Integrated control method and device for low-Earth orbit satellite communication and orbit maintenance

Abstract

This invention provides an integrated control method and apparatus for low-Earth orbit (LEO) satellite communication and orbit maintenance, relating to the technical field of satellite communication. The method determines the target orbit of the LEO satellite based on its current orbit, the location coordinates of the user target, and the data transmission and reception coverage area of ​​the user target. The user target is located at the center of the sub-satellite trajectory network when the LEO satellite is in the target orbit, and the distance between the boundary of the sub-satellite trajectory network and the user target is less than a first threshold. This maximizes the service period and communication frequency of the LEO satellite for the user target, thereby achieving routine communication support for the user target using a single LEO satellite. Furthermore, this method integrates satellite communication and orbit maintenance, ensuring communication for the user target while minimizing satellite fuel consumption and optimizing long-term satellite management efficiency.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite communication, in particular to a low-orbit satellite communication and orbit maintenance integrated control method and device. BACKGROUND

[0002] Currently, low-orbit satellite communication mainly uses electromagnetic waves as information transmission media, and phased array technology is also used on the satellite to achieve rapid adjustment of beam pointing. The ground operation and control system usually obtains the orbit elements of the satellite based on the received GNSS data, extrapolates the satellite orbit to predict the sub-satellite point trajectory, and combines the position of the communication target, the communication period, etc. to complete the coverage judgment of the satellite to the communication target. The existing technical solution mainly designs a task planning method based on the coverage of the satellite to the communication target to complete the demand analysis and task planning of the user.

[0003] In order to ensure that information transmission guarantee can be realized for a certain user target for as long as possible, low-orbit communication satellites often design different constellations to achieve optimal matching of beam resources and guarantee requirements. The above-mentioned scheme can complete the planning of low-orbit satellite communication guarantee requirements, but when the number of low-orbit satellites and the capacity of the beam are significantly limited, it is difficult to realize efficient communication guarantee for a specific user. SUMMARY

[0004] The purpose of the present application is to provide a low-orbit satellite communication and orbit maintenance integrated control method and device to alleviate the technical problem of high requirements for the number of low-orbit satellites and the capacity of the beam in the prior art based on the information transmission guarantee method of the satellite to the communication target.

[0005] In a first aspect, the present application provides a low-orbit satellite communication and orbit maintenance integrated control method, comprising: obtaining the current orbit of a low-orbit satellite, the position coordinates of a user target, and the data transmission and reception coverage range of the user target; determining the target orbit of the low-orbit satellite based on the current orbit of the low-orbit satellite, the position coordinates of the user target, and the data transmission and reception coverage range; wherein the user target is located at the center of the sub-satellite point trajectory network of the low-orbit satellite when it is in the target orbit, and the distance between the boundary of the sub-satellite point trajectory network and the user target is less than a first threshold value; determining the orbit control strategy of the low-orbit satellite based on the current orbit and the target orbit; and controlling the orbit state of the low-orbit satellite based on the orbit control strategy, so that the error between the controlled orbit and the target orbit is less than a second threshold value.

[0006] In an optional embodiment, the controlling the orbit state of the low-orbit satellite based on the orbit control strategy to make the error between the controlled orbit and the target orbit less than the second threshold value comprises: controlling the orbit state of the low-orbit satellite based on the orbit control strategy to obtain a controlled orbit; calculating the error between the controlled orbit and the target orbit to obtain an orbit error; judging whether the orbit error is less than the second threshold value; if yes, maintaining the controlled orbit; and if no, adjusting the orbit control strategy of the low-orbit satellite based on the controlled orbit and the target orbit until the error between the controlled orbit and the target orbit is less than the second threshold value.

[0007] In an optional embodiment, after determining that the error between the controlled orbit and the target orbit is less than the second threshold value, the method further comprises: obtaining a first time period of a requested communication of the user target and a measurement and control plan of the low-orbit satellite; calculating a second time period of a data transceiving coverage range of the low-orbit satellite covering the user target by orbit extrapolation on the target orbit; determining a communication plan of the low-orbit satellite and the user target based on the first time period and the second time period; and determining an on-board load control plan and a data transmission plan between the low-orbit satellite and a user center based on the communication plan and the measurement and control plan.

[0008] In an optional embodiment, the method further comprises: periodically monitoring a sub-satellite point track of the low-orbit satellite; and in a case where it is determined that the sub-satellite point track of the low-orbit satellite exceeds a boundary of a sub-satellite point track network of the target orbit, updating the orbit control strategy of the low-orbit satellite based on a current orbit of the low-orbit satellite and the target orbit to make the low-orbit satellite normally cover the user target.

[0009] In a second aspect, the present application provides an integrated control device for low-orbit satellite communication and orbit maintenance, comprising: a first obtaining module configured to obtain a current orbit of a low-orbit satellite, a position coordinate of a user target, and a data transceiving coverage range of the user target; a first determining module configured to determine a target orbit of the low-orbit satellite based on the current orbit of the low-orbit satellite, the position coordinate of the user target, and the data transceiving coverage range; wherein the user target is located at the center of a sub-satellite point track network of the low-orbit satellite when the low-orbit satellite is in the target orbit, and the distance between the boundary of the sub-satellite point track network and the user target is less than a first threshold value; a second determining module configured to determine an orbit control strategy of the low-orbit satellite based on the current orbit and the target orbit; and a control module configured to control the orbit state of the low-orbit satellite based on the orbit control strategy to make the error between a controlled orbit and the target orbit less than a second threshold value.

[0010] In an optional implementation, the control module is specifically configured to: control the orbit state of the low-orbit satellite by using the orbit control strategy, to obtain a controlled orbit; calculate an error between the controlled orbit and the target orbit, to obtain an orbit error; determine whether the orbit error is less than the second threshold; if yes, maintain the controlled orbit; and if no, adjust the orbit control strategy of the low-orbit satellite based on the controlled orbit and the target orbit, until the error between the controlled orbit and the target orbit is less than the second threshold.

[0011] In an optional implementation, the apparatus further includes: a second acquisition module configured to acquire a first time period of a request communication of the user target and a measurement and control plan of the low-orbit satellite; a calculation module configured to calculate a second time period of a data transceiving coverage range of the low-orbit satellite covering the user target by orbit extrapolation on the target orbit; a third determination module configured to determine a communication plan of the low-orbit satellite and the user target based on the first time period and the second time period; and a fourth determination module configured to determine an on-satellite payload control plan and a data transmission plan between the low-orbit satellite and a user center based on the communication plan and the measurement and control plan.

[0012] In an optional implementation, the apparatus further includes: a monitoring module configured to periodically monitor a subsatellite point trajectory of the low-orbit satellite; and an updating module configured to, in a case where it is determined that the subsatellite point trajectory of the low-orbit satellite exceeds a boundary of a subsatellite point trajectory network of the target orbit, update an orbit control strategy of the low-orbit satellite based on a current orbit of the low-orbit satellite and the target orbit, to enable the low-orbit satellite to normally cover the user target.

[0013] In a third aspect, the present application provides an electronic device, including a memory and a processor, the memory storing a computer program capable of running on the processor, and the processor implements the steps of the low-orbit satellite communication and orbit maintenance integrated control method according to any one of the preceding embodiments when executing the computer program.

[0014] In a fourth aspect, the present application provides a computer readable storage medium, the computer readable storage medium storing computer instructions, and the computer instructions implement the low-orbit satellite communication and orbit maintenance integrated control method according to any one of the preceding embodiments when executed by a processor.

[0015] This invention provides an integrated control method for low-Earth orbit (LEO) satellite communication and orbit maintenance. The method determines the target orbit of the LEO satellite based on its current orbit, the location coordinates of the user target, and the data transmission and reception coverage area of ​​the user target. The user target is located at the center of the sub-satellite trajectory network when the LEO satellite is in the target orbit, and the distance between the boundary of the sub-satellite trajectory network and the user target is less than a first threshold. This maximizes the service period and communication frequency of the LEO satellite for the user target, thereby achieving routine communication support for the user target using a single LEO satellite. Furthermore, this method integrates satellite communication and orbit maintenance planning, ensuring communication for the user target while minimizing satellite fuel consumption and optimizing long-term satellite management efficiency. Attached Figure Description

[0016] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0017] Figure 1 A flowchart illustrating an integrated control method for low-Earth orbit satellite communication and orbit maintenance provided in an embodiment of the present invention;

[0018] Figure 2 A schematic diagram illustrating the normal evolution of the nadir trajectory of a low-Earth orbit satellite.

[0019] Figure 3 This is a schematic diagram illustrating how a low-Earth orbit satellite's nadir trajectory network covers a user target in a target orbit, as provided in an embodiment of the present invention.

[0020] Figure 4 This is a schematic diagram of a satellite communication support scenario provided by an embodiment of the present invention;

[0021] Figure 5 A functional block diagram of an integrated control device for low-Earth orbit satellite communication and orbit maintenance provided in an embodiment of the present invention;

[0022] Figure 6 This is a schematic diagram of an electronic device provided in an embodiment of the present invention. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0024] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0025] The following detailed description of some embodiments of the present invention is provided in conjunction with the accompanying drawings. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0026] Existing technologies often employ satellite constellations to provide information transmission guarantees for communication targets. While this can fulfill the planning requirements for low-Earth orbit (LEO) satellite communication guarantees, it becomes difficult to achieve efficient guarantees for a specific user when the number of LEO satellites and beam capabilities are significantly limited. Therefore, this invention provides an integrated control method for LEO satellite communication and orbit maintenance to alleviate the technical problems mentioned above.

[0027] Example 1

[0028] Figure 1 A flowchart illustrating an integrated control method for low-Earth orbit satellite communication and orbit maintenance, as provided in an embodiment of the present invention, is shown below. Figure 1 As shown, the method specifically includes the following steps:

[0029] Step S102: Obtain the current orbit of the low-orbit satellite, the position coordinates of the user target, and the data transmission and reception coverage of the user target.

[0030] Step S104: Determine the target orbit of the low-Earth orbit satellite based on the current orbit of the low-Earth orbit satellite, the position coordinates of the user target, and the data transmission and reception coverage area.

[0031] The user target is located at the center of the nadir trajectory network of the low-Earth orbit satellite when it is in the target orbit, and the distance between the boundary of the nadir trajectory network and the user target is less than a first threshold.

[0032] Figure 2 This is a schematic diagram illustrating the normal evolution of the nadir trajectory of a low-Earth orbit satellite. Figure 2 The lines in the image represent the trajectory of the satellite's nadir point. Figure 2 The five-pointed star in the image represents the location of the user's target.Figure 2 The circles in the image represent the transmission and reception coverage circle, determined based on the location coordinates of the user target and its data transmission and reception coverage range. The length of the line within the transmission and reception coverage circle represents the length of time that the low-Earth orbit satellite can establish communication with the user target. Figure 2 It can be seen that after a certain period of satellite orbit change, the length of its nadir point trajectory within the coverage area will become shorter and shorter. Only lines that meet the preset length requirements can be used for communication, because if the communication time is too short, it will not be able to support the complete data transmission and reception process.

[0033] In this embodiment of the invention, based on the transmission and reception coverage circle of the user target, to ensure that a single low-Earth orbit satellite can provide routine communication guarantees for the user target, the trajectory network of the satellite's nadir should pass through the transmission and reception coverage circle as many times as possible, and the duration within the coverage circle should meet the communication time period requirements. When the satellite's orbital nadir trajectory network covers the user target as... Figure 3 In the state shown, the low-orbit satellite can ensure the longest service period and the most communications for the user target.

[0034] Figure 3 The lines in the diagram represent the nadir trajectory network of the low-Earth orbit satellite in the target orbit. The nadir trajectory network of the target orbit is derived from the nadir trajectory of the low-Earth orbit satellite during its ascent. Figure 3 The right-leaning lines in the middle) and the nadir trajectory of a low-orbit satellite in its descent state ( Figure 3 The left-leaning lines in the middle constitute the target. In other words, in order to achieve the goal of providing the longest service guarantee period and the most communication times for a single low-Earth orbit satellite to the user target, it should be ensured that the user target is located at the center of the nadir point trajectory network when the low-Earth orbit satellite is in the target orbit, and the distance between the boundary of the nadir point trajectory network and the user target is less than the first threshold.

[0035] By setting the user target to be at the center of the nadir trajectory network of the low-Earth orbit satellite in the target orbit, it can be ensured that the nadir trajectory network of the low-Earth orbit satellite passes through the user target's transmission and reception coverage circle the most times. It is required that the distance between the boundary of the nadir trajectory network and the user target be less than a first threshold, which is equivalent to limiting the range of changes in the orbital altitude of the low-Earth orbit satellite. If the distance increases, the orbital drift will increase, which will lead to a shortening of the service guarantee period. At this time, satellite orbit control is required.

[0036] For example, the orbital state first moves from west to east ( Figure 3 (From left to right) As the orbital altitude naturally decreases, if the orbital altitude is not intervened, the trajectory will continue eastward, which will compromise communication duration. Therefore, it is necessary to adjust its westward movement in a timely manner to form a "pipeline" around the user's target location (adjacent trajectories are close together, forming a "pipeline" shape), so that its sub-satellite point remains at... Figure 3The trajectory "pipeline" is shown. Based on the above analysis, it can be seen that this embodiment of the invention couples the orbital control quantities required for maintaining the low-Earth orbit satellite's own orbital altitude with the orbital control quantities required for ensuring satellite communication, thereby minimizing satellite fuel consumption.

[0037] Therefore, given the location coordinates of the user target and its data transmission and reception coverage area, it is necessary to determine the target orbit by combining the current orbit of the low-Earth orbit satellite, so as to maximize the coverage efficiency of the low-Earth orbit satellite for the user target. The method of determining the target orbit of the low-Earth orbit satellite based on the above information is a well-known technology in the field, and will not be described in detail here in the embodiments of the present invention.

[0038] Step S106: Determine the orbit control strategy for the low-Earth orbit satellite based on the current orbit and the target orbit.

[0039] The target orbit is the operational orbit of a low-Earth orbit (LEO) satellite when providing communication support to a user target. Therefore, given the current orbit of the LEO satellite, it is necessary to determine its orbit control strategy based on both the current and target orbits. The purpose of implementing the orbit control strategy is to adjust the LEO satellite from its current orbit to the target orbit. Methods for formulating orbit control strategies to adjust LEO satellites from one orbital state to another are well-known techniques in the field and will not be elaborated upon here.

[0040] Step S108: Control the orbital state of the low-orbit satellite based on the orbital control strategy so that the error between the controlled orbit and the target orbit is less than the second threshold.

[0041] Once the orbit control strategy is determined, it can be used to control the orbital state of the low-Earth orbit satellite. When the error between the controlled orbit and the target orbit is less than the second threshold, the current orbital state of the low-Earth orbit satellite is considered to meet the requirements of providing communication assurance for the user target.

[0042] This invention provides an integrated control method for low-Earth orbit (LEO) satellite communication and orbit maintenance. The method determines the target orbit of the LEO satellite based on its current orbit, the location coordinates of the user target, and the data transmission and reception coverage area of ​​the user target. The user target is located at the center of the sub-satellite trajectory network when the LEO satellite is in the target orbit, and the distance between the boundary of the sub-satellite trajectory network and the user target is less than a first threshold. This maximizes the service period and communication frequency of the LEO satellite for the user target, thereby achieving routine communication support for the user target using a single LEO satellite. Furthermore, this method integrates satellite communication and orbit maintenance, ensuring communication for the user target while minimizing satellite fuel consumption and optimizing long-term satellite management efficiency.

[0043] In an optional implementation, step S108, which controls the orbital state of the low-Earth orbit satellite based on an orbital control strategy to ensure that the error between the controlled orbit and the target orbit is less than a second threshold, specifically includes the following steps:

[0044] Step S1081: Use the orbit control strategy to control the orbital state of the low-Earth orbit satellite to obtain the controlled orbit.

[0045] Step S1082: Calculate the error between the controlled orbit and the target orbit to obtain the orbital error.

[0046] Step S1083: Determine whether the track error is less than the second threshold.

[0047] If yes, proceed to step S1084; if no, proceed to step S1085.

[0048] Step S1084: Maintain the controlled orbit.

[0049] Step S1085: Based on the post-controlled orbit and the target orbit, adjust the orbit control strategy of the low-orbit satellite until the error between the post-controlled orbit and the target orbit is less than the second threshold.

[0050] The orbit control strategy is a theoretical derivation. During implementation, various factors may cause the post-control effect to fall short of the ideal state. Therefore, after controlling the orbital state of the low-Earth orbit satellite using the orbit control strategy, it is necessary to further determine whether it has achieved the expected control objective. Specifically, this involves calculating the orbital error between the post-control orbit and the target orbit. If the orbital error is less than the second threshold, it indicates that the expectation has been achieved, and the current post-control orbit can be maintained. However, if the orbital error is greater than or equal to the second threshold, it indicates that the expectation has not been achieved, and the orbit control strategy of the low-Earth orbit satellite needs to be adjusted according to the current post-control orbit and the target orbit. This adjustment is continued until the error between the post-control orbit and the target orbit is less than the second threshold.

[0051] In an alternative implementation, after determining that the error between the controlled orbit and the target orbit is less than a second threshold, the method further includes the following steps:

[0052] Step S201: Obtain the first time period of the user target's request communication and the telemetry and control plan of the low-orbit satellite.

[0053] Step S202 involves extrapolating the target orbit to calculate the second time period of the data transmission and reception coverage area of ​​the low-orbit satellite covering the user target.

[0054] Step S203: Based on the first time period and the second time period, determine the communication plan between the low-orbit satellite and the user target.

[0055] Specifically, if the error between the controlled orbit and the target orbit of the low-Earth orbit satellite is less than the second threshold, it indicates that the low-Earth orbit satellite has met the optimal coverage requirement for the user target. Thus, the mission planning process can be carried out. On the one hand, the first time period of the user target's request for communication is obtained. On the other hand, the second time period of the data transmission and reception coverage range of the low-Earth orbit satellite over the user target is calculated by orbit extrapolation. Based on the above two time periods, the communication plan between the low-Earth orbit satellite and the user target can be determined.

[0056] In this embodiment of the invention, the intersection of the first time period and the second time period is taken as the time period corresponding to the communication plan. The communication plan refers to the process by which a low-Earth orbit satellite establishes a two-way connection with a user target to transmit and receive data.

[0057] Step S204: Based on the communication plan and the telemetry and control plan, determine the onboard payload control plan and the data transmission plan between the low-Earth orbit satellite and the user center.

[0058] Figure 4 This illustration shows a satellite communication support scenario provided by an embodiment of the present invention. Based on a determined communication plan, the embodiment formulates an on-board payload control plan according to the low-Earth orbit (LEO) satellite's telemetry and control plan, under the constraint that the on-board payload control plan precedes the communication plan by a preset time period. It also formulates a data transmission plan according to the constraint that the data transmission plan follows the communication plan. The on-board payload control plan refers to the process of uploading the payload control commands required for the communication plan to the LEO satellite through satellite telemetry and control before the communication plan is implemented. The data transmission plan refers to the process of sending the data received by the LEO satellite to the user center through satellite telemetry and control after the communication plan is completed. In other words, the user center receives the user target data forwarded by the LEO satellite during the time period corresponding to the data transmission plan.

[0059] Optionally, the onboard payload control plan and data transmission plan are planned according to the constraints one hour before the communication plan and the constraints after the communication plan, and each plan is sent to the ground user center.

[0060] In one optional embodiment, the method of the present invention further includes the following:

[0061] Periodically monitor the nadir trajectory of low-Earth orbit (LEO) satellites; if it is determined that the nadir trajectory of a LEO satellite exceeds the boundary of the nadir trajectory network of the target orbit, update the LEO satellite's orbit control strategy based on the LEO satellite's current orbit and the target orbit, so as to enable LEO satellites to provide routine coverage of user targets.

[0062] In other words, after discovering that the satellite's orbit exceeds... Figure 3When the trajectory "pipeline" boundary is reached in the example, the orbit control strategy is calculated again and orbit control is completed according to the target orbit that meets the required orbit characteristics as planned in the early stage, so as to control the low-orbit satellite to achieve normal coverage of the user target.

[0063] In summary, this invention, based on the orbital characteristics of low-Earth orbit (LEO) communication satellites, conducts orbital analysis according to the location coordinates, time period, and data transmission / reception capabilities of user targets. It proposes a method that comprehensively considers satellite communication planning and orbit maintenance. This method can improve the support efficiency for specific user targets when the number of LEO satellites is insufficient. Simultaneously, it achieves integrated planning of satellite communication and orbit maintenance, enabling satellites to provide satellite communication support services for the longest possible time with limited fuel, thus optimizing the long-term management efficiency of satellites. Furthermore, based on this invention, by rationally planning the positions of ground targets, the communication needs of multiple targets can also be guaranteed.

[0064] Example 2

[0065] This invention also provides an integrated control device for low-Earth orbit satellite communication and orbit maintenance. This device is mainly used to execute the integrated control method for low-Earth orbit satellite communication and orbit maintenance provided in Embodiment 1 above. The device provided in this invention will be described in detail below.

[0066] Figure 5 This is a functional block diagram of an integrated control device for low-Earth orbit satellite communication and orbit maintenance provided in an embodiment of the present invention, as shown below. Figure 5 As shown, the device mainly includes: a first acquisition module 10, a first determination module 20, a second determination module 30, and a control module 40, wherein:

[0067] The first acquisition module 10 is used to acquire the current orbit of the low-orbit satellite, the position coordinates of the user target, and the data transmission and reception coverage of the user target.

[0068] The first determining module 20 is used to determine the target orbit of the low-Earth orbit satellite based on the current orbit of the low-Earth orbit satellite, the position coordinates of the user target, and the data transmission and reception coverage area; wherein the user target is located at the center of the nadir point trajectory network when the low-Earth orbit satellite is in the target orbit, and the distance between the boundary of the nadir point trajectory network and the user target is less than a first threshold.

[0069] The second determining module 30 is used to determine the orbit control strategy for low-orbit satellites based on the current orbit and the target orbit.

[0070] The control module 40 is used to control the orbital state of the low-orbit satellite based on the orbital control strategy, so that the error between the controlled orbit and the target orbit is less than a second threshold.

[0071] This invention provides an integrated control device for low-Earth orbit (LEO) satellite communication and orbit maintenance. The device determines the target orbit of the LEO satellite based on its current orbit, the location coordinates of the user target, and the data transmission and reception coverage area of ​​the user target. The user target is located at the center of the sub-satellite trajectory network when the LEO satellite is in the target orbit, and the distance between the boundary of the sub-satellite trajectory network and the user target is less than a first threshold. This maximizes the service period and communication frequency of the LEO satellite for the user target, thereby achieving routine communication support for the user target using a single LEO satellite. Furthermore, this method integrates satellite communication and orbit maintenance, ensuring communication for the user target while minimizing satellite fuel consumption and optimizing long-term satellite management efficiency.

[0072] Optionally, the control module is specifically used for:

[0073] By using orbit control strategies to control the orbital state of low-Earth orbit satellites, the controlled orbit can be obtained.

[0074] The error between the controlled orbit and the target orbit is calculated to obtain the orbital error.

[0075] Determine whether the orbital error is less than the second threshold.

[0076] If so, then maintain the controlled trajectory.

[0077] If not, then based on the post-controlled orbit and the target orbit, adjust the orbit control strategy of the low-Earth orbit satellite until the error between the post-controlled orbit and the target orbit is less than the second threshold.

[0078] Optionally, the device further includes:

[0079] The second acquisition module is used to acquire the first time period of the user target's request communication and the telemetry and control plan of the low-orbit satellite.

[0080] The calculation module is used to calculate the second time period of data transmission and reception coverage of the user target by extrapolating the target orbit.

[0081] The third determining module is used to determine the communication plan between the low-orbit satellite and the user target based on the first time period and the second time period.

[0082] The fourth determination module is used to determine the onboard payload control plan and the data transmission plan between the low-Earth orbit satellite and the user center based on the communication plan and the telemetry and control plan.

[0083] Optionally, the device further includes:

[0084] The monitoring module is used to periodically monitor the nadir trajectory of low-orbit satellites.

[0085] The update module is used to update the orbit control strategy of the low-Earth orbit satellite based on its current orbit and the target orbit when the satellite's nadir point trajectory exceeds the boundary of the target orbit's nadir point trajectory network, so as to enable the low-Earth orbit satellite to provide normalized coverage of the user's target.

[0086] Example 3

[0087] See Figure 6 This invention provides an electronic device, which includes a processor 60, a memory 61, a bus 62, and a communication interface 63. The processor 60, the communication interface 63, and the memory 61 are connected via the bus 62. The processor 60 is used to execute executable modules, such as computer programs, stored in the memory 61.

[0088] The memory 61 may include high-speed random access memory (RAM) or non-volatile memory, such as at least one disk storage device. Communication between this system network element and at least one other network element is achieved through at least one communication interface 63 (which can be wired or wireless), such as the Internet, wide area network, local area network, metropolitan area network, etc.

[0089] Bus 62 can be an ISA bus, PCI bus, or EISA bus, etc. The bus can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 6 The symbol is represented by a single double-headed arrow, but this does not mean that there is only one bus or one type of bus.

[0090] The memory 61 is used to store programs. After receiving an execution instruction, the processor 60 executes the program. The method executed by the apparatus defined by the process disclosed in any of the foregoing embodiments of the present invention can be applied to the processor 60 or implemented by the processor 60.

[0091] Processor 60 may be an integrated circuit chip with signal processing capabilities. In implementation, each step of the above method can be completed by the integrated logic circuitry in the hardware of processor 60 or by instructions in software form. Processor 60 can be a general-purpose processor, including a Central Processing Unit (CPU), a Network Processor (NP), etc.; it can also be a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field-Programmable Gate Array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. It can implement or execute the methods, steps, and logic block diagrams disclosed in the embodiments of this invention. The general-purpose processor can be a microprocessor or any conventional processor. The steps of the methods disclosed in the embodiments of this invention can be directly embodied in the execution of a hardware decoding processor, or executed by a combination of hardware and software modules in the decoding processor. The software modules can reside in random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, or other mature storage media in the art. The storage medium is located in memory 61. Processor 60 reads the information in memory 61 and, in conjunction with its hardware, completes the steps of the above method.

[0092] The computer program product of the integrated control method and apparatus for low-Earth orbit satellite communication and orbit maintenance provided in this embodiment of the invention includes a computer-readable storage medium storing non-volatile program code executable by a processor. The instructions included in the program code can be used to execute the methods described in the preceding method embodiments. For specific implementation, please refer to the method embodiments, which will not be repeated here.

[0093] In addition, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit.

[0094] If the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a processor-executable, non-volatile, computer-readable storage medium. Based on this understanding, the technical solution of this invention, essentially, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0095] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0096] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. In addition, the terms "first," "second," "third," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0097] Furthermore, terms such as "horizontal," "vertical," and "sag" do not imply that components must be absolutely horizontal or suspended, but rather that they can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0098] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0099] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An integrated control method for low-Earth orbit satellite communication and orbit maintenance, characterized in that, The method comprises: acquiring a current orbit of a low-orbit satellite, position coordinates of a user target, and a data transmission coverage range of the user target; determining a target orbit of the low-orbit satellite based on the current orbit of the low-orbit satellite, the position coordinates of the user target, and the data transmission coverage range, wherein the user target is located at the center of a footprint network of the low-orbit satellite when the low-orbit satellite is in the target orbit, and the distance between the boundary of the footprint network and the user target is less than a first threshold value; the footprint network of the target orbit is composed of a footprint in a state of orbit raising of the low-orbit satellite and a footprint in a state of orbit lowering of the low-orbit satellite; determining an orbit control strategy of the low-orbit satellite based on the current orbit and the target orbit; controlling the orbit state of the low-orbit satellite based on the orbit control strategy, so that the error between the controlled orbit and the target orbit is less than a second threshold value.

2. The integrated control method of low earth orbit satellite communication and orbit maintenance according to claim 1, wherein, controlling the orbit state of the low-orbit satellite based on the orbit control strategy, so that the error between the controlled orbit and the target orbit is less than a second threshold value, comprises: controlling the orbit state of the low-orbit satellite by using the orbit control strategy to obtain a controlled orbit; calculating the error between the controlled orbit and the target orbit to obtain an orbit error; determining whether the orbit error is less than the second threshold value; if yes, maintaining the controlled orbit; if no, adjusting the orbit control strategy of the low-orbit satellite based on the controlled orbit and the target orbit until the error between the controlled orbit and the target orbit is less than the second threshold value. 3.The method of claim 1, wherein, After determining that the error between the controlled orbit and the target orbit is less than the second threshold value, the method further comprises: acquiring a first time period of a requested communication of the user target and a measurement and control plan of the low-orbit satellite; calculating a second time period of a data transmission coverage range of the low-orbit satellite covering the user target by orbit extrapolation on the target orbit; determining a communication plan of the low-orbit satellite and the user target based on the first time period and the second time period; determining a satellite-borne load control plan and a data transmission plan between the low-orbit satellite and the user center based on the communication plan and the measurement and control plan. 4.The method of claim 1, wherein The method further comprises: periodically monitoring the footprint of the low-orbit satellite; in a case where it is determined that the footprint of the low-orbit satellite exceeds the boundary of the footprint network of the target orbit, updating the orbit control strategy of the low-orbit satellite based on the current orbit of the low-orbit satellite and the target orbit, so that the low-orbit satellite normally covers the user target.

5. An integrated control device for low earth orbit satellite communication and orbit maintenance, characterized by, The method comprises: a first acquisition module configured to acquire a current orbit of a low-orbit satellite, position coordinates of a user target, and a data transmission coverage range of the user target; The first determining module is configured to determine a target orbit of the low-orbit satellite based on a current orbit of the low-orbit satellite, a position coordinate of the user target, and the data transceiving coverage range; wherein the user target is located at a center of a footprint network of the low-orbit satellite when the low-orbit satellite is in the target orbit, and a distance between a boundary of the footprint network and the user target is less than a first threshold value; the footprint network of the target orbit is composed of a footprint in a state of orbit raising of the low-orbit satellite and a footprint in a state of orbit lowering of the low-orbit satellite; The second determining module is configured to determine an orbit control strategy of the low-orbit satellite based on the current orbit and the target orbit; The control module is configured to control an orbit state of the low-orbit satellite based on the orbit control strategy, so that an error between a controlled orbit and the target orbit is less than a second threshold value.

6. The integrated control of low earth orbit satellite communications and orbit maintenance apparatus of claim 5, wherein, The control module is specifically configured to: control the orbit state of the low-orbit satellite by using the orbit control strategy to obtain the controlled orbit; calculate the error between the controlled orbit and the target orbit to obtain an orbit error; determine whether the orbit error is less than the second threshold value; if yes, maintain the controlled orbit; if no, adjust the orbit control strategy of the low-orbit satellite based on the controlled orbit and the target orbit until the error between the controlled orbit and the target orbit is less than the second threshold value.

7. The integrated control of low earth orbit satellite communications and orbit maintenance apparatus of claim 5, wherein, The device further comprises: The second obtaining module is configured to obtain a first time period of a requested communication of the user target and a measurement and control plan of the low-orbit satellite; The calculation module is configured to calculate a second time period of the data transceiving coverage range of the low-orbit satellite covering the user target by orbit extrapolation on the target orbit; The third determining module is configured to determine a communication plan of the low-orbit satellite and the user target based on the first time period and the second time period; The fourth determining module is configured to determine an on-satellite payload control plan and a data transmission plan between the low-orbit satellite and the user center based on the communication plan and the measurement and control plan.

8. The integrated control of low earth orbit satellite communications and orbit maintenance apparatus of claim 5, wherein, The device further comprises: The monitoring module is configured to periodically monitor a footprint of the low-orbit satellite; The updating module is configured to update the orbit control strategy of the low-orbit satellite based on the current orbit of the low-orbit satellite and the target orbit in a case where it is determined that the footprint of the low-orbit satellite exceeds a boundary of the footprint network of the target orbit, so that the low-orbit satellite normally covers the user target.

9. An electronic device comprising a memory, a processor, said memory having stored thereon a computer program operable to run on said processor, characterized in that, The processor executes the computer program to implement the steps of the integrated control method for low-orbit satellite communication and orbit maintenance according to any one of claims 1 to 4.

10. A computer-readable storage medium, characterized in that, The computer readable storage medium stores computer instructions, and the computer instructions are executed by the processor to implement the integrated control method for low-orbit satellite communication and orbit maintenance according to any one of claims 1 to 4.

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