Method and device for maintaining regression common ground track constellation applying tangential thrust

Abstract

The invention provides a method and device for maintaining a regression common ground trajectory constellation applying tangential thrust, and relates to the technical field of constellation orbit power and control. The method comprises the steps that first tangential thrust needed by a first satellite is determined according to a predetermined correction value of sub-satellite point longitude drift of the first satellite in a constellation, the first tangential thrust is applied to the first satellite, and the first tangential thrust is used for maintaining a regression common ground track of the first satellite; and applying a second tangential thrust corresponding to a second satellite except the first satellite in the constellation to maintain a relative phase between the second satellite and the first satellite. According to the method provided by the embodiment of the invention, only tangential thrust needs to be applied to the satellites, orbital normal thrust does not need to be applied to the satellites, and the sub-satellite point trajectory of the satellite regression common ground trajectory constellation in the constellation can be maintained.

Description

Technical Field

[0001] The present invention relates to the field of satellite communication technology, in particular to the field of constellation orbit power and control technology, and specifically to a method and device for maintaining a regressive common ground trajectory constellation by applying tangential thrust. Background Art

[0002] Existing research methods for maintaining re-entry orbits for satellites and constellations focus on single-satellite scenarios, rather than constellations operating on a common ground track. The impact of field harmonic perturbations on re-entry satellites manifests as long-period terms, including the orbital semi-major axis and inclination. Furthermore, atmospheric drag in low-orbit orbits causes a continuous decrease in the orbital semi-major axis. The sub-satellite trajectory is a function of the satellite's orbital semi-major axis and inclination, resulting in deviations from the nominal value. Summary of the Invention

[0003] In response to the problems in the prior art, embodiments of the present invention provide a method and apparatus for maintaining a regressive common 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 invention provides a method for maintaining a common ground trajectory constellation by applying tangential thrust, wherein the method is applied to any satellite in a constellation and comprises:

[0005] 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;

[0006] A second tangential thrust corresponding to a second satellite other than the first satellite in the constellation is applied to maintain a relative phase between the second satellite and the first satellite, thereby maintaining a sub-satellite point trajectory of the entire constellation.

[0007] In some embodiments of the present invention, determining the first tangential thrust required for the first satellite based on a predetermined correction value of a sub-satellite point longitude drift of the first satellite in the constellation includes:

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

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

[0010] The first tangential thrust is determined according to the adjustment value.

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

[0012] determining a longitude difference of an intersection point where the first satellite passes through the equatorial plane during an orbital period;

[0013] 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;

[0014] The map is generated according to the variation and the semi-major axis deviation.

[0015] In some embodiments of the present invention, 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 invention, a method for maintaining a common ground track constellation by applying tangential thrust further includes:

[0018] 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.

[0019] In some embodiments of the present invention, the step of determining the second tangential thrust includes:

[0020] 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.

[0021] In some embodiments of the present invention, 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] On the other hand, the present invention further provides a device for maintaining a recurrent common ground track constellation by applying tangential thrust, wherein the device for maintaining a recurrent common ground track constellation by applying tangential thrust is applied to all satellites in a constellation, comprising:

[0024] 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;

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

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

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

[0028] The memory stores program instructions that can be executed by the processor, and the processor calls the program instructions to execute the following method:

[0029] 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;

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

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

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

[0033] 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;

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

[0035] An embodiment of the present invention further provides a computer program product, comprising a computer program. When the computer program is executed by a processor, the computer program implements the following method:

[0036] 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;

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

[0038] In summary, the method and apparatus for maintaining a common ground trajectory constellation by applying tangential thrust provided by an embodiment of the present invention first determine the first tangential thrust required by the first satellite based on a predetermined correction value for the sub-satellite point longitude drift of the first satellite in the constellation, and apply the first tangential thrust to the first satellite. The first tangential thrust is used to maintain the common ground trajectory of the first satellite. Next, a second tangential thrust corresponding to the second satellite in the constellation is applied to the second satellite other than the first satellite to maintain the relative phase between the second satellite and the first satellite.

[0039] The method for maintaining a common ground trajectory constellation by applying tangential thrust provided in an embodiment of the present invention only requires applying tangential thrust to the satellites in the constellation, without applying orbital normal thrust to the satellites, so as to maintain the sub-satellite point trajectory of the satellites in the constellation returning to the common ground trajectory constellation. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work. In the drawings:

[0041] Figure 1 The present invention is a flowchart of a method for maintaining a common ground trajectory constellation by applying tangential thrust provided by an embodiment of the present invention.

[0042] Figure 2 1 is a flow chart of step 100 provided in one embodiment of the present invention.

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

[0044] Figure 4 This is a second flow chart of a method for maintaining a common ground trajectory constellation by applying tangential thrust provided by an embodiment of the present invention.

[0045] Figure 5 1 is a third flow chart of a method for maintaining a common ground trajectory constellation by applying tangential thrust provided by an embodiment of the present invention.

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

[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," and the like in the description and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or precedence. It should be understood that the numbers used in this manner are interchangeable where appropriate so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having," as well as any variations thereof, are intended to cover non-exclusive inclusions. For example, a process, method, apparatus, product, or device comprising a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units that are not explicitly listed or that are inherent to these processes, methods, products, or devices.

[0058] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0059] A regression orbit is a special type of orbit in which the sub-satellite point trajectory repeats periodically. The sub-satellite point of this type of orbit has the characteristic of repeating the ground trajectory after a regression period (an integer number of days), thereby meeting the mission requirements of periodic observations, helping to improve the consistency before and after imaging, and has important applications in fields such as synthetic aperture radar satellites (Synthetic Aperture Radar, SRA).

[0060] Correspondingly, multiple regression orbit satellites are placed on the same ground track at certain phase intervals to form a constellation of regression common ground tracks.

[0061] In remote sensing, common ground track constellations can shorten observation intervals for ground targets. In communications, as all satellites in a common ground track constellation pass sequentially, the pointing history of the satellites from ground communication terminals remains essentially unchanged over time. Therefore, common ground track deployment can simplify ground terminal access and connectivity strategies, and also has potential value in communications constellations.

[0062] The regression orbit repeatedly passes through the gravity field with the same longitude, and an orbital resonance effect occurs between the satellite motion and the field harmonic terms of the earth's gravity whose order is a multiple of the regression circle number. The main manifestation is that the influence of the corresponding field harmonic terms on the satellite orbit is no longer a general short-period influence with a small amplitude, but a long-period influence, causing the satellite's sub-satellite point trajectory to deviate from its nominal orbit, affecting the mission implementation effect.

[0063] It is understandable that for a constellation deployed using a common ground track, uniform coverage can be achieved when the transit time differences of adjacent satellites are the same. Therefore, the regression common ground track constellation has the dual requirements of track maintenance and phase maintenance. However, there are no relevant methods for track maintenance and phase maintenance for the regression common ground track constellation in the prior art.

[0064] Field harmonic perturbations cause periodic oscillations in the semi-major axis and inclination of re-entry satellites. Low-orbit atmospheric drag also causes a continuous decrease in the semi-major axis. Both the semi-major axis and inclination can be adjusted to maintain the sub-satellite trajectory and the inter-satellite phase difference near the nominal value. Control of the semi-major axis requires the application of tangential thrust, while control of the inclination requires the application of orbital normal thrust. If a satellite is equipped with only one thruster, satellite attitude adjustments are required during the application of both tangential and normal thrust, which can affect the effectiveness of the satellite's on-orbit mission. However, if a satellite is equipped with two thrusters, with thrust applied in the orbital tangential and orbital normal directions, respectively, the cost of the satellite platform will increase.

[0065] In order to solve the above technical problems, see Figure 1 (A flowchart of a method for maintaining a common ground trajectory constellation by applying tangential thrust according to an embodiment of the present invention) The method for maintaining a common ground trajectory constellation by applying tangential thrust according to an embodiment of the present invention (the method is applicable to any satellite in a constellation) includes:

[0066] Step 100: Determine a first tangential thrust required for a first satellite in a predetermined constellation based on a correction value of a sub-satellite point longitude drift, and apply the first tangential thrust to the first satellite, wherein the first tangential thrust is used to maintain a common ground trajectory of the first satellite.

[0067] Step 200: 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.

[0068] In summary, the method for maintaining a common ground trajectory constellation by applying tangential thrust provided in an embodiment of the present invention first determines a first tangential thrust required for the first satellite based on a predetermined correction value for the sub-satellite point longitude drift of the first satellite in the constellation, and applies the first tangential thrust to the first satellite. The first tangential thrust is used to maintain the common ground trajectory of the first satellite. Next, a second tangential thrust corresponding to a second satellite in the constellation, excluding the first satellite, is applied to maintain the relative phase between the second satellite and the first satellite.

[0069] It can be seen that, first, the method provided in the embodiment of the present invention only applies tangential thrust to the first satellite (equivalent to the reference satellite in the constellation), thereby maintaining the regression common ground track of the reference satellite. Secondly, the present invention only applies tangential thrust to the second satellite (satellites other than the reference satellite) (this tangential thrust may be different from the tangential thrust applied to the reference satellite, and the tangential thrust corresponding to each second satellite may also be different), thereby maintaining the relative phase of other satellites and the reference satellite, indirectly maintaining the sub-satellite point track of other satellites, and thus maintaining the sub-satellite point track of the entire constellation.

[0070] In some embodiments of the present invention, with respect to step 100, the applicant has discovered that by periodically applying a predetermined tangential thrust to a pre-selected first satellite in a constellation (a reference satellite, optionally one of the satellites in the constellation), the semi-major axis deviation of the reference satellite can be adjusted, and ultimately the longitude drift rate of the reference satellite can be controlled, thereby maintaining the sub-satellite point trajectory of the reference satellite near a 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 other satellites except the reference satellite.

[0072] In some embodiments of the present invention, for step 200, by applying corresponding second tangential thrusts to other satellites (all satellites except the reference satellite), the relative phase between the other satellites and the reference satellite can be maintained, thereby indirectly maintaining the sub-satellite point trajectory of the other satellites, thereby achieving the sub-satellite point trajectory and phase maintenance of the entire constellation.

[0073] In some embodiments of the present invention, see Figure 2 , step 100 includes:

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

[0075] In some embodiments of the present invention, see Figure 3 , step 101 includes:

[0076] Step 1011: Determine the longitude difference of the intersection point where the first satellite passes through the equatorial plane during the orbital period;

[0077] Specifically, in one orbital period , the longitude difference between the first satellite's two passes through the intersection with the equatorial plane is:

[0078]

[0079] 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 first satellite's orbit, 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.

[0080] Step 1012: determining a change in the sub-satellite point longitude difference caused by the semi-major axis deviation within the orbital period based on the longitude difference;

[0081] In one orbital period, according to formula (1), it can be known that the semi-major axis deviation of the first satellite is The change in the longitude difference of the first satellite caused by for:

[0082]

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

[0084] Based on formula (1) and formula (2), the longitude drift rate of the first satellite and the semi-major axis deviation are The mapping (relationship) is:

[0085]

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

[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: Determine 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 longitude of the sub-satellite point intersection (i.e., the sub-satellite point trajectory) of the first satellite can be adjusted by applying tangential thrust only to the first satellite.

[0090] In some embodiments of the present invention, 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 hour( is the adjustment value of the semi-major axis deviation), the direction of the first thrust applied to the first satellite is a positive tangential direction; otherwise, the direction of the first thrust applied to the first satellite is a negative tangential direction.

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

[0093] In some embodiments of the present invention, see Figure 4 , a method for maintaining a common ground track constellation by applying tangential thrust, further comprising:

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

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

[0096]

[0097] in, is the time to apply 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 knowing the direction of the first tangential thrust (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 precisely controlling the application time of the first tangential thrust, a better maintenance effect of the sub-satellite point trajectory of the first satellite returning to the common ground track constellation can be achieved, and satellite fuel and satellite platform management costs can be saved.

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

[0100] 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.

[0101] It is understandable that a cluster of satellites in a regressive orbit deployed in a common subsatellite trajectory can repeatedly pass through a specific area. In order to make the ground tracks of multiple satellites in a regressive orbit the same, the right ascension difference between the ascending node of the other satellites (all the second satellites) and the first satellite is Peaceful anomaly The following relationship needs to be satisfied:

[0102]

[0103] in, is the number of regression cycles, is the number of days to return.

[0104] Since the temporal rate of change of a satellite's ascending node right ascension and mean anomaly depends primarily on its semi-major axis, eccentricity, and orbital inclination, for a near-circular orbit, the eccentricity is close to zero, and thus the temporal rate of change of the satellite's ascending node right ascension and mean anomaly depends primarily on its semi-major axis, it is possible to place a second satellite on a common ground track with the first simply by adjusting its semi-major axis.

[0105] At the initial moment, the semi-major axis of the current satellite (one satellite is selected from all the second satellites) is adjusted (the adjustment amount is determined by the number of regression circles of the current satellite, the number of regression days, the right ascension difference of the ascending node between the current satellite and the first satellite, and the mean anomaly difference) so that the right ascension difference of the ascending node and the mean anomaly difference between the current satellite and the first satellite satisfy formula (5), thereby making the current satellite and the first satellite share the same ground track at the initial moment.

[0106] Next, the current satellite maintains its phase relative to the first satellite, maintaining a nearly constant phase difference between them. This ensures that the semi-major axes of the current and first satellites are aligned. Because neither the current satellite nor the first satellite maintains or adjusts its orbital inclination, the two satellites (the current satellite and the first satellite) have the same orbital inclination numbering pattern, resulting in essentially the same orbital inclination.

[0107] In summary, this application maintains the relative phase between the current satellite and the first satellite, ensuring that the semi-major axis and orbital inclination of the current satellite and the first satellite are identical, thereby indirectly maintaining the sub-satellite point trajectory of the current satellite. Other satellites refer to the maintenance strategy of the current satellite, thereby maintaining the sub-satellite point trajectory and phase of the entire constellation.

[0108] In some embodiments of the present invention, see Figure 5 , a method for maintaining a common ground track constellation by applying tangential thrust, further comprising:

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

[0110] Next, see Figure 6 , step 400 includes:

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

[0112] Step 402: Determine the longitude drift value of the first satellite during the historical period based on the initial longitude value and the final longitude value;

[0113] Step 403: Determine the correction value of the longitude drift according to the predetermined longitude drift target value and the longitude drift value of the historical period.

[0114] In steps 401 to 403, during the satellite's on-orbit operation, it is affected by orbital perturbations such as the Earth's non-spherical perturbations, atmospheric drag, gravitational perturbations of the Sun and Moon, and solar pressure perturbations. In particular, atmospheric drag causes the satellite's orbital altitude to continuously decay, affecting the satellite's on-orbit mission. Without considering the maintenance of the satellite's sub-satellite point trajectory, thrust still needs to be applied to maintain the orbital altitude, but the orbital altitude is only maintained at a constant value. Due to the influence of the Earth's field harmonic perturbations, the sub-satellite point trajectory will deviate from the nominal value. Therefore, the present invention provides an implementation method of step 400, which maintains the sub-satellite point trajectory near the nominal value by periodically adjusting the nominal value of the satellite's semi-major axis.

[0115] The specific strategy is as follows: take N days (preferably 10 days) as the adjustment period of the semi-major axis nominal axis, and calculate the actual value of the ascending node longitude drift rate within N days based on the initial and final values ​​of the ascending node longitude within N days; and based on the target value and actual value of the ascending node longitude drift at the end of N days, and considering the ascending node longitude adjustment that needs to be completed in the next N days, obtain the target value of the ascending node longitude drift (target value of the ascending node longitude drift rate); deviate the target value of the ascending node longitude drift rate from the actual value to obtain the target value of the ascending node longitude drift rate change (corrected value of the longitude drift), and then calculate the target value of the semi-major axis change.

[0116] In some embodiments of the present invention, 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 in this application only needs to adjust the semi-major axis of the first satellite to maintain the first satellite's regression common ground track. Similarly, by only adjusting the semi-major axes of other satellites, the relative phases of other satellites and the first satellite can be maintained, and the sub-satellite point tracks of other satellites can be indirectly maintained, thereby maintaining the sub-satellite point track of the entire constellation.

[0118] In summary, the method for maintaining a common ground track constellation by applying tangential thrust provided in the embodiments of the present invention only requires applying tangential thrust to the satellite, and can simultaneously achieve the ground track maintenance and relative phase maintenance of the constellation's common ground track constellation.

[0119] Specifically, the method provided by the embodiment of the present invention does not require the application of orbital normal thrust to the satellite, the satellite does not need to be equipped with a normal thruster, and does not require normal thrust fuel consumption, thereby reducing the direct cost of the satellite platform and the fuel consumption cost.

[0120] To further illustrate this solution, the present invention also provides a specific application example of a method for maintaining a common ground track constellation by applying tangential thrust, see Figure 7 , specifically including the following contents.

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

[0122] For specific implementations, see formulas (1) to (3) and related descriptions.

[0123] S2: Maintaining the reference satellite's return to the common ground track by applying a first tangential thrust to the reference satellite for a preset time.

[0124] The method for obtaining the preset time in step S2 is shown in formula (4) and related descriptions.

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

[0126] Specifically, by applying a second tangential thrust to other satellites, the corresponding sub-satellite point trajectory of the other satellites is maintained. Furthermore, by maintaining the relative phase of the other satellites with the reference satellite, the sub-satellite point trajectory is indirectly maintained, thereby achieving sub-satellite point trajectory and phase maintenance for the entire constellation. For a specific implementation, see formula (5) and related descriptions.

[0127] Technical effect: Here, an orbit with an altitude of 500.77 km, an inclination of 55.1°, 15 regression circles, and a regression day is selected as the nominal orbit. The satellite orbit has 15 ascending nodes. The simulation analysis selects the ascending node longitude of the reference satellite in a certain circle as 86.8°. The simulation includes two satellites, A and B, and the effectiveness of the control strategy is verified through the simulation of the two satellites. A satellite is used as the reference satellite. The subsatellite point trajectory of B is the same as that of A, and the phase angle difference between B and A is -15°. The total simulation time is selected as 50 days.

[0128] In the scenario with a simulation time of 50 days, the results of the sub-satellite point trajectory of satellite A (reference satellite) show that the sub-satellite point trajectory of satellite A is well maintained and there is no drift. The results of the sub-satellite point trajectory of satellite B (other satellite) in the scenario with a simulation time of 50 days also show that the sub-satellite point trajectory of satellite B is well maintained and there is no drift. The results of the sub-satellite point trajectory of satellite A and satellite B combined show that the sub-satellite point trajectories of the two satellites overlap and are indistinguishable. Further observation Figure 8 In the figure, the blue dot is the subsatellite point trajectory of star A, and the red dot is the subsatellite point trajectory of star B. The figure shows that the subsatellite point trajectories of stars A and B coincide.

[0129] Figure 9 The time history of the phase angle difference between satellite B and satellite A shows that the phase angle difference between the two satellites is basically around -15°, ranging from -15.04° to -14.95°, and the maximum deviation does not exceed 0.05°. Figure 10 is the time history of the longitudes of the ascending nodes of the two satellites. The longitudes of the ascending nodes of the two satellites are both within the nominal value (around 86.8°), ranging from 86.794 to 86.812°, and the maximum deviation does not exceed 0.05°.

[0130] In summary, the method for maintaining a common ground track constellation by applying tangential thrust provided by a specific application example of the present invention only requires applying tangential thrust to the satellites, and can simultaneously maintain the ground tracks and relative phases of the satellites in the constellation.

[0131] Based on the same inventive concept, an embodiment of the present invention also provides a device for maintaining a regression common ground track constellation by applying tangential thrust, which can be used to implement the method described in the above embodiment, such as the following embodiment. Since the principle of solving the problem by the device for maintaining a regression common ground track constellation by applying tangential thrust is similar to that of the method for maintaining a regression common ground track constellation by applying tangential thrust, the implementation of the device for maintaining a regression common ground track constellation by applying tangential thrust can refer to the implementation of the method for maintaining a regression common ground track constellation by applying tangential thrust, and the repeated parts will not be repeated. As used below, the term "unit" or "module" can be a combination of software and / or hardware that implements a predetermined function. Although the system described in the following embodiments is preferably implemented in software, implementation in hardware, or a combination of software and hardware, is also possible and conceived.

[0132] The embodiment of the present invention provides a specific implementation of a device for maintaining a common ground track constellation by applying tangential thrust, which can realize a method for maintaining a common ground track constellation by applying tangential thrust. Figure 11 A device for maintaining a common ground trajectory constellation by applying tangential thrust specifically includes the following contents: a first tangential thrust determination module 10, configured to determine 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, and apply the first tangential thrust to the first satellite, wherein the first tangential thrust is used to maintain a common ground trajectory of the first satellite; The phase maintaining module 20 is configured to apply a second tangential thrust corresponding to a second satellite other than the first satellite in the constellation to maintain a relative phase between the second satellite and the first satellite.

[0133] In some embodiments of the present invention, see Figure 12 , the first tangential thrust determination module 10 includes: A mapping generating unit 10a is configured to generate a mapping between the semi-major axis deviation of the first satellite and the longitude drift of the sub-satellite point; an adjustment value determining unit 10b, configured to determine an adjustment value of the semi-major axis deviation of the first satellite based on the mapping and the correction value; The second tangential thrust determining unit 10c is configured to determine the first tangential thrust according to the adjustment value.

[0134] In some embodiments of the present invention, see Figure 13 , the mapping generation unit 10a includes: a longitude difference determining unit 10a1, configured to determine a longitude difference of an intersection point where the first satellite passes through the equatorial plane during an orbital period; a change amount determining unit 10a2, configured to determine, based on the longitude difference, a change amount of the sub-satellite point longitude difference caused by the semi-major axis deviation within the orbital period; The map generation subunit 10a3 is configured to generate the map according to the variation and the semi-major axis deviation.

[0135] In some embodiments of the present invention, 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.

[0136] In some embodiments of the present invention, see Figure 14 , a regressive common ground track constellation maintaining device, further comprising: The application time determination module 30 is configured to determine a time for applying the first tangential thrust to the first satellite according to the mass and orbital angular velocity of the first satellite and the magnitude of the first tangential thrust.

[0137] In some embodiments of the present invention, the step of determining the second tangential thrust includes: 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.

[0138] In some embodiments of the present invention, 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.

[0139] The embodiment of the present invention also provides a specific implementation of an electronic device capable of implementing all steps of the method for maintaining a common ground track constellation by applying tangential thrust in the above embodiment, see Figure 15 , electronic equipment specifically includes the following: Processor 1201, memory 1202, communications interface 1203, and bus 1204; The processor 1201 , the memory 1202 , and the communication interface 1203 communicate with each other via the bus 1204 . The communication interface 1203 is used to implement information transmission between relevant devices such as the server-side device, the power measurement device, and the user-side device.

[0140] The processor 1201 is configured to call a computer program in the memory 1202. When the processor executes the computer program, all steps of the method for maintaining a common ground track constellation by applying tangential thrust in the above embodiment are implemented. For example, when the processor executes the computer program, the following steps are implemented: 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; A second tangential thrust corresponding to a second satellite in the constellation other than the first satellite is applied to maintain a relative phase between the second satellite and the first satellite.

[0141] An embodiment of the present invention also provides a computer-readable storage medium capable of implementing all steps of the method for maintaining a common ground track constellation by applying tangential thrust in the above-mentioned embodiment. The computer-readable storage medium stores a computer program. When the computer program is executed by a processor, all steps of the method for maintaining a common ground track constellation by applying tangential thrust in the above-mentioned embodiment are implemented. For example, when the processor executes the computer program, the following steps are implemented: 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; A second tangential thrust corresponding to a second satellite in the constellation other than the first satellite is applied to maintain a relative phase between the second satellite and the first satellite.

[0142] The various embodiments in this specification are described in a progressive manner. Similar portions between the various embodiments can be referenced to each other. Each embodiment focuses on the differences between the other embodiments. In particular, the hardware + program embodiments are generally similar to the method embodiments, so their description is relatively simple. For relevant portions, refer to the description of the method embodiments.

[0143] The foregoing description of this specification describes specific embodiments. 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 an order different from that described in the embodiments and still achieve the desired results. Furthermore, the processes depicted in the accompanying drawings do not necessarily require the specific order shown or the sequential order to achieve the desired results. In certain embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0144] While the present invention provides method steps as shown in the embodiments or flowcharts, more or fewer steps may be included based on routine or uninventive practice. The order of steps listed in the embodiments is merely one of many possible execution sequences and does not represent the only execution sequence. When implemented in a real device or client product, the methods shown in the embodiments or figures may be executed sequentially or in parallel (e.g., in a parallel processor or multi-threaded processing environment).

[0145] The present invention is described with reference to flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowcharts and / or block diagrams, as well as combinations of processes and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowcharts and / or block diagrams. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0146] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0147] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0148] Specific embodiments are used in the present invention to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core ideas. At the same time, for those skilled in the art, according to the ideas of the present invention, there may be changes in the specific implementation methods and application scopes. In summary, the contents of this specification should not be understood as limiting the present invention.

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

2. The method for maintaining a regressive common ground track constellation according to claim 1, wherein: 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; The first tangential thrust is determined according to the adjustment value.

3. The method for maintaining a regressive common ground track constellation according to claim 2, wherein: 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 map is generated according to the variation and the semi-major axis deviation.

4. The method for maintaining a recurrent common ground track constellation according to claim 2, 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.

5. 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.

6. 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.

7. The method for maintaining a regressive common ground track constellation according to any one of claims 1 to 6, 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.

8. A device for maintaining a common ground trajectory 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 is configured to apply a second tangential thrust corresponding to a second satellite other than the first satellite in the constellation to maintain a relative phase between the second satellite and the first satellite.

9. 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 7 are implemented.

10. 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 7 are implemented.

11. 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 7 is implemented.

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