CN111532455B - Method, device, equipment and storage medium for realizing satellite drift of synchronous orbit - Google Patents

Method, device, equipment and storage medium for realizing satellite drift of synchronous orbit Download PDF

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CN111532455B
CN111532455B CN202010247249.8A CN202010247249A CN111532455B CN 111532455 B CN111532455 B CN 111532455B CN 202010247249 A CN202010247249 A CN 202010247249A CN 111532455 B CN111532455 B CN 111532455B
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orbit satellite
parameters
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parameter
satellite
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CN111532455A (en
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赵悦
杨学猛
张东旭
许珩
盖琦超
张维奇
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China Satellite Communications Co Ltd
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    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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Abstract

本申请公开了一种实现同步轨道卫星漂星的方法及装置,该方法包括:接收输入的漂星任务信息以及目标同步轨道卫星的第一系统参数,并根据所述第一系统参数以及所述漂星任务信息确定至少一个同步轨道卫星的第二系统参数,其中,所述至少一个同步轨道卫星是指与所述目标同步轨道卫星邻近的卫星;根据所述漂星任务信息、所述第一系统参数以及所述第二系统参数确定起漂参数以及捕获参数;根据所述起漂参数以及所述捕获参数生成控制指令,并将所述控制指令发送给所述目标同步轨道卫星,其中,所述控制指令用于控制所述目标同步轨道卫星移动到预设的目标轨位。本申请解决了现有技术中可靠性较低的技术问题。

Figure 202010247249

The present application discloses a method and device for realizing synchronous orbit satellite drift. The method includes: receiving input star drift task information and first system parameters of a target synchronous orbit satellite, and according to the first system parameters and the The star drift task information determines the second system parameter of at least one synchronous orbit satellite, wherein the at least one synchronous orbit satellite refers to a satellite adjacent to the target synchronous orbit satellite; according to the drift star task information, the first The system parameter and the second system parameter determine the drift parameter and the acquisition parameter; generate a control instruction according to the drift parameter and the acquisition parameter, and send the control instruction to the target synchronous orbit satellite, wherein the The control instruction is used to control the target synchronous orbit satellite to move to a preset target orbit position. The present application solves the technical problem of low reliability in the prior art.

Figure 202010247249

Description

Method, device, equipment and storage medium for realizing satellite drift of synchronous orbit
Technical Field
The application relates to the technical field of spacecraft control, in particular to a method and a device for realizing satellite drifting of a synchronous orbit satellite.
Background
A geosynchronous orbit satellite refers to a satellite that surrounds the earth, the sun, or stars, etc. and moves in a specific orbit, for example, a geosynchronous orbit satellite, a solar geosynchronous orbit satellite, etc., in which the geosynchronous orbit satellite is in a relatively stationary state with respect to the earth, the sun, or stars, etc. After a geostationary orbit satellite enters orbit, the satellite will typically provide full life service at a certain location until the on-board fuel is exhausted, but to meet different requirements, the satellite needs to be controlled to move from the current orbit position to the target orbit position to perform a specific task, an operation known as "floating star".
At present, a common method for realizing satellite drift of a synchronous orbit satellite is as follows: and calculating a floating satellite parameter and a capturing parameter according to the satellite rail position information and preset target rail position information, and further controlling the satellite to realize floating satellite operation according to the floating satellite parameter and the capturing parameter. With the rapid development of satellite communication technology, the number of on-orbit satellites is more and more, and not only the factors of the satellites but also the influence factors on other satellites need to be considered in the satellite floating process, so that the method for realizing satellite floating of the synchronous orbit satellite in the prior art only considers the system parameters of the satellite, and the reliability of the prior art is lower.
Disclosure of Invention
The technical problem that this application was solved is: aiming at the problem of lower reliability of the prior art, the method and the device for realizing satellite floating of the synchronous orbit satellite are provided, and in the satellite floating process of the target synchronous orbit satellite, not only the self factors of the target synchronous orbit satellite but also the influence factors on other satellites need to be considered, so that the reliability of the scheme is improved.
In a first aspect, an embodiment of the present application provides a method for implementing synchronous orbit satellite drifting, where the method includes:
receiving input floating satellite task information and a first system parameter of a target synchronous orbit satellite, and determining a second system parameter of at least one synchronous orbit satellite according to the first system parameter and the floating satellite task information, wherein the at least one synchronous orbit satellite is a satellite adjacent to the target synchronous orbit satellite;
determining a floating starting parameter and a capturing parameter according to the floating star task information, the first system parameter and the second system parameter;
and generating a control instruction according to the drift parameter and the capture parameter, and sending the control instruction to the target synchronous orbit satellite, wherein the control instruction is used for controlling the target synchronous orbit satellite to move to a preset target orbit position.
In the scheme provided by the embodiment of the application, the computer equipment determines the floating starting parameter and the capturing parameter according to floating satellite task information, the target synchronous orbit satellite and system parameters of the synchronous orbit satellite adjacent to or co-located with the target synchronous orbit satellite, then generates a control instruction according to the floating starting parameter and the capturing parameter, and controls the target synchronous orbit satellite according to the control instruction to realize the floating satellite operation. Therefore, in the scheme provided by the embodiment of the application, in the drifting process of the target synchronous orbit satellite, not only the self factors of the target synchronous orbit satellite but also the influence factors on other satellites need to be considered, so that the reliability of the scheme is improved.
Optionally, determining a drift starting parameter and a capture parameter according to the floating star task information, the first system parameter, and the second system parameter includes:
calculating the floating starting parameters according to the floating star task information, the first system parameters, the second system parameters and a preset first constraint condition, wherein the floating starting parameters comprise floating starting times, floating starting speed increment of each time and floating starting time;
and calculating the capturing parameters according to the floating star task information, the first system parameters, the second system parameters and a preset second constraint condition, wherein the capturing parameters comprise capturing times, capturing speed increment each time and capturing time.
Optionally, the first constraint condition includes: calculating according to the each time drift-up speed increment and the drift-up time to obtain that a first distance between the target synchronous orbit satellite and an adjacent synchronous orbit satellite is not less than a preset first threshold value; calculating to obtain that the orbit eccentricity ratio of the target synchronous orbit satellite is smaller than a preset second threshold value according to the each time drift starting speed increment and the drift starting time;
the second constraint includes: calculating according to the capturing speed increment and the capturing time each time to obtain a second distance between the target synchronous orbit satellite and an adjacent synchronous orbit satellite, wherein the second distance is not smaller than a preset third threshold value; the total capture velocity increment is equal in magnitude and opposite in direction to the total drift star velocity increment.
Optionally, before generating a control instruction according to the floating parameter and the capture parameter, the method further includes:
establishing a synchronous orbit satellite simulation model, and taking the floating parameter and the capturing parameter as input parameters of the synchronous orbit satellite simulation model, wherein the system parameters of the synchronous orbit satellite simulation model are consistent with the first system parameters;
controlling the synchronous orbit satellite simulation model to operate according to the floating parameter and the capturing parameter to obtain an operation result;
judging whether the running result reaches the preset target rail position or not;
and if not, re-determining the floating parameters and the capture parameters until the preset target rail position is reached.
In the scheme provided by the embodiment of the application, the computer equipment carries out simulation verification on the determined floating satellite parameters and the determined capture parameters by establishing a synchronous orbit satellite simulation model, and judges whether the target orbit satellite can reach the preset target orbit position; and if not, re-determining the floating parameters and the capture parameters until the preset target rail position is reached. Therefore, the scheme that the elimination distance does not meet the requirement is calculated through simulation, and the collision risk of the target synchronous orbit satellite and the adjacent or co-located synchronous satellite in the satellite floating process is effectively reduced.
In a second aspect, an embodiment of the present application provides an apparatus for implementing synchronous orbit satellite drifting, where the apparatus includes:
the system comprises a first determining unit, a second determining unit and a third determining unit, wherein the first determining unit is used for receiving input floating satellite task information and first system parameters of a target synchronous orbit satellite and determining second system parameters of at least one synchronous orbit satellite according to the first system parameters and the floating satellite task information, and the at least one synchronous orbit satellite refers to a satellite adjacent to the target synchronous orbit satellite;
the second determining unit is used for determining a floating parameter and a capturing parameter according to the floating star task information, the first system parameter and the second system parameter;
and the generating unit is used for generating a control instruction according to the floating parameter and the capturing parameter and sending the control instruction to the target synchronous orbit satellite, wherein the control instruction is used for controlling the target synchronous orbit satellite to move to a preset target orbit position.
Optionally, the second determining unit is specifically configured to:
calculating the floating starting parameters according to the floating star task information, the first system parameters, the second system parameters and a preset first constraint condition, wherein the floating starting parameters comprise floating starting times, floating starting speed increment of each time and floating starting time;
and calculating the capturing parameters according to the floating star task information, the first system parameters, the second system parameters and a preset second constraint condition, wherein the capturing parameters comprise capturing times, capturing speed increment each time and capturing time.
Optionally, the first constraint condition includes: calculating according to the each time drift-up speed increment and the drift-up time to obtain that a first distance between the target synchronous orbit satellite and an adjacent synchronous orbit satellite is not less than a preset first threshold value; calculating to obtain that the orbit eccentricity ratio of the target synchronous orbit satellite is smaller than a preset second threshold value according to the each time drift starting speed increment and the drift starting time;
the second constraint includes: calculating according to the capturing speed increment and the capturing time each time to obtain a second distance between the target synchronous orbit satellite and an adjacent synchronous orbit satellite, wherein the second distance is not smaller than a preset third threshold value; the total capture velocity increment is equal in magnitude and opposite in direction to the total drift star velocity increment.
Optionally, the apparatus further includes a simulation unit; the simulation unit is specifically configured to:
establishing a synchronous orbit satellite simulation model, and taking the floating parameter and the capturing parameter as input parameters of the synchronous orbit satellite simulation model, wherein the system parameters of the synchronous orbit satellite simulation model are consistent with the first system parameters;
controlling the synchronous orbit satellite simulation model to operate according to the floating parameter and the capturing parameter to obtain an operation result;
judging whether the running result reaches the preset target rail position or not;
and if not, re-determining the floating parameters and the capture parameters until the preset target rail position is reached.
In a third aspect, the present application provides a computer device, comprising:
a memory for storing instructions for execution by at least one processor;
a processor for executing instructions stored in a memory to perform the method of the first aspect.
In a fourth aspect, the present application provides a computer readable storage medium having stored thereon computer instructions which, when run on a computer, cause the computer to perform the method of the first aspect.
Drawings
Fig. 1 is a schematic structural diagram of a system for implementing synchronous orbit satellite drifting according to an embodiment of the present disclosure;
fig. 2 is a schematic flowchart of a method for implementing satellite drifting in a synchronous orbit according to an embodiment of the present disclosure;
fig. 3 is a schematic structural diagram of an apparatus for implementing synchronous orbit satellite drifting according to an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of an apparatus for implementing synchronous orbit satellite drifting according to an embodiment of the present disclosure;
fig. 5 is a schematic structural diagram of a computer device according to an embodiment of the present application.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
Referring to fig. 1, an embodiment of the present application provides a system for implementing floating of a synchronous orbit satellite, the system including a computer device 1, a target synchronous orbit satellite 2, and at least one synchronous orbit satellite 3, wherein the computer device 1 is configured to acquire system parameters of the target synchronous orbit satellite 2 and the at least one synchronous orbit satellite 3, determine floating parameters and capturing parameters of the target synchronous orbit satellite 2 according to the system parameters, generate a control instruction according to the floating parameters and the capturing parameters, and send the control instruction to the target synchronous orbit satellite 2; the target synchronous orbit satellite 2 is used for realizing the floating satellite operation according to the control instruction.
It should be understood that the solution provided by the embodiments of the present application provides that at least one geostationary orbit satellite 3 is a neighboring or co-located satellite of the target geostationary orbit satellite 2.
The method for realizing the drift of the geostationary orbit satellite provided by the embodiment of the present application is further described in detail with reference to the drawings in the specification, and a specific implementation manner of the method may include the following steps (a method flow is shown in fig. 2):
step 201, a computer device receives input floating satellite task information and a first system parameter of a target synchronous orbit satellite, and determines a second system parameter of at least one synchronous orbit satellite according to the first system parameter and the floating satellite task information, wherein the at least one synchronous orbit satellite is a satellite adjacent to or co-located with the target synchronous orbit satellite.
Specifically, in the solution provided in the embodiment of the present application, the target geostationary orbit satellite refers to a geostationary orbit satellite that performs a floating satellite operation. The first system parameters comprise operation and state parameters of each subsystem in the target synchronous orbit satellite, operation parameters of the target synchronous orbit satellite, attitude and orbit parameters of the target synchronous orbit satellite and the like. For example, for the telemetry and telecontrol subsystem, the first system parameters include link, equipment and software states, uplink and downlink frequency point use conditions and the like; for the attitude and orbit control subsystem, the first system parameters comprise link, equipment and software states, satellite attitude bias conditions, ground-sensitive interference protection conditions and the like; for the propulsion subsystem, the first system parameters comprise link, equipment and software states, thruster branching, configuration, efficiency and the like; for the power subsystem, the first system parameters comprise link, equipment and software states, energy use evaluation in the illumination period and the ground shadow period, advance/lag conditions of the solar sailboard and the like; for the temperature control subsystem, the first system parameters comprise link, equipment and software states, temperature change conditions of the whole satellite and key devices and the like; for the integrated electronic subsystem, the first system parameters comprise link, equipment, software state and the like; for the payload subsystem, the first system parameters include link, device, software status, etc. The floating satellite task information comprises preset target track position information, time for reaching the target track position, position keeping precision and the like.
Further, after receiving the floating satellite task information and the first system parameter of the target synchronous orbit satellite, the computer device determines the second system parameter of at least one synchronous orbit satellite according to the first system parameter and the floating satellite task information.
In one possible implementation, determining a second system parameter of at least one geostationary orbit satellite according to the first system parameter and the floating satellite mission information includes: determining an initial floating orbit of the target synchronous orbit satellite according to the first system parameter; and determining the at least one synchronous orbit satellite and the second system parameter according to the initial floating orbit and the floating satellite task information.
Further, in the solution provided in this embodiment of the present application, the computer device needs to determine the system parameters of the computer device in addition to the first system parameter and the second system parameter, for example, the system parameters of the computer device themselves include: in a computing device, measuring and controlling antenna system parameters and measuring and controlling rail system parameters, for example, the measuring and controlling antenna system parameters include: available antennas, the support capability of each sector of the antenna in the drift star longitude range, antenna sector switching plans and the like; and ground measurement and control equipment states such as a server, a baseband, a frequency converter, a low-noise amplifier and the like; for example, the measured rail system parameters include available antennas, the support capability of each sector of the antenna in the drift star longitude range, antenna sector switching plans, and the like; system device states, such as states of a server, a baseband, a frequency converter, a low-noise amplifier and other main and standby devices; system monitoring, scheduling, orbit determination software status, and the like.
Step 202, the computer device determines a floating parameter and a capturing parameter according to the floating star task information, the first system parameter and the second system parameter.
Specifically, after determining the first system parameter and the second system parameter, the computer device determines a drift starting parameter and a capture parameter according to the first system parameter, the second system parameter and the floating star task information. In the solution provided in the embodiment of the present application, there are various ways for the computer device to determine the attack drift parameter and the capture parameter, and a preferred way is described as an example below.
In one possible implementation, determining a drift parameter and a capture parameter according to the floating star task information, the first system parameter and the second system parameter includes: calculating the floating starting parameters according to the floating star task information, the first system parameters, the second system parameters and a preset first constraint condition, wherein the floating starting parameters comprise floating starting times, floating starting speed increment of each time and floating starting time; and calculating the capturing parameters according to the floating star task information, the first system parameters, the second system parameters and a preset second constraint condition, wherein the capturing parameters comprise capturing times, capturing speed increment each time and capturing time.
Specifically, in order to move the target geostationary orbit satellite to the preset target orbit position, in the solution provided in the embodiment of the present application, at least two floating operations in the same direction and at least two capturing operations in the opposite direction need to be performed. In the process of floating the target synchronous orbit satellite, in order to ensure that the target synchronous orbit satellite collides with an adjacent or co-located orbit satellite, a first constraint condition of floating satellite operation and a second constraint condition of acquisition operation are preset in a database of a computer device.
In one possible implementation, the first constraint includes: calculating according to the each time drift-up speed increment and the drift-up time to obtain that a first distance between the target synchronous orbit satellite and an adjacent synchronous orbit satellite is not less than a preset first threshold value; calculating to obtain that the orbit eccentricity ratio of the target synchronous orbit satellite is smaller than a preset second threshold value according to the each time drift starting speed increment and the drift starting time; the second constraint includes: calculating according to the capturing speed increment and the capturing time each time to obtain a second distance between the target synchronous orbit satellite and an adjacent synchronous orbit satellite, wherein the second distance is not smaller than a preset third threshold value; the total capture velocity increment is equal in magnitude and opposite in direction to the total drift star velocity increment.
Specifically, the computer device determines the orbit information of any one of the at least one geostationary orbit satellite according to the second system parameter, determines the number of floating operations, the floating speed increment of each floating operation and the floating time according to the initial floating orbit of the target geostationary orbit satellite, the orbit information of any one of the geostationary orbit satellites and a preset first constraint condition, and determines the number of acquisition operations, the acquisition speed increment of each acquisition operation and the acquisition time according to the initial floating orbit, the orbit information of any one of the geostationary orbit satellites and a preset second constraint condition.
Step 203, the computer device generates a control instruction according to the floating parameter and the capturing parameter, and sends the control instruction to the target synchronous orbit satellite, wherein the control instruction is used for controlling the target synchronous orbit satellite to move to a preset target orbit position.
Specifically, after determining the drift parameter and the capture parameter, the computer device packages the drift parameter and the capture parameter to generate a control instruction, and sends the control instruction to the target synchronous orbit satellite; and the target synchronous orbit satellite receives the control instruction, and controls the target synchronous orbit satellite to float and capture according to the floating starting parameter and the capturing parameter carried by the control instruction, so that the target synchronous orbit satellite moves to a preset target orbit position from the current orbit.
Further, in order to ensure that the target geostationary orbit satellite can accurately move to the preset target orbit position, in the solution provided in this embodiment of the application, before step 203, the solution further includes:
establishing a synchronous orbit satellite simulation model, and taking the floating parameter and the capturing parameter as input parameters of the synchronous orbit satellite simulation model, wherein the system parameters of the synchronous orbit satellite simulation model are consistent with the first system parameters; controlling the synchronous orbit satellite simulation model to operate according to the floating parameter and the capturing parameter to obtain an operation result; judging whether the running result reaches the preset target rail position or not; and if not, re-determining the floating parameters and the capture parameters until the preset target rail position is reached.
Further, in order to ensure that the target synchronous orbit satellite smoothly moves to a preset target orbit position, in the scheme provided by the embodiment of the application, in the satellite floating process of the target synchronous orbit satellite, the target synchronous orbit satellite needs to forecast the earth shadow period in real time by using satellite orbit tool software, determine the earth shadow emergence time, estimate the charging and discharging conditions of a battery, and ensure that the energy supply on the satellite meets the requirements; for the satellite adopting the earth sensor to carry out attitude control, day/month interference forecast is needed to be carried out on earth sensitivity, and an earth sensitivity interference protection plan is made in advance to ensure the smoothness of an instruction channel.
In the scheme provided by the embodiment of the application, the computer equipment determines the floating starting parameter and the capturing parameter according to floating satellite task information, the target synchronous orbit satellite and the system parameter of the synchronous orbit satellite adjacent to or co-located with the target synchronous orbit satellite, then generates a control instruction according to the floating starting parameter and the capturing parameter, and controls the target synchronous orbit satellite according to the control instruction to realize the floating satellite operation. Therefore, in the scheme provided by the embodiment of the application, in the drifting process of the target synchronous orbit satellite, not only the self factors of the target synchronous orbit satellite but also the influence factors on other satellites need to be considered, so that the reliability of the scheme is improved.
Based on the same inventive concept as the method shown in fig. 2, the embodiment of the present application provides an apparatus for implementing synchronous orbit satellite drift, which includes, referring to fig. 3:
a first determining unit 301, configured to receive input floating satellite task information and a first system parameter of a target synchronous orbit satellite, and determine a second system parameter of at least one synchronous orbit satellite according to the first system parameter and the floating satellite task information, where the at least one synchronous orbit satellite is a satellite adjacent to the target synchronous orbit satellite;
a second determining unit 302, configured to determine a floating parameter and a capturing parameter according to the floating star task information, the first system parameter, and the second system parameter;
a generating unit 303, configured to generate a control instruction according to the floating parameter and the capturing parameter, and send the control instruction to the target synchronous orbit satellite, where the control instruction is used to control the target synchronous orbit satellite to move to a preset target orbit position.
Optionally, the second determining unit 302 is specifically configured to:
calculating the floating starting parameters according to the floating star task information, the first system parameters, the second system parameters and a preset first constraint condition, wherein the floating starting parameters comprise floating starting times, floating starting speed increment of each time and floating starting time;
and calculating the capturing parameters according to the floating star task information, the first system parameters, the second system parameters and a preset second constraint condition, wherein the capturing parameters comprise capturing times, capturing speed increment each time and capturing time.
Optionally, the first constraint condition includes: calculating according to the each time drift-up speed increment and the drift-up time to obtain that a first distance between the target synchronous orbit satellite and an adjacent synchronous orbit satellite is not less than a preset first threshold value; calculating to obtain that the orbit eccentricity ratio of the target synchronous orbit satellite is smaller than a preset second threshold value according to the each time drift starting speed increment and the drift starting time;
the second constraint includes: calculating according to the capturing speed increment and the capturing time each time to obtain a second distance between the target synchronous orbit satellite and an adjacent synchronous orbit satellite, wherein the second distance is not smaller than a preset third threshold value; the total capture velocity increment is equal in magnitude and opposite in direction to the total drift star velocity increment.
Optionally, referring to fig. 4, the apparatus further includes a simulation unit 304; the simulation unit 304 is specifically configured to:
establishing a synchronous orbit satellite simulation model, and taking the floating parameter and the capturing parameter as input parameters of the synchronous orbit satellite simulation model, wherein the system parameters of the synchronous orbit satellite simulation model are consistent with the first system parameters;
controlling the synchronous orbit satellite simulation model to operate according to the floating parameter and the capturing parameter to obtain an operation result;
judging whether the running result reaches the preset target rail position or not;
and if not, re-determining the floating parameters and the capture parameters until the preset target rail position is reached.
Referring to fig. 5, the present application provides a computer device comprising:
a memory 501 for storing instructions for execution by at least one processor;
a processor 502 for executing instructions stored in memory to perform the method described in fig. 2.
A computer-readable storage medium having stored thereon computer instructions which, when executed on a computer, cause the computer to perform the method of fig. 2.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.

Claims (8)

1.一种实现同步轨道卫星漂星的方法,其特征在于,包括:1. a method for realizing synchronous orbit satellite drift star, is characterized in that, comprises: 接收输入的漂星任务信息以及目标同步轨道卫星的第一系统参数,并根据所述第一系统参数以及所述漂星任务信息确定至少一个同步轨道卫星的第二系统参数,其中,所述至少一个同步轨道卫星是指与所述目标同步轨道卫星邻近的卫星;漂星任务信息包括预设的目标轨位信息、到达目标轨位的时间以及位保持精度;第一系统参数包括目标同步轨道卫星中各子系统的运行及状态参数,目标同步轨道卫星的运行参数以及目标同步轨道卫星的姿轨参数;Receive the input drifting task information and the first system parameters of the target synchronous orbit satellite, and determine the second system parameters of at least one synchronous orbit satellite according to the first system parameters and the drifting task information, wherein the at least one synchronous orbit satellite is A synchronous orbit satellite refers to a satellite adjacent to the target synchronous orbit satellite; the drifting task information includes preset target orbit position information, time to reach the target orbit position, and bit retention accuracy; the first system parameter includes the target synchronous orbit satellite. The operation and state parameters of each subsystem in the system, the operation parameters of the target synchronous orbit satellite and the attitude and orbit parameters of the target synchronous orbit satellite; 根据所述漂星任务信息、所述第一系统参数以及所述第二系统参数确定起漂参数以及捕获参数,包括:According to the drifting mission information, the first system parameters and the second system parameters, the drift parameters and capture parameters are determined, including: 根据所述漂星任务信息、所述第一系统参数、所述第二系统参数以及预设的第一约束条件计算所述起漂参数,其中,所述起漂参数包括起漂的次数、每次起漂速度增量以及起漂时间;The drifting parameter is calculated according to the drifting star task information, the first system parameter, the second system parameter and the preset first constraint, wherein the drifting parameter includes the number of drifting, the The second start-up speed increment and the start-up time; 根据所述漂星任务信息、所述第一系统参数、所述第二系统参数以及预设的第二约束条件计算所述捕获参数,其中,所述捕获参数包括捕获的次数、每次捕获速度增量以及捕获时间;The acquisition parameters are calculated according to the star drifting mission information, the first system parameters, the second system parameters, and a preset second constraint, where the acquisition parameters include the number of times of capture, the speed of each capture Increment and capture time; 根据所述起漂参数以及所述捕获参数生成控制指令,并将所述控制指令发送给所述目标同步轨道卫星,其中,所述控制指令用于控制所述目标同步轨道卫星移动到预设的目标轨位。Generate a control instruction according to the drift parameter and the acquisition parameter, and send the control instruction to the target geostationary orbit satellite, wherein the control instruction is used to control the target geostationary orbit satellite to move to a preset target track position. 2.如权利要求1所述的方法,其特征在于,所述第一约束条件包括:根据所述每次起漂速度增量以及起漂时间计算得到的所述目标同步轨道卫星与邻近同步轨道卫星之间的第一距离不小于预设第一阈值;以及根据所述每次起漂速度增量以及起漂时间计算得到所述目标同步轨道卫星的轨道偏心率小于预设第二阈值;2 . The method according to claim 1 , wherein the first constraint condition comprises: the target synchronous orbit satellite and the adjacent synchronous orbit calculated according to the drift speed increment and the drift time each time. 3 . The first distance between satellites is not less than a preset first threshold; and the orbital eccentricity of the target geostationary orbit satellite is calculated according to each take-off speed increment and take-off time is less than a preset second threshold; 所述第二约束条件包括:根据所述每次捕获速度增量以及所述捕获时间计算得到的所述目标同步轨道卫星与邻近同步轨道卫星之间的第二距离不小于预设第三阈值;总的捕获速度增量与总的漂星速度增量的大小相等,方向相反。The second constraint condition includes: the second distance between the target geostationary orbit satellite and the adjacent geostationary orbit satellite calculated according to each acquisition speed increment and the acquisition time is not less than a preset third threshold; The total capture velocity increment is equal to and opposite to the total drifting star velocity increment. 3.如权利要求1~2任一项所述的方法,其特征在于,根据所述起漂参数以及所述捕获参数生成控制指令之前,还包括:3. The method according to any one of claims 1 to 2, wherein before generating a control command according to the drift parameter and the capture parameter, the method further comprises: 建立同步轨道卫星仿真模型,并将所述起漂参数以及所述捕获参数作为所述同步轨道卫星仿真模型的输入参数,其中,所述同步轨道卫星仿真模型的系统参数与所述第一系统参数一致;establishing a geostationary orbit satellite simulation model, and using the drift parameters and the capture parameters as input parameters of the geostationary orbit satellite simulation model, wherein the system parameters of the geostationary orbit satellite simulation model and the first system parameters consistent; 根据所述起漂参数以及所述捕获参数控制所述同步轨道卫星仿真模型运行,得到运行结果;Control the operation of the synchronous orbit satellite simulation model according to the drift parameter and the capture parameter, and obtain the operation result; 判断所述运行结果判断是否到达所述预设的目标轨位;Judging whether the operation result has reached the preset target orbit; 若未到达,则重新确定起漂参数以及捕获参数,直到到达所述预设的目标轨位为止。If not, then re-determine the takeoff parameters and the capture parameters until the preset target orbit position is reached. 4.一种实现同步轨道卫星漂星的装置,其特征在于,包括:4. a device for realizing synchronous orbit satellite drift star, is characterized in that, comprises: 第一确定单元,用于接收输入的漂星任务信息以及目标同步轨道卫星的第一系统参数,并根据所述第一系统参数以及所述漂星任务信息确定至少一个同步轨道卫星的第二系统参数,其中,所述至少一个同步轨道卫星是指与所述目标同步轨道卫星邻近的卫星;漂星任务信息包括预设的目标轨位信息、到达目标轨位的时间以及位保持精度;第一系统参数包括目标同步轨道卫星中各子系统的运行及状态参数,目标同步轨道卫星的运行参数以及目标同步轨道卫星的姿轨参数;a first determination unit, configured to receive the input drifting task information and the first system parameters of the target synchronous orbit satellite, and determine the second system of at least one synchronous orbit satellite according to the first system parameters and the drifting task information parameters, wherein, the at least one synchronous orbit satellite refers to a satellite adjacent to the target synchronous orbit satellite; the star drift task information includes preset target orbit position information, time to reach the target orbit position, and bit retention accuracy; first The system parameters include the operation and state parameters of each subsystem in the target synchronous orbit satellite, the operation parameters of the target synchronous orbit satellite, and the attitude and orbit parameters of the target synchronous orbit satellite; 第二确定单元,用于根据所述漂星任务信息、所述第一系统参数以及所述第二系统参数确定起漂参数以及捕获参数;a second determining unit, configured to determine a drift parameter and a capture parameter according to the drift star task information, the first system parameter and the second system parameter; 所述第二确定单元,具体用于:The second determining unit is specifically used for: 根据所述漂星任务信息、所述第一系统参数、所述第二系统参数以及预设的第一约束条件计算所述起漂参数,其中,所述起漂参数包括起漂的次数、每次起漂速度增量以及起漂时间;The drifting parameter is calculated according to the drifting star task information, the first system parameter, the second system parameter and the preset first constraint, wherein the drifting parameter includes the number of drifting, the The second start-up speed increment and the start-up time; 根据所述漂星任务信息、所述第一系统参数、所述第二系统参数以及预设的第二约束条件计算所述捕获参数,其中,所述捕获参数包括捕获的次数、每次捕获速度增量以及捕获时间;The acquisition parameters are calculated according to the star drifting mission information, the first system parameters, the second system parameters, and a preset second constraint, where the acquisition parameters include the number of times of capture, the speed of each capture Increment and capture time; 生成单元,用于根据所述起漂参数以及所述捕获参数生成控制指令,并将所述控制指令发送给所述目标同步轨道卫星,其中,所述控制指令用于控制所述目标同步轨道卫星移动到预设的目标轨位。A generating unit, configured to generate a control instruction according to the drift parameter and the capture parameter, and send the control instruction to the target geostationary orbit satellite, wherein the control instruction is used to control the target geostationary orbit satellite Move to the preset target track position. 5.如权利要求4所述的装置,其特征在于,所述第一约束条件包括:根据所述每次起漂速度增量以及起漂时间计算得到的所述目标同步轨道卫星与邻近同步轨道卫星之间的第一距离不小于预设第一阈值;以及根据所述每次起漂速度增量以及起漂时间计算得到所述目标同步轨道卫星的轨道偏心率小于预设第二阈值;5 . The apparatus according to claim 4 , wherein the first constraint condition comprises: the target synchronous orbit satellite and the adjacent synchronous orbit calculated according to the drift speed increment and the drift time each time. 6 . The first distance between satellites is not less than a preset first threshold; and the orbital eccentricity of the target geostationary orbit satellite is calculated according to each take-off speed increment and take-off time is less than a preset second threshold; 所述第二约束条件包括:根据所述每次捕获速度增量以及所述捕获时间计算得到的所述目标同步轨道卫星与邻近同步轨道卫星之间的第二距离不小于预设第三阈值;总的捕获速度增量与总的漂星速度增量的大小相等,方向相反。The second constraint condition includes: the second distance between the target geostationary orbit satellite and the adjacent geostationary orbit satellite calculated according to each acquisition speed increment and the acquisition time is not less than a preset third threshold; The total capture velocity increment is equal to and opposite to the total drifting star velocity increment. 6.如权利要求4~5任一项所述的装置,其特征在于,所述装置,还包括仿真单元;所述仿真单元,具体用于:6. The device according to any one of claims 4 to 5, wherein the device further comprises a simulation unit; the simulation unit is specifically used for: 建立同步轨道卫星仿真模型,并将所述起漂参数以及所述捕获参数作为所述同步轨道卫星仿真模型的输入参数,其中,所述同步轨道卫星仿真模型的系统参数与所述第一系统参数一致;establishing a geostationary orbit satellite simulation model, and using the drift parameters and the capture parameters as input parameters of the geostationary orbit satellite simulation model, wherein the system parameters of the geostationary orbit satellite simulation model and the first system parameters consistent; 根据所述起漂参数以及所述捕获参数控制所述同步轨道卫星仿真模型运行,得到运行结果;Control the operation of the synchronous orbit satellite simulation model according to the drift parameter and the capture parameter, and obtain the operation result; 判断所述运行结果判断是否到达所述预设的目标轨位;Judging whether the operation result has reached the preset target orbit; 若未到达,则重新确定起漂参数以及捕获参数,直到到达所述预设的目标轨位为止。If not, then re-determine the takeoff parameters and the capture parameters until the preset target orbit position is reached. 7.一种计算机设备,其特征在于,包括:7. A computer equipment, characterized in that, comprising: 存储器,用于存储至少一个处理器所执行的指令;memory for storing instructions executed by at least one processor; 处理器,用于执行存储器中存储的指令执行如权利要求1~3任一项所述的方法。The processor is configured to execute the instructions stored in the memory to execute the method according to any one of claims 1 to 3. 8.一种计算机可读存储介质,其特征在于,所述计算机可读存储介质存储有计算机指令,当所述计算机指令在计算机上运行时,使得计算机执行如权利要求1~3任一项所述的方法。8. A computer-readable storage medium, characterized in that the computer-readable storage medium stores computer instructions, which, when the computer instructions are executed on a computer, cause the computer to execute the method according to any one of claims 1 to 3. method described.
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