Orbit control plan generation method and system, electronic equipment and storage medium

Abstract

The invention relates to the technical field of spacecraft orbit control, and particularly discloses an orbit control plan generation method and system, electronic equipment and a storage medium, and the method comprises the steps: constructing an orbit control instruction set containing all preset orbit control instructions during the in-orbit flight of a target spacecraft, determining a target orbit control strategy of the target spacecraft in a target sub-time period after the preset time; determining each preset orbit control instruction screened out from the orbit control instruction set as a first orbit control instruction to be executed within a target time period after the preset moment according to the instruction issuing route, the spacecraft state and the orbit control mode of the target spacecraft at the preset moment; and based on the target orbit control strategy, the target order issuing time and the orbit control name, correcting the instruction basic parameter of each first orbit control instruction, and generating a target orbit control R sequence. According to the method, time consumption of orbit control preparation processes such as planning, countersigning and data generation can be reduced, the efficiency of orbit control planning is improved, and the method can be used as a backup means for collision avoidance in emergency situations.

Description

Background Art

[0002] In recent years, with the development of microsatellite constellations, the number of near-Earth space targets has increased rapidly. Taking large spacecraft in near-Earth space as an example, the number of space targets with a statistical area of more than 0.1 m 2 and within the range of perigee altitude from 160 km to 450 km reaches thousands. According to the target classification, it includes satellites, rocket bodies, space debris, etc. If there is a risk of collision with a target, the spacecraft needs to actively perform orbital maneuver control to complete collision avoidance.

[0003] The orbital maneuver of large spacecraft is jointly implemented by the spacecraft research and development department and the flight control center. Generally, target warning information is obtained before approaching a dangerous target, and the orbital control strategy is designed. In the existing technical solutions, the process of implementing an orbital maneuver control includes: flight program arrangement, instruction plan countersignature, orbital control data generation, orbital control program injection, and orbital control implementation monitoring.

[0004] However, in the existing technical solutions, processes such as program arrangement, plan countersignature, and data generation all need to be carried out sequentially after the orbital control strategy design is completed, resulting in a relatively long preparation time for the orbital control implementation process. Currently, the number of targets in near-Earth space is increasing, and the collision probability is also gradually increasing. If there are situations such as the target making a temporary maneuver and orbit change or malicious approaching, conventional target monitoring means may not be able to predict dangerous targets in time, and the existing solutions are difficult to meet the requirements of rapid implementation of spacecraft orbital control in emergency situations.

[0005] Therefore, there is an urgent need to provide a technical solution to solve the above problems. Summary of the Invention

[0006] To solve the above technical problems, the present invention provides an orbital control planning generation method, system, electronic device, and storage medium.

[0007] In the first aspect, the present invention provides an orbital control planning generation method, and the technical solution of this method is as follows:

[0008] Construct an orbital control instruction set including all preset orbital control instructions during the on-orbit flight of the target spacecraft, and determine the target orbital control strategy of the target spacecraft within the target sub-time period after the preset moment; wherein, the configuration information of each preset orbital control instruction includes: instruction basic parameters, command routing, spacecraft state, orbital control mode, and command timing;

[0009] According to the target command routing, target spacecraft state, and target orbital control mode of the target spacecraft at the preset moment, each preset orbital control instruction screened out from the orbital control instruction set is determined as the first orbital control instruction to be executed within the target time period after the preset moment; wherein, the target time period includes the target sub-time period;

[0010] Based on the target orbit control strategy, correct the basic instruction parameters of the first orbit control instruction whose command timing is the target command timing, and correct the basic instruction parameters of each first orbit control instruction based on the orbit control name of the target spacecraft during the target time period, and generate a target orbit control R sequence containing multiple target orbit control instructions.

[0011] The beneficial effects of an orbit control planning generation method of the present invention are as follows:

[0012] The method of the present invention can quickly plan and generate the corresponding R sequence after constructing the preset orbit control instruction set and determining the orbit control strategy, and immediately execute the orbit control, which can reduce the time consumption of orbit control preparation processes such as plan arrangement, countersignature, and data generation, improve the efficiency of orbit control planning, and this method can be used as a backup means for collision avoidance in emergency situations.

[0013] On the basis of the above solution, an orbit control planning generation method of the present invention can also be improved as follows.

[0014] In an optional manner, the basic instruction parameters include: command time point; the target orbit control strategy includes: the power-on time parameter and the power-off time parameter of the target sub-time period; the command timing includes: with time constraint and without time constraint; the target command timing is: with time constraint;

[0015] The step of correcting the basic instruction parameters of the first orbit control instruction whose command timing is the target command timing based on the target orbit control strategy includes:

[0016] Based on the power-on time parameter and the power-off time parameter of the target sub-time period, correct the command time point of the first orbit control instruction with time constraint.

[0017] In an optional manner, the basic instruction parameters further include: instruction code; the step of correcting the basic instruction parameters of each first orbit control instruction based on the orbit control name of the target spacecraft during the target time period includes:

[0018] Replace the target field in the instruction code of each first orbit control instruction with the orbit control name of the target spacecraft during the target time period.

[0019] In an optional manner, the step of generating a target orbit control R sequence containing multiple target orbit control instructions includes:

[0020] For the target orbit control instruction whose command timing is with time constraint, sort them in the order of the command time point and control them to be executed at the corresponding command time point in the target sub-time period in sequence;

[0021] For target orbit control commands whose command timing is not time - constrained and that meet the first preset condition, sort them in ascending order of the command time points and sequentially control them to be executed before the target sub - time period within the target time period; wherein, the second preset condition is: among all the first orbit control commands, the command time point is before each first orbit control command whose command timing is time - constrained.

[0022] For target orbit control commands whose command timing is not time - constrained and that meet the first preset condition, sort them in descending order of the command time points and sequentially control them to be executed after the target sub - time period within the target time period; wherein, the second preset condition is: among all the first orbit control commands, the command time point is after each first orbit control command whose command timing is time - constrained.

[0023] In an alternative manner, it further includes:

[0024] Based on the target orbit control R sequence, perform orbit control on the target spacecraft within the target time period.

[0025] In a second aspect, the present invention provides an orbit control planning generation system, and the technical solution of this system is as follows:

[0026] It includes: a construction module, a processing module, and a generation module;

[0027] The construction module is used to: construct an orbit control command set containing all preset orbit control commands during the in - orbit flight of the target spacecraft, and determine the target orbit control strategy within the target sub - time period after the preset moment of the target spacecraft; wherein, the configuration information of each preset orbit control command includes: command basic parameters, command routing, spacecraft status, orbit control mode, and command timing.

[0028] The processing module is used to: according to the target command routing, target spacecraft status, and target orbit control mode of the target spacecraft at the preset moment, determine each preset orbit control command screened from the orbit control command set as the first orbit control command to be executed within the target time period after the preset moment; wherein, the target time period includes the target sub - time period.

[0029] The generation module is used to: based on the target orbit control strategy, correct the command basic parameters of the first orbit control commands whose command timing is the target command timing, and based on the orbit control name of the target spacecraft within the target time period, correct the command basic parameters of each first orbit control command, and generate a target orbit control R sequence containing multiple target orbit control commands.

[0030] The beneficial effects of an orbit control planning generation system of the present invention are as follows:

[0031] The system of the present invention can quickly plan and generate the corresponding R sequence after constructing a preset orbit control instruction set and determining the orbit control strategy, and immediately execute orbit control, which can reduce the time consumption in the orbit control preparation process such as plan arrangement, countersignature, and data generation, improve the efficiency of orbit control planning, and the system can be used as a backup means for collision avoidance in case of emergency.

[0032] On the basis of the above solution, an orbit control planning generation system of the present invention can also be improved as follows.

[0033] In an optional manner, the basic instruction parameters include: the command time point; the target orbit control strategy includes: the power-on time parameter and the power-off time parameter of the target sub-time period; the command timing includes: with time constraint and without time constraint; the target command timing is: with time constraint; the generation module is specifically used for:

[0034] Based on the power-on time parameter and the power-off time parameter of the target sub-time period, correct the command time point of the first orbit control instruction with time constraint.

[0035] In an optional manner, the basic instruction parameters further include: the instruction code; the generation module is specifically used for:

[0036] Replace the target field in the instruction code of each first orbit control instruction with the orbit control name of the target spacecraft in the target time period.

[0037] In a third aspect, the technical solution of an electronic device of the present invention is as follows:

[0038] It includes a memory, a processor, and a program stored on the memory and running on the processor. When the processor executes the program, it implements the steps of the orbit control planning generation method of the present invention.

[0039] In a fourth aspect, the technical solution of a computer-readable storage medium provided by the present invention is as follows:

[0040] Instructions are stored in the computer-readable storage medium. When the computer-readable storage medium reads the instructions, the computer-readable storage medium is caused to execute the steps of the orbit control planning generation method of the present invention.

[0041] The above description is only an overview of the technical solution of the present invention. In order to be able to understand the technical means of the present invention more clearly, it can be implemented according to the content of the specification. And in order to make the above and other purposes, features, and advantages of the present invention more obvious and understandable, the specific embodiments of the present invention are specifically exemplified below. Description of the Drawings

[0042] The accompanying drawings are only used to illustrate the embodiments and are not considered to limit the present invention. Moreover, throughout the accompanying drawings, the same reference numerals are used to represent the same components. In the accompanying drawings:

[0043] Figure 1 is a schematic flowchart of an embodiment of a method for generating orbit control planning according to the present invention;

[0044] Figure 2 is a schematic diagram of an interface for configuring the orbit control R sequence description;

[0045] Figure 3 is a schematic diagram of the spacecraft status filling specification;

[0046] Figure 4 is a schematic diagram of the orbit control mode filling specification;

[0047] Figure 5 is a schematic diagram of the command timing filling specification;

[0048] Figure 6 is a schematic diagram of the orbit control R sequence menu;

[0049] Figure 7 is a schematic structural diagram of an embodiment of a system for generating orbit control planning according to the present invention;

[0050] Figure 8 is a schematic structural diagram of an embodiment of an electronic device according to the present invention. Detailed Embodiments

[0051] Hereinafter, exemplary embodiments of the present invention will be described in more detail with reference to the accompanying drawings. Although the exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein.

[0052] Figure 1 shows a schematic flowchart of an embodiment of a method for generating orbit control planning provided by the present invention. The method for generating orbit control planning can be executed by an electronic device such as a terminal device or a server. Among them, the terminal device can be any fixed or mobile terminal such as a user equipment (UE), a mobile device, a user terminal, a terminal, a cellular phone, a cordless phone, a personal digital assistant (PDA), a handheld device, a computing device, a vehicle-mounted device, a wearable device, etc. The server can be a single server or a server cluster composed of multiple servers. Any electronic device can implement the method for generating orbit control planning by a processor calling computer-readable instructions stored in a memory. As Figure 1 shown, it includes the following steps:

[0053] S1. Construct a set of orbit control instructions that includes all preset orbit control instructions during the on-orbit flight of the target spacecraft, and determine the target orbit control strategy for the target sub-time period after the preset time.

[0054] Among them, the target spacecraft is the spacecraft that needs to perform orbit control in this embodiment, and the specific spacecraft model is not limited here. The on-orbit flight period is the total time period of the target spacecraft's on-orbit flight. The set of orbit control instructions refers to: designing a set of instruction logics that cover all scenarios for the on-orbit control of the spacecraft to ensure that it can autonomously or under control respond to all possible operation modes, fault scenarios, and environmental changes in a complex space environment. All preset orbit control instructions include but are not limited to: ① Routine operations: orbit adjustment, attitude control, payload switch, data transmission; ② Emergency response: fault isolation, safety mode switching, redundant system activation; ③ Environment adaptation: contingency plans for dealing with radiation, temperature difference, and debris impact.

[0055] Among them, the configuration information of each preset orbit control instruction includes: instruction basic parameters, command routing, spacecraft status, orbit control mode, and command timing. The instruction basic parameters include but are not limited to: instruction name, instruction code, command time point, instruction attribute, and feature identifier.

[0056] Among them, the preset time T k is default set to: the current time, and the target sub-time period is default set to: [T k+c , T k+d ; k, c, and d are all constants, and the unit is min. For example, [T k+120 , T k+130 . The target orbit control strategy is an orbit control parameter file, which specifically includes the power-on time parameter and power-off time parameter of the target sub-time period.

[0057] It should be noted that the time point for constructing the set of orbit control instructions can be completed before the spacecraft launch time T0, and the time point for starting to formulate the orbit control strategy is: a certain target time point before the preset time T k , and this time point is usually T k-120 ; the time point for completing the formulation of the orbit control strategy is before the preset time T k .

[0058] S2. According to the target command routing, target spacecraft status, and target orbit control mode of the target spacecraft at the preset time, determine each preset orbit control instruction selected from the set of orbit control instructions as the first orbit control instruction to be executed during the target time period after the preset time.

[0059] Among them, the number of command routing is determined according to the actual situation, for example, it includes: the first command routing, the second command routing, and the third command routing. The target command routing is any one of them. It should be noted that for large spacecraft, there may be multiple TT&C receiving devices. The command direction is used to describe the target routing for sending the command to the spacecraft, and different routings correspond to different sending methods of the commands in the sequence.

[0060] Among them, the spacecraft state is the state of the spacecraft during on-orbit flight. During the on-orbit flight of the spacecraft, due to factors such as light and temperature, the attitude and the state of the solar panels are adjusted. There may be multiple attitude characteristics for the attitude. Under each characteristic, the corresponding orbit control related commands are different. During orbit control, it is necessary to select the corresponding control commands according to the different characteristics of each spacecraft state. In this embodiment, the spacecraft state is defaultly included: no characteristic, the first characteristic, the second characteristic, and the third characteristic. Each preset orbit control command can correspond to at least one spacecraft state (except no characteristic).

[0061] Among them, the orbit control mode includes: the time mode and the speed mode. The target orbit control mode is one of them. Specifically: ① In the time mode, by reading the power-on time parameter and the power-off time parameter in the orbit control parameter file, the commands related to power-off in the R sequence are arranged at the determined moment; ② In the speed mode, the power-on moment of orbit control and the target value of the control speed increment are determined values. After the orbit control is powered on, the accelerometer and other measurement sensors are used to measure the cumulative speed increment of this orbit control. When the cumulative value reaches the target value, it automatically powers off, and the power-off command is arranged at 1.1 - 1.5 times of the power-on time (duration) as a backup power-off method.

[0062] Among them, the first orbit control command is: among all the preset orbit control commands, the preset orbit control command that simultaneously meets the target command routing, the target spacecraft state, and the target orbit control mode. The target time period includes the target sub-time period. For example, the target time period is [T k+b , T k+e , where T k+a is the moment when the target orbit control R sequence is completed, a < b < c, d < e.

[0063] S3. Based on the target orbit control strategy, correct the basic command parameters of the first orbit control command whose command timing is the target command timing, and correct the basic command parameters of each first orbit control command based on the orbit control name of the target spacecraft in the target time period, and generate a target orbit control R sequence containing multiple target orbit control commands.

[0064] Among them, the command timing includes: with time constraint and without time constraint; the target command timing is: with time constraint. Some orbit control commands do not have strict time constraints and are sent through manual control; some orbit control commands such as orbit control power-on / off commands need to read the orbit control parameter file and be sent according to strict moments. The commands marked with command timing requirements in the orbit control R sequence (i.e., orbit control commands with time constraints for command timing) need to be sent according to the time stipulated in the control parameter file.

[0065] It should be noted that the arrangement timing of the shutdown commands in the orbit control R sequences corresponding to the two orbit control modes (time mode and speed mode) is different, and selection should be made according to the actual orbit control mode. The orbit control command set configures a description interface for the orbit control R sequence in this embodiment. As Figure 2 shown, the orbit control R sequence configuration description interface is described in XML format. The specific filling specifications of this interface include:

[0066] ① The filling specification of the command routing is: "Command routing" cannot be empty. All command routing methods of the spacecraft need to be listed and numbered in sequence as "1, 2, 3...". In the orbit control R sequence, the filling requirements for the "command routing" column corresponding to each orbit control command are the same.

[0067] ② The filling specification of the spacecraft state is: The filling format of "spacecraft state" is as Figure 3 shown. The parameter can be filled with "0" or "1". If "feature" is empty, "default" is filled with "1"; if any "feature" is filled with "1", then "default" is filled with "0" or not filled. If a certain orbit control command in the orbit control R sequence output under a certain "feature" of "spacecraft state", then "1" is filled in the corresponding "feature", as Figure 3 shown on the left; if multiple features are all output, then "1" is filled in simultaneously, as Figure 3 shown in the middle; if this orbit control command is a general command and has nothing to do with the feature, then "1" is filled in by default and others are not filled, as Figure 3 shown on the right.

[0068] ③ The filling specification of the orbit control mode is: The filling format of "orbit control mode" is as Figure 4 shown. The parameter can be filled with "0" or "1". If this orbit control command in the orbit control R sequence is used in the speed mode, then "speed mode" is filled with "1"; if it is used in the time mode, then "time mode" is filled with "1"; if this orbit control command is a general command and has nothing to do with the feature, then it is not filled by default.

[0069] ④ The filling specification of the command timing is: As Figure 5As shown, in the orbit control R sequence, it is divided into "instructions with strict time constraints" and "instructions without strict time constraints". "Instructions with strict time constraints" need to be sent according to strict moments. For example, for orbit control power-on and power-off instructions, fill in "1" in the "Read" column. "Instructions without strict time constraints" can be sent at any time as needed. For example, for orbit control pre-state setting instructions, fill in "1" in the "Default" column. For orbit control instructions in the orbit control R sequence marked with requirements for sending timing, it is necessary to read the agreed time in the orbit control parameter interface for sending.

[0070] In an alternative approach, the step of modifying the basic instruction parameters of the first orbit control instruction with a target sending timing based on the target orbit control strategy includes:

[0071] Modifying the sending time point of the first orbit control instruction with time constraints based on the power-on time parameter and power-off time parameter of the target sub-time period.

[0072] Among them, the sending time point of the first orbit control instruction with time constraints is modified to the power-on time parameter or power-off time parameter, which is specifically determined according to the actual orbit control instruction.

[0073] In an alternative approach, the step of modifying the basic instruction parameters of each first orbit control instruction based on the orbit control name of the target spacecraft in the target time period includes:

[0074] Replacing the target field in the instruction code of each first orbit control instruction with the orbit control name of the target spacecraft in the target time period.

[0075] Among them, if the orbit control name is "ABC", the instruction code of a certain first orbit control instruction is "KXX01", and the target field is "KXX", then "KXX" is replaced with "ABC" to obtain "ABC01".

[0076] It should be noted that as Figure 6 shown, in the orbit control R sequence menu, the target route selects the first route (Route 1), the spacecraft status selects the second feature (Feature 2), and the orbit control mode selects the time mode. Specifically:

[0077] ① Select any one of the "sending routes". When generating the orbit control R sequence, the sending route of each orbit control instruction in the sequence is automatically changed.

[0078] ② Select "spacecraft status". When the instructions in the orbit control instruction set with the "spacecraft status" attribute are consistent with the selection in the menu, output this orbit control instruction.

[0079] ③ Select "orbit control mode". When the instructions in the orbit control instruction set with the "orbit control mode" attribute are consistent with the selection in the menu, output this orbit control instruction.

[0080] ④ In the "Ordering Time" column, select the orbit control parameter file used for this orbit control, read the startup time parameter and shutdown time parameter in the orbit control parameter file interface, and automatically correct the instruction sending time with the "orbit control mode" attribute. If the "orbit control mode" is "time mode", the shutdown-related instructions in the orbit control R sequence are generated according to the shutdown time in the orbit control parameter file; if it is "speed mode", they are generated according to 1.1 - 1.5 times the orbit control startup time (duration) in the orbit control parameter file.

[0081] ⑤ In the "Orbit Control Data" column, fill in the data name used for this orbit control. When generating the orbit control R sequence, the orbit control data in the configuration is automatically replaced with the data name input in the menu.

[0082] In an optional manner, the steps of generating a target orbit control R sequence including multiple target orbit control instructions include:

[0083] For target orbit control instructions with a time constraint for the ordering time, sort them in the order of the ordering time points and sequentially control them to be executed at the ordering time points corresponding to the target sub - time periods.

[0084] Among them, for example, the serial numbers of all target orbit control instructions arranged in the order of the ordering time points are 01 - 10. Assume that the ordering times of the target orbit control instructions with serial numbers 06 and 07 are time - constrained, and the ordering times of the target orbit control instructions with the remaining serial numbers are not time - constrained. Then, in the target sub - time period, execute at the ordering time points corresponding to the target orbit control instructions with serial numbers 06 and 07.

[0085] For target orbit control instructions with no time constraint for the ordering time and satisfying the first preset condition, sort them in the order of the ordering time points and sequentially control them to be executed before the target sub - time periods within the target time period.

[0086] Among them, the first preset condition is: among all the first orbit control instructions, the ordering time point is before each first orbit control instruction with a time - constrained ordering time. In the above example, the target orbit control instructions with no time constraint for the ordering time and satisfying the first preset condition are: the target orbit control instructions with serial numbers 01 - 05.

[0087] For target orbit control instructions with no time constraint for the ordering time and satisfying the second preset condition, sort them in the order of the ordering time points and sequentially control them to be executed after the target sub - time periods within the target time period.

[0088] Among them, the second preset condition is that among all the first orbit control instructions, the time points of issuing the instructions are after each first orbit control instruction with a time constraint for the issuing opportunity. In the above example, the target orbit control instructions with no time constraint for the issuing opportunity and satisfying the second preset condition are the target orbit control instructions numbered 08 - 10.

[0089] In an optional manner, it further includes:

[0090] Based on the target orbit control R sequence, perform orbit control on the target spacecraft within the target time period.

[0091] Among them, in the order of the target orbit control instructions in the target orbit control R sequence, the orbit control instructions without time constraints are sequentially sent within the target time period, and the target orbit control instructions with time constraints are automatically executed according to the plan within the target sub - time period until the orbit control is completed.

[0092] The technical solution of this embodiment can reduce the time consumption in orbit control preparation processes such as plan arrangement, countersignature, and data generation, and improve the efficiency of orbit control planning by constructing a preset orbit control instruction set, quickly planning and generating the corresponding R sequence after the orbit control strategy is determined, and immediately executing orbit control. This method can be used as a backup means for collision avoidance in emergency situations.

[0093] Figure 7 Shows a schematic structural diagram of an embodiment of an orbit control planning generation system 200 provided by the present invention. As Figure 7 shown, the system 200 includes: a construction module 210, a processing module 220, and a generation module 230;

[0094] The construction module 210 is used to: construct an orbit control instruction set including all preset orbit control instructions during the in - orbit flight of the target spacecraft, and determine the target orbit control strategy of the target spacecraft within the target sub - time period after the preset moment; among them, the configuration information of each preset orbit control instruction includes: instruction basic parameters, issuing route, spacecraft state, orbit control mode, and issuing opportunity;

[0095] The processing module 220 is used to: according to the target issuing route, target spacecraft state, and target orbit control mode of the target spacecraft at the preset moment, determine each preset orbit control instruction screened from the orbit control instruction set as the first orbit control instruction to be executed within the target time period after the preset moment; where the target time period includes the target sub - time period;

[0096] The generating module 230 is configured to: based on the target orbit control strategy, correct the basic instruction parameters of the first orbit control instruction whose command timing is the target command timing, and based on the orbit control name of the target spacecraft in the target time period, correct the basic instruction parameters of each first orbit control instruction, and generate a target orbit control R sequence including multiple target orbit control instructions.

[0097] In an optional manner, the basic instruction parameters include: command time point; the target orbit control strategy includes: the power-on time parameter and the power-off time parameter of the target sub-time period; the command timing includes: with time constraint and without time constraint; the target command timing is: with time constraint; the generating module 230 is specifically configured to:

[0098] Based on the power-on time parameter and the power-off time parameter of the target sub-time period, correct the command time point of the first orbit control instruction with time constraint.

[0099] In an optional manner, the basic instruction parameters further include: instruction code; the generating module 230 is specifically configured to:

[0100] Replace the target field in the instruction code of each first orbit control instruction with the orbit control name of the target spacecraft in the target time period.

[0101] In an optional manner, the generating module 230 is specifically configured to:

[0102] For the target orbit control instruction whose command timing is with time constraint, sort them in the order of the command time point and sequentially control them to be executed at the corresponding command time points in the target sub-time period;

[0103] For the target orbit control instruction whose command timing is without time constraint and meets the first preset condition, sort them in the order of the command time point and sequentially control them to be executed before the target sub-time period in the target time period; wherein, the first preset condition is: among all the first orbit control instructions, the command time point is before each first orbit control instruction whose command timing is with time constraint;

[0104] For the target orbit control instruction whose command timing is without time constraint and meets the second preset condition, sort them in the order of the command time point and sequentially control them to be executed after the target sub-time period in the target time period; wherein, the second preset condition is: among all the first orbit control instructions, the command time point is after each first orbit control instruction whose command timing is with time constraint.

[0105] In an optional manner, it further includes: a control module;

[0106] The control module is configured to: perform orbit control on the target spacecraft within the target time period based on the target orbit control R sequence.

[0107] It should be noted that the beneficial effects of the orbit control planning generation system provided in the above embodiments are the same as those of the orbit control planning generation method, which will not be elaborated here. In addition, when the system provided in the above embodiments implements its functions, only the division of the above function modules is used for illustration. In practical applications, the above functions can be allocated to different function modules according to needs, that is, the system can be divided into different function modules according to the actual situation to complete all or part of the functions described above. In addition, the system and method embodiments provided in the above embodiments belong to the same concept, and the specific implementation process can be seen in the method embodiments, which will not be elaborated here.

[0108] Among them, the orbit control planning generation system of the present invention can be a computer program (including program code) running in a computer device. For example, the orbit control planning generation system of the present invention is an application software and can be used to execute the corresponding steps in the orbit control planning generation method of the present invention.

[0109] In some embodiments, the orbit control planning generation system of the present invention can be implemented in a combination of software and hardware. As an example, the orbit control planning generation system of the present invention can be a processor in the form of a hardware decoding processor, which is programmed to execute the orbit control planning generation method of the present invention. For example, the processor in the form of a hardware decoding processor can adopt one or more application-specific integrated circuits (ASICs), DSPs, programmable logic devices (PLDs), complex programmable logic devices (CPLDs), field-programmable gate arrays (FPGAs) or other electronic components.

[0110] Among them, the modules described in the embodiments of the present invention can be implemented by software or by hardware. Among them, the name of the module does not constitute a limitation to the module itself in some cases.

[0111] An electronic device according to an embodiment of the present invention includes a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the above-mentioned any one of the trajectory control planning generation methods is implemented. That is to say, an electronic device according to an embodiment of the present invention may include, but is not limited to: a processor and a memory; the memory is used to store a computer program; the processor is used to execute the trajectory control planning generation method shown in any one of the embodiments of the present invention by calling the computer program.

[0112] In an alternative embodiment, an electronic device is provided, as Figure 8 shown Figure 8 The electronic device 4000 shown includes: a processor 4001 and a memory 4003. Among them, the processor 4001 and the memory 4003 are connected, such as connected through a bus 4002. Optionally, the electronic device 4000 may further include a transceiver 4004, and the transceiver 4004 may be used for data interaction between this electronic device and other electronic devices, such as sending and / or receiving data, etc. It should be noted that in practical applications, the transceiver 4004 is not limited to one, and the structure of the electronic device 4000 does not constitute a limitation to the embodiments of the present invention.

[0113] The processor 4001 may be a CPU (Central Processing Unit, central processing unit), a general-purpose processor, a DSP (Digital Signal Processor, data signal processor), an ASIC (Application Specific Integrated Circuit, application-specific integrated circuit), an FPGA (Field Programmable Gate Array, field programmable gate array) or other programmable logic devices, transistor logic devices, hardware components or any combination thereof. It can implement or execute various exemplary logic blocks, modules and circuits described in connection with the disclosure of the present invention. The processor 4001 may also be a combination for implementing computing functions, such as a combination including one or more microprocessors, a combination of a DSP and a microprocessor, etc.

[0114] The bus 4002 may include a path for transmitting information between the above-mentioned components. The bus 4002 may be a PCI (Peripheral Component Interconnect, peripheral component interconnect standard) bus or an EISA (Extended Industry Standard Architecture, extended industry standard architecture) bus, etc. The bus 4002 may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 8In the figure, the bus 4002 is represented only by a thick line, but it does not mean that there is only one bus or one type of bus.

[0115] The memory 4003 can be a ROM (Read Only Memory), or other types of static storage devices that can store static information and instructions, a RAM (Random Access Memory), or other types of dynamic storage devices that can store information and instructions. It can also be an EEPROM (Electrically Erasable Programmable Read Only Memory), a CD-ROM (Compact Disc Read Only Memory), or other optical disc storage, optical disc storage (including compact discs, laser discs, optical discs, digital versatile discs, Blu-ray discs, etc.), magnetic disk storage media, or other magnetic storage devices, or any other medium that can be used to carry or store the desired program code in the form of instructions or data structures and can be accessed by a computer, but is not limited thereto.

[0116] The memory 4003 is used to store the application program code (computer program) for implementing the solution of the present invention, and is controlled and executed by the processor 4001. The processor 4001 is used to execute the application program code stored in the memory 4003 to implement the content shown in the foregoing method embodiments.

[0117] Among them, the electronic device can also be a terminal device. The terminal device can be any terminal device that can install an application and access a web page through the application, including at least one of a smart phone, a tablet computer, a notebook computer, a desktop computer, a smart speaker, a smart watch, a smart TV, and a smart vehicle-mounted device.

[0118] It should be noted that Figure 8 The electronic device shown is only an example and should not impose any limitations on the functions and usage scope of the embodiments of the present invention.

[0119] A computer-readable storage medium according to an embodiment of the present invention has a computer program stored thereon. When the computer program is executed by a processor, it implements any one of the above-mentioned trajectory control planning generation methods.

[0120] Optionally, the computer-readable storage medium can be a Read-Only Memory (ROM), a Random Access Memory (RAM), a Compact Disc Read-Only Memory (CD-ROM), magnetic tape, floppy disk, and optical data storage device, etc.

[0121] In an exemplary embodiment, a computer program product or a computer program is further provided. The computer program product or the computer program includes computer instructions, and the computer instructions are stored in a computer-readable storage medium. A processor of the electronic device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions, so that the electronic device executes the above-mentioned trajectory control planning generation method.

[0122] Computer program code for performing the operations of the present invention may be written in one or more programming languages or combinations thereof. The above-mentioned programming languages include object-oriented programming languages - such as Java, Smalltalk, C++, and also include conventional procedural programming languages - such as the "C" language or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, executed as a stand-alone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any type of network - including a local area network (LAN) or a wide area network (WAN) - or, alternatively, may be connected to an external computer (e.g., by using an Internet service provider to connect through the Internet).

[0123] It should be understood that the flowcharts and block diagrams in the accompanying drawings illustrate the possible architectures, functions, and operations of the methods and computer program products according to various embodiments of the present invention. In this regard, each block in the flowchart or block diagram may represent a module, a program segment, or a part of code that contains one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the blocks may occur in a different order than that marked in the accompanying drawings. For example, two consecutive blocks shown may actually be executed substantially in parallel, and they may sometimes be executed in the reverse order, depending on the functions involved. It should also be noted that each block in the block diagram and / or flowchart, and the combination of blocks in the block diagram and / or flowchart, may be implemented by a dedicated hardware-based system for performing the specified functions or operations, or may be implemented by a combination of dedicated hardware and computer instructions.

[0124] The computer-readable storage medium provided by the embodiments of the present invention may be, but is not limited to, a system, device, or component of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of the computer-readable storage medium may include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In the present invention, the computer-readable storage medium may be any tangible medium that contains or stores a program, and this program can be used by or in combination with an instruction execution system, device, or component.

[0125] The above computer-readable storage medium carries one or more programs. When the above one or more programs are executed by the electronic device, the electronic device is caused to execute the method shown in the above embodiments.

[0126] The above description is only the preferred embodiments of the present invention and the description of the applied technical principles. Those skilled in the art should understand that the scope of disclosure involved in the present invention is not limited to the technical solutions formed by the specific combination of the above technical features, and should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosure concept. For example, the technical solutions formed by mutually replacing the above features with the technical features (but not limited to) having similar functions disclosed in the present invention.

[0127] It should be noted that the terms "first", "second", etc. in the description and claims of this application are used to distinguish similar objects, and do not represent a limitation on a specific order or sequence. In appropriate cases, the order of use of similar objects may be interchanged so that the embodiments of this application described here can be implemented in an order other than the order shown or described.

[0128] Those skilled in the art know that the present invention can be implemented as a system, method, or computer program product. Therefore, the present invention can be specifically implemented in the following forms: it can be completely hardware, can also be completely software (including firmware, resident software, microcode, etc.), or can also be in the form of a combination of hardware and software, generally referred to as "circuit", "module", or "system" in this article. In addition, in some embodiments, the present invention can also be implemented in the form of a computer program product in one or more computer-readable media, and the computer-readable media contains computer-readable program code.

[0129] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A method for generating a track control plan, characterized in that: include: Constructing an orbital control instruction set including all preset orbital control instructions during the on-orbit flight of the target spacecraft, and determining a target orbital control strategy for the target spacecraft in a target sub-time period after a preset time; wherein the configuration information of each preset orbital control instruction includes: basic instruction parameters, command routing, spacecraft status, orbital control mode and command timing; According to the target command route, the target spacecraft state and the target orbital control mode of the target spacecraft at the preset time, each preset orbital control instruction selected from the orbital control instruction set is determined as the first orbital control instruction to be executed in the target time period after the preset time; wherein the target time period includes the target sub-time period; Based on the target orbit control strategy, the basic parameters of the first orbit control instruction whose issuing timing is the target issuing timing are corrected, and based on the orbit control name of the target spacecraft in the target time period, the basic parameters of each first orbit control instruction are corrected to generate a target orbit control R sequence containing multiple target orbit control instructions.

2. The method for generating a track control plan according to claim 1, characterized in that: The basic parameters of the instruction include: the time point of the command; the target orbit control strategy includes: the start time parameter and the shutdown time parameter of the target sub-time period; the timing of the command includes: with time constraint and without time constraint; the target timing of the command is: with time constraint; The step of modifying basic parameters of a first orbit control instruction whose issuance timing is the target issuance timing based on the target orbit control strategy includes: Based on the startup time parameter and the shutdown time parameter of the target sub-time period, the issuing time point of the first track control instruction with time constraint is corrected.

3. The method for generating a track control plan according to claim 2, characterized in that: The basic instruction parameters also include: an instruction code; based on the orbital control name of the target spacecraft in the target time period, the step of modifying the basic instruction parameters of each first orbital control instruction includes: The target field in the instruction code of each first orbital control instruction is replaced with the orbital control name of the target spacecraft in the target time period.

4. The method for generating a track control plan according to claim 2, characterized in that: The step of generating a target orbit control R sequence including a plurality of target orbit control instructions comprises: For target orbit control instructions with time constraints for issuing timing, they are sorted in the order of issuing time points and controlled to be executed in sequence at the issuing time points corresponding to the target sub-time periods; For target orbit control instructions whose issuing timing is not time-constrained and which meet the first preset condition, the issuing time points are sorted in the order of the issuing time points and are sequentially controlled to be executed before the target sub-time period within the target time period; wherein the second preset condition is: among all first orbit control instructions, the issuing time point is located before each first orbit control instruction whose issuing timing is time-constrained; For target orbit control instructions whose issuing timing is not time-constrained and which meet the first preset condition, they are sorted in the order of the issuing time points and controlled to be executed after the target sub-time period within the target time period in sequence; wherein the second preset condition is: among all the first orbit control instructions, the issuing time point is located after each first orbit control instruction whose issuing timing is time-constrained.

5. The method for generating a track control plan according to any one of claims 1 to 4, characterized in that: Also includes: Based on the target orbit control R sequence, the target spacecraft is orbitally controlled within the target time period.

6. A track control planning generation system, characterized in that: include: Building modules, processing modules, and generating modules; The construction module is used to: construct an orbit control instruction set including all preset orbit control instructions during the on-orbit flight of the target spacecraft, and determine the target orbit control strategy of the target spacecraft in a target sub-time period after a preset time; wherein the configuration information of each preset orbit control instruction includes: basic instruction parameters, command routing, spacecraft status, orbit control mode and command timing; The processing module is used to: determine each preset orbital control instruction screened from the orbital control instruction set as the first orbital control instruction to be executed in a target time period after the preset time according to the target command route, the target spacecraft state and the target orbital control mode of the target spacecraft at the preset time; wherein the target time period includes the target sub-time period; The generation module is used to: based on the target orbit control strategy, correct the basic command parameters of the first orbit control instruction whose issuance timing is the target issuance timing, and based on the orbit control name of the target spacecraft in the target time period, correct the basic command parameters of each first orbit control instruction to generate a target orbit control R sequence containing multiple target orbit control instructions.

7. The track control planning generation system according to claim 6, characterized in that: The basic parameters of the instruction include: the time point of the command; the target orbit control strategy includes: the startup time parameter and the shutdown time parameter of the target sub-time period; the timing of the command includes: with time constraint and without time constraint; the target timing of the command is: with time constraint; the generation module is specifically used for: Based on the startup time parameter and the shutdown time parameter of the target sub-time period, the issuing time point of the first track control instruction with time constraint is corrected.

8. The track control planning generation system according to claim 7, characterized in that: The basic parameters of the instruction also include: instruction code; the generation module is specifically used for: The target field in the instruction code of each first orbital control instruction is replaced with the orbital control name of the target spacecraft in the target time period.

9. An electronic device, characterized in that: The electronic device includes a processor, the processor is coupled to a memory, at least one computer program is stored in the memory, and the at least one computer program is loaded and executed by the processor so that the electronic device implements the trajectory control planning generation method as described in any one of claims 1 to 5.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores at least one computer program, and the at least one computer program is loaded and executed by the processor so that the computer-readable storage medium implements the trajectory control planning generation method according to any one of claims 1 to 5.

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