Regenerative coplanar trajectory constellation maintenance method and apparatus applying tangential thrust

Abstract

The application provides a method and device for maintaining a retrograde co-ground track constellation by applying tangential thrust, and relates to the technical field of constellation orbit dynamics and control. The method comprises the following steps: determining a first tangential thrust required by a first satellite in a predetermined constellation according to a correction value of a subsatellite point longitude drift of the first satellite, and applying the first tangential thrust to the first satellite, wherein the first tangential thrust is used for maintaining a retrograde co-ground track of the first satellite; and applying a second tangential thrust corresponding to a second satellite in the constellation to the second satellite to maintain a relative phase between the second satellite and the first satellite. The method provided by the embodiment of the application only needs to apply a tangential thrust to a satellite, does not need to apply an orbit normal thrust to the satellite, and can maintain a subsatellite point track of a retrograde co-ground track constellation in the constellation.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite communication, in particular to the technical field of constellation orbit dynamics and control, and specifically to a method and device for maintaining a regression co-ground track constellation by applying tangential thrust. BACKGROUND

[0002] For the problem of maintaining a regression orbit of a satellite and a constellation, existing research methods are all for a single satellite scenario, rather than for a co-ground track constellation scenario. The influence of the J2 perturbation on a regression orbit satellite is manifested as long-period terms, including the orbital semi-major axis and the orbital inclination; in addition, low-orbit atmospheric drag also causes the orbital semi-major axis to continuously decrease, and the subsatellite point track is a function of the orbital semi-major axis and the orbital inclination, thereby manifesting as the subsatellite point track deviating from the nominal value. SUMMARY

[0003] To solve the problems in the prior art, the embodiments of the present application provide a method and device for maintaining a regression co-ground track constellation by applying tangential thrust, which can at least partially solve the problems in the prior art.

[0004] In one aspect, the present application provides a method for maintaining a regression co-ground track constellation by applying tangential thrust, which is applied to any satellite in a constellation, and includes:

[0005] determining a first tangential thrust required by a first satellite in the constellation according to a predetermined correction value of a subsatellite point longitude drift of the first satellite, and applying the first tangential thrust to the first satellite, the first tangential thrust being used to maintain a regression co-ground track of the first satellite;

[0006] applying a second tangential thrust corresponding to a second satellite in the constellation to the second satellite to maintain a relative phase between the second satellite and the first satellite, thereby achieving subsatellite point track maintenance of the entire constellation.

[0007] In some embodiments of the present application, the determination of the first tangential thrust required by the first satellite according to the predetermined correction value of the subsatellite point longitude drift of the first satellite includes:

[0008] generating a mapping between a semi-major axis deviation of the first satellite and the subsatellite point longitude drift;

[0009] determining an adjustment value of the semi-major axis deviation of the first satellite according to the mapping and the correction value;

[0010] determining the first tangential thrust according to the adjustment value.

[0011] In some embodiments of the present application, the generating of the mapping between the semi-major axis deviation of the first satellite and the drift of the sub-satellite point longitude comprises:

[0012] determining a longitude difference of the intersection of the first satellite with the equatorial plane in an orbit period;

[0013] determining a variation of the sub-satellite point longitude difference caused by the semi-major axis deviation in the orbit period according to the longitude difference;

[0014] generating the mapping according to the variation and the semi-major axis deviation.

[0015] In some embodiments of the present application, if the adjustment value of the semi-major axis deviation is greater than 0, the first tangential thrust direction is positive tangential;

[0016] if the adjustment value of the semi-major axis deviation is less than 0, the first tangential thrust direction is negative tangential.

[0017] In some embodiments of the present application, a regression co-ground track constellation maintaining method of applying a tangential thrust further comprises:

[0018] determining a time of applying the first tangential thrust to the first satellite according to the mass of the first satellite, the orbit angular velocity of the first satellite, and the amplitude of the first tangential thrust.

[0019] In some embodiments of the present application, the determining of the second tangential thrust comprises:

[0020] determining the second tangential thrust according to the regression number of the second satellite, the regression days of the second satellite, the ascending node right ascension difference between the second satellite and the first satellite, and the mean anomaly difference between the second satellite and the first satellite.

[0021] In some embodiments of the present application, the first tangential thrust is used to adjust the semi-major axis of the first satellite;

[0022] the second tangential thrust is used to adjust the semi-major axis of the second satellite.

[0023] In another aspect, the present application further provides a regression co-ground track constellation maintaining device of applying a tangential thrust, which is applied to all satellites in a constellation, comprising:

[0024] a first tangential thrust determining module, configured to determine a first tangential thrust required by a first satellite in a predetermined constellation according to a correction value of the drift of the sub-satellite point longitude of the first satellite, and apply the first tangential thrust to the first satellite, the first tangential thrust being used to maintain the regression co-ground track of the first satellite;

[0025] A phase maintaining module is configured to apply a second tangential thrust corresponding to a second satellite in the constellation other than the first satellite to maintain a relative phase between the second satellite and the first satellite.

[0026] In still another aspect, an embodiment of the present application provides an electronic device, comprising: a processor, a memory and a bus, wherein:

[0027] The processor and the memory communicate with each other through the bus;

[0028] The memory stores program instructions executable by the processor, and the processor invoking the program instructions can execute the following method:

[0029] determining a first tangential thrust required by a first satellite in a predetermined constellation according to a correction value of a sub-satellite point longitude drift of the first satellite, and applying the first tangential thrust to the first satellite, the first tangential thrust being used to maintain a retrograde co-ground track of the first satellite;

[0030] applying a second tangential thrust corresponding to a second satellite in the constellation other than the first satellite to maintain a relative phase between the second satellite and the first satellite.

[0031] An embodiment of the present application provides a non-transitory computer readable storage medium, comprising:

[0032] The non-transitory computer readable storage medium stores computer instructions, and the computer instructions cause the computer to execute the following method:

[0033] determining a first tangential thrust required by a first satellite in a predetermined constellation according to a correction value of a sub-satellite point longitude drift of the first satellite, and applying the first tangential thrust to the first satellite, the first tangential thrust being used to maintain a retrograde co-ground track of the first satellite;

[0034] applying a second tangential thrust corresponding to a second satellite in the constellation other than the first satellite to maintain a relative phase between the second satellite and the first satellite.

[0035] An embodiment of the present application further provides a computer program product, the computer program product comprising a computer program, and the computer program is executed by a processor to implement the following method:

[0036] determining a first tangential thrust required by a first satellite in a predetermined constellation according to a correction value of a sub-satellite point longitude drift of the first satellite, and applying the first tangential thrust to the first satellite, the first tangential thrust being used to maintain a retrograde co-ground track of the first satellite;

[0037] A second tangential thrust corresponding to a second satellite in the constellation other than the first satellite is applied to the second satellite to maintain the relative phase between the second satellite and the first satellite.

[0038] In summary, the method and device for maintaining a retrograde co-ground track constellation by applying a tangential thrust provided by the embodiments of the present application first determine the first tangential thrust required by the first satellite according to the correction value of the sub-satellite point longitude drift of the first satellite in the predetermined constellation, and apply the first tangential thrust to the first satellite, the first tangential thrust being used to maintain the retrograde co-ground track of the first satellite; then, a second tangential thrust corresponding to a second satellite in the constellation other than the first satellite is applied to the second satellite to maintain the relative phase between the second satellite and the first satellite.

[0039] The method for maintaining a retrograde co-ground track constellation by applying a tangential thrust provided by the embodiments of the present application only needs to apply a tangential thrust to the satellites in the constellation, and does not need to apply an orbit normal thrust to the satellites, so that the sub-satellite point track of the satellites in the retrograde co-ground track constellation can be maintained. BRIEF DESCRIPTION OF DRAWINGS

[0040] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description only represent some embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort. In the drawings:

[0041] Figure 1 is a flowchart of the method for maintaining a retrograde co-ground track constellation by applying a tangential thrust provided by an embodiment of the present application.

[0042] Figure 2 is a flowchart of step 100 provided by an embodiment of the present application.

[0043] Figure 3 is a flowchart of step 101 provided by an embodiment of the present application.

[0044] Figure 4 is a second flowchart of the method for maintaining a retrograde co-ground track constellation by applying a tangential thrust provided by an embodiment of the present application.

[0045] Figure 5 is a third flowchart of the method for maintaining a retrograde co-ground track constellation by applying a tangential thrust provided by an embodiment of the present application.

[0046] Figure 6 is a flowchart of step 400 provided by an embodiment of the present application.

[0047] Figure 7 This is a flow chart of a method for maintaining a regressive common ground track constellation by applying tangential thrust provided in a specific application example of the present invention.

[0048] Figure 8 This is a schematic diagram of the sub-satellite point trajectory of the combination of satellites A and B provided in a specific application example of the present invention (sub-satellite point trajectory 2D).

[0049] Figure 9 This is a schematic diagram of the time history of the phase angle difference between star B and star A provided in a specific application example of the present invention.

[0050] Figure 10 This is a schematic diagram of the time history of the longitude of the ascending node of star A and star B provided in a specific application example of the present invention.

[0051] Figure 11 The figure is a schematic structural diagram of a device for maintaining a regressive common ground track constellation provided by one embodiment of the present invention.

[0052] Figure 12 2 is a schematic structural diagram of a first tangential thrust determination module 10 provided in one embodiment of the present invention.

[0053] Figure 13 FIG. 1 is a schematic structural diagram of a mapping generation unit 10a provided in one embodiment of the present invention.

[0054] Figure 14 This is a schematic diagram of a second structure of a device for maintaining a regressive common ground track constellation provided by an embodiment of the present invention.

[0055] Figure 15 A schematic diagram of the physical structure of an electronic device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0056] In order to enable those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the embodiments described are only 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 making creative efforts should fall within the scope of protection of the present invention.

[0057] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and in the above drawings are used to distinguish similar objects, and do not necessarily have to be used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances, so that the embodiments of the application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion, for example, a process, method, device, product or equipment including a series of steps or units does not have to be limited to those steps or units clearly listed, but can include other steps or units not clearly listed or inherent to these processes, methods, products or equipment.

[0058] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0059] The regression orbit is a special orbit in which the subspace point trajectory repeats periodically. The subspace point of the regression orbit has the characteristic that the ground track appears repeatedly after a regression period (which is an integer day), thereby meeting the task requirement of periodic observation, helping to improve the consistency before and after imaging, and having important application in the field of Synthetic Aperture Radar (SRA) and other fields.

[0060] Correspondingly, a plurality of regression orbit satellites are arranged at a certain phase interval to cover the same ground track, thereby forming a regression common ground track constellation.

[0061] In the field of remote sensing, the common ground track constellation can shorten the observation interval of the ground target. In the field of communication, the pointing of the ground communication terminal to the satellite during the process of the passage of all satellites of the common ground track constellation changes over time, and the process is basically unchanged, so that the deployment mode of the common ground track can simplify the access and connectivity strategy of the ground terminal, and has potential value in the communication constellation.

[0062] The regression orbit repeatedly passes through the gravity field with the same longitude, and the orbit resonance effect occurs between the satellite motion and the earth's gravity with the order of multiple of the regression number of circles, which mainly manifests that the influence of the corresponding harmonic term on the satellite orbit is no longer a general short-period influence with small amplitude, but a long-period influence, which causes the subspace point trajectory of the satellite to deviate from the nominal orbit, and affects the implementation effect of the task.

[0063] It can be understood that the constellation deployed by the common ground track can realize uniform coverage when the time difference of the passage of adjacent satellites is the same, therefore, the regression common ground track constellation has dual requirements of trajectory maintenance and phase maintenance, but there is no related method about the trajectory maintenance and phase maintenance of the regression common ground track constellation in the prior art.

[0064] The perturbation of the zonal term causes the periodic oscillation of the semi-major axis and the inclination of the orbit of the satellite in the regression orbit, and the atmospheric resistance in the low orbit also causes the continuous reduction of the semi-major axis. The semi-major axis can be controlled by adjusting the semi-major axis and the inclination of the orbit, so as to maintain the sub-satellite point trajectory and the phase difference between the satellites near the nominal value. The control of the semi-major axis needs to apply the tangential thrust, and the control of the inclination of the orbit needs to apply the normal thrust of the orbit. If only one thruster is configured for the satellite, the satellite attitude needs to be adjusted during the application of the tangential thrust and the normal thrust, so as to affect the implementation effect of the satellite on-orbit task; and if two thrusters are configured for the satellite, the normal thrusts of the two thrusters are respectively the tangential thrust and the normal thrust of the orbit, so as to increase the cost of the satellite platform.

[0065] In order to solve the above technical problems, referring to Figure 1 , (a flowchart of a method for maintaining a regression co-ground track constellation by applying a tangential thrust according to an embodiment of the present application), the method for maintaining a regression co-ground track constellation by applying a tangential thrust according to the embodiment of the present application (the method is applied to any satellite in the constellation) comprises the following steps.

[0066] Step 100: determining a first tangential thrust required by a first satellite in the constellation according to a correction value of the drift of the sub-satellite point longitude of the first satellite in the constellation, and applying the first tangential thrust to the first satellite, the first tangential thrust being used for maintaining the regression co-ground track of the first satellite.

[0067] Step 200: applying a second tangential thrust corresponding to a second satellite in the constellation to the second satellite, so as to maintain the relative phase between the second satellite and the first satellite.

[0068] In summary, the method for maintaining a regression co-ground track constellation by applying a tangential thrust according to the embodiment of the present application first determines a first tangential thrust required by a first satellite in the constellation according to a correction value of the drift of the sub-satellite point longitude of the first satellite in the constellation, and applies the first tangential thrust to the first satellite, the first tangential thrust being used for maintaining the regression co-ground track of the first satellite; then, a second tangential thrust corresponding to a second satellite in the constellation is applied to the second satellite, so as to maintain the relative phase between the second satellite and the first satellite.

[0069] It can be seen that, first, the method provided by the embodiment of the present application only implements tangential thrust on the first satellite (equivalent to a reference satellite in the constellation), so as to maintain the retrograde co-ground track of the reference satellite, and second, the present application only implements tangential thrust (which can be different from the tangential thrust applied to the reference satellite, and the tangential thrust corresponding to each second satellite can also be different) on the second satellite (other satellites in addition to the reference satellite), so as to maintain the relative phase of the other satellites and the reference satellite, indirectly maintain the subsatellite point track of the other satellites, and thereby maintain the subsatellite point track of the entire constellation.

[0070] In some embodiments of the present application, for the above step 100, the applicant finds that by periodically applying a predetermined tangential thrust to a preselected first satellite (reference satellite, optionally a satellite in the constellation) in the constellation, the semi-major axis deviation of the reference satellite can be adjusted, and the longitude drift rate of the reference satellite can be ultimately controlled, so as to maintain the subsatellite point track of the reference satellite near the nominal value.

[0071] It can be understood that the above-mentioned reference satellite (first satellite) is used as a reference to adjust the orbital parameters (preferably the semi-major axis) of the other satellites in addition to the reference satellite.

[0072] In some embodiments of the present application, for step 200, by applying a corresponding second tangential thrust to the other satellites (all satellites in addition to the reference satellite), the relative phase between the other satellites and the reference satellite can be maintained, and the subsatellite point track of the other satellites can be indirectly maintained, so as to achieve the maintenance of the subsatellite point track and the phase of the entire constellation.

[0073] In some embodiments of the present application, referring to Figure 2 , step 100 comprises:

[0074] Step 101: generating a mapping between the semi-major axis deviation of the first satellite and the subsatellite longitude drift;

[0075] In some embodiments of the present application, referring to Figure 3 , step 101 comprises:

[0076] Step 1011: determining the longitude difference of the first satellite passing through the intersection of the equatorial plane in an orbital period;

[0077] Specifically, in one orbital period , the longitude difference of the first satellite passing through the intersection of the equatorial plane twice is:

[0078]

[0079] wherein, is the orbital period of the first satellite, is the right ascension change rate of the ascending node of the first satellite, is an orbit semi-major axis of the first satellite, is an orbit inclination of the first satellite, is an orbit angular velocity of the first satellite, is an average equatorial radius of the earth, is an earth rotation angular velocity.

[0080] Step 1012: determining a variation of a sub-satellite point longitude difference caused by the semi-major axis deviation in the orbit period according to the longitude difference;

[0081] According to formula (1), in an orbit period, the longitude difference variation of the first satellite caused by the semi-major axis deviation of the first satellite is:

[0082]

[0083] Step 1013: generating the mapping according to the variation and the semi-major axis deviation.

[0084] According to formula (1) and formula (2), the mapping (relationship) between the longitude drift rate of the first satellite and the semi-major axis deviation is:

[0085]

[0086] Step 102: determining an adjustment value of the semi-major axis deviation of the first satellite according to the mapping and the correction value of the longitude drift;

[0087] Specifically, according to the mapping between the semi-major axis deviation and the longitude drift, the adjustment value of the semi-major axis deviation corresponding to the correction value of the longitude drift is found.

[0088] Step 103: determining the first tangential thrust according to the adjustment value.

[0089] Specifically, formula (3) shows that the angular longitude drift rate can be controlled by adjusting the semi-major axis deviation of the first satellite. Thus, the sub-satellite point intersection longitude (i.e. the sub-satellite point track) of the first satellite can be adjusted by only applying a tangential thrust to the first satellite.

[0090] In some embodiments of the present application, if the adjustment value of the semi-major axis deviation is greater than 0, the tangential thrust direction is positive tangential; if the adjustment value of the semi-major axis deviation is less than 0, the tangential thrust direction is negative tangential.

[0091] Specifically, when ​​If the adjustment value of the semi-major axis deviation is greater than 0, the first thrust direction applied to the first satellite is positive tangential; otherwise, the first thrust direction applied to the first satellite is negative tangential.

[0092] It can be understood that, due to the atmospheric drag causing the orbital height of the first satellite to decay, the adjustment value of the semi-major axis deviation is generally greater than 0, so that only a positive tangential thrust needs to be applied to the first satellite.

[0093] In some embodiments of the present application, referring to Figure 4 A method for maintaining a retrograde co-ground track constellation by applying a tangential thrust, further comprises:

[0094] Step 300: determining a time for applying the first tangential thrust to the first satellite according to the mass of the first satellite, the orbital angular velocity of the first satellite, and the amplitude of the first tangential thrust.

[0095] Specifically, the time for applying the first tangential thrust to the first satellite in step 200 can be calculated according to formula (4):

[0096]

[0097] Wherein, is the time for applying the first tangential thrust to the first satellite, is the mass of the first satellite, is the amplitude of the first tangential thrust, is the orbital angular velocity of the first satellite.

[0098] After the direction of the first tangential thrust is known (if the adjustment value of the semi-major axis deviation is greater than 0, the direction of the first tangential thrust is positive tangential; if the adjustment value of the semi-major axis deviation is less than 0, the direction of the first tangential thrust is negative tangential), by accurately controlling the time for applying the first tangential thrust, a better maintenance effect of the sub-satellite track of the first satellite in the retrograde co-ground track constellation can be obtained, and the satellite fuel and the management cost of the satellite platform can be saved.

[0099] In some embodiments of the present application, the step of determining the second tangential thrust comprises:

[0100] The second tangential thrust is determined according to the number of revolutions, the number of days of revolution, the difference in right ascension of the ascending node, and the difference in mean anomaly between the second satellite and the first satellite.

[0101] It can be understood that, a cluster of retrograde orbit satellites deployed in a sub-satellite track can repeatedly pass through a specific area. In order to make the ground tracks of multiple satellites using a retrograde orbit the same, the difference in right ascension of the ascending node and the difference in mean anomaly between the other satellites (all second satellites) and the first satellite need to satisfy the following relationship:

[0102]

[0103] wherein, is the regression number of circles, is the regression number of days.

[0104] Since the rate of change of the right ascension of the ascending node and the argument of the perigee of a satellite with time mainly depends on the semi-major axis, the eccentricity and the inclination of the orbit of the satellite. For a near-circular orbit, the eccentricity is close to 0, so the rate of change of the right ascension of the ascending node and the argument of the perigee of the satellite with time mainly depends on the semi-major axis, so the second satellite can have the same ground track as the first satellite only by adjusting the semi-major axis of the second satellite.

[0105] At the initial moment, by adjusting the semi-major axis of the current satellite (optionally one of all the second satellites) (the adjustment amount is determined by the regression number of circles, the regression number of days, the right ascension difference of the ascending node and the argument of the perigee difference between the current satellite and the first satellite), the right ascension difference of the ascending node and the argument of the perigee between the current satellite and the first satellite satisfy formula (5), so that at the initial moment, the current satellite and the first satellite have the same ground track.

[0106] Then, the relative phase of the current satellite to the first satellite is maintained, so that the phase difference between the current satellite and the first satellite is close to constant, so that the semi-major axis of the current satellite and the first satellite is consistent. Since neither the current satellite nor the first satellite performs orbit inclination maintenance or adjustment, the orbit inclination numbers of the two satellites (the current satellite and the first satellite) are consistent, so that the orbit inclinations are basically the same.

[0107] In summary, by maintaining the relative phase of the current satellite to the first satellite, the semi-major axis and the orbit inclination of the current satellite and the first satellite are respectively the same, so that the subsatellite track of the current satellite is indirectly maintained. Other satellites refer to the maintenance strategy of the current satellite, so that the subsatellite track and phase maintenance of the entire constellation can be realized.

[0108] In some embodiments of the present application, referring to Figure 5 , a regression same-ground-track constellation maintenance method for applying tangential thrust further comprises:

[0109] Step 400: determining the correction value of the longitude drift.

[0110] Then, referring to Figure 6 , step 400 comprises:

[0111] Step 401: determining the initial value and the final value of the longitude of the ascending node of the first satellite in the preset historical period;

[0112] Step 402: determining the longitude drift value of the first satellite in the history period according to the longitude initial value and the longitude final value;

[0113] Step 403: determining the correction value of the longitude drift according to the predetermined longitude drift target value and the longitude drift value in the history period.

[0114] In steps 401 to 403, during the on-orbit operation of the satellite, the satellite is affected by orbit perturbations such as the earth non-spherical perturbation, atmospheric drag, third body gravitational perturbation of the sun and the moon, and solar radiation pressure perturbation, especially the atmospheric drag, which causes the orbit altitude of the satellite to continuously decay, affecting the realization of the on-orbit working task of the satellite. In the case of not considering the maintenance of the subsatellite point trajectory, it is still necessary to apply a thrust to realize the orbit altitude maintenance. However, only maintaining the orbit altitude at a constant value, due to the influence of the earth harmonic term perturbation, the subsatellite point trajectory will deviate from the nominal value. Therefore, the embodiment of step 400 is provided to realize the maintenance of the subsatellite point trajectory near the nominal value by periodically adjusting the nominal value of the semi-major axis of the satellite.

[0115] The specific strategy is as follows: taking N days (preferably 10 days) as the adjustment period of the nominal value of the semi-major axis, calculating the actual value of the ascending node longitude drift rate in N days according to the initial value and the final value of the ascending node longitude in N days; and obtaining the target value of the ascending node longitude drift (the target value of the ascending node longitude drift rate) according to the target value and the actual value of the ascending node longitude drift at the end of N days, and considering the ascending node longitude adjustment required to be completed in the next N days; obtaining the target value of the ascending node longitude drift rate change (the correction value of the longitude drift) by offsetting the target value and the actual value of the ascending node longitude drift rate; and then calculating the target value of the semi-major axis change.

[0116] In some embodiments of the present application, the first tangential thrust is used to adjust the semi-major axis of the first satellite; and the second tangential thrust is used to adjust the semi-major axis of the second satellite.

[0117] As can be seen from the above description, the method provided by the present application only needs to adjust the semi-major axis of the first satellite, so as to maintain the retrograde co-ground track of the first satellite. Similarly, only adjusting the semi-major axis of the other satellites can maintain the relative phase of the other satellites and the first satellite, and indirectly maintain the subsatellite point trajectory of the other satellites, so as to maintain the subsatellite point trajectory of the entire constellation.

[0118] In summary, the method for maintaining the retrograde co-ground track constellation provided by the embodiments of the present application only needs to apply a tangential thrust to the satellite, and can simultaneously realize the ground trajectory maintenance and relative phase maintenance of the retrograde co-ground track constellation of the constellation.

[0119] Specifically, the method provided by the embodiment of the present application does not need to apply an orbit normal thrust to the satellite, the satellite does not need to be configured with a normal thruster, and no normal thrust fuel consumption is needed, thereby reducing the direct cost of the satellite platform and the fuel consumption cost.

[0120] To further illustrate the present solution, the present application further provides a specific application example of the method for maintaining a retrograde co-ground track constellation by applying a tangential thrust, which is described in detail in Figure 7 , and specifically includes the following contents.

[0121] S1: determining the relationship between the semi-major axis deviation and the longitude drift rate of a reference satellite.

[0122] The specific implementation is described in the formula (1) to formula (3) and the related description.

[0123] S2: maintaining the retrograde co-ground track of the reference satellite by applying a first tangential thrust to the reference satellite for a preset time.

[0124] The preset time of step S2 is calculated in the formula (4) and the related description.

[0125] S3: determining and adjusting the target orbit parameters of other satellites (all satellites except the reference satellite).

[0126] Specifically, the corresponding other satellite ground track is maintained by applying a second tangential thrust to the other satellite, and the other satellite ground track is indirectly maintained by keeping the relative phase of the other satellite with the reference satellite, thereby achieving the ground track and phase maintenance of the entire constellation. The specific implementation is described in the formula (5) and the related description.

[0127] Technical effect: here, the orbit with an orbit height of 500.77 km, an orbit inclination of 55.1°, a retrograde number of 15, and a retrograde day of 1 day is selected as the nominal orbit. The satellite orbit has 15 ascending nodes, and the simulation analysis selects the ascending node longitude of a certain orbit of the reference satellite as 86.8°. The simulation includes two satellites, A and B. The effectiveness of the control strategy is verified through the simulation of the two satellites. A is the reference satellite, and B has the same ground track as A. The phase angle difference between B and A is -15°. The total simulation time is selected as 50 days.

[0128] The results of the subsatellite point trajectory of Astar (reference satellite) in the scenario of 50 days of simulation time show that the subsatellite point trajectory of Astar keeps good effect and the subsatellite point trajectory does not drift. The results of the subsatellite point trajectory of Bstar (other star) in the scenario of 50 days of simulation time also show that the subsatellite point trajectory of Bstar keeps good effect and the subsatellite point trajectory does not drift. The results of the subsatellite point trajectory of Astar and Bstar combination show that the subsatellite point trajectories of the two satellites coincide and the subsatellite point trajectories of the two satellites cannot be distinguished. Further observation Figure 8 , in the figure, the blue dot is the subsatellite point trajectory of Astar, the red dot is the subsatellite point trajectory of Bstar, and the figure shows that the subsatellite point trajectories of Astar and Bstar coincide.

[0129] Figure 9 is the phase angle difference time history of Bstar and Astar, and the results show that the phase angle difference of the two satellites is basically near-15°, the change range is-15.04° to-14.95°, and the maximum deviation is not more than 0.05°. Figure 10 is the time history of the ascending node longitude of the two satellites, and the ascending node longitudes of the two satellites are both near the nominal value (86.8°), the change range is 86.794 to 86.812°, and the maximum deviation is not more than 0.05°.

[0130] In summary, the constellation maintenance method of the regressive co-ground track by applying tangential thrust provided by the specific application example of the application can simultaneously maintain the ground track and relative phase of the satellites in the constellation by only applying tangential thrust to the satellites.

[0131] Based on the same inventive concept, the application embodiment further provides a regressive co-ground track constellation maintenance device for applying tangential thrust, which can be used to realize the method described in the above embodiment, as follows. Since the principle of solving problems of the regressive co-ground track constellation maintenance device for applying tangential thrust is similar to that of the regressive co-ground track constellation maintenance method for applying tangential thrust, the implementation of the regressive co-ground track constellation maintenance device for applying tangential thrust can be referred to the implementation of the regressive co-ground track constellation maintenance method for applying tangential thrust, and the repeated parts will not be described herein. The term "unit" or "module" used below can be a combination of software and / or hardware that can realize a predetermined function. Although the system described in the following embodiment is preferably realized in software, the realization of hardware or a combination of software and hardware is also possible and conceived.

[0132] The embodiment of the application provides a specific implementation of a regressive co-ground track constellation maintenance device for applying tangential thrust, which can realize the regressive co-ground track constellation maintenance method for applying tangential thrust, referring to Figure 11 The regressive co-ground track constellation maintenance device for applying tangential thrust specifically includes the following contents:

[0133] The first tangential thrust determination module 10 is configured to determine a first tangential thrust required by a first satellite in the constellation according to a correction value of a subsolar longitude drift of the first satellite, and apply the first tangential thrust to the first satellite, wherein the first tangential thrust is used to maintain a regressive co-ground track of the first satellite.

[0134] The phase maintaining module 20 is configured to apply a second tangential thrust corresponding to a second satellite in the constellation to the second satellite, so as to maintain a relative phase between the second satellite and the first satellite.

[0135] In some embodiments of the present application, referring to Figure 12 , the first tangential thrust determination module 10 comprises:

[0136] The mapping generation unit 10a is configured to generate a mapping between the semi-major axis deviation of the first satellite and the subsolar longitude drift.

[0137] The adjustment value determination unit 10b is configured to determine an adjustment value of the semi-major axis deviation of the first satellite according to the mapping and the correction value.

[0138] The first tangential thrust determination unit 10c is configured to determine the first tangential thrust according to the adjustment value.

[0139] In some embodiments of the present application, referring to Figure 13 , the mapping generation unit 10a comprises:

[0140] The longitude difference determination unit 10a1 is configured to determine a longitude difference of the first satellite passing through the intersection of the equatorial plane in an orbit period.

[0141] The variation amount determination unit 10a2 is configured to determine a variation amount of the subsolar longitude drift caused by the semi-major axis deviation in the orbit period according to the longitude difference.

[0142] The mapping generation sub-unit 10a3 is configured to generate the mapping according to the variation amount and the semi-major axis deviation.

[0143] In some embodiments of the present application, if the adjustment value of the semi-major axis deviation is greater than 0, the direction of the first tangential thrust is positive tangential.

[0144] If the adjustment value of the semi-major axis deviation is less than 0, the direction of the first tangential thrust is negative tangential.

[0145] In some embodiments of the present application, referring to Figure 14 , the regressive co-ground track constellation maintaining device further comprises:

[0146] The application time determining module 30 is configured to determine the application time of the first tangential thrust to the first satellite according to the mass of the first satellite, the orbital angular velocity, and the amplitude of the first tangential thrust.

[0147] In some embodiments of the application, the step of determining the second tangential thrust comprises:

[0148] The second tangential thrust is determined according to the regression number of the second satellite, the regression days, the ascending node right ascension difference between the second satellite and the first satellite, and the mean anomaly difference.

[0149] In some embodiments of the application, the first tangential thrust is used to adjust the semi-major axis of the first satellite.

[0150] The second tangential thrust is used to adjust the semi-major axis of the second satellite.

[0151] Embodiments of the application also provide a specific implementation of an electronic device capable of implementing all the steps of the above-mentioned method for maintaining a regression co-ground track constellation by applying a tangential thrust. Figure 15 The electronic device specifically includes the following contents:

[0152] The electronic device specifically includes the following contents:

[0153] The processor 1201, the memory 1202, and the communications interface 1203 are connected through the bus 1204 to communicate with each other; and the communications interface 1203 is configured to realize information transmission between the server-side device, the power measurement device, and the user-side device, and other related devices.

[0154] The processor 1201 is configured to call the computer program in the memory 1202, and the processor implements all the steps of the above-mentioned method for maintaining a regression co-ground track constellation by applying a tangential thrust when executing the computer program, for example, the processor implements the following steps when executing the computer program:

[0155] The first tangential thrust required by the first satellite is determined according to the correction value of the subterranean point longitude drift of the first satellite in the predetermined constellation, and the first tangential thrust is applied to the first satellite, and the first tangential thrust is used to maintain the regression co-ground track of the first satellite.

[0156] The second tangential thrust corresponding to the second satellite other than the first satellite in the constellation is applied to the second satellite to maintain the relative phase between the second satellite and the first satellite.

[0157] The embodiment of the present application also provides a computer readable storage medium capable of realizing all steps of the method for maintaining a constellation of satellites in a retrograde co-ground track by applying tangential thrusts in the above-mentioned embodiment, wherein the computer readable storage medium stores a computer program, and the computer program realizes all steps of the method for maintaining a constellation of satellites in a retrograde co-ground track by applying tangential thrusts in the above-mentioned embodiment when executed by a processor, for example, the following steps are realized when the processor executes the computer program:

[0158] determining a first tangential thrust required by the first satellite according to the correction value of the longitude drift of the subsolar point of the first satellite in the predetermined constellation, and applying the first tangential thrust to the first satellite, wherein the first tangential thrust is used for maintaining a retrograde co-ground track of the first satellite;

[0159] applying a second tangential thrust corresponding to a second satellite to the second satellite to maintain a relative phase between the second satellite and the first satellite.

[0160] Each of the embodiments in the specification is described in a progressive manner, and the same or similar parts of each of the embodiments can be referred to each other, and each of the embodiments mainly describes the difference from other embodiments. In particular, for the hardware+program type embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the related parts can be referred to the part of the method embodiment.

[0161] The above describes specific embodiments of the present application. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims can be performed in a different order and still accomplish desirable results. Additionally, the processes depicted in the figures do not necessarily require the particular order shown, or sequential order, to achieve desirable results. In certain implementations, multitasking and parallel processing can be advantageous.

[0162] Although the present application provides method operation steps as embodiments or flowcharts, more or fewer operation steps can be included based on conventional or non-inventive labor. The order of steps listed in the embodiments is only one of the many execution orders of the steps, and does not represent the only execution order. When the device or client product in the actual implementation is executed, the method order shown in the embodiments or the drawings can be executed in sequence or in parallel (for example, in the environment of parallel processor or multi-thread processing).

[0163] The computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart block or blocks. Figure 1 one or more flow or blocks Figure 1 one or more flow or blocks

[0164] These computer program instructions can also be stored in a computer readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer readable memory produce an article of manufacture including instructions which implement the function specified in the flowchart block or blocks. Figure 1 one or more flow or blocks Figure 1 one or more flow or blocks

[0165] The computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart block or blocks. Figure 1 one or more flow or blocks Figure 1 one or more flow or blocks

[0166] The principles and implementations of the present application are described in the specific embodiments, the above description of the embodiments is only to help understand the method of the present application and its core idea; at the same time, for those skilled in the art, according to the idea of the present application, the specific implementation and application range will be changed, and the above description of the present application should not be understood as the limitation of the present application.

Claims

1. A method for maintaining a common ground trajectory constellation by applying tangential thrust, characterized in that: include: determining a first tangential thrust required for a first satellite in a predetermined constellation according to a correction value for a sub-satellite point longitude drift of the first satellite, and applying the first tangential thrust to the first satellite, wherein the first tangential thrust is used to maintain a return common ground track of the first satellite; applying a second tangential thrust corresponding to a second satellite in the constellation other than the first satellite to maintain a relative phase between the second satellite and the first satellite; The determining, based on a correction value of a sub-satellite point longitude drift of a first satellite in a predetermined constellation, a first tangential thrust required by the first satellite comprises: generating a mapping between the semi-major axis deviation of the first satellite and the longitude drift of the sub-satellite point; determining an adjustment value for the semi-major axis deviation of the first satellite based on the mapping and the correction value; determining the first tangential thrust according to the adjustment value; Generating a mapping between the semi-major axis deviation of the first satellite and the sub-satellite point longitude drift includes: determining a longitude difference of an intersection point where the first satellite passes through the equatorial plane during an orbital period; determining, based on the longitude difference, a change in the sub-satellite point longitude difference caused by the semi-major axis deviation within the orbital period; The mapping is generated according to the variation and the semi-major axis deviation, specifically: In one orbital period, the longitude difference between the first satellite's two passes through the equatorial plane is: in, is the orbital period of the first satellite, is the right ascension change rate of the ascending node of the first satellite, is the semi-major axis of the orbit of the first satellite, is the orbital inclination of the first satellite, is the orbital angular velocity of the first satellite, is the mean equatorial radius of the Earth, is the angular velocity of the Earth's rotation; In one orbital period, according to formula (1), the semi-major axis deviation of the first satellite is The change in the longitude difference of the first satellite caused by for: Based on formula (1) and formula (2), the longitude drift rate and semi-major axis deviation of the first satellite are The mapping is: 。 2. The method for maintaining a regressive common ground track constellation according to claim 1, wherein: If the adjustment value of the semi-major axis deviation is greater than 0, the first tangential thrust direction is positive tangential; If the adjustment value of the semi-major axis deviation is less than 0, the first tangential thrust direction is negative tangential.

3. The method for maintaining a regressive common ground track constellation according to claim 1, wherein: Also includes: The time for applying the first tangential thrust to the first satellite is determined according to the mass and orbital angular velocity of the first satellite and the magnitude of the first tangential thrust.

4. The method for maintaining a regressive common ground track constellation according to claim 1, wherein: The step of determining the second tangential thrust comprises: The second tangential thrust is determined according to the number of regression circles and regression days of the second satellite, the right ascension difference of the ascending node and the mean anomaly difference between the second satellite and the first satellite.

5. The method for maintaining a regressive common ground track constellation according to any one of claims 1 to 4, characterized in that: The first tangential thrust is used to adjust the semi-major axis of the first satellite; The second tangential thrust is used to adjust the semi-major axis of the second satellite.

6. A device for maintaining a common ground track constellation by applying tangential thrust, characterized in that: include: a first tangential thrust determination module, configured to determine a first tangential thrust required by a first satellite according to a predetermined correction value of a sub-satellite point longitude drift of a first satellite in a constellation, and apply the first tangential thrust to the first satellite, wherein the first tangential thrust is used to maintain a return common ground track of the first satellite; a phase maintaining module, configured to apply a second tangential thrust corresponding to a second satellite other than the first satellite in the constellation, so as to maintain a relative phase between the second satellite and the first satellite; The determining, based on a correction value of a sub-satellite point longitude drift of a first satellite in a predetermined constellation, a first tangential thrust required by the first satellite comprises: generating a mapping between the semi-major axis deviation of the first satellite and the longitude drift of the sub-satellite point; determining an adjustment value for the semi-major axis deviation of the first satellite based on the mapping and the correction value; determining the first tangential thrust according to the adjustment value; Generating a mapping between the semi-major axis deviation of the first satellite and the sub-satellite point longitude drift includes: determining a longitude difference of an intersection point where the first satellite passes through the equatorial plane during an orbital period; determining, based on the longitude difference, a change in the sub-satellite point longitude difference caused by the semi-major axis deviation within the orbital period; The mapping is generated according to the variation and the semi-major axis deviation, specifically: In one orbital period , the longitude difference between the first satellite's two passes through the intersection with the equatorial plane is: in, is the orbital period of the first satellite, is the right ascension change rate of the ascending node of the first satellite, is the semi-major axis of the orbit of the first satellite, is the orbital inclination of the first satellite, is the orbital angular velocity of the first satellite, is the mean equatorial radius of the Earth, is the angular velocity of the Earth's rotation; In one orbital period, according to formula (1), the semi-major axis deviation of the first satellite is The change in the longitude difference of the first satellite caused by for: Based on formula (1) and formula (2), the longitude drift rate and semi-major axis deviation of the first satellite are The mapping is: 。 7. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 5 are implemented.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 5 are implemented.

9. A computer program product, characterized in that The computer program product comprises a computer program, and when the computer program is executed by a processor, the method according to any one of claims 1 to 5 is implemented.

Images