of control time and optimization of control quantity considering arbitrary target inclination angles, which leads to poor North-South control effect. Based on this, the present invention implements a method, device and equipment for optimizing the satellite North-South control strategy, which effectively improves the problem of optimization of the North-South control strategy, thereby significantly improving the control effect of the North-South control strategy.

[0053] To facilitate understanding of this embodiment, firstly, a satellite north-south control strategy optimization method disclosed in an embodiment of the present invention is described in detail, see Figure 1 The flowchart of a method for optimizing a satellite north-south control strategy is shown in FIG. 1 , and the method mainly includes the following steps S102 to S106:

[0054] Step S102, identifying the north and south exit times of the target satellite based on the current instantaneous root orbit, the inclination holding range and the predicted start and end times of the target satellite.

[0055] Among them, the target satellite can be a GEO satellite, and the north and south exit-loop moments are the moments when the true equatorial orbit inclination value of the target satellite exceeds the inclination retention range within the forecast start and end time. In one example, the current instantaneous root orbit can be numerically predicted and the forecast result can be subjected to coordinate system conversion processing to generate a true equatorial orbit position velocity set and a true equatorial orbit instantaneous root set, and the true equatorial orbit inclination sequence of the target satellite within the forecast start and end time can be extracted from the true equatorial orbit instantaneous root set, and then each true equatorial orbit inclination value in the true equatorial orbit inclination sequence is compared with the inclination retention range, and the north and south exit-loop moments can be identified.

[0056] Step S104, calculate the differential inclination vector according to the instantaneous root of the true equatorial orbit system corresponding to the north and south exit times and the target inclination vector, and determine the control time, speed increment and the post-control inclination vector corresponding to the speed increment in the north-south control strategy according to the differential inclination vector.

[0057] In one example, the initial inclination vector is first determined based on the inclination value of the exit point in the instantaneous root of the true equatorial orbit system corresponding to the north and south exit times and the right ascension of the ascending node of the exit point, and the differential inclination vector is obtained by subtracting the initial inclination vector from the target inclination vector; then, the right ascension of the ascending node at the control time (referred to as the right ascension of the ascending node of the control point) is calculated based on the differential inclination vector; then, according to the thruster direction, the right ascension of the ascending node at the control time is optimized in consideration of the gravitational effect of the sun; the control time in the north-south control strategy is determined based on the optimized right ascension of the ascending node, and the speed increment in the north-south control strategy and the post-control inclination vector corresponding to the speed increment are determined based on the control time.

[0058] Step S106, if the difference between the rear control tilt angle vector and the target tilt angle vector does not meet the preset conditions, the target tilt angle vector is updated based on the difference, so as to iteratively optimize the differential tilt angle vector, the control moment, the speed increment and the rear control tilt angle vector corresponding to the speed increment based on the updated target tilt angle vector until the preset conditions are met, thereby obtaining the target control moment and the target speed increment in the north-south control strategy.

[0059] In one example, the difference between the rear-controlled tilt angle vector and the target tilt angle vector can be compared with a difference threshold to determine whether the preset condition is met. If the preset condition is not met, the target tilt angle vector can be updated, and step S104 is performed again to implement iterative updates of the differential tilt angle vector, the control moment, the speed increment, and the rear-controlled tilt angle vector corresponding to the speed increment, and determine whether the difference between the new rear-controlled tilt angle vector and the target tilt angle vector meets the preset condition. If the preset condition is met, the iteration can be stopped to obtain the target control moment and the target speed increment in the north-south control strategy.

[0060] The satellite north-south control strategy optimization method provided by the embodiment of the present invention, after identifying the north-south exit moment when the inclination of the target satellite is about to exceed the inclination holding range, uses the instantaneous root of the true equatorial orbit system at this moment and the target inclination vector to calculate the differential inclination vector, so as to select the control moment and the speed increment based on the differential inclination vector, and continue to iteratively optimize the control moment and the speed increment according to the post-control inclination vector and the target inclination vector, and finally generate the optimal north-south control strategy for the target satellite. The embodiment of the present invention effectively improves the problem of optimizing the north-south control strategy, including realizing the selection of the control moment based on an arbitrary target inclination vector, optimizing the iterative step size of the speed increment, etc., thereby significantly improving the control effect of the north-south control strategy.

[0061] For ease of understanding, an embodiment of the present invention provides a specific implementation of a method for optimizing a satellite north-south control strategy.

[0062] For the aforementioned step S102, the embodiment of the present invention provides an implementation method for identifying the north and south exit times of the target satellite based on the current instantaneous root orbit, the inclination holding range and the predicted start and end time of the target satellite, see the following steps 1A to 1C:

[0063] Step 1A, preprocessing the current instantaneous root orbit of the target satellite to generate a true equatorial orbit system position velocity set and a true equatorial orbit system instantaneous root set.

[0064] The preprocessing includes numerical prediction and coordinate system conversion. In one example, the current J2000 instantaneous root orbit Perform numerical prediction to obtain the instantaneous position and velocity set of J2000 ( , , … ) and J2000 instant root collection ( , , … ), converted to the true equatorial orbital position velocity set ( , , … ) and the instantaneous root set of the true equatorial orbital system ( , , … ).

[0065] Step 1B: extracting the true equatorial orbit inclination sequence within a preset start and end time range from the true equatorial orbit instant root set.

[0066] In one example, the forecast start and end time range is ( - ), from the instantaneous root set of the true equatorial orbit system ( , , … ) Extract the preset start and end time range ( - ) in the true equatorial orbital system inclination sequence ( , , … ).

[0067] Step 1C, traverse the true equatorial orbit inclination sequence, when the true equatorial orbit inclination value in the true equatorial orbit inclination sequence exceeds the inclination retention range, obtain the north and south exit times of the target satellite and the true equatorial orbit instantaneous root corresponding to the north and south exit times.

[0068] In one example, the minimum value in the inclination holding range is a° and the maximum value is b°. The true equatorial orbit inclination sequence is traversed. When the true equatorial orbit inclination exceeds the inclination holding range, it is the current satellite's north-south orbit exit time. , get the north and south ring exit time J2000 Instant Root The instantaneous root of the true equatorial orbital system .

[0069] For the aforementioned step S104, the embodiment of the present invention provides an implementation method for calculating the differential inclination vector according to the instantaneous root of the true equatorial orbit system corresponding to the north and south exit times and the target inclination vector, wherein the inclination vector is composed of the current inclination value and right ascension of the ascending node The inclination vector calculation formula is as follows: .

[0070] Based on this formula, the differential tilt vector can be determined according to the following steps 2A to 2C:

[0071] Step 2A, extracting the loop point inclination value and the right ascension of the ascending node of the loop point from the instantaneous root of the true equatorial orbit system corresponding to the north and south loop exit times, so as to calculate the initial inclination vector based on the loop exit point inclination value and the right ascension of the ascending node of the loop exit time.

[0072] In one example, the time from the north to the south The corresponding instantaneous root of the true equatorial orbital system Extract the inclination value of the ring point and the right ascension of the ascending node of the exit point , put it into the inclination vector calculation formula, and you can get the initial inclination vector , which is the initial inclination vector Corresponding to the inclination value of the ring exit point and the right ascension of the ascending node of the exit point .

[0073] Step 2B, if the target inclination value and the target right ascension of the ascending node are configured, the target inclination vector is calculated based on the target inclination value and the target right ascension of the ascending node; if the target inclination value and the target right ascension of the ascending node are not configured, the target inclination value and the target right ascension of the ascending node are determined according to the inclination value of the exit point and the right ascension of the ascending node of the exit point, respectively, and the target inclination vector is calculated based on the target inclination value and the target right ascension of the ascending node.

[0074] In one example, if a target inclination value is configured and the right ascension of the target ascending node , then substitute it into the inclination vector calculation formula to get the target inclination vector , that is, the target inclination vector Corresponding target inclination value and the right ascension of the target ascending node .

[0075] In one example, if the target inclination value is not configured and the right ascension of the target ascending node , then set the target inclination value The inclination value of the loop exit point , right ascension of target ascending node The right ascension of the ascending node of the ring exit point , and substitute it into the inclination vector calculation formula to obtain the target inclination vector .

[0076] Step 2C, calculating the difference inclination vector between the initial inclination vector and the target inclination vector.

[0077] In one example, the differential inclination vector can be calculated as follows: :

[0078] .

[0079] For the aforementioned step S104, the embodiment of the present invention further provides an implementation method for determining the control moment, speed increment, and the post-control tilt angle vector corresponding to the speed increment in the north-south control strategy according to the differential tilt angle vector, see the following steps 3A to 3D:

[0080] Step 3A, determining the corrected inclination value and the right ascension of the ascending node of the initial control point according to the differential inclination vector.

[0081] In one example, the differential inclination vector , calculate the corrected inclination value according to the following formula :

[0082] ;

[0083] In one example, the differential inclination vector Calculate the right ascension of the ascending node according to the following formula :

[0084] ;

[0085] in, is the right ascension corresponding to the position at the control moment (that is, the right ascension of the ascending node of the initial control point), let = .

[0086] Step 3B, extract the position velocity set of the date of the north and south exit moments from the true equatorial orbit system position velocity set, optimize the right ascension of the ascending node of the initial control point based on the position velocity set and thruster direction of the date, and obtain the right ascension of the ascending node of the target control point.

[0087] In one example, we first start from the true equatorial orbital position velocity set Extract the position and velocity set of the date when the north and south rings exit (i.e. the day of exiting the ring) Then, according to the following steps (1) to (4), the right ascension of the ascending node of the initial control point is optimized based on the position velocity set and thruster direction of the date to obtain the right ascension of the ascending node of the target control point:

[0088] (1) Based on the position and velocity set on that date, calculate the right ascension of the ascending node on the day of looping and the right ascension of the descending node on the day of exiting the loop.

[0089] In one example, based on the location speed set for that date Calculate the right ascension of the ascending node on the current day and the right ascension of the descending node on the day of the ring exit .

[0090] (2) Determine the first absolute value of the difference between the right ascension of the ascending node of the initial control point and the right ascension of the ascending node on the day of exiting the loop, and determine the second absolute value of the difference between the right ascension of the ascending node of the initial control point and the descending node on the day of exiting the loop.

[0091] (3) Based on the thruster direction, the first comparison result between the absolute value of the first difference and the absolute value of the second difference, and the second comparison result between the right ascension of the ascending node on the day of exiting the loop and the preset threshold, determine whether to optimize the right ascension of the ascending node of the initial control point. Specifically, it may include the following four situations:

[0092] Case 1: When the thruster is facing south, if the first comparison result indicates that the control point is close to the ascending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is greater than the preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized.

[0093] Specifically, when the thruster is facing south, if < , that is, the control point is close to the ascending node. When >180°, the right ascension of the ascending node of the initial control point is optimized, and the right ascension of the ascending node of the target control point after optimization is: = +180°.

[0094] Case 2: When the thruster is facing south, if the first comparison result indicates that the control point is close to the descending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is less than the preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized.

[0095] Specifically, when the thruster is facing south, if > , that is, the control point is close to the descending intersection. <180°, the right ascension of the ascending node of the initial control point is optimized, and the right ascension of the ascending node of the target control point after optimization is: = +180°.

[0096] Case 3: When the thruster is facing north, if the first comparison result indicates that the control point is close to the descending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is greater than the preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized.

[0097] Specifically, when the thruster is facing the > , that is, the control point is close to the descending intersection. When >180°, the right ascension of the ascending node of the initial control point is optimized, and the right ascension of the ascending node of the target control point after optimization is: = +180°.

[0098] Case 4: When the thruster is facing north, if the first comparison result indicates that the control point is close to the ascending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is less than the preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized.

[0099] Specifically, when the thruster is facing the < , that is, the control point is close to the ascending node. <180°, the right ascension of the ascending node of the initial control point is optimized, and the right ascension of the ascending node of the target control point after optimization is: = +180°.

[0100] (4) If yes, the sum of the right ascension of the ascending node of the initial control point and 180° is taken as the right ascension of the ascending node of the optimized target control point.

[0101] Step 3C, extracting a first true equatorial orbit system position velocity subset before the north and south exiting loop moments and a second true equatorial orbit system position velocity subset after the north and south exiting loop moments from the true equatorial orbit system position velocity set, and determining the control moment in the north-south control strategy and the J2000 position velocity corresponding to the control moment based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset;

[0102] In one example, according to the north-south ring exit time , from the true equatorial orbital position velocity set Extract the north and south ring exit times The position and velocity subsets based on the first true equatorial orbit system before and after ( , , … ), the second true equatorial orbital position velocity subset ( … , ), and on this basis, the steps of determining the control time in the north-south control strategy and the J2000 position velocity corresponding to the control time are performed based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset according to the following (a) to (d):

[0103] (a) determining, based on the first true equatorial orbit system position-velocity subset or the second true equatorial orbit system position-velocity subset, a first right ascension value and a second right ascension value that are within a threshold interval corresponding to the right ascension of the ascending node of the target control point; wherein the time corresponding to the first right ascension value is less than the time corresponding to the second right ascension value, and the right ascension of the ascending node of the target control point is greater than the first right ascension value and less than the second right ascension value;

[0104] In one example, the first true equatorial orbit position velocity subset is used Calculate the right ascension closest to the exit point as If the first true equatorial orbital position velocity subset If there is no suitable control point in the equation, the second true equatorial orbit position velocity subset is used. Calculate the right ascension closest to the exit point: The specific steps are as follows:

[0105] (a1) Based on the first true equatorial orbital system position velocity subset , using the formula Calculate the right ascension sequence of each point ( , , … ), the right ascension sequence Sort by time from largest to smallest ( , … , ).

[0106] (a2) Find the right ascension from front to back. Nearby Moments and ,in < , < < , For the moment The first right ascension value at For the moment The second right ascension value at .

[0107] (a3) If there is no moment and , so that < < , then according to the formula shown in (a1), based on the second true equatorial orbital system position velocity subset Calculate the new right ascension sequence, that is, the right ascension sequence after leaving the loop ( , , … ), the right ascension sequence after leaving the loop Sort by time from smallest to largest. Find the right ascension from front to back. Nearby Moments and ,in < , < < , For the moment The first right ascension value at For the moment The second right ascension value at .

[0108] (b) Generate a set of J2000 position velocity and true equatorial orbital position velocity in the time period between the time corresponding to the first right ascension value and the time corresponding to the second right ascension value.

[0109] In one example, in the J2000 instantaneous root collection Extract the time Corresponding J2000 instant root , according to J2000 instantaneous root , with a 2-second time interval for forecasting time periods ( , ) within the J2000 position speed ( , , … ) and the true equatorial orbital position velocity ( , , … ).

[0110] (c) Based on the true equatorial orbital system position velocity set within the time period, determine the third right ascension value and the fourth right ascension value within the threshold interval corresponding to the right ascension of the ascending node of the target control point; wherein the time corresponding to the third right ascension value is less than the time corresponding to the fourth right ascension value, and the right ascension of the ascending node of the target control point is greater than the third right ascension value and less than the fourth right ascension value.

[0111] In one example, for a time period ( , ) in the true equatorial orbital system position velocity set , according to the method shown in (a) above, from the true equatorial orbital position velocity set Extract the right ascension size in Nearby Moments and ,in < , < < , For the moment The third right ascension value at For the moment The fourth right ascension value at .

[0112] (d) The time corresponding to the fourth right ascension value is taken as the control moment in the north-south control strategy, and the J2000 position velocity corresponding to the control moment is extracted from the J2000 position velocity within the time period.

[0113] In one example, the time That is the control moment, at the J2000 position speed Extract the time The corresponding point is the position speed of J2000 at the control moment.

[0114] Step 3D, according to the corrected tilt angle value and the J2000 position speed corresponding to the control time, determine the speed increment in the north-south control strategy and the post-control tilt angle vector corresponding to the speed increment.

[0115] In one example, the normal velocity increment of the RTN system can be calculated according to the following formula: :

[0116] ;

[0117] in, For RTN system The x-axis velocity component, Depend on It is calculated by converting the instantaneous position velocity of J2000 into the true equatorial orbital position velocity.

[0118] Before executing the aforementioned step S106, it can be determined whether the difference between the controlled rear tilt angle vector and the target tilt angle vector meets the preset conditions according to the following steps: if the difference between the controlled rear tilt angle value in the controlled rear tilt angle vector and the target tilt angle value in the target tilt angle vector is greater than a first difference threshold, or the difference between the right ascension of the controlled rear ascending node in the controlled rear tilt angle vector and the right ascension of the target ascending node in the target tilt angle vector is greater than a second difference threshold, it is determined that the preset conditions are not met.

[0119] Specifically, the normal velocity increment The RTN velocity vector can be obtained ,Will Convert to J2000 coordinate system and superimpose on control point coordinates , get the instantaneous root coordinates of J2000 after control ,Will Convert to true equatorial orbital system instant root .

[0120] In one example, the difference between the controlled tilt angle vector and the target tilt angle vector is calculated according to the following formula:

[0121] ;

[0122] ;

[0123] in, The caster angle value With the target inclination value The difference between To control the right ascension of the posterior ascending node Right Ascension from the Target Ascending Node The difference between .

[0124] like > or > , it is determined that the preset condition is not met, and the target inclination vector is updated according to the following formula, and the above step S104 is repeated until < and < , complete the iteration of the differential inclination vector and optimize the control time and speed increment:

[0125] .

[0126] Compared with the traditional north-south control method, the embodiment of the present invention mainly solves the problem of optimizing the north-south control strategy, including the selection of control time, optimization of the iterative step size of the control amount and calculation of the control amount when considering the arbitrary direction of the target inclination angle.

[0127] Furthermore, the embodiment of the present invention also provides Figure 2 The overall process diagram of a satellite north-south control strategy optimization method shown in the figure includes: inputting the current orbit, the inclination holding range, the target inclination vector (size and direction), the start time and the end time; numerically predicting the current orbit; judging whether to exit the loop, if not, generating a control strategy of empty, if yes, calculating the control time and the corrected inclination value; calculating the velocity increment; calculating the inclination size and direction of the orbit after control; calculating the inclination size difference of the orbit after control , and calculate the target pointing difference of the controlled orbit ; Determine the difference in inclination angle Difference between the target and the If the inclination angle difference Greater than the first difference threshold , and the target points to the difference Greater than the second difference threshold , then optimize the control time and correct the inclination value. If the inclination difference Less than the first difference threshold , or target pointing difference Less than the second difference threshold , then the output control strategy is: control time, speed increment, front and rear control tracks.

[0128] In summary, the technical solution of the embodiment of the present invention is: when the GEO satellite inclination is about to exceed the maintenance requirement, the target inclination and the target inclination direction are used to calculate the control time selection and the initial value of the control amount, and the control time and the control amount are iteratively selected according to the direction and size of the orbital inclination after control, and finally the optimal north-south control strategy for the target is generated. On this basis, the embodiment of the present invention has at least the following characteristics: (a) By iterating the differential inclination vector, the control time and speed increment are quickly optimized, and the calculation efficiency and accuracy are higher. (b) It can realize the north-south control of the inclination direction of any target, with higher flexibility. (c) All core algorithms are autonomous and controllable, and can be used separately and integrated. (d) Cross-platform use, such as: Windows system, Ubuntu series system, CentOS series system, Kylin Linux operating system, etc. (v) The calculation efficiency and accuracy are higher.

[0129] Based on the above embodiments, the present invention provides a satellite north-south control strategy optimization device, see Figure 3 The schematic diagram of the structure of a satellite north-south control strategy optimization device shown in FIG. 1 mainly includes the following parts:

[0130] The data acquisition module 302 is used to identify the north and south exit times of the target satellite based on the current instantaneous root orbit, the inclination holding range and the predicted start and end times of the target satellite;

[0131] The strategy determination module 304 is used to calculate the differential inclination vector according to the instantaneous root of the true equatorial orbit system corresponding to the north and south exit times and the target inclination vector, and determine the control time, velocity increment and the post-control inclination vector corresponding to the velocity increment in the north-south control strategy according to the differential inclination vector;

[0132] The strategy optimization module 306 is used to update the target inclination vector based on the difference if the difference between the control tilt angle vector and the target inclination vector does not meet the preset conditions, so as to iteratively optimize the differential inclination vector, the control moment, the speed increment and the control tilt angle vector corresponding to the speed increment based on the updated target inclination vector until the preset conditions are met, thereby obtaining the target control moment and the target speed increment in the north-south control strategy.

[0133] The satellite north-south control strategy optimization device provided by the embodiment of the present invention, after identifying the north-south exit moment when the inclination of the target satellite is about to exceed the inclination holding range, uses the instantaneous root of the true equatorial orbit system at this moment and the target inclination vector to calculate the differential inclination vector, so as to select the control moment and the speed increment based on the differential inclination vector, and continue to iteratively optimize the control moment and the speed increment according to the post-control inclination vector and the target inclination vector, and finally generate the optimal north-south control strategy for the target satellite. The embodiment of the present invention effectively improves the problem of optimizing the north-south control strategy, including realizing the selection of the control moment based on any target inclination vector, optimizing the iterative step size of the speed increment, etc., thereby significantly improving the control effect of the north-south control strategy.

[0134] In one implementation, the data acquisition module 302 is specifically used to:

[0135] Preprocessing the current instantaneous root orbit of the target satellite to generate a true equatorial orbit system position velocity set and a true equatorial orbit system instantaneous root set;

[0136] Extract the true equatorial orbit inclination angle sequence within the preset start and end time range from the true equatorial orbit instant root set;

[0137] The true equatorial orbit inclination sequence is traversed, and when the true equatorial orbit inclination value in the true equatorial orbit inclination sequence exceeds the inclination holding range, the north and south exit-loop times of the target satellite and the true equatorial orbit instantaneous roots corresponding to the north and south exit-loop times are obtained.

[0138] In one implementation, the policy determination module 304 is specifically configured to:

[0139] Extract the inclination value of the loop point and the right ascension of the ascending node of the loop point from the instantaneous root of the true equatorial orbit system corresponding to the north and south loop exit times, and calculate the initial inclination vector based on the inclination value of the loop point and the right ascension of the ascending node of the loop exit time;

[0140] and, if the target inclination value and the target ascending node right ascension are configured, the target inclination vector is calculated based on the target inclination value and the target ascending node right ascension; if the target inclination value and the target ascending node right ascension are not configured, the target inclination value and the target ascending node right ascension are determined according to the loop-out point inclination value and the loop-out point ascending node right ascension, respectively, and the target inclination vector is calculated based on the target inclination value and the target ascending node right ascension;

[0141] Calculate the difference inclination vector between the initial inclination vector and the target inclination vector.

[0142] In one implementation, the policy determination module 304 is specifically configured to:

[0143] Determine the corrected inclination value and the right ascension of the ascending node of the initial control point according to the differential inclination vector;

[0144] The position velocity set of the date of the north and south exit time is extracted from the true equatorial orbit system position velocity set, and based on the position velocity set of the date and the thruster direction, the right ascension of the ascending node of the initial control point is optimized to obtain the right ascension of the ascending node of the target control point;

[0145] Extracting a first true equatorial orbit system position velocity subset before the north-south exit-loop moment and a second true equatorial orbit system position velocity subset after the north-south exit-loop moment from the true equatorial orbit system position velocity set, and determining the control moment in the north-south control strategy and the J2000 position velocity corresponding to the control moment based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset;

[0146] According to the corrected tilt angle value and the J2000 position speed corresponding to the control time, the speed increment in the north-south control strategy and the post-control tilt angle vector corresponding to the speed increment are determined.

[0147] In one implementation, the policy determination module 304 is specifically configured to:

[0148] Based on the position and velocity set of that date, the right ascension of the ascending node on the day of looping and the right ascension of the descending node on the day of exiting the loop are calculated;

[0149] Determine the first absolute value of the difference between the right ascension of the ascending node of the initial control point and the right ascension of the ascending node on the day of exiting the loop, and determine the second absolute value of the difference between the right ascension of the ascending node of the initial control point and the descending node on the day of exiting the loop;

[0150] Based on the thruster direction, a first comparison result between the first difference absolute value and the second difference absolute value, and a second comparison result between the right ascension of the ascending node on the day of exiting the loop and a preset threshold, determining whether to optimize the right ascension of the ascending node of the initial control point;

[0151] If yes, the sum of the ascending node right ascension of the initial control point and 180° is used as the optimized ascending node right ascension of the target control point.

[0152] In one implementation, the policy determination module 304 is specifically configured to:

[0153] When the thruster is facing south, if the first comparison result indicates that the control point is close to the ascending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is greater than the preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized;

[0154] Alternatively, when the thruster is facing south, if the first comparison result indicates that the control point is close to the descending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is less than the preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized;

[0155] Alternatively, when the thruster is facing north, if the first comparison result indicates that the control point is close to the descending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is greater than a preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized;

[0156] Alternatively, when the thruster is facing north, if the first comparison result indicates that the control point is close to the ascending node, and the second comparison result is that the right ascension of the ascending node on the day of leaving the loop is less than a preset threshold, it is determined that the right ascension of the ascending node of the initial control point is optimized.

[0157] In one embodiment, it is specifically used for:

[0158] Based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset, determining a first right ascension value and a second right ascension value located within a threshold interval corresponding to the right ascension of the ascending node of the target control point; wherein the time corresponding to the first right ascension value is less than the time corresponding to the second right ascension value, and the right ascension of the ascending node of the target control point is greater than the first right ascension value and less than the second right ascension value;

[0159] Generate a J2000 position velocity and a true equatorial orbit system position velocity set within a time period between a time corresponding to a first right ascension value and a time corresponding to a second right ascension value;

[0160] Based on the true equatorial orbit system position velocity set within the time period, determine a third right ascension value and a fourth right ascension value within a threshold interval corresponding to the right ascension of the ascending node of the target control point; wherein the time corresponding to the third right ascension value is less than the time corresponding to the fourth right ascension value, and the right ascension of the ascending node of the target control point is greater than the third right ascension value and less than the fourth right ascension value;

[0161] The time corresponding to the fourth right ascension value is taken as the control moment in the north-south control strategy, and the J2000 position velocity corresponding to the control moment is extracted from the J2000 position velocity within the time period.

[0162] In one embodiment, the policy optimization module 306 is further configured to:

[0163] If the difference between the controlled back tilt angle value in the controlled back tilt angle vector and the target tilt angle value in the target tilt angle vector is greater than the first difference threshold, or the difference between the right ascension of the controlled back ascending node in the controlled back tilt angle vector and the right ascension of the target ascending node in the target tilt angle vector is greater than the second difference threshold, it is determined that the preset condition is not met.

[0164] The device provided in the embodiment of the present invention has the same implementation principle and technical effects as those of the aforementioned method embodiment. For the sake of brief description, for matters not mentioned in the device embodiment, reference may be made to the corresponding contents in the aforementioned method embodiment.

[0165] An embodiment of the present invention provides an electronic device. Specifically, the electronic device includes a processor and a storage device. The storage device stores a computer program, and when the computer program is executed by the processor, it executes the method described in any one of the above-mentioned implementation methods.

[0166] Figure 4 A structural diagram of an electronic device provided in an embodiment of the present invention, the electronic device 100 includes: a processor 40, a memory 41, a bus 42 and a communication interface 43, wherein the processor 40, the communication interface 43 and the memory 41 are connected via the bus 42; the processor 40 is used to execute an executable module stored in the memory 41, such as a computer program.

[0167] The memory 41 may include a high-speed random access memory (RAM), and may also include a non-volatile memory, such as at least one disk memory. The communication connection between the system network element and at least one other network element is realized through at least one communication interface 43 (which may be wired or wireless), and the Internet, wide area network, local area network, metropolitan area network, etc. may be used.

[0168] The bus 42 may be an ISA bus, a PCI bus, or an EISA bus, etc. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 4 Only one bidirectional arrow is used in the diagram, but this does not mean that there is only one bus or only one type of bus.

[0169] Among them, the memory 41 is used to store programs, and the processor 40 executes the program after receiving the execution instruction. The method executed by the device for flow process definition disclosed in any embodiment of the above-mentioned embodiment of the present invention can be applied to the processor 40 or implemented by the processor 40.

[0170] The processor 40 may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method can be completed by the hardware integrated logic circuit or software instructions in the processor 40. The above processor 40 can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. The methods, steps and logic block diagrams disclosed in the embodiments of the present invention can be implemented or executed. The general-purpose processor can be a microprocessor or the processor can also be any conventional processor. The steps of the method disclosed in the embodiment of the present invention can be directly embodied as a hardware decoding processor to be executed, or the hardware and software modules in the decoding processor can be executed. The software module can be located in a mature storage medium in the field such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. The storage medium is located in the memory 41, and the processor 40 reads the information in the memory 41 and completes the steps of the above method in combination with its hardware.

[0171] The computer program product of the readable storage medium provided in the embodiment of the present invention includes a computer-readable storage medium storing program code, and the instructions included in the program code can be used to execute the methods described in the previous method embodiments. The specific implementation can be referred to the previous method embodiments, which will not be repeated here.

[0172] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium, including several instructions to enable a computer device (which can be a personal computer, server, or network device, etc.) to perform all or part of the steps of the methods described in various embodiments of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc., which can store program codes.

[0173] Finally, it should be noted that the above-described embodiments are only specific implementations of the present invention, which are used to illustrate the technical solutions of the present invention, rather than to limit them. The protection scope of the present invention is not limited thereto. Although the present invention is described in detail with reference to the above-described embodiments, ordinary technicians in the field should understand that any technician familiar with the technical field can still modify the technical solutions recorded in the above-described embodiments within the technical scope disclosed by the present invention, or can easily think of changes, or make equivalent replacements for some of the technical features therein; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A satellite north-south control strategy optimization method, characterized in that: include: Identify the north and south exit times of the target satellite based on the current instantaneous root orbit, the inclination holding range and the predicted start and end times of the target satellite; Calculate the differential inclination vector according to the instantaneous root of the true equatorial orbit system corresponding to the north-south exit time and the target inclination vector, and determine the control time, velocity increment and the post-control inclination vector corresponding to the velocity increment in the north-south control strategy according to the differential inclination vector; If the difference between the post-control tilt angle vector and the target tilt angle vector does not meet the preset condition, the target tilt angle vector is updated based on the difference, so as to iteratively optimize the differential tilt angle vector, the control moment, the speed increment, and the post-control tilt angle vector corresponding to the speed increment based on the updated target tilt angle vector until the preset condition is met, thereby obtaining the target control moment and the target speed increment in the north-south control strategy; Determining the control moment, velocity increment and the control back tilt angle vector corresponding to the velocity increment in the north-south control strategy according to the differential inclination vector, including: determining the corrected inclination value and the right ascension of the ascending node of the initial control point according to the differential inclination vector; extracting the position velocity set of the date to which the north-south exit-loop moment belongs from the true equatorial orbit system position velocity set, optimizing the right ascension of the ascending node of the initial control point based on the position velocity set and the thruster direction of the date, and obtaining the right ascension of the ascending node of the target control point; extracting the first true equatorial orbit system position velocity subset before the north-south exit-loop moment and the second true equatorial orbit system position velocity subset after the north-south exit-loop moment from the true equatorial orbit system position velocity set, and determining the control moment in the north-south control strategy and the J2000 position velocity corresponding to the control moment based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset; determining the velocity increment in the north-south control strategy and the control back tilt angle vector corresponding to the velocity increment according to the corrected inclination value and the J2000 position velocity corresponding to the control moment; Based on the position velocity set and thruster direction of the date, the right ascension of the ascending node of the initial control point is optimized to obtain the right ascension of the ascending node of the target control point, including: calculating the right ascension of the ascending node on the loop day and the right ascension of the descending node on the loop exit day based on the position velocity set of the date; determining a first difference absolute value between the right ascension of the ascending node of the initial control point and the right ascension of the ascending node on the loop exit day, and determining a second difference absolute value between the right ascension of the ascending node of the initial control point and the right ascension of the descending node on the loop exit day; based on a first comparison result between the thruster direction, the first difference absolute value and the second difference absolute value, and a second comparison result between the right ascension of the ascending node on the loop exit day and a preset threshold, judging whether to optimize the right ascension of the ascending node of the initial control point; if yes, taking the sum of the right ascension of the ascending node of the initial control point and 180° as the optimized right ascension of the ascending node of the target control point; Based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset, determining the control moment in the north-south control strategy and the J2000 position velocity corresponding to the control moment, including: based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset, determining a first right ascension value and a second right ascension value within a threshold interval corresponding to the right ascension of the ascending node of the target control point; wherein the time corresponding to the first right ascension value is less than the time corresponding to the second right ascension value, and the right ascension of the ascending node of the target control point is greater than the first right ascension value and less than the second right ascension value; generating the time corresponding to the first right ascension value and the a set of J2000 position velocity and true equatorial orbit system position velocity in a time period between the times corresponding to the second right ascension value; based on the set of true equatorial orbit system position velocity in the time period, determining a third right ascension value and a fourth right ascension value within a threshold interval corresponding to the right ascension of the ascending node of the target control point; wherein the time corresponding to the third right ascension value is less than the time corresponding to the fourth right ascension value, and the right ascension of the ascending node of the target control point is greater than the third right ascension value and less than the fourth right ascension value; taking the time corresponding to the fourth right ascension value as the control moment in the north-south control strategy, and extracting the J2000 position velocity corresponding to the control moment from the J2000 position velocity in the time period.

2. The satellite north-south control strategy optimization method according to claim 1, characterized in that: The north and south exit times of the target satellite are identified based on the current instantaneous root orbit, the inclination holding range and the predicted start and end times of the target satellite, including: Preprocessing the current instantaneous root orbit of the target satellite to generate a true equatorial orbit system position velocity set and a true equatorial orbit system instantaneous root set; Extracting a true equatorial orbit system inclination sequence within a preset start and end time range from the true equatorial orbit system instant root set; The true equatorial orbit inclination sequence is traversed, and when the true equatorial orbit inclination value in the true equatorial orbit inclination sequence exceeds the inclination retention range, the north and south exit-of-the-loop times of the target satellite and the true equatorial orbit instantaneous roots corresponding to the north and south exit-of-the-loop times are obtained.

3. The satellite north-south control strategy optimization method according to claim 1, characterized in that: The differential inclination vector is calculated according to the instantaneous root of the true equatorial orbit system corresponding to the north and south exit times and the target inclination vector, including: Extracting the inclination value of the loop point and the right ascension of the ascending node of the loop point from the instantaneous root of the true equatorial orbit system corresponding to the north and south loop exit times, so as to calculate the initial inclination vector based on the inclination value of the loop exit point and the right ascension of the ascending node of the loop exit point; And, if the target inclination value and the target right ascension of the ascending node are configured, the target inclination vector is calculated based on the target inclination value and the target right ascension of the ascending node; if the target inclination value and the target right ascension of the ascending node are not configured, the target inclination value and the target right ascension of the ascending node are determined according to the inclination value of the exit point and the right ascension of the ascending node of the exit point, respectively, and the target inclination vector is calculated based on the target inclination value and the target right ascension of the ascending node; A differential inclination vector between the initial inclination vector and the target inclination vector is calculated.

4. The satellite north-south control strategy optimization method according to claim 1 is characterized in that: Based on a first comparison result between a thruster direction, the first difference absolute value and the second difference absolute value, and a second comparison result between the right ascension of the ascending node on the day of exiting the loop and a preset threshold, determining whether to optimize the right ascension of the ascending node of the initial control point includes: When the thruster is facing south, if the first comparison result indicates that the control point is close to the ascending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is greater than a preset threshold, then it is determined to optimize the right ascension of the ascending node of the initial control point; Alternatively, when the thruster is facing south, if the first comparison result indicates that the control point is close to the descending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is less than a preset threshold, it is determined to optimize the right ascension of the ascending node of the initial control point; Alternatively, when the thruster is facing north, if the first comparison result indicates that the control point is close to the descending node, and the second comparison result indicates that the right ascension of the ascending node on the day of exiting the loop is greater than a preset threshold, it is determined to optimize the right ascension of the ascending node of the initial control point; Alternatively, when the thruster is facing north, if the first comparison result indicates that the control point is close to the ascending node, and the second comparison result is that the right ascension of the ascending node on the day of leaving the loop is less than a preset threshold, it is determined to optimize the right ascension of the ascending node of the initial control point.

5. The satellite north-south control strategy optimization method according to claim 1, characterized in that: If the difference between the post-control tilt angle vector and the target tilt angle vector does not meet a preset condition, the method further includes: If the difference between the controlled back tilt angle value in the controlled back tilt angle vector and the target tilt angle value in the target tilt angle vector is greater than a first difference threshold, or the difference between the right ascension of the controlled back ascending node in the controlled back tilt angle vector and the right ascension of the target ascending node in the target tilt angle vector is greater than a second difference threshold, it is determined that the preset condition is not met.

6. A satellite north-south control strategy optimization device, characterized in that: include: A data acquisition module, used to identify the north and south exit times of the target satellite based on the current instantaneous root orbit, the inclination holding range and the predicted start and end times of the target satellite; A strategy determination module, used to calculate a differential inclination vector according to the instantaneous root of the true equatorial orbit system corresponding to the north and south exit moments and the target inclination vector, and determine the control moment, speed increment and the post-control inclination vector corresponding to the speed increment in the north-south control strategy according to the differential inclination vector; a strategy optimization module, configured to update the target tilt angle vector based on the difference if the difference between the control rear tilt angle vector and the target tilt angle vector does not meet a preset condition, so as to iteratively optimize the differential tilt angle vector, the control moment, the speed increment, and the control rear tilt angle vector corresponding to the speed increment based on the updated target tilt angle vector until the preset condition is met, thereby obtaining a target control moment and a target speed increment in the north-south control strategy; The strategy determination module is specifically used for: determining the corrected inclination value and the right ascension of the ascending node of the initial control point according to the differential inclination vector; extracting the position velocity set of the date to which the north and south exit-loop moments belong from the true equatorial orbit system position velocity set, optimizing the right ascension of the ascending node of the initial control point based on the position velocity set and the thruster direction of the date, and obtaining the right ascension of the ascending node of the target control point; extracting the first true equatorial orbit system position velocity subset before the north and south exit-loop moments and the second true equatorial orbit system position velocity subset after the north and south exit-loop moments from the true equatorial orbit system position velocity set, and determining the control moment in the north-south control strategy and the J2000 position velocity corresponding to the control moment based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset; determining the velocity increment in the north-south control strategy and the post-control inclination angle vector corresponding to the velocity increment according to the corrected inclination value and the J2000 position velocity corresponding to the control moment; The strategy determination module is further specifically used for: calculating the right ascension of the ascending node on the loop day and the right ascension of the descending node on the loop exit day based on the position velocity set of the date; determining a first difference absolute value between the right ascension of the ascending node of the initial control point and the right ascension of the ascending node on the loop exit day, and determining a second difference absolute value between the right ascension of the ascending node of the initial control point and the right ascension of the descending node on the loop exit day; judging whether to optimize the right ascension of the ascending node of the initial control point based on a first comparison result between the thruster direction, the first difference absolute value and the second difference absolute value, and a second comparison result between the right ascension of the ascending node on the loop exit day and a preset threshold; if yes, taking the sum of the right ascension of the ascending node of the initial control point and 180° as the optimized right ascension of the ascending node of the target control point; The strategy determination module is further specifically used for: determining a first right ascension value and a second right ascension value within a threshold interval corresponding to the right ascension of the ascending node of the target control point based on the first true equatorial orbit system position velocity subset or the second true equatorial orbit system position velocity subset; wherein the time corresponding to the first right ascension value is less than the time corresponding to the second right ascension value, and the right ascension of the ascending node of the target control point is greater than the first right ascension value and less than the second right ascension value; generating a J2000 position velocity and a true equatorial orbit system position velocity set within a time period between the time corresponding to the first right ascension value and the time corresponding to the second right ascension value; determining a third right ascension value and a fourth right ascension value within a threshold interval corresponding to the right ascension of the ascending node of the target control point based on the true equatorial orbit system position velocity set within the time period; wherein the time corresponding to the third right ascension value is less than the time corresponding to the fourth right ascension value, and the right ascension of the ascending node of the target control point is greater than the third right ascension value and less than the fourth right ascension value; using the time corresponding to the fourth right ascension value as the control moment in the north-south control strategy, and extracting the J2000 position velocity corresponding to the control moment from the J2000 position velocity within the time period.

7. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores computer executable instructions that can be executed by the processor, and the processor executes the computer executable instructions to implement the method according to any one of claims 1 to 5.

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