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 PDFInfo
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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。
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.
Description
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.
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| CN113928598A (en) * | 2021-12-16 | 2022-01-14 | 亚太卫星宽带通信（深圳）有限公司 | Method and device for realizing satellite drift of synchronous orbit satellite |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002041093A2 (en) * | 2000-11-13 | 2002-05-23 | Draim John E | System and method for implementing a constellation of non-geostationary satellites that does not interfere with the geostationary ring |
| CN101219713A (en) * | 2007-12-26 | 2008-07-16 | 北京控制工程研究所 | A method for autonomous orbit change of a satellite |
| CN103684628A (en) * | 2013-11-18 | 2014-03-26 | 航天东方红卫星有限公司 | Method of simultaneously acquiring target track and sub-satellite point track |
| CN104015938A (en) * | 2014-05-07 | 2014-09-03 | 北京理工大学 | Position keeping method of electric propulsion stationary orbit satellite |
| CN105383713A (en) * | 2014-08-28 | 2016-03-09 | 波音公司 | Satellite transfer orbit search methods |
| CN109592079A (en) * | 2018-12-03 | 2019-04-09 | 哈尔滨工业大学 | A kind of spacecraft coplanar encounter of limiting time becomes rail strategy and determines method |
| CN110450990A (en) * | 2019-08-16 | 2019-11-15 | 西北工业大学 | Space non-cooperative target capture systems and catching method based on micro-nano satellite cluster |
-
2020
- 2020-03-31 CN CN202010247249.8A patent/CN111532455B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002041093A2 (en) * | 2000-11-13 | 2002-05-23 | Draim John E | System and method for implementing a constellation of non-geostationary satellites that does not interfere with the geostationary ring |
| CN101219713A (en) * | 2007-12-26 | 2008-07-16 | 北京控制工程研究所 | A method for autonomous orbit change of a satellite |
| CN103684628A (en) * | 2013-11-18 | 2014-03-26 | 航天东方红卫星有限公司 | Method of simultaneously acquiring target track and sub-satellite point track |
| CN104015938A (en) * | 2014-05-07 | 2014-09-03 | 北京理工大学 | Position keeping method of electric propulsion stationary orbit satellite |
| CN105383713A (en) * | 2014-08-28 | 2016-03-09 | 波音公司 | Satellite transfer orbit search methods |
| CN109592079A (en) * | 2018-12-03 | 2019-04-09 | 哈尔滨工业大学 | A kind of spacecraft coplanar encounter of limiting time becomes rail strategy and determines method |
| CN110450990A (en) * | 2019-08-16 | 2019-11-15 | 西北工业大学 | Space non-cooperative target capture systems and catching method based on micro-nano satellite cluster |
Non-Patent Citations (2)
| Title |
|---|
| 《星座备份策略研究进展》;王许煜等;《中国空间科学技术》;20200120;第40卷(第3期);43-55 * |
| 《风云二号气象卫星双星共轨技术研究与应用》;冯小虎等;《气象科技》;20180215;第46卷(第1期);34-38 * |
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